~ 100
:a 0 0 ~
..i 0
..
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:a 0
~ D 0
'" r;P 0
...
<
50 IJ 0
0
0.7
FilllJ'8
VI-20
0.05
o
0.02
0.05
0.03
0.011
Fuel Air PBtio - fta
0.8
0.7
0.03
0.8
0.11
0.5
0.6
rqui valence :?at io - image:
-------
200
,*-II~
naaD.ln
150 : ..LI1In '100"
J!
....
~
.c
:II 100
.
w
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S
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..
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50
. t. J
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o
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0.3 0.4
'AXVE IUJIIIER STABILITT DATil
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20
. 0 - IUIIIt18
A - LIaIt
C - 0... o.t
---- Yol" . D.a ...a
15
0.03 0.0.
Fuel Air Ratio - f/a
o
Go 05
0.05
0.5
0.6
0.7
0.8
PAXVE BUP~T.R STABILITY DATA
Propane Ambi_t
g- Stable
- Limit
- Goes Out
BURNER VOLUI'£ ' 52.3 in3
0.10
o .15
o .20
.
1.0
3.0
EquiYalence Ratio -
image:
-------
150 -
H
..c
......
.Q 100
....
.
<
;J:
..
II
...
III
t>:
~
....
t..
H
....
<
50
PAXVE BURNER STABILITY DATA
Kerosene - Antbient
200 -
I
!
1HEOJETICAL STABILITY
'IIIIT -70 F
o~
0.02
&
0.03
ruel Air Ratio - f/a
0.3
0."
0.5
e -StUlle
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-Goe. Out
Burner Volume z 52.3 in3
o
06
~
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o
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0.6
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ECluivalence Ratio -
image:
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~
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c
:.
.
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~
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C
200
~
15
50
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'.
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0.8
0.06
SUMMARY OF PAXVE BURNER STABILITY DATA
e d
d
o
: 0 .08
1.0
1.2
(j)
c1
d
c;J
(;)
(11)(;)
(I)
o .10 .
0.12
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1."
I
1.8
I
2.0
1.6
Equivalence Ratio - cp
o Stable
t:,. Limit
o Goes Out
. Open Symbols - Propane
rilled " - l image:
-------
100.000
10.000
1000
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. --.- -- - - - - . ., . -.. . ~ - ' "- -" oj: j - - I
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-i:Y :-~-- ::.- CO ~Issi~HS D~TA FR~r1 THE P1-XVE DURNER '!! i
tltf - -: FUEL :PROPANE ! I' !
Ir; i 4:j -, AIR TEMP :UNDER 250 F I ~ 1 I i
!;:'~_""'.-:.~.VO.LU.f...1E' ..,5 C.~.~INI#I 11;; II'
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Fi~ VI
27
image:
-------
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NOMINAL FUEL AIR BATIO -FAN
o .16
Figure
VI-28
image:
-------
100,000
10,000
1,000
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RUNS WITH NO CO IETEC'J'ED VERE :H:f!:
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from No. 282 ON
100
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1
0.02
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0.06
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NOMINAL FUEL AIR RATIO - FAN
Figure
image:
-------
10,000
:0: 100
'"
'"
....
o
u
PAM' BURNEPt::-~.~
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. . . , j .
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.------.--
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10
I:Q~LIBRIUM
co
+
atIfS VITH 110 CO IETEC1ED VElIE
PLOfTED AS 5 "11 IIHlai 15 THE
IIESOLUrIIII LIIIIT OF THE GAS
CIIJIOIlATOGRAPII
1
0.02
0.03
o .0'1
0.05
o .06
0.07
NOMINAL fUEL AlE
. F1gure
VI-31
eo EMISSIOnS DATA FROr1 TilE Pl.X'IE
. FUEL IJ>ROJ>1U1.
AIR T~W IOvr.~ 2S0 F
BURNER VOLUME: S2. 3 en IN
. VAPOR GENERJlTOP EXlIJlUST D1T1
nur-:a:!
10,000 .
1000
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r:c:mL~L feEL F.E RATIO -FAIl
'rigU1'8
VI-32
image:
-------
100,000
10,000
llico
m
8
~
. :
1000
EMISSIONS DJI.TT\ FRO'" TilE P1\XVE
FUEL :PP.OP11U;
1\IR TEMr :lmuER 250 F
BURNER VOLUME: 52.3 CU IN
BURlIER
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CO El-fISSIOllS DATA FROP.! THE PNWE BURNER
. FUEL :KEROSEUE
AIR TEMP :UNUEP. 250 F
BURNER VOLUHE : 52.3 CU IN
1
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f.!" RATIO - FAN
Figure
VI-3rt
image:
-------
10,000
co EMISSIONS DA'fA PROM THE PAXVE
PUBL I ltEROSENE
AIR TEMP lOVER 250 P
BURRER VOLUME I 52.3 CU IN.
1000
100 100
:E
"-
"-
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&
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120 -150 0
. 10 OVer 150 ° 10
atIIS WItH 10 CO IlETECftD WEP:E
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1
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Nm!INAL ruEL AIR AATIO -FAJI
ria-
VI-35
10,000
1000
~.- r-------
:! ;
.. .
AIR FLOW
'/Hr.
Under 40
40 - 70
70 -120
120 -150
OVer 150
+
o
6.
.0
0.
F1aq indicate. run.
frOD No. 282 ON
1
. r-r
0.02
0.03
0.04
o .05
0.0(,
0.07
:IOI!I?~L f1Jr.L M P RATIO -FAN
Figure
VI-3&
image:
-------
10,000
. .CO EMISSIONS 'DATA FROM TilE PAXVE BURNER
. FUEL zKEPOSENF.
AIR TEMP rOVER 250 F
BURNER VOLUME: 52.3 CU IN
VAPOR GENEPATOR EXHAV:';T DATA
. ,
... I
.. .
., ,
,:: I
, . . .
! i.::
! :
... .
AIR FLOW
'/Hr.
Under 40
40 - 70
70 -120
120 -150
OVer 150
+
o
~
o
o
Flag indicate. run.
frOlll No. 282 ON
~
p
~
.....
c
(J
t7>
:;::.
t:' 1.0
o
tJ
1
~
0.02
O. .0'1
0.06
0.07
O.O~
o .03
Ii Oi'I!;AL FU!':L A I"
Figure
VI 3'
1000
BU RNFP
COG EMISSIONS DATA FRO~ Till' PJlXVE
FUEL :PPOprNF.
AIR TE~W :UNDEF 250 F
BURNER VOLUME: 52.3 CU It1
100
10
.10
0.02
,r- .
0.03
o .04
RUNS WITH NO CO DETECTED WERE
PLOTTED AS 5 PPM WHICH IS THE
RESOLUTION LIMIT OF THE GAS
CHROMATOGRAPH
0.05
o .06
N01'IHl\L FUEL AIR RATIO -FAN
:.:+
0.07
Figure
VI-38
image:
-------
lO~
103
102
t7\
,.\(
'-
.
u
u
10
1.
0.1
0.02
0003
0.04
0.05
NOMINAL FUEL AIR RATIO - FAN
RUNS WITH NO CO DETECTED WERE
PLOTTED AS 5 PPM WHICH IS THE
RESOLUTION LIMIT or THE GAS
CHROMATOGRAPH
0.06
0.07
0.08
0..10
0.09
Figure
VI-39
image:
-------
t7I
~
"-
b>
o
U
1000
100
10
1.0
RUNS WITH NO CO DETECTED WERE
PLOTTED AS 5 PPM WHICH IS THE
RESOLUTION LIMIT OF THE GAS
. CHROMATOGRAPH .
0.1
0.02
0.03
0.04
0.05
0.06
NOMINJI,L FUEL AIR RATIO -FAN
CO~ EMISSIONS DATA FRO~1 THE P1<.XVE
FUEL :PROPJlNF
AIR TEMP :OVER 250 F
BURNER VOLUME: 33.0 CU IN
BURNER
0.07
0.08
Figure
VI-"O
image:
-------
10
- . ~~
100.000 --
10.000
1000
e
0..
0..
.......
o
u
100
1
0.02
00011-
o oM
Q CQ. 0 . 10 ° . 12..
NOMINAL FUEL AIR IaATIO -FAN
o .1~
o .16
Figure
VI-41
image:
-------
g,
~
g,
8 1.0
COG EMISSIONS DATI. FP.Ot' 'Z'JIT. PI\XVE BUImEI'
FUEL I PPOPJltIF.
AIR TEMP lOVER 250 r
BURNER VOLUME I 52.3 CU IN
102
10
AIR FLOW
./Hr.
uDder 40
40 - 70
70 -120
120 -150
OVer 150
+
o
~
D
o
Flag indicate. run.
fraa Ho. :282 CIf
CUO
0.02
0.03
IIIIS VI1II 110 CO IETEC1ED ~
Pl.Dl"rED AS 5 ".. WHICH IS THE
IESOLUrICIf LIIIIT or THE GAS
CRJI).TOGUPII
0.011
0.05
0.0'
0.07
NOMINAL FUEL AIR IlATIO - F.
n.-.
"--2
.1000
100
COG El'!ISSIONS DATA FRO"" 'rilE P~XVE BURlIEP
P'OEL I PpOP1-UE
AlP. TEMP IUNDER 250 F
BURlmp. VOLUME I 52.3 co IN
~POR GENEU'l"OR EXiIAUST DATA
AIR FLOIII
'/Hr.
UDder 40
40 - 70
70 -120
120-150
OVer 150
+
o
6
D
o
10 .
Flag indicate. run.
fraa No. 282 CIf
J!
......
110
8
1.0
"
IIIIS VI1II 110 CO IETECTED ~
PLOnED AS 5 PPII VIlla! IS THE
RESOLUrICIf LIIIIT OF THE GAS
CIIJOMTOGIW'H
0.10
0.02
0.03
0.0"
0.05
0.06
0.07
IIONIIIAL FtEL AIIt RATIO
rl~
n--3
image:
-------
1000
100
10
~
.....
CIO
o
CJ
100
0010
0002
,f'iO
,-
0003
0004
0005
0.06
0.07
NO~1NfIL rUEL AXR RATXO - rAN
Figure
VI-44
image:
-------
103
I;Jt
~
I;Jt
8
104
102
10
1.0
0.1
Q02
0.03
0.04
0.05 0.06 0.07
NOMINAL FUEL AIR RATIO - FAN
RtifS WITH NO CO DETECTED WERE
PLOTTED AS 5 PPM VHIaf IS THE
RESOLUTION LIMIT OF THE GAS
CHROMATOGRAPH
- -
: ~. :. i:.. .1-
\-
- -.
o .08 0 .09
F1gU1'8
VI-4S
image:
-------
103 :.. ;.;:
., ['; .
HP~S:~s~~O;; ~YA ~ROM THE PAXVE BUmEp.
FUEL I KEItOSEliE
AIR TEMP lOVER 250 P
BURNER VOLUME I 52.3 CU IN
0>
,.I(
"
0>
o
.U
. ,.h. r"""'
10
&XR 1?W::-J
O/M~o
Uffi)~Q~ <10
<1!! = 70
70 =120
!20 =150
0\70&" 150
+
o
t:::.
o
o
17109 !~d!co~o ~~o
!::ZCD WOo 202 O:J
1.0
1:1II:JS tJX'ill 110 CO ~CU:J) Im:\I
.10
0.02
0.03
0.04
0.05
0.06
0.07
.llo:JXNI\L FUXL AU RAYXO - FAtJ
Fia-
YI-1J6
1000
COG EMISSIONS DAT~ FROM THE
FUEL :KF.POSENF:
AIR TEMP :UNDEP. 250 F
BURNER VOLUME: 52.3 CU IN
:~---
BUR..~E" r
100
EXHAUST DATJI.
:.~ :: f : : : : I : : :: ., - -
-f"-'" +;~:--+:-.: : :
10
C)
'"
.....
C)
8
1.0
0.10
0.02
0.03
0.04
0.05
0.06
NOMINI\L nIEL AIR RATIO - rAN
-
0.07
Figure
VI-"7
image:
-------
1000
t1>
~
......
t1>
o
U
, ."
COG EMISSIONS DATA FROM THE PAXVE
FUEL I KEPOSENE
AIR TEMP lOVER 250 F
BURNER VOLUME: 52.3 CU IN
-'E'
10
under 40
40 - 70
70 -120
120 -150
OVer 150
+
o
6
o
o
1.0
Flag indicate. run.
fraa No. :l82 011
RtifS VItH 110 CO IETECTED WERE
PLO'I'TED AS 5 PPII WHIOI IS THE
RESOLUrI08 LIIiIT OF THE GAS
atJOIlATOGaAPH
0.10
0.02
0.03
0.011
0.05
0.06
0.07
IIOIIIIIAL FUEL AIR RATIO - FAIl
rig-
VI-'"
IiC EMISSIONS DlITl> FROp.! THE PJI.Xvr:
FUF.L :PROPANF.
lIIR TEr~ :UNDEP 250 F
BURNER VOLUME: 52.3 CU IN
BURNER
VAPOR GDfERATOR EXifAUST DATA
RUfS FROM 282 ON
10
1.0
s
p.
co
~
0,1
0,01
t ~
o ,O::?
0,03
0,011
0,05
0,06
QO
!"10'11'1AL ~Ur.L AlP. R.\TIO - FAN
Figure
VI-Ij9
image:
-------
10.0
EtUSSIOIJS 01\T,., FI'ClM TI:r:
RIBIS noM 282 (If
FIJrr. : I'rop-",ur
AIR TEMP :UNnE~ 2~n V
IJUT:NEH VOLlJ/'1': : N.S n;, IU
10
1.0
AIR FLOW
. /Hr.
Under 40
40 - 70
70 -120
120 -150
OVer 150
Flag indicau. run.
fr08 No. 282 ON
+
o
6-
o
o
RtIIS VITH ZERO HYDROCARBOII
IlEADIIIGS ARE PLOTTED BELOII
THE SCALE OM SEMILOG PLm'S
c::
p.,
.....
u
:r
0.10
0.02
0.03
IIOIIIIIAL mEt AIR RATIO - FAM
0.011
0.05
0.06
0.07
0.08
O.O~
FJc-
VI-50
IIC EMISSIons Dl\TJI, FFOH TlIr I'1'}"'VE
FUEL' :PROJ>l'tIE
AlP TE~T :OVER 250 F
BURNER VOLUME: 52.3 CU IN
VAPo~ GENERA~'OR LXliJ,t15T DATJI,
BURNER
RUNS FROM N' 282 ON
10
E
C,
C.
U
:r
1.0 -
o .10
0.01
0.02
0.03
0.04
o .05
0.06
o .07
~!mlnIAL rUf.L AlP RATIO - FAM
VI
,i,'.51
image:
-------
.HC EMISSIONS DJ.TJ. FROM THE PI.XVE
FUEL :JeEROSENE
J.IR TEMP :UNDEF. 250 F
BURNER VOLUME: 52. 3 CU IN
BURNER
BURNER DATA
RUNS ArTER N9 282
1000
,C/ ...,
I' .
, . .1.
,I
"
100 .: I ~ I
' ,
100
AIR FLOW
'/Hr.
Under 40 + E
: 40 - 70 0 t:..
A t:..
, L 70 -120
(oj 120 -150 0 g
10 OVer 150 0
F1aq indicate. run. 10
frC8 No. 28~ 011
E: I1r
p.
Po
U
x
1.0
~ 1.0
a
0.07
0.08
0.09
0.0"
0.05
0.06
KOIlIIIA!. nEL AIR RATIO - FAIl
VI
Fig.52
10"
- fie EMISSIONS DJ.TA FPml THE P~XVE BURNE?
FUEL: KEP,OSr.tJI' ,
AIR TE~~ :OVE? 250 F
BURNER VOLUME: 52.3 CU IN
103
.. I .. .-..
. -~ : 2~! .
0.1
0.02
0.03
0.04 0.05 0,06
:! image:
-------
VAPOR GBHBPA'fOR B~US'f M'fA
RUMS AFTER R. 282
. HC EMISSIONS DNrl'. nor.! THE I'l'XVE
FUEL I KJ:POSF.rJr.
AIR 'fEf.W lOVER 250 1"
BURNER VOLU!"E I 52.3 CU IN
LOQD IJATA
RUNS ArTER ,,~ 282
Bl'P.NU~
HC BMISSIC8S DA'fA FROM 'fIlE PAXVE BUIINER
l'UEL a KE1IQ6ERZ
. AIR 'fEMI' aUNDER no F
BURNER VOLUME I 52.3 CO IR
10
10
0.01
o .02
0.03
0.0..
0.05
o .06
0.07
1.0
1.0
AIR FLOW
./Hr. Under 40 +
under 40 + 6 40 - 70 0
40 - 70 0 P. 70 -120 L::.
Ii! 70 -120 L::. u 120 -150 0
Po :x: OVer 150
Po 120 -150 0 0
u OVer 150 0
:x: 1"1aq indicates runs -
1"1aq indicates runs 0 .10 from No. 282 Oil
frma No. 282 OJ(
0.10
. 0.01
0.02
0.03
0.0"
0.05
0.06
0.07
NOMINAL F1JEL AIR RATIO - FAIl
BomBAI. nEL AIR IlATIO -FAX
VI
Fig.S"
VI
H~,.5~
image:
-------
0.02
fICG EMISSIqns DAT/, FROf.! THE PAXVE
FUEL :l'ROPJ\NI:
hIR TE~T :OVER 250 F
BURlIER VOLUt'.E : 52.3 CU IN
.- 'r -" RUNS AFTER 282 .
10
1.0
. OJ'
-"
......
t~
<..J
::r:
0.1
RtlfS VITH ZERO HYDROCARBON
READINGS ARE PLO'M'ED BELOIl
THE SCALE OM SEMI LOG PL01'S
0.01
0.03
0.04
0.05
0.06
0.07
0.08
0.09
NOMINAL ruF.L AIR RATIO - FAN
0.01
n
0.02
0.03
0.04
0.05
o . Or.
0.07
0.08
O.O~
~1()tHK".L qJr./, AIR RATIO - FAN
VI
fJ.~c;.~f.
YT
.,.::.. .,:;.',
image:
-------
1000
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--
-
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--1-1-++-+ f-t
I
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-t. + l".T
-+- + t- -
100
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-r H.t: ~-t..;.. t
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::c +- ...,.
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Flag indicates runs
fram No. 282 ON
-
-
-
-
--
.-
---
-
-
--f- :Vt
if t:-~1 -'-1 j !
J 41=- - fIT :=Tf11:'t- ---i j :-
-7~ 'l-l=tT1L- ,ji~,
+ -I - t ~ 1 :tt i 1 t- ~ ~! j t i -1
:t-; .1 t ; ~t -j-;:i:t 't j t I, r t
j- t- I" T -t -+ .. + \1 I ,t t II
\ .\- -,. { --t ~ - t .. .. 1 i . - ~
-~-
+
--=;::rrt~-f+=t He.
+-1"- n--H- -
rtt:-;-=r:t .1~t1:Hj' i. t .1"
....-+....... \-. f-\-w + +,..
-
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--
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-
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'¥E READINGS ARE PLOTTED BELOW
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-"'" -
-
:::t=t:-
-
- --
it - --+ t- +-
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-t :1
-+
t- +
0 .05 0 .06 0.07
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NOMTNAL F'IJF.T. Aa RATIO - FAN
VI
Fig. 58
image:
-------
oc
.>:
"-
b.'
t)
x
0.1
~s VI'ftI zERO HYDROCARBON
~ADIJGS ARE PLOrTED BELOW
'ftIE SCALE OJ SEMILOG PL01'S
0.01
,
0.02
0.06
0.07
0.03
o .04
0.05
NOI-:INAL ruEL AIR RATIO -FAIl
VI
FiB.59
t1>
.>:
"
tr>
~ 0.1
0.01
HCG I:~USSIOns DlITl, FRO/I THE PAXVE
FUEL :PROPHn::
JI.IF TE1IP :UNDE!' 250 F
BUFNER VOLUHE : 52.3 CU IN
VAPOR r.ENEPATOR EXIIl\UST DATJI
RUMS FROM 282 OM
10
1.0
BURNER
RlIfS WITH ZERO HYDROCARBON.
READIKGS ARE PLOrTED BELOW ,
THE SCALE ON SEMlLOG PLOTS
" ,
o .02
0.03
0.05
NOl.fINl.L I:UJ::L J'.I P. RATIO - FAIl
0.04
o .06
0.07
VI
~i "Tf,,)
image:
-------
100
BCG EMISSIONS DATA FROM THE PAXVE
. FUEL :KEROSENE
AIR TEMP :UNDER 2SQ F
BURNER VOLUME: 52.3 CU 'IN
10
1.0
0>
.J(
......
a>
~
0.1
0.1)1
0,02
, +-
O. JfJ
0.04
0.')5
0.%
0.1)7
0.03
O. 'J':
NOMINAL FUEL AIR RATIO -rAIl
VI
Fig.61
1000
!lCG ErUSSIO!IS Dl'.TA FRO!~ THE PJ\XVE
FUEL: KE!'()SEJ:E
AIR TErlP :OVI;P 250 r
BURNER VOLunE : 52.3 Cti IN
BUm;F.r -
-,. .
. -.
-,... ,
-~..>~. .-...,-...
r~::.+~ :~. ~ :
~ . .,--
100
10
..
.><
"-
..
tJ
X
1.0
0.1
0.01
0.02
0.03
0.04
0.05
0.06
0.07
_,VI
_.- . i.',.
NOMINAL rt'r.!. An RATIO - FAN
------
image:
-------
10 10
BCG EMISSIONS DATA P'ROM '1'HE PAXVE HCG EMISSIONS DATA FRCH THE
FUEL I ItBROSBHE FUEL :J{ER~F.NE
AIR ~ IUNDER 250 P' AlP .TEUP :OVER 250 F
BURNER VOLUME I 52.3 CV III BURNER VOLUME : 52.3 CU IN
VAPOR GEllEUTOP. EXHAUST DATA VAPOR GENERATOR EXHAUST DATA
- :-
. AIR now AIR FLOW
1.0 '/Hr. 1.0 '/Hr.
Under 40 + undar 40. +
40 - 70' 0 40 - 70 0
70 -120 ~ 70 -120 ~
120 -150 0 120 -150 0
OVer 150 0 III OVer 150 0
.. ,>(
"
~ Flag indicate. run. lID
118 frC18 110. 2U (If ~
g
0.1 0.1
0.02
0.05
Q,CMI
0.07.
IIUIS VI1'H ZE1IO HTDItOCAIIION 7
IlEADIles ARE PLOTTED BELOW -
THE SCALE ON SENlLOG PLOTS
... 11m ZDO H'fDlOr.AJllOll
IIEADDIGII dE PLOftED IELOII
'IBE seALE (II SEJlJLOG 'LOrI
0.01
0.0
o .02
0.03
0.05
°.06
0.07
MONDAL FtEL AIR,RATIO - FAIt
NOMINAL FUEL AIR RATIO - FAN
Fi~f\3
VI
~ -, ~~, '.
image:
-------
~.
P:
Il.
......
><
o
z
100
100
'", : .
.~. .
, ,
, I '
10-: "i I '
'}i ,; ii'
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; ; i ' i '
lU'i
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Ql
0.02
, i
I
, , ,
;' ': ! ~:-..: n :
: i .i... I
r ' ' I
, i '
!,
i :,." NOX EMISSIONS DATA FROM THE PAXVE BURNER
I '...: ':' '
, i FUEL: PROPANE
: I /' : AIF TEMP: UNDER 250 F
: " BUMER VOLUME: 66.5 CU IH
'T !'+'W~11HT"r :i .;, ' i :oLI.L .0 ;
:. I' ':: !,;: :': ," i
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1
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[]
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A
;A
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'&I:(:
.'~UILIBRruM N02 '
AIR FLOW
t/Hr.
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40 - 70
70 -120
120 -150
OVer 150
I
!
~ 0
cf
ci ~ (j
L1r
+
o
A
o
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Flag indicate. runs
from No. 282 ON
0.04
0.05 0.06 0.07
H0!1INAL rUEL AIR. RATIO - FAN
;
t :
~
i i~
1 !
0.08
0.09
VI
Fig.55 ,
image:
-------
:;:
D-
p..
......
><
o
~
!lOOO
100
10
1
0.1
0.02
0.03
0.04
0.05
0.05
0,07
0.00
0,09
NOHIllAL FUEL AIR RATIO - FAN
VI
Fig.56
image:
-------
-
P:
r.
......
x
o
z
100
10
1.0
0.1
.01
.001
.02
.04
.05
~lor1INAL rUEL AIR
.05
.08
.09
.07
.03
VI
Fig.57
image:
-------
1000
100
..,.
~
c..
......
>~
~
10
1.0
'~
0.1
0.02
';][£1: r
~
1-
0.03
o . 05 @ . 0\3 . @ .0.'
NOMINAL FUEL AIR i image:
-------
r---
I
:II:
CI.
CI.
""
>C
o
~
1.
o.
0.02
0.03
0.04
0.05
0.06
0.07
0.08
0,09
NOMINAL FUEL AIR RATIO - FAN
.VI69
F1.g.
image:
-------
Xo. EJaSSIOIIS DATA FW)IIJ !IE PUYE Imam .
nEL I PIIOPAIrE
AIIt TEll' I tlllEIt 250" F
IURKEIt.VOLURE I 66.5 CU IX
tIC)
.>c
"&
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VII.
ANALYTICAL INVESTIGATION
During the course of the program Paxve conducted several
analytical studies related to burner operation. The purpose of
these studies was to model the performance of a burner to determine
which parameters affect the stability limits, the completeness of
combustion, and the burner emissions. It was found that a
simplified. well stirred reactor model could be used to correlate
some of the experimental data. The background for that analytical
study is presented in Section A below. The analysis itself is
presented in Sections Band C.
A.
Literature Survey
Combustion theory has been the subject of a wide
variety of analytical and experimental investigations for the
last several decades. Analyses have included ignition theory, .
flame stability theory for flame holders and enclosed burners,
and analysis of operation and stabilization in recirculating
burners.
1.
Ignition Theory
Quoting Frank-Kamenetski (Reference I), tiThe
basic idea .of the theory of thermal ignition is due to Van't
Hoff (Reference 2). According to it, a condition of thermal
ignition consists in the impossibility of a thermal equilibrium
between the reacting system and the surrounding medium. The
qualitative formulation of this condition as contact between
the curve. of heat supply and the straight line of heat removal
was first given by Le Chatelier (Reference 3). The mathematical
formulation was given by Semenov (Reference 4) who obtained an
expression for the relation between the explosion parameters
(temperature and pressure at the explosion limit) which was later
confirmed by Zagulin and a number of other investigators."
The essence of the thermal iqnition theory is illustrated
in Figure 1 which shows the heat release and heat loss from a vessel
in which a combustible mixture has been placed. The walls of the
vessel are.heated to a temperature TW and the combustible material
inside the vessel undergoes chemical reaction governed by an
Arrhenius type equation of the form .
01 - I e -EA/RT
where
OI . rate of heat release in the gas
I . a constant which takes into account the concetration
of the fuel and oxidizer within the vessel and other parameters
siqnificant to the rate of the ?hemical reaction.
image:
-------
EA = the activation energy of the combustion reaction
T = the gas temperature
R = the universal gas constant
The gas mixture in the vessel loses heat to the walls
in accordance with an equation such as
OII = hA (T-TW)
whe re
.Orr =.rate of heat loss from the gas to the wall
h = heat transfer coefficient from gas to wall
A = wall surface area
TW = wall temperature
Semenov examined these two curves, Or the heat
production curve, anQ Qrr the heat loss curve. When the
two curves intersect (line 3 in figure 1) the gas exists at
a temperature slightly higher than the temperature of the wall
.('1'W3) with heat production in the gas being carried to the wall
as a result of the minor temperature difference. .For a higher
wall temperature, TW2' the t~o curves are t~gent~ and (c~se 2)
the. temperature of the gas r1ses, but there 1S st1ll a p01nt,
TA' at which. the rate of heat production and the rate of heat
loss to the wall are equal. Hence a stable system can exist.
At still higher wall temperature, TWl, there is no point
of intersection (case 1). The rate of heat production in the gas is
now always greater than the rate in which heat can be lost to the
wall. Thus in case 1, if the gas starts out initially at the
wall temperature Twl' the temperature of the gas will increase and
although the rate of heat loss will also increase the heat
production will always exceed the heat loss rate. Once the point
TA has been reached, the rate of heat production will accelerate
and the temperature of the gas will increase at an exponential
rate.
Semenov termed the value of TW2' for which the tangent
point case occurs, the adiabatic explosion temperature. The
adiabatic explosion temperature depends not only on the factors
influencing rate of heat liberation, but also on the surface
area of the vessel. The time required for the gas to reach the
exponential temperature rise situation is called the induction
period. Semenov examined these factors mathematically in some
detail.
2.
Stability Theory for Combustion Chambers
Vulis (Ref. 5) performed an extensive analysis
of the problems of furnance combustion using Semonov's thermal
VII-2
image:
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ignition theory as a starting point. Vulis argued that, just as
the rate of heat production and the rate of heat loss could be
used to compute the ignition temperature, one could also compare
the rate of heat production with the heat required in a flowing system
to analyze the cornbustion process. The heat required is that needed
to heat the inflowing gases to the chamber condition and to make
up heat losses from the burner. Vulis analysis is very extensive
and covers a great many of the cases of interest to us, and goes
beyond those cases to consider in some detail the influence of
heat loss by radiation and convection. He only considered first
order reactions, however, which limits but greatly simplified
the analysis. 'Tulis also considered the flow case in which heat
is transferred back to the incoming gases by radiation and mixing.
Vulis' analysis for burner stability follows substantially
the same lines as the analysis presented in Section VII B of this
report. It differs from our analysis in two respects. First,
Vulis considered only first order combustion kinetics. This greatly
simplifies the analysis, but at the same time it restricts the
validity of the results. In partiuclar, the influence of
pressure on stability tends to be lost with this approach. The
other difference bebleen Vulis' analysis and that presented
below lies in the grouping of parameters used in the solution.
Vulis defined a considerable number of non-dimensional parameters
whose arrangement was convenient for his analytical work. Vulis'
parameters, however, tend to obscure the heat release and the
sensible heat requirements of the analysis. In our analytical
wor)c we have used parameter groupings of a more conventional type.
Our analysis in this regard follows more closely the work of
Longwell and \'7eiss. .
yulis' analysis, in cornmon with Semenov, assumes that
the rate of the combustion reaction is given by an Arrhenious
equation. Vulis writes
01 = ko c q e-EA/RT
where
01 ~ heat release rate
ko . a con.tant
c . concentration of reacting material
q . heat relea.e of the reaction
EA' R, T . a. before
This heat relea.e i. a.8umed to take place within a chamber as
shown in Figure 2. Here combu.tible material enter. the chamber
from the left while burned material leave. the chamber on the right.
It is assumed in the analysis that mixing of the unreacted material
with the burning material in the chamber takes place instantaneously
and continuously with zero mixing time and distance. It is a180
assumed that the concentration of r.aeti~q material varies
VII"]
image:
-------
linearly with t~e temperature. In other words, as C goes from its
initial value Co to zero, the temperature increases from the inlet
to the theoretical flame temperature.
The heat supply required to raise the incoming material
to the temperature at \-lhich it leaves the chamber can be expressed
in terms of the sensible heat of the reacting material
QII = W Cp (T-To)
where
QII = sensible heat increase in the exhaust products
W = flow rate of reacting material into the chamber
Cp = specific heat of the exhaust products
T = temperature in the chamber which is the same as
, the exhaust temperature
TO = inlet temperature
Figure 3 shows the heat release (QI) and sensible heat
(QII) curves as a function of the temperature in the combustion
chamber. These curves are similar to those drawn by Semenov in
his ignition theory analysis. There are two differences, however;
in Semenov's analysis, only the lower portion of.the heat release
curve was considered. Vulis, on the other hand, considers the
entire heat release curve from below the inlet temperature up to
the theoretical flame temperature. The other difference is that
the straight line in Semenov's theory represented heat 10S5 to
the wall. In Vulis' theory, the straight lines represent the
sensible heat of the exit flow.
A stable situation for both Vulis' and Semenov's analyses
is represented by an intersection of the two curves for which the
heat requirement curve, QII, increases more rapidly to the right
of the intersection than the heat supply, QI. An intersection for
which QI increases faster than QII is an unstable point which
cannot correspond to a steady state solution. This matter is
discussed more fully under Section VII B below.
Vulis considered a number of concepts important in
burner operation which can be understood by reference to the balance
between the heat release rate and the sensible heat required.
Figure 4 shows the influence of changing the inlet temperature. The
effect here is very similar to that discussed by Semenov when he
discus'sed the influence of changing wall temperature. At some
sufficiently high inlet temperature, TIl' there is only one
intersection and hence only one operating point for the system.
That intersection corresponds to stable combustion taking place
wi thin the chamber. This inlet. temperature represents and gives
rise to the situation in which spontaneous ignition occurs as
the gas flows into the chamber. .
VII-4
image:
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If we lower the inlet temperature to the value labeled
TI2' spontaneous ignition no longer takes place. If there is no
combustion occuring in the chamber, the gas will flow through the
chamber and, the stable intersection to ,the left of the figure which
represents only a small temperature rise, will pertain. If on the
other hand, combustion has already been initiated, then the stable
intersection to the right will pertain, and the system will continue
to burn even though' we no longer have a temperature above the
ignition temperature at the inlet.
If we further reduce the inlet temperature sufficiently, we
can in principle cause the burner to go out. The incipient
extinction condition corresponds to TI3 in Figure 4. Here, there is
only a single point of tangency between the heat release curve
and the heat required curve that corresponds to combustion within
the chamber. A further reduction in inlet temperature will
eliminate this solution which permits combustion to continue, and
the burner will go out.
In a similar fashion, Vulis observed that air flow
could be varied in such a 'fashion as to allow ignition or
extinction of the chamber. Figure 5 illustrates the influence of
varying the flow rate. Here the lower straight line labeled WI
corresponds to the flow through the chamber for which spontaneous
ignition will take place. The flow line W2 allows for stable
combustion to continue, provided it has somehow been initiated.
The flow rate corresponding to W2 will not, however allow the
burner to spontaneously ignite. A further increase in flow to
W3 corresponds to incipient blow-out. Any further increase in flow
will result in a situation in the burner for which no stable
combustion solution exists, and the burner will be extinguished.
Another feature of combustion chambers which was noted
by Vulis, is that for a sufficiently high inlet temperature, the
critical phenomena of ignition and extinction do not occur. Such
a situation is illustrated in Figure 6. We see that for a
continuous variation flow rate from a very low value to a very
high value, no tangent points exist between the straight line
family of curves (011) and the heat releases curves (01)' At
this inlet temPerature, only combustion solutions are possible
since there is only one intersection between 0u line and the QI
curve. The combustion becomes increasingly eff1cient as the flow
rate is reduced, but even at high flow rates ,some combustion takes
place.
Vulis considered not only variations in flow and inlet
temperature, but also variations in other significant parameters
such as the heat of reaction (q). Additionally, he considered the
influence of factors such as heat loss and flow recirculation on
performance of combustion systems. By restricting himself to
first order reaction kinetics he was able to handle the
mathematical details of his analysis and provide generalized curves
which are of great interest.
VII-S
image:
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3.
Gutter Burner and Can Burner Stability
Dezubay (Reference 6), Scurlock (Reference 7)
and others have conducted experiments on .flame stablization on bluff
bodies. They were able to show that the flame holding action of a
bluff body such as a disc or V shaped gutter can be correlated in
terms of the flow velocity by the flame holder, the dimensions of
the flame holder, the pressure level in the burner, and the fuel/air
mixture ratio. Dezubay's empirical correlations were of the form
shown in Figure 7. The ordinate in Figure 7 is the fuel/air
ratio at the flame holder. The abcissa in Figure 7 is a combination
of burner parameters given approximately by V/PD.
Longwell and Weiss (Reference 8) conducted
experiments similar to those Dezubay except that their flame
stabilization testing was done for a can type burner. Burner
stability correlations for can burners are generally similar
to those for gutter type burners. Figure 8 shows a typical can
burner flame stabilization curve. The ordinate again is fuel/air
ratio. The abcissa in this case is the burner intensity parameter
I = WA/Vol p2.
Longwell and Weiss also conducted analyses
similar to those of Vulis. They considered second order combustion
reactions. Longwell is generally considered the author of the
.phrase "well stirred reactor theory" which covers the case
which Vulis called the "zero dimensional case" in which rapid
mixing of the inlet flow with the burning material in the chamber
is assumed to take place.
Because we will use "well stirred reactor"
theory in Section VII B, we will not deal extensively with the
details of this type of analysis here. It is interesting to note
however, that Dezubay's correlation parameter and the combustion
intensity parameter of Longwell and Weiss are closely related.
Figure 9 shows how each of these resembles the well stirred chamber
considered by Vulis. On the left hand side of Figure 9 we have a
sketch of the front portion of a can burner, the air flow WA enters
first row of holes and circulates within the pilot region of the
burner, mixing with the burning gases which are contained therein.
The volume of the pilot zone and its pressure level are the other
parameters of significance in the intensity parameter. On the
right hand side of Figure 9, we see a sketch of the recirculation
region behind a gutter burner or disc type flame holder. As
illustrated here a separated region exists downstream of the
flame holder within which the material flowing past the obstruction
is recirculated and mixed with burning material which has been
stabilized on the baffle. The length of the separated
recirculation wake will be proportional to the characteristic
dimension of the flame holder, D. If we now consider the rate of
air flow into the recirculation volume we can write
WA ex PVD2
Similarly, the size of the recirculation volume should be given by
VII-6
image:
-------
Vol ex 03
Thus, if we form the ratio for the combustion intensity
parameter with regard to the separated wake on the baffle type
flame holder, we see that. .
WA . PV02 V
Vol p~ ex p~ O~ = PO
and therefore the two combustion parameter expressions are
equivalent.
4.
Comments on Well Stirred Reactor Analysis
Analyses of the well stirred reactor concept have been
carried out by many investi~ators. References 9, 10, 11, and 12
as well as many others deal in various degrees of sophistication
and elaboration on the concepts set forth. in the works of Vulis
and Longwell. It is interesting that this type of analysis is
applicable to virtually any type of chemical reaction process in
which heat release and a thermally controlled reaction rate are
significant. Zwick and Bjerklie conducted analyses on the
thermal decomposition of a monopropellant in a gas generator. Their
analyses included a well s.tirred reactor approach as well as one
dimensional kinetics approach. The well stirred reactor type of
analysis was shown to give a means of correlating experimental data
which agreed very well with the experimentally observed behavior of
the monopropellant gas generator.
Well stirred reactor theory is quite useful in that it
provides a means of correlating experimental data and predicting
the influence of various parameters on burner operation. It is not
in general "an accurate description, however, of the actual situation
existing within the chamber. In a well stirred reactor analysis,
we assume that the temperature, pressure and compositon everYWhere
within the region being analyzed are uniform. In practice, of
course this is not, and in fact cannot be true. It is not
surprising therefore that real chambers show deviations from
the predictions made by well stirred reactor analysis and that
the variation. depend on the extent to which the processes in
the chamber lead to inhomogeneity and non-uniformity.
~ngwell and Wei.. fabricated a reactor which was designed
to be a. 910.e a Phr.cial embodiment of thorouqh mixing a8 they
could acheive. The r analy.i. proved capable of c9rrelatinq their
experimental data quite clo.ely, which i. not too surprising since
they had attempted to phy~ically .imulate the mathematical model.
More recently however, Reference 13, ha. .hewn that even in an
experimental well .tirred reactor comparable to that. used by
Longwell and Wei.., detail. .uch ,a. the .ize and location of the
injection port. and the magnitude of the injection velocity
influence the behavior of the .y.tem. Thi. is of course what one
might expect a. a re.ult of non-uniformity within the chamber
it.-H.
We mu.t expect therefore that well stirred reactor theory
VII-7
image:
-------
will provide insight, but not complete detailed information on
burner performance. In this regard it was inevitable that the
simple "well stirred reactor" theory developed by Vulis and Longwell
would lead to more elaborate treatments of burner behavior based
on the same basic concepts. Several of the references cited
above attempt to refine the analysis by examining in more detail
the internal flow pattern, the chemical reactions, or the
character of the combusiton products leaving the burner under
conditons of incomplete combustion. While the merit of these
refinements can be argued, it was our purpose in the present
program to use this analytical method as means of understanding
and interpreting the experimental behavior of a real burner.
With this aim in mind, we decided to use the simplest model and
analytical method which would involv~ the parameters. of significance
in our experimental program. The analysis itself is prese~ted
later in this section of the report. The numerical constants
requi,r~d _for _the chemical reaction rate expressj,ons were,
obtained from Reference 14 which gives a review of the various
analytical procedures devised by other investigators and also
presents equations and constants which give the best fit
to available experimental data.
5.
Recirculating Flame Stabilization Analysis
In addition to well stirred reactor theory,
there is another simple model of burner performance which also
provides some interesting insight into burner operation and
yet is relatively simple in basic concept. In the analysis by
Zwick and Bjerklie (Reference 9) this type of process was defined
as recirculation theory. '
Vulis distinguishes betwegn the well stirred reactor and
the recirculation'cases by identifying one of them as the zero
dimensional case and the other as the one dimensional case.
The mode of analysis is illustrated in Figure 10. Here
we assume instantaneous mixing of the recirculated portion of the
exhaust products with the incoming stream of combustibles.
After the mixing takes place, we follow the combustion process
in the mixture as a funcion of time. The material which finally
emerges from the chamber differs from the material present at
the initial mixing point because of the reaction which takes place
during passage through the chamber. This material now represents
both the effluent from the chamber, and input to the recirculation
pattern.
Recirculation theory leads to predictions of chamber
performance which are similar to those of well stirred reactor
theory. They include, however, an additional parameter, the
degree of recirculation. When the degree of recirculation
approaches infinity the two analytical procedures yield the
same result.
Recirculation theory has an advantage over well stirred
reactor theory in that it allows one to' consider a wider variety
of cases. Staged combustion which is common in many types of
VII-8
image:
-------
gas turbine engine burners and two stage and multi-stage
combustion industrial and public utility boilers are burners for
which recirculation theory provides additional insight while still
allowing for a simple and straight forward analytical procedure.
The true picture of what goes on within a combustion
chamber is of course quite complex. Multi-dimensional analysis
involving both space and time are required for an accurate model
of any real system. Unfortunately such analytical procedures
are extremely complex and further handicapped by the fact that the
flow patterns and mixing patterns which actually exist in a real
apparatus are sometimes unknown and almost beyond reach of any
reasonable analysis.
B.
Burner Analysis
1.
General
For the work conducted here it was decided to
perform a well stirred reactor type of analysis rather than to "
engage in a more sophisticated recirculation type of study. The
Paxve burner has considerable internal mixing and hence should be
fairly well modeled by well stirred reactor theory.
The purpose of this analysis was two fold. First, we
wished to investigate the influence of various parameters such as
fuel/air (mixture) ratio and inlet temperature on the stability
of the burner. Early observations led us to believe that
the Paxve burner was stable over a wider rang~ of operating.
conditions than other burners with which we were familiar. The
possibility of exploring this analytically was therefore desired.
Secondly, we hoped that the analysis would shed some light on the
relationship between burner operating conditons and the
production of air pollution type emissions. In particular, the
degree of completness of reaction was to be determined to see
if this concept could serve as a means of correlating the
experimental data.
The model for the burner analysis is illustrated in Figure
11. Here the burner is represented by a chamber into which the
combustible mixture flows and from which the combustion gases
exhaust. within the burner a homogeneous mixture is undergoing
chemical reaction. The rate of that reaction is assumed to be
given by an Arrhenius type equation. Because we were principally
interested in lean combustion we restricted our analyses to
mixtures which were "leaner than stoichiometric.
The heat which is being generated by chemical reaction
within the chamber serves three purposes. First it raises the
incoming gas to the temperature ~ithin the reaction chamber.
Secondly, it sustains the reaction at a rate which is dependent
on that temperature. Thirdly, it supplies the heat which leaves
the chamber both in the form of hot gases in the exhaust and also
in the form of heat loss to the surroundings.
Chamber heat loss is potentially an important parameter
VII-9
image:
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in the analysis. If the walls of the chamber are radiating to
the outside there will be heat loss which must be supplied to
those walls by convection and radiation from the combustion
gases. The chamber can also lose heat to the outside by
conduction through the chamber walls. This heat loss must be
made up by extraction of heat from the combustion process. Because
the stability and efficiency of the burner are very sensitive to the
combustion temperature, any heat loss will be significant. The
Paxve burner is a relatively well insulated chamber. To a
first approximation, therefore, we have ignored heat loss from
the burner. .
2.
Basic Flame Stabilization Analysis
The fundamental concepts involved in combustion
within an enclosed space such as the burner of a gas turbine engine
can be understood by reference to Figure 11. Here we see a volumne
with a fuel air mixture entering from the left at a given set .of
initial conditions and combustion products leaving on the
right. The simplest method of analysis for such a system involves
the so called well-stirred reactor concept. The idea is that as the
material on the left enters the reactor, it mixes instantaneously
and uniformly with the material contained in the volume where the
combustion process is taking place. The material which leaves the
combustion chamber is assumed to have exactly the same properties
as the material contained within the chamber, and the exit flow
rate is assumed to be equal to the inlet flow rate.
The analytical method involves equating the rate of
heat release in the chamber, determined by chemical kinetic
considerations, to the rate of heat release required to raise the
gaseous exhaust products to their final temperature. In performing
this heat balance. we make use of a concept which runs through the
entire analytical scheme; that one can consider the reaction as only
being partially complete. We use the Greek letter £ to symoblize
the "reactedness" of the material passing through the combustion
chamber. It corresponds roughly to a combustion efficiency. For
a reactedness of 1.0, all of the material which enters the chamber
from the left leaves in the form of theoretical combustion products
and temperature in the chamber is the theoretical flame temperature
diminished by any heat transfer which occurs from the combustion
gases to the outside through the chamber walls. If £, is less
than 1.0, a portion of the exhaust products is unburned material
and the combustion temperature is correspondingly less.
The analysis is subject to various degrees of sophistica-
tion depending on how one treats the unreacted or partially reacted
material which leaves a chamber. The simpliest treatment, and
the one which will be followed here, is to assume that it leaves
as vaporized fuel. A more sophisticated approach which more nearly
fits the facts for lean mixtures of hydrocarbon fuels with air,
is to assume that the unreacted material leaves as the partial
reaction products which are water and carbon monoxide. The degree
of unreactedness is then represented by the failure of the carbon
monoxide formed to convert to carbon dioxide before leaving the
VII-10
image:
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chamber. While this more sophisticated approach is in closer
agreement with reality, it introduces some difficulties in the
analysis which do not help to clarify the points which.we wish to
make in this report. We will adopt the simpler approach here.
3.
Hass Balance
.
. Entering the burner are a flow of air, WA, and a
ftoW of fuel, Wf. Flowing out is a mixture of combustion products,
WB, together with the unburned material, Wu. The chemical reaction
involved (at stoichiometric mixture) is
A + F ... B + 6HB
The unburned material exists in a state which may be different
from the original, perhaps involving only vaporization of liquid,
or possibly involving partial reaction.
Let
e = stoichiometric f/a
cfI .. (f/a) "' e
£ .. fraction reacted
Then for lean operation, the air which can .burn with WF is
.
WAB .. ~
leavinq
WAX. WA
-~
which i. exce.. air.
The fraction of the combu.tible mixture which burns pro-
duce. exhau.t flow
.
~.t{~F+~)
of the
The exc... air fraction toqether with the unburned portion
combustible mixture yi.ld.
. ~ -(WI. -~) + (;, + ~)(l-')
.
If we divide the above expre..ion. by the air flow, WA' and sub-
sU tute and :dmplify we obtain.
VI 1-11
image:
-------
~= €>(l+8)
.
Wu-
~ - (l-» + > (1+8) (l-€)
.
The unburned material may be thought of as unburned air, WAU' plus
unburned fuel, WFU'
then
. .
WAU = WA(l-» + WA>(l-€)
= WA(l-€»
and
WFU = \iF (l-€)
.
= WA >8 (l-€)
4. Heat Balance
The heat release will be assumed to be given by
.
Or = WBllHB
= WAllHB€> (1+8)
For no heat loss from the system, the heat balance in terms of mean
specific heats is .
. .
On .. t'lBllHB = (WBCPB + WAU CPA + WFU CPF) llT + WFU llHV
= WA [(€>(1+8) CPB + (l-€» CPA
+ (l-€)>SCPF)llT + (l-€)~SllHV]
where
llHV = latent heat of vaporization of fuel
WFU' WAU = total unburned fuel and air in exhaust
CPB' CPA, CPF = mean specific heats of combustion products,
air and fuel
This yields a combustion temperature of
TB = Tl +
€>(l+S)llHB - (1-€)8>llHv
CPB €>(l+S) + CPA (l-€S) + CPF (1-€)>8
5.
Reaction Rate
The reaction rate for the combustion reaction in
the volume is given by
WB = K [F]x [a]n-y (..L) n Vol e-E/RTB
. ~B.
VII-12
image:
-------
where
K = K(T)
= collision factor
[F], [a]
= concentration of reactants in mole fraction
. --
x
= fractional order ~ 1
n
= order of reaction ~ 2
vol .= volume- of chamber
E
= activation energy of the combustion reaction
We can easily show that
[F) = ~BlMB + WF7MF + WF/MF J
WAV MA
= (1-£)419 (1-£)~9 £~(1+9) :i
+ (1-£ ) ~ +
- A
and
[a) .
(1-£)~9 +
(1-£1) ~
(1-£~ !!l +
MA
£~(l+9) ~
-118
where
MA' Ma, MF - Molecular weight. of air, combustion ga8es, and
fuel vapoJ;
This gives us
Wa .
6.
Stability Re~uirement
:. .
Stable operation will take place if the rate of
heat release is equal to the heat production necessary to heat the
exhaust product.. There are several way. to approach this last
equation. Perhaps the c1eare8t i8 the one which involves plotting
the heat relea8e rate and the heat production rate required
against temperature in the burner. The result is two curves of
the sort shown in Figure 12. .
In Figure 12 there are two line8, one labeled 011 and the
other 01. 01 is the rate of heat relea8e ba8ed on the reaction
VII -13
image:
-------
rate equation while QII is the heat flux necessary to achieve
the indicated temperature. In general these curves will have 3
points of intersection, one close to the origin and the other two
as noted in Figure 12 and marked a and b.
The intersection at point b represents a stable operating
point for the burner. For temperatures higher than Tb, the heat flux
necessary to achieve the indicated temperature is higher than the
rate of heat generation available in the burner. As a result,
if .the burner is initially at a temperature slightly higher
than Tb' it will corne back' to the operating point indicated by.b.
On the other hand, if the temperature is slightly less than the
temperature corresponding to intersection b, the rate of heat flux
in the system is greater than that necessary to heat the products
to the indicated temperature and hence the temperature in the
combustion volume will increase until the stable operating
point b is reached.
Point a is an unstable point. If the temperature is
slightly less than that indicated by the intersection at a, the rate
of heat production is less than the heat necessary to achieve the
indicated operating temperature. The temperature of the combustion
gases will fall towards zero and the burner will go out. If the
termperature of the gas in the burner is slightly higher than
Ta, the rate of heat production will exceed the rate of heat
required for the temperature in question and the temperature
of the gases in the burner will increase until stable point b is
again reached.
It is interesting that in practical combustion devices
the phenomena discussed above can be observed, sometimes with unusual
results. For example a small gas generator with which we have had
operating experience, could be inadvertantly placed into operation at
this partial reaction point for a matter of many minutes before it would
either jump up to point b and operate stable and efficiently, or else
quench ~d go o.ut.
The heat release rate indicated by the curve QI depends
on the volume of the system, its pressure and temperature, but
does not depend directly on the flow rate through the burner.
The curve labeled QBal' on the other hand, is directly proportional
to the flow rate through the burner. If we increase the flow
rate, new points of intersection between the two curves will
be achieved. Figure 13 shows the limiting case where the two
curves are tangent at only one point which in this case is
labeled c. Point c is the incipient blowout limit of the burner.
The burner may operate at this point for an extended period of time,
but it has no stability margin. Any minor shift in conditions in
an unfavorable direction will cause the reaction to die away.
It should be noted that there are two ways in which
one can reach a point of incipient blowout in a given burner.
We can change the conditions of the line affecting QII by
increasing the air flow, or we can change the factors affecting
QJo The principal factor influencing Q React in an otherwise stable
s1tuation is the equivalence ratio~. One might also, however,
VII -14
image:
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change the reaction rate as a result in change of pressure.
the experiments conducted by Paxve on the Paxve Burner for
APCO, we have determined incipient blowout by reducing the
air ratio until the lean limit was reached.
In
fuel/
A factor which was not introduced in the above equation,
but which is significiant in a real burner, is heat transfer from
the gases. Heat transfer has the effect of reducing the heat
release indicated by the curve QI by an amount which depends on
the temperature of the surroundings and the mode of heat transfer
involved. In particular, heat transfer to the wall of the burner
has a dramatic affect on the stability of the burner. A burner
of the type utilized by Paxve has very little heat transfer
to the walls under steady state operating conditions. During
startup and shutdown, and when changing operating conditions, heat
exchange between the gases and the wall plays a significant rble.
As incipient blowout is reached, the burner will remain lit for a
matter of 10 to 20 minutes even though the equivalence ratio has
been reduced below blowout limit. The difference between the
heat required and the heat available in these conditions is quite
small, and the warm walls of the burner provide the necessary
difference during the time the burner takes to go out.
If we equate the heat production required to achieve a
given temperature with the heat production available as a function
of reaction rate, we obtain the following equation.
I=. WA =
p" Vol'
.!:!£ E/T.
k (I-e:) (l-e:~) e MA e- .B R B
E: (1 + e) [ cp (1+ e ) e: ME. + ( 1- E: 4> ) .
~B
~ +(l-E:)E:4>J"TB 1.5
rotA
The reaction rate constant K here has been related to temperature by.
K = k TO.s
and x = 1 and n = 2 are assumed.
The equation for I can be solved if we have values for,all
of the parameters and TE. The equation for TB requires th~t we have
values for.the average specific heats of the air, the fuel and
combustion products. For the present analysis, equations
were generated for these specific heat values using data from
reference 15.
The specific heat data (in metric units) and the averaging
equations (in English units) were:
Air
cp = 6.557+1.477 x 10-3 T-2.148 X 10-6 T2 cal/~'!ole oK
CAavg = 0.22618 + 1.4147 x 10-s(T+Tq) - 7.8229 x 10-10 (T3_T03)
/(T-To) BTU/lboR' .
VII-15
image:
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Fuel
cp = 0.02 + 1.51 x 10-3T - 7.7 x 10-7T2 + 1.5 x 10-10T3 Cal/gmOK
CFavg = 0.02 + 4.194 x 10-" (T+To)-7.9218 X 10-8 (T3_T03)/(T'-To)
+ 6.43 x 10-12 (T"-To")/(T-To)
BTU/lbOR
co,
C = 18.036 - 4.474 x 10-5 T - 158.08 1fT
P.
CC02avg = 0.40991 - 2.8245 x 10-7(T+To)-9.6403 (fT -{io)/(T-TO) BTU/lboR
Cal/moleoK
H20
Cp = 6.970 + 3.464 x 10-3 T - 4.833 X 10-7 T2
CH20avg = 0.38722 + 5.3457 x 10-5 (T+To)
.:. 2.7623 x 10-9 (T3-T03)/(T-To) BTU/lboR
~
Cp = 6.529 + 1.488 x 10-3 T - 2.271 X 10-7 T2
CN2 = 0.23318 + 1.4762 x 10-5 (T+To) - 8.3444
avg
(T3_T03 )/'{T-To) BTU/lboR
. . For purposes of the analysis , the reaction taking place
was assumed to be that of octane with air. The reaction was given by
C8 HI8 + ¥ .(02 +' '3.77 N2) + SC02 + 9H20 + 47.125 N2
Cal/mo1°K
Cal/mole oK
X 10-10'
This gives an exhaust gas composition of
N2 - 73.489 Mole% - 71. 966 wt%
C02 - 12.476 r~ole % - 19.198 wt%.
H20 - 14.035 Ho1e% - 8.8356 Nt%
The average specific heat of the combustion products is therefore:
. CBavg = 0.28072 + 1.5293 x 10-5 (T+To) - 8.4458 x 10-10
(T3_T03)/(T-TO) BTU/lboR
-1. 8508 (rT - .[fu) I (T-To)
7. Limitations on the Analysis
The theoretical analysis performed here was
limited in two major aspects. First the influence of heat loss on
the stability and performance of the burner was not investigated.
Secondly, the performance and stability of the burner for fuel
rich operation were not investigated. ,The failure to investigate
heat. loss effects was the result of a lack of available
funds on the program rather tha~ a l~c~ of interest in the
VII-16
image:
-------
. .
subject. Failure to investigate fuel rich operation \'las. due
primarily to a combination of lack of interest and the
factors sighted above.
The influence of heat loss on burner performance and
stability is a subject which should be studied closely. It may be
that the outstanding performance of the Paxve burner is in some
measure attributable .to the low heat loss characteristics of this
device. Fuel rich operation is of some interest for burner
applications to systems in which two stage combustion would
desirable feature. Fuel rich operation of the Paxve burner
not contemplated for automotive Rankine cycle or automotive
turbine applications.
be a
is
gas
C.
Computer Analysis
The theoretical burner analysis equations presented
above were programmed for analysis on a digital computer.
The programs were written in APL, a new programming language
devised by IBM and made available on a time sharing basis
through Proprietary Computer Services, Inc., of Van Nuys. A
number of programs and sub-routines were written. The purpose
of each program and the results of the analyses are discussed below.
1.
Program CAL
Program CAL, shown in Table 1, is the basic
computation program used in the burner analysis. This program
was used as a subroutine in a number of the other programs. For
given input'values of air inlet temperatures, (TI - degrees Rankine)
and equivalence ratio (PH), CAL computes the combustion temperature
(TB) and the combustion intensity parameter (INT).
CAL includes a correction to the heat of combustion which
allows for the heat required to warm the fuel up to the initial
temperature, and an iteration procedure for the specific heats
of the air/fuel and combustion products. Initial values for
these three specific heats are assumed in order to make an initial
estimate of the combustion temperature. The specific heats are then
corrected for the average value between the inlet temperature and
the combustion temperature and the process iterated until the
computed combustion temperature agrees with the previous value
to within one degree.
CAL returns values of TB (the combustion temperature), and
INT (the combustion intensity parameter) to the other. programs.
2.
Program HOT
Program HOT" shown in Table 2 was used to
compute tables of TB and INT for sets of inlet temperature,
equivalence ratio, and combustion. efficiency values. HOT calls CAL
as a subroutine. HOT was used to generate the results presented
in Tables 3 through 8.
During the course of the contract, we frequently found
VII-I7
image:
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it desirable to be able to compare the predicted efficiency of the
burner with the experimentally measured values of carbon monoxide
and unburned hydrocarbons. In this regard, curves were made of
the so-called "unreactedness" which is defined as .
<5 = 1 - E
where
E = Burner Efficiency
Figures 14 thru 19 show the,unreactedness plotted against the
intensity parameter I for various values of inlet temperature.
parameter in the curves is the equivalence ratio PHI.
The
3.
Programs BURN and STABILITY
BURN is the computer program which was used to
compute the stability of the burner. BURN accepts an inlet
temperature TI as its input. It then examines the value of the
combustion intensity parameter, INT, over the range of burper
efficiencies from 0.3 up to 1.0. It uses the subroutine CAL
to perform this calculation. BURN then selects the maximum value of
INT, and calculates 10 new values, five on either side of the
maximum. It returns this value of INT together with the
corresponding value of burner temp. (TB) and combustion efficiency
(E) . .
STABILITY is a small program shown in Table 9 which was
used to vary the imput' temperature and accumulate the output for
the combustion stability calculations. It used BURN as a
subroutine for the stability calculation.
Tables 10 and 11 show the results of the stability
calculations made using STABILITY and BURN. The output columns
give the equivalence ratio, the efficiency at the stability limit,
the predicted combustion temperature at the stability limit
allowing for the inefficiency, and the combustion intensity
parameter at the stability limit.
Figure 20 shows a plot of the combustion stability data.
In this figure, the limiting value of the combustion intensity
parameter is the abscissa and the equivalence ratio is the
ordinate. The parameter for the curves is the burner air inlet
temperature.
4.
Program INTPLOT.
In performing the combustion stability analysis
with Program BURN, we assumed that the intensity parameter would
show a local maximum with varying efficiency. This is not
always the case, as was pointed out in the earlier discussion
of combustion theory. When the inlet temperature is raised to
a sufficiently high value we find that the critical conditions
which normally characterize burner operation are no longer
VII-l8
image:
-------
present.
The normal phenomena in a burner involves both ignition
and extinction limits. For a given value of an inlet temperature
and equivalence ratio there are normally two air flow rates
(combustion intensity parameter conditions) which correspond to
these two critical values. At a sufficiently low value of air
flow rate, an adiabatic burner will spontaneously ignite. At
some higher value of air flow rate the burner is unable to
sustain combustion. and the burner blows out.
This form of ignition only occurs in practice at hiqh
inlet temperatures. It is not the one which is used in most
conventional burners. It is nevertheless a concept which is readily
apparent from the combustion analysis. High flow rate flame-out
is, however, a common occurence in any burner system.
In order to examine this question further, the values
of combustion intensity parameter corresponding to various.
values of combu$tion efficiency and equivalence ratio were computed
using computer program INTPLOT, shown in Table 12. It uses CAL as
a subroutine for computing temperature and intensity parameter. The
results from INTPLOT are.shown in Table 13. This same information
is plotted in Figure 21. The ordinate of the figure is the fraction
burned or as it is more generally termed, the combustion
efficiency. The abscissa is the intensity parameter.
Examination of the curves in Figure 21 reveal clearly
the nature of the critical conditions which normally exist within' .
a burner, and how, for some values of burner operating conditions,
these critical phenomena no longer occur. Referring to the curve
for equivalence ratio 1.0, we see that the ignition condition
corresponds approximately to INT = 371 which occurs at
about 10% combustion efficiency. This means that for an inlet
temperature of 2000°F, .with a stoichiometric mixture, we will
achieve spontaneous ignition in the burner if we reduce the air
flow level to the point where the itensity parameter is below the
value 371 which corresponds to the ignition critical point.
The blowout condition, on the other hand, can be seen
from'Figure 21 to occur at I = 982, at an equivalence ratio of
0.5. This means that once we have ignited the burner, we can then
increase the flow rate through the burner to approximately 2.5
times the flow rate at ignition before the burner will blowout.
Examination of the other curves in Figure 21 show that
these two critical conditions, which correspond to the vertical
tangents of the constant equivalence ratio curves, ,exist
for those curves for which the equivalence ratio is 0.3 or higher.
For ~ < 0.3, the curve has no vertical intercept. The curve for an
equivalence ratio of 0.1 does not even approach a vertical slope.
For this set of burner operating conditions, therefore, we cannot
speak of an ignition or a blowout condition. Some reaction
will take place within the burner at any value of flow
rate. In a manner of speaking; the hurner is always ignited and
cannot be blown out. This is apa!ticularly interesting phenomena
VII-19
image:
-------
in view of the fact that the combination of high inlet temperatures
and low equivalence ratios which lead to this situation may
ari.. in burners for regenerative gas turbines.
It should be appreciated that the stability analysis
which was conducted using program BURN was not able to evaluate
.tability limits when in fact none existed. To prevent the
compu~er from encountering this situation two safeguards were put
in~o program BURN. First, no efficiency values less than 0.3
.were~exandned by. the compQter. Secondly, if the maximum value of
the in~ensi~y parmeter within the region of the analysis was
carre.ponded to the first point analyzed (~=0.35), the computer
skipped tne remainder of the calculation and.went on to the next
point. in the t.able of values that it was computing. The
. ".' .COft4i~ions in Table 11 for which no critical phenomena occur
are indicated by *.*...
,'.: .'
'1'.' 0"'..,'. ..:,. ,".'
. .' '::' ," ',' ~ .,' ,":: .
I .
"'-.
VII-20
image:
-------
Q
Q I HEAT RELEASE CURVE
H t.. po.. "\ LO 55
C.URV£.~ .
QII
'w,
TA
TOAS
S~OV'S THERMAL IGNITION THEORY
Figure VII-l
W --+-
'0
.. ,
T
SIMPLIFIED COMBUSTIOM MODEL
!i'igure
VII-2
image:
-------
Q
TI
VULIS' COMBUSTION THEORY
T
jo'1gure VII-3
Q
QII
Q.
TII TI2 TI,
iFFECT CF INIEI' TEMP&RATUR&
ON CRITICAL PHENOMENON
,
Io'1gure
VII-IJ
image:
-------
Q
~
o
~
v
.~
J..-
~
4J
QII
TI
t;Ii'}o'iC'!' (Ii' FLOW RATE ON CRITICAL P~O~ON
1
.F1gureVII-.5,
QI
Q
Wa
11
COMBUSTION SYSTEM
WITHOl11' CRITICAL (IGNITION AND EXTINCTION) PJOOiOMii:NON.
QI
T
F1gure
VII-6
image:
-------
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=
AIR FLOW
VOLUME
1#
--
see
-
i
, I
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ft3
I
I
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'H
,
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~
p,:0 .14
H
<
....:I
~ O. 12
""
!
i.
'; II.
, I!
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II
V
a
PRESSURE
ATMOSPHERE
-
-
-
I:,;,:
I;'
,
, .
1..-
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, --+-
.1 I
..I j...
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"1'
-t- ...!.
.t t
"1 --i-
p
=
r---,
i' I
!
I
I
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I
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- i~--!:FC+ .... -:---1
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:
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J
i
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: ! ~
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i !
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. j
.- ... j
!
-.
'i
J
i
! ,
i i
6
..-_0---' .-- ---
..-.---..-..
CHARACTERISTIC NUMBER - WA/vp2
8
i." T
! !
!
10
.~-- ...-- .-.
"
I
I ,
..--1.----.--.-
i
-
--
70
-
.-_U ...
---..0..-.-.--
.. '
-'
.'
..0
60
, ,
, .
i - ""'R_'
I
!
i
I . . j.
.1',+
" I
I i
,.
!
I'
..,.
.J j:.
-j
: I
I..
I i
i .. . +.
.. 1:.-1:
.j:t
i---r
i ...\
-
I ! I
J ! "1
,
!. - j ~--.~~::-
i . i
--..--- ---7'.'-
..
80
100
image:
-------
v
(
~
f~C)~
~~C)/
o
p
CAN BUJOO:R AND GiJrTER BURNER CONCEPTS
Figure VII-9
W
VOL
--
W
..
(l + K) W
.
p.
~
..
o'W
~
RECIRCULATION MODEL
Fi~ure VII-10
BURNER ANALYSIS TECHNOLOGY
P TB
VOL . . . .
VA , Wr T1 TB WB + Wu = WA + Wr
.. ...
E..= FRACT. BURNED
INLET FLOW EXHAUST FLOW
BURNER
Figure VII-ll
image:
-------
Q
/
T
5\~~\..'i.. O?t...'i'..JIo.\\t-\(:) ""t..'-'" 't>"'\..M'~C.£.
Q
Figure VII-12
QII
T
\ ~('\~\'t:..~\ ~\..OW QUi \-\t."'" 'O"'L"'NC.~
Figure VII-13
image:
-------
II)
II)
~
~
CJ
-<
~
~
THEORETICAL BURNER- ANALYSIS
10"'
! ~_:t: I.' -:~~-.-:;~ .~~: ~ ~ - - ~ -+ ~- ~
; -L ' .: ; -~_._-'~~-=-- ::.:.:' ::::=:.
I " i ' . ; t i._~__~_.._-,
h____- .._.. + ..
: r
10-
-.-._.~-..;._~_..---+-------.. ------.. -
. ,-: l'
\'.
....--!-_.
: t
'.------.- + -.-'
-,-- .'-'~"'"'' .' -...-
-.--.->.. -.-
- _h__'~__--- .
, ,
"'-1- '--'--'-"'~-"'-- .-..
. ~.. ',-
. ,
10-
---.--...
~--------
'--~"i-.
. -- 0" - .-
. - -- ,. --.. ."--
- .-- -- -.-.-...
-,'
INT = WA/VOL p2
o = 1-Eff
AIR IHLET. TEMP. OOF
10-
10-1
10
102
10-3
1
COMBUSTION INTENSITY PARAMETER - INT
*
See ft3atm2
Figure VII - 14
image:
-------
U)
U)
~
J.:J
t
<
~
!5
10-3
10-1
THEORETICAL BURHER ANALYSIS
-
..
; +f-+ i-t:"=-r1::i) ::;-! --"'-~i-"_..' :~:~t=g!~t,--.:~:~~:..jf"":' ; ;.' ;::; '7~ ':. .
. .' "-~1;l:..+...-::==E;~ftGt::)?~rL::~:~-~~i<,
: . : .., i,,: : ."". . :' : :' -t+tJi i,.I.. . - : . -1--'; I ''''''--r--rn.n~.+-:-+Tt
.. H +~:;.;........ 1- ... ,- .J. ...,; '/:!. I, ,-, 7 -::. ~" "', ~ 'ill :.',,: .', , :
..\::1/. t:. . .c-'~-k+I', .. .'~.:, :; 0"" ~,j'c~c:l'f;,~:,:TtH~J
.. ,. ". -~~,l i':" .. /:: ::;;'~.,; . ii,; V ..!,...U~ . '.,. .. 1 t i l--tI .
,+-,+++
:+t
10-2
~..
~ ~~.
L4W' ,.':t.
'To
f"'~ .,' .. .::
'.. n._'. o' ,":. '. i,. ."
'0:' ... ." .'
,::'~ .. :~: '..1
-f=-;-. 1.,', . ',;".
-+-' ~- L...: ..~.I:
! - + '" ~ i~~ :!. i
:j'
...
..
,i", ! :
,
,r
":J..
n
I'
:1.' ..
. ,
, ..... .. ."" ..
,,,., ~.L ./ (~: n
"/.i' i I:.
" . i !IK:f.. : ',: J /~ v. : :
': .. T' ~ ,)'Il+- ..' .-;pl-t. ~: .,-"c-..';"
, . k: "\" '- ., ;{ ';I ~. . + '" -
~~~ --~.~ I _....,::L/l2~~.riin!- -~"f~~' !'1.1.~,ll t- i':
'Y'. I ~ ~ ", /'f'. : Y./: . I ';: INT = WA/VOL p2
WI' "II ~: I'
. '/ - ''I. .:~~--.-i,.:" . . -r
'J I""''' ", ~-h-' . '1-'
. . i !'N ,V/y'. ::.1 :! f -W,~ 1 u::
I;j/: I' y. lA'~h'lI'iI'l'''TT'I!' '! .' : . 0
l ,~V ..':'7)'''¥'" ,.' .' ~: ;:,-,.,,, ...,. ..-r~iT; ~~ AIR. INLET TEMP. - 1/00 F
~ '.~ - -- -/7t' ,:., ....;i., !' L~~'~ ~ : i~Ti' ':':+fr'--:---:~~~'T:T-~-:~-n"---"-"u
I) : I ! V : .t--w'--; ',: l'r,-,~--"-~,,,,:,,:,,:u'-"'T-' ..,......_-;---,.. . . ,-
..,' Y'. ~:'I'-' '''';-''''I~:.:.t''l(..t II' .., .".. .. .;':' . :'" ., ,. , ., '. .
I . '.': 1:; ~ ~ :
10-~I",... . ,.J i . I. .: " i
.
10-3 10-2 10-1
u
...
:
T
-- '''-'1--
;
,.!.. I'
';'1 " 'j I j-I
'-.. n~ttttTt
-L
..:U:. !.. :.f
~;'~:: :r'
c " ..1:."
- .. . . r . ...lJ
:.i-h.' ''J
':':!-~1~1-' ~:jm1r:,
.. '1::,: ":L;,.. ::
: :!~lIl I "I,.o~
-;, /. , L.,.
~
'.
'..
j~:- .:t--
~,~Uc_, ..:
..
.,
, -
, --
" :
V,
-..-
:-~:
cfr:
1 - Eft
u
.. :'
,
i
: ....:..J..
, I'
: :" I,: ,
y.: i' "
.::!
100
1
10
COMBUSTION INTENSITY PARAMETER
1#
See ft3atm2
INT
Figure VII - 15
image:
-------
THEORETICAL BURNER. ANALYSIS
10-
en
en
~
~
~
t
<
~
~
-L-L .
. ;!~i.
10"
:. - ... I
. . I
I
I
I
I
...-+
----~_.t--~
. !
1
INT
,rAlVOL
p2 ".
=
cf=
1 - Eff
AIR. INLET TEMP.
80QO F
..
10-3
100
101
10-2
10-1
COMBUSTION INTENSITY PARAMETER - INT
*
See ft3atm2
Figure VII - 16
..
,. '., ::i
......;
. .
.,'':''"
..' ~
. ,
10 2
image:
-------
10-1
.b', t",
,.
.:'
..-
..
-.
11fEORETICAL BURNER ANALYSIS
I
I
-
..
.
Ir .!: '::::,:::: .... --. ~:/ .:.1 u:f.-, . ll: l-1t--
'::-~I...'- on. ,;.,- . ~- .:-:: -+-~- - '--, i!!
:2 -," i",:' "'- -jllbl. ", ~"--- '- i I '. i "---- :...---- -.- .. -'
.. ~"",;:.
, r -. ...
10-
--.
.i
: fH..
g
1:::: ,.
j:: ...~1;;T' ~..-
. . ..:i:!,.. --,'
en
en
!
w
t
<
t!
~
;1 I
. .
,.:
..
u
':t J
-
~ ". r:
,"
-, -,
10-
I::::.
..- ~-
.u -.
~
....
V --'
~.+._- --~: .J,
--
.;',
. . . i' .. . ).'
:--V._.L
~/ ! i
10- ~
10-3
'r :~ --._,.
.~
..
--
---... ..
..
--_u-
..
..i.j
1 ii.
"-~'4 D5 ~ -- ...
'III ~ ..
y LV~'
.)' L;' --; ! f: ~ ;,..
I ~-- I I --r(J~)'t
k:' ~,'VV'!:
- .._~-.
-,
--.
-
--
- ..... ---- -------...-.-..
,
---.0- -j-
~
--
--
--
- .
..... "
.....
--
.--
t.
i'+~-+ .u.
t-- .-
~I/ : ~ 141
t- -t :~r-~~ 0 --
:-t'7..~-~.i O.
),1-'1.' I
''1'1
I
'i,; I.; '~ ", -- 'c" -- -- .-- -
.j~f~ L .~.v ' ,. "., - :...,. '.-" - i
,:~ . :- "'--'--
~-:i'
"I .. 'u
--
"
,
-;: j
)'
- ---~
n~
--
:';-~ t
-.z: i
, ~-'~'~/V1'~ .,I.
Ib
O'
.(. --
1
I ,
10-2
10-1
- .-. ...
..
,- --
fi
lSf- .
.,..
. ,
';-'~'1'.' -
., ._-
! . I
; ,
--
COMB(J)TION INTENSITY PARAMETER - IIn'
_..n
--
-.. _.-
--
--
-
--
--
- ---.--
--
_u-
". __n
..
..-
---
.._--
.... .-
--.
. -
." ..- -'-.. --.
~
o-!
--- .-is) ~ .
-------~.
-
INT . VA/VOL p2
d . 1 - Eff
AIR INLET TEMP.
-
..
100
101
*
See ft;'atm2
--
--
--
.
..-
- 12000F
10 2
Figure VII - 17
image:
-------
THEORETICAL BURNER ANALYSIS
10.1
10.2
(0 " q)
~O' ~O' *0'
&&&
. ---t-
+-
--4-+-
-=t._~.~~r-I~::-~i ; ..
II)
II)
~
f,.:I
t
<
~
~
10.3
INT
=
WA/VOL
p2
cf=
1 . Eff
. AIR INLET TEMP. .1bOOoF
10."
10. 4l
10.1
10°
~01
~o 2
103
COMBUSTION INTENSITY PARAMETER - INT
II
See ft:3atm2
Figure VII - 18
. /
image:
-------
THEORETICAL BURNER ANALYSIS
10-
- -.-"... ----"- .
10-
I-
en
en
w
~
~ ~ .,:
-<
~
! .- ...
.:J"
10-3
. ,'j
, . ; I
~ ! Ii: . j
" ~~,mmtc~~,.
--.' I- .-+-Wl ~. - . . - 17-+',-
. : 1 - :1--iT 1+"-' -., 'Ii '.;"-. !; : f
t I ~--T.-::T1i-r: ~, , ":' !!. !
, ' : r It ! : - r,-j ! - i r"ll - - . i - ~-: J . r'; i ; l
L-_-_~.- "".T~t--- ._--~._-_.--.-.;-~-~-..l-L ' .-t--T:t-._~_._;.J
!,~ : '-~~_:':~~t:-i==~lNTi~:~'IJA;'J:J }i ~.' ' ~
.' '<.;1 n "'.~:_~~L~-;.l' rf. 1 - Eff . ,
, - ,---'~;r AIR INLET TEMP. lOOOoF
i
. ,
i<. .i. J.:
, !
. -..- -.------ - -,".--
10-4
10-2
10-1-
100
i01
1'02
103
COMBUSTION ItrrENSITT PARAMETER - INT
*
See ft3atm2
Figure VII.- 19
image:
-------
CUF:r:Ep. STArlILlTY LlnlT I\llt.LYSI':
~ n.704
, ~
o ,
~ ~.Cr.4
:! :
t! 0 . ~0t+
~
...
o
o
w
0.01
r-
1.00r
~
n. ()O4
- .
IrITEfJSITY Pt.RAIlr.n:r. TNT = I-IA!(VOL.P*2)
O.lD 1.00 10."10 100.00 1000.00
I -+----+-
f'\.8n4
;
;
C.11"~
..,
...
:IQ
~
-
-
-
<
...
....
I
'"
o
L':UI V
;-~--
rT' '+..o.. ...., ",..... ,. .~+ ,..... - .'''~1' '--~-'''In'" .., ...-.+
".("11 '1.1," 1.r.Q J.0.0''''1 ]0';.0'" 1'!0r).0("'1
T':'Tr":'STTY r/\i.,.j': T- r rt:7 = "I\/(V""L.P*'2)
C! I
:JSTWf, Ii'TI'~ SI,':' rfJ:';:rT::r
L':r. 'LnT
T! = 2!H"!"';"
n:TEi.~ ITY r,ll.r.n:LTU' !lH
I.or 3.1' I~.~- 31.(? I~r.n~ 3J(.23 10f'\D.nr
,-+ -. "~"'..-f--'" ..-+."*.. ......1--.. .--." +-.-- --..1-0.-- +
1.'"'0~
~'.!
r;
,
',.~1:.1~:
0.C~~.
0.7~f+ lr
w
co ".I">~- 0.2
~ ."'. s~f-" 0.3
III 0.4
~ 0.5
... '"'.111++
~ 0.6
~.:;1f+ 0.7
( 0.0
,
-::.207+ 0.9
1.0
(! . 1 ':'\ "7t-
:T/,C
~\~.
-'.Jr: :~~~.:.:- "-~:;-r'-" ...;: !~'r."'''.'--'3'1':;:'''' ";~,~;:'~'~ -" '~'1'/,~"~' -.. ~'.'~-~!".,
n:T:TrITY r,~r:J''''H:r T!'T
. ,
,
image:
-------
VCAL(O]
V CAL
CA+-O.27
CP+-O.7
Cn+-O.32
TBI+TI .
HP+(O.02xTI-537h(O.OOOIf194x«TI*2)-537*2»+(-7.9218E-8x«TI*3)-537*3»+6.43E-12x(TI*4)-537*4
BB+HBO-(O.81+0.633)xBFxTHf1+Tll
TENP:TI+-TI
TB+TI+«HBxPHx(1+TB)xE)-(PHxTilxBVX1-E»f«CBxPHx(1+TH)xE)+(CAx(1-ExPH»+CFxPHxTHx1-E)
+«ITB-TBI)$1)/CONT
TBI+TB .
CA+(O.22618)+(1.4147E-5xTB+TI)+-7.8229E-10x(TB*2)+(TExTI)+TI*2
CP+(O.02)+(O.0004194xTB+TI)+(-7.9218E-8x(TB*2)+(TBxTI)+TI*2)+6.43E-12x«TB*4)-(TI*4»+TB-TI
CB+(O.28072)+(1.5293E-5xTE+TI)+(-8.4458E-10x(TB*2)+(TBxTI)+(TI*2»
CB+CB+(-1.8508x«TB*O.5)-(TI*O.5»fTB-TI)-88.356fTB-TI
+TEMP
CONT:TBI+TB
IRT+Kx(1-E)xTllx(1-ExPH}x(MFfMA)x(*-EAfRxTP)f(1+Tll)xEx((PHxTHx1-E)+«1-ExPH)xMFtMA)+PHxEx(1+TH)xMFfMB)*2
INT+INTx(TB*O.5)x(29x2116f1545xTB)*2 .. .
[ 1]
[2]
[3]
[4 ]
[5]
[6]
[7]
[8]
[9]
[10]
[11]
[12]
[13]
[14]
[15]
[16]
[17]
[18]
V
[19]
...
So
...
.
<
M
M
.
...
image:
-------
I
I
[1 ]
[2]
[3]
['I J
[ 5 ]
[6]
[7]
[8]
[9]
[1f)]
[11 ]
[12]
[13]
[14]
~
v HOT[ r] 17
'V l:tr~~;J;!:
J'llA+O.1x\10
~IJ+460+ 0 400 800 1200 1600 2G00
E+ C.g 0.99 O.U99 O.~999
/i.rr+( (p;2IA). (pPilA ). (pI:'). 5) pO
/.~+1
PUT': 'i'I +'1' IA un
J+1
JUT': T'/l+FHAr J]
~~ .
A J;"n[N ; J ; ; ] +~ ( 5 . ( p E) ) n ( ( r t:) p~' J - 4 G C. ) . ( ( f1 r) p i)f!) .77. ( ~ j, -I~ C, ;j ) .I t"~'
J+J+1 .
+(J$pPIIA) /JUP
If+I.{+l
+( !.{Sp~'I I!) /!:U:~'
Table VII-2
image:
-------
TA
~. ()OOr.L~:)
(,).OQ001:0
;). r. ~j 0l;~.: U
;.CCijO:O
(;. [)C.OCi;ij
\!.OcuCDC
c..v()()()~;U
f: . e 0 C' 0 1~ C
0.000::;0
~. 0000;::0
v.COOOl,Q
0.0000;:0
0.0000.".'0
o.aOQOro
O.(\()01):70
1).0000'-::0
':
i
0.0000;:'0
o.noooF.O
a. no 00::0
O.OOO{)f,Q
0.00001,'0
o.oocoro
a.aoooro
a.ooooro
0.00001;'0
O.OOOOi;O
o.ooo:>ro
o.ooaOEO
o.ooooro
O.OQOO£'O
O.OOOOEO
0.0000F.'0
O.OOOOEO
O.OOOOEO
a.ooooEO
o.ooaoEO
a.OOOOi:'O
0.0000£'0
o.ooaoro
a.ooooEO
THEORETICAL BU~ER ANALYSIS
Effect Of Equivalence Ratio and Efficiency On
TnperatUN and tnten8ity pazo_ter
Ail' T8IIIP. . OOF
PHI
1.0Cr.~.:'-1
1.000U,-;;-1
1.0000;'-1
1. 00 0 O~' 1
2.0000z.;-1
:.00002;-1
2.00Dor-1
2.000CZ-1
3.0QDOr 1
3.0000:"-1
3.0000[.'-1
3.0000['-1
4.0(JCOI:-1
11.0ooor"-1
. 4.00 OOL;'-l
1+.0000':::-1
5.0000;:::-1
!i.0000/;'-1
S..00002-1
5.0000[;'-1
6.00CO£'-1
c..oooor-1
(;.OOCO;:--l
6.00001'-1
7.0000E-1
7. aOOOi;.'-l
7.0000Z;-1
7.0000!.'-1
D.OOOOZ;-l
8.0000E-1
8 '-0000E-1
0.00001:-1
9.0000r-1
9.00001;'-1
9.0000L'-1
9.0000E-1
1.0000l.'0
1.0000EO
1, OOOOEO
1.0000£'0
ETA
9 . (\~) 0 C::--1
~I. 9000['-1
'].9'JOU";'-1
:; . ':! (j rJ C.. 1
S.0UOOl.-1
~.S'O()OL'-l
9.99('0::-1
'J.9~:~O,::'-1
(J.onOOD-l
~.9000;.-1
:1 .g!100~.'-1
9. ~~!90i:"-1
~.O:J:Jor-l
9. !J 0 00.:.. -1
\,).9noor-l
~J.'j990L-1
9.00002-1
9.9000r,-1
9.9!;OCoI;-1
;.91)9C[,-1
9.00002-1
9.9000,;'-1
!).9900'::-1
9.9990i:-1
9.0000E-1
9. 900 0 L~-l
9.9900E-1
~J.9990L'-1
9.0000£'-1
9.9000E-1
9.9900[;'-1
9.9990L'-1
9.0000[.'-1
9.90002-1
9.9900£'-1
9.9990=-1
9.0000E'-1
!).9000S-1
9.99COE-1
9.9990[.'-1
TA - Ail' Inlet TemperatUN or
ETA - Efficiency
lIT - Burner lnteneity Parameter
TB
L~.(:9:'1~:~2
r..1 S4 ,.;.1."2
~.:: r:D 7 ~.,'::
5. 2':.IS2;:'~
j. :j~7~..'2
~!. 89 CFL"2
':1.'.)7F7;':-:
9 . ~ ~ S ~;:2
1.3041l,2
l.l!~G71::l
1.l!3':iO:3
1.4402;,'~
1.670:)[.':::
1.831+1.',3
1.A4\JCL-73
L8!;11,"::'3
~. "2.7'JT'~
:.214~r.3
:.233~:;3
2. :3S4:~3
:!.3!iG~";3
:.S729t3
~.59104,-:-3
2.59Cfif3
2 . 6 Ei 7 3~' 3
~. Q10A;"3
2.9:!SH':)
2.'337!:b'3
:!.9611L'3
3.2309£'3
:3.25771;'3
~. 2£,04(:3
3.24!J1!:'3
3.S349!:'3
3.5GI+3£'3
3.!i672r3
3.5055:':3
3.8246f3
3.nS(,4L:3
3.B596t3
IN!
3.2:::1'::f 11
:2 . 1 :: S ('.- - 11
:'.:; ':1::. 1.:'
2 . C :: 4 ~! ::: 13
1'; . r: 1 r. r- ,~,- f',
3.['84G:-r,
If . 2 :;. 5 t~.: - i
LI,.27~~~: B
2.!)1.~7:"-:}
\,).5409,:'-4
1.0(:10:;--4
1.i)731L'-~
A .4:!r-,2:.~-2
;.: . 177':,i:.'-2
-
2 . ~ 7 3 3 ,:~ .3
~.39~6n'-1.4
6.':941+'::'-1
1.5211P-l
l.f:30F-2
1. G 1+ 13E-:\
2.0731+z:'0
5.30nl:-1
5.GB67E 2
5.717C£-3
7.1+900[.'0
1.2110'::'0
1.2GOOr-1
1. 26~9L'-2
1.39111:'1
1. 88A9L'0
1.921+~[.'-1
1. :12B3E-2
1.9331+L'1
1.909~z:'0
1. A5 £2F.-1
1.8503.:' 2
1.8103::'1
2.97S9V-1
3.117.1E-3
3.12S9E-S
PHI - Equivalence Ratio
TB - .COIIb\&8t ion Temperature of
Table VII - 3
image:
-------
TA
4.0000E2
4.0000D2
4.00001.'2
4.0000E2
4.0000S2
4. r.0 00'::'2
4.00001'2
4.00001:'2
4.0000E2
4.0000£'2
4.0000E2
4.0000E2
4 . 0 0001'2
4.0000E2
4.0000E2
4.0000E2
4.00"OOF.2
4.0000E2
4.0000E'2
4.0000::'2
4.0000F.2
4.0000 E'2
4.0000E2
4.0000E~
4.0000E2
4.0000E2
4.000082
4.0000E'2
4.0000E2
4.0000E2
4.000082
4.0000E2
4.0000E2
4.000082
4.0000E2
4. 000 OE2
4.0000E2
4.0000E2
4.0000E2
4.0000E2
THEORETICAL BURNER ANALYSIS
Effect of Equivalence Ratio and Efficiency On
Temperature and Intensity Parameter
Air Temp. = 400°F
PHI
1.0000E'-1
1.00nOz.:-1
1.00002:'-1
1. OOOOr-1
2.0000r-1
2.0000£-1
2.0000r-1
2.0000E-1
3.0000i;'-1
3.00001;-1
3.0000E-1
3.00001'-1
4.0000r::-1
4.0000E-1
4.0000E-1
4.0000['-1
5.0000[,'-1
5.0000[;'-1
5.0000r.-1
5.00008-1
6.0000r.-l
6.0000[,'-1
6.00008-1
6.0000E-1
7.0000E'-1
7.0000Z;-1
7.0000E'-1
7.0000E-1
8.0000r.-1
8.0000P-1
8.0000E-1
8.0000E-1
9.0000E-1
9.0000E-l
9.0000E-1
9.0000E-l
1.0000EO
1.0000EO
1.0000EO
1.0000rO
ETA
~.OOOO,:::'-l
~J.90GOD-l
9.9900E-1
9.99':)Or-1
9.0000E-1
9.90002-1
:J.990rC-1
9.9%0::'-1
a.oooor-1
9.9000;':-1
9.9900r-1
9.9990E-1
9.0000L'-1
9.9000E-l
9;990Cr 1
9.9990;:-1
'.1.0000::;'-1
9.'3000£-1
9.9900[,'-1
9.9990r-l
9.0000E-l
9.9000;:-1
9.9900E 1
9.9990£-1
9.0000["-1
9.9000Z;-1
'3.9900r-1
9.9990£'-1
9.0000F-l
9.9000[-1
9.9900r-1
9.9990F-1
9.0000['-1
9.9000r-r
9.9900[,'-1
9.9990['-1
9.0000E-1
9.9000£' 1
9.9900D-1
9.9990E-'1
TB
D.l~52lJL:2
R.r.<::09r2
n.934Cr2
e.93~O,~2
1 . 2 ~ 7 Ii::: 3
1. 2lltJ3: '3
1. :11fnr;,';:)
1. 34~!4:~3
1. f,409E3
1.7591C3
1.7712E~
1.7724!-'3
1.9993r:3
2.15~j7r3
::. if; ~ P. :,'3
2.1G73E3
2.335',';:3
2.5179[:'3
2.53GE3
2.5379L,1~
2 . r, 5 3 I, E 3
2 . 8 (;1;:; ['3
2.P.853~3
2.8874L'3
2.95311.::'3
3.1'j17E3
3.21S5D3
3.2178:;'3
3.23CO:73
3.5025E3
3.52881:'3
3.5315E'3
3.5086Z3
3.7982':3
3.827L-:'3
3.8300E3
3.7E,64E3
4.080323
4.1117E3
4.11l~8r3
INT
3.0n5'JE-G
6.6389Z; 7
7. 1E4 'J::' 3
7.219S::-9
1.'?1!8l!E-3
11.117Gl,::-4
4. n4~;9L'-5
4. 87 r. 8 ;7- G
7.2L451:'-2
1. 5 3(j5,-:;-~
1.64~r,2-3
1.6£il0r.-ll
C.':925[;,-1
1.31121E-1
1.4248:':-:
1.4333;:-3
3.1672:'0
5.50'.::4':'-1
5.7913E-2
5. P. 20Q,t;-3
B . 9 SSG T'O
1.4092:>'0
1.460['-1
1.4719E-2
1.822221
2.5G01EO
2.6312.r;' 1
2.6382£'-2
2.8599d
3.4434FO
3.47372-1
3.l~764E-2
3.4912£'1
3.1274£'0
3.01'47E-1
3.0025E-2
2.9755L'1
4.49992-1
4.6720E-3
4.6894."'-5
TA - Inlet Temperature of
ETA - Efficiency
INT - Burner Intensity Parameter
PHI - Equivalence Ratio
TB - Combustion Temperature of
Table VII - 4
image:
-------
THEORETICAL BURNER ANALYSIS
Effect of Equivalence Ratio and Efficiency On
Temperature and Intensity Parameter
Air Temp. = Booor
TA PHI ETA TB INT
e.00GOE2 1.0000E-1 !J.OOOOL.' - 1 1.?2:' 1;,'3 1. 111381:-:1
8.0000.:.:'2 1.0000E 1 9.9000E - 1 1.263SF,3 2.1~EE - 4
n . 00 00;:'2 1.0000E-1 9.'3900['-1 1.268110'3 2.2071.'"' - S
8.0000[2 1.0000L'-1 9.9990F 1 1.208:::1:.'3 2.215CD-F
8.0000L'2 2.0000[.'-1 g. OOO(ji' - 1 1.6143['3 r.. r. 5 r,4;' - .2
8 . 00 0022 2.0000E-l 9.9000': - 1 1.69392;'3 1.1 (J 002: - ::
8.0000E2 2.0000F'-1 9.99001 - 1 1. 7() HE 3 1.153J? - 3
8.0000['2 2.0000E - 1 9.9990£'-1 1.7 02(:L'3 1. 15<;: 5l: - If
8.0000E2 3.0000[.'-1 I).OOOOE - 1 1 . '3 807:: 3 7.2310£ - 1
8. 0000 Z2 3.00001:,' - 1 9.9000E-1 2.094SZ.'3 1.1(\422-1
8.0000E2 3.0000F - 1 9.99001.: 1 2.106223 1.211011E' 2
8.0000E2 3.0000E-l 9.9990T.' - 1 2.107423 1.24£,11.'-3
O.OOOO['~ 4.0000['-1 9.0000E-l :? . :1:; If 3 [' 3 3.5343EO
8.0000['2 4.0000E-l 9.9000L' - 1 2.4705r3 5.5If:2T - 1
8.0000E2 4.0000E - 1 '}.9900r - 1 2.48Sn::1 5. 7771IE--;.
f!.OOOOL'2 4.0000E'-1 9.G990:':-1 2.48E6F3 5.8013E-3
8.0000£2 5.0000£'-1 9.0000D - 1 2. 6C178L3 1. 0595;;1
8.0000E2 S.OOOGE 1 Q.90GO}'-1 2. 824~Z.'3 1. 5671L'D
8.0000E2 5.0000E-l g. 9 900~:-1 2.841f1E3 1.[,2352" - 1
8.0000P2 5.0000E-1 9.99901:-1 2.fJ43CI:'3 1.629~L' - 2
8.0000E2 G.oooor-l 9.000Q;':-1 2.:1S35;3 2.2G55!:'1
9.0000E2 c.OOOO£'-l ~.900C2-1 3.15847:3 1. llf 7 SEO
fl.OOOO£'2 6.0000l' - 1 !J.090(L~7 - 1 3.178[1:3 3.23f3: - 1
e.OOOOF.'2 6.0000r-l 9. 99~.IOi:'-1 3.1f'O~,D3 ::! . :? I~ 5 1 ~- 2
0.0000E2 7.0000L' - 1 9.0000':: - 1 3. 21~31j73 ::!. fJ 3A2,n1
8. COOOL'2 7.0000'::-1 S. 9 oro;: - 1 3.47511:2 4.81lR7FO
8.0000'::2 7.0000':: 1 ~.9~,OO,"7 - 1 3.4:)8:3:.3 4.9:145:: - 1
0.0000E2 7.0000E - 1 9.'3990j: - 1 :\ . 500 E;' 3 l;.g429L.' - ~
L
8.0000::2 n.OOOOS-l ~!.GnGor - 1 3. 510 2 i.' 3 5.2922.-1
8.000022 a.OOOOE' 1 ~j.9COO:; - 1 3.771;3]'3 5.7:3:'9['0
a. 0000E2 8.0000E - 1 9.9900J:' - 1 3 . 802 O}-3 5. 7n4i: - 1
0.000 OI,' 2 O.0000E-1 9 . 9 9 9 0 ~-' - 1 3.804(;£'3 5.7981.::' - 2
8.0000E2 9.0000[' - 1 ~.OOOOE - 1 3.78017'3 5.0432:'1
8.0000£'2 9.0000E-1 9.9000[' - 1 4~0633E3 4.8237EO
8.0000E2 g.OOOOE' 1 9.9900P-l I,. C9 16.';'3 4.61672' - 1
8.0000E2 9.0000E-1 9.9990['-1 4.09441:'3 Lt.5~4RE - .,
L
8 . 0 0 00;'2 1.0000DO 9.00QOP' - 1 4.03 (\ 0:~3 4.r,110[,'1
8.0000::2 1.0000IlO 9.9000;--1 4.3375i'3 (>.4936I1 - 1
O.OOOOE2 1.0000£0 9.9900D 1 If . 3 5 0 3 :.: 3 6.700:\[-3
8.0000E2 1.0000['0 9.9090r - 1 4.37131:3 C . 7 211L'- 5
TA - Inlet Temperature of
ETA - Efficiency
INT - Burner Intensity Parameter
PHI - Equivalence Ratio
18 - Combustion Temperature or
Table VII - 5
image:
-------
THEORETICAL BURNER ANALYSIS
Effect of Equivalence Ratio and Efficiency On
Temperature and Intensity Parameter
Air Temp. = l2000r
TA PHI ETA TB INT
1.200023 1.0000E - 1 9.00002:' - 1.f,OOlr3 1..J.G?,t~:~~ -
1 -
1.2000£3 1 . () 0 0 0;: - 1 9 . 9 0 0 0 I,' - 1 l.E3:J9F.'3 8.2::9L' - 3
1.20007':3 1.0000[' - 1 9.9900L' - 1 1. 61~39,""3 R . L~ 0 C 3 j' - L!
1. ~D002'3 1.0000E'"":1 0.9990E-1 1 . 6 II 4- 3:73 8.4~4::E - S
1.2000E3 2.0000E - 1 9.00001:.' - 1 1.9735E3 7.8S85L' - 1
...
1.2000E3 2.GOODE - 1 '3.9000[' - 1 2.C495F.'3 1.07G7~ - 1
1.2000£3 2.0000E - 1 9.9900£-1 2.057L.:3 1.1031;,' - :;:
1.2000£3 2.00001' - 1 '3.9990L' - 1 2.05791'3 1 . 1 (J 6 3~: - 3
1.2 000E'3 3.0000I-; - 1 g.OOOD£' - 1 2.3231E3 4.0466['0
1. 20001'3 3.0000E - 1 9.9000L' - 1 2.4328;J'3 5.6029:: - 1
1. 2 00 01:.'3 3.0000E - 1 9.9900£-1 2.4437E3 5.7781[;'-2
1.2000£3 3.00 O,OE,' - 1 9.9990[' - 1 2.441182:'3 5.7958[' - 3
1.2000E3 4.0000E - 1 9.0000F - 1 2.6521["3 1.2627£1
1.2000E3 4.0000E - 1 9.9000g-1 2.7931E3 1.7176EO
1.2000E3 4.0000E - 1 9.99002.' - 1 2. 8071E3 1.7674£ - 1
1.2000£3 4.0000L' - 1 9.9990E - 1 2.808523 1. 7725£-2
1.2000E3 5.0000£ - 1 9.0000E-1 2.9627£'3 2.8295E1'
1.2000E3 5.0000E - 1 9.9000E-1 3.1331E3 3.7092£'0
1.20001:.'3 5.0000E - 1 9.9900E-1 3.1501E3 3.80123'-1
1. 2000E3 '5.0000E-1 9.9990L'-1 3.1518E3 3.8104£'-2
1. 2000£3 6.0000E - 1 9.0000['-1 3.2567£3 4.9972£1
1.2000E3 6.0000E-1 9.9000E 1 3.4552.:'3 6.2081EO
1. 2000E3 6.0000£-1 - 3.4750L'3 6.3242E-1
9.9900::' 1
1. 2000E3 6.0000E 1 9.99901'-1 3.4770E3 6.3358E-2
1.2000E3 7.0000E-1 9.0000E-1 3.5358E3 7.3095E1
1.2000E3 7.0000£ 1 9.9000E'-1 3.7610E3 8.4038EO
1.2000E3 7.0000E - 1 9.9900£-1 3.78351-,'3 8.4847E-1
1.2000E3 7.0000E-1 9.9990£-1 3.7858£3 8.4925E-2
1.2000E3 8.0000E - 1 9.0000E-1 3.8013£'3 9.0145E1
1.2000E3 8.0000E-1 9.9000E-1 4.0523E3 9.1346EO
1.2000E3 8.0000E 1 9.9900E-1 4.07741:'3 9.0758E 1
1. 2000E3 8.0000E-1 9.9990E-1 4.0.79983 9.0691£-2
1.2000E3 9.0000E - 1 9.0000E-1 4.0544E3 9.1763E1
1. 2 000E3 9.0000E-1 9.9000E-1 4.3302£3 7.0746EO
1.2000E3 9.0000E-1 9.9900E-1 4.3579£3 6.7302E-1
1. 200,OE3 9.0000E-1 9.9990£-1 4.3606£3 6.6943E-2
1.2000E3 1.0000EO 9.0000£-1 4.2959E3 6.79541'1
1.2000E3 1.0000EO 9.9000E-1 4.596123 9.0065E-1
1.2000£'3 1.0000EO 9.9900E-1 4.6262E3 9.2436E 3
1. 200 OE 3 1.0000EO 9.9990E -i 4.6292F.3 9.2675E-5
TA - Inlet Temperature of PHI - Equivalence Ratio
ETA - Efficiency TB - Combustion Temperature of
INT - Burner Intensity Parameter
Table VII - 6
image:
-------
THEORETICAL BURNER ANALYSIS
Effect of Equivalence Ratio and Efficiency On
Temperature and Intensity Parameter
Air Temp. :: 1600° F
TA PHI ETA TB IKT
1. f,0'JO~3 1.0000F - 1 9.001,0."-1 1. :-:7 ',' 11;'3 '.) .1:-)[ l,"" - 1
1. :000.""3 1 . 0 0 0 0 E' - 1 9.90CO~: - 1 ~.017'.:.r3 1 . ,; 1 ~ c '" - 1
1.COOOi'3 1.0000:' - 1 C:.Cjr':00T' - 1 ~.I".:?jIJI'3 1.0~71.; - ,
1.(i()(10I:3 1.0000.::7 - 1 9.9?'?O.:' - 1 ~.0214~~-3 1.0::83,~ - 3
1.C:OOOF3 2.0000R - 1 9.00oa: - 1 2.33ILl:F:2 4.P200:~,;
1 . E () 0 OL' 3 2.0000I~ - 1 ~.~JCOE - 1 2.1t~7:'r3 5.11 16 71:' - 1
1. f. ':::0 0T'3 2.0000F - 1 (1.99001" - 1 :>. L1145:'3 5.S2LiL'--:;:.
1.GOOOL'3 2.0000L" - 1 S . ?:) ~J 0 I; - 1 :.415L3 5.<.}314(",:-' - ..,
1.60002.'3 3.0000r - 1 'J.OCCO:' - 1 2. Gf.:.J4;':'; 1.S3£:2T'1
1.COOO.::3 3.0000T - 1 9.9(\00£ - 1 2.7735:'3 1 . 8 (! 7 (> ~ 0
1.COOO:.'3 3.0000I: - 1 9. :)9(:C':::'-1 ~.7840r:J 1.:):1S :,[ 1
1. G 80 0:'3 3 . 0 ° 00 I: - 1 C;. J'J':' 0,':' - 1 :.785r;T,';! 1.~'3:':4:' - 2
1.£)000173 4.0000i: - 1 ~. or,oct:' - 1 :~ . 9 n 3 '.,,-' 3 3.5174; 1
1.£r:OO,.'3 4.0000r - 1 9.900CE - 1 3.1187;'3 11.3171::0
l.GOOO1:3 4.0000F - 1 ':'!.:J :Jon T,' - 1 3.1322:.'3 4.400LJE-l
l.GOOO£3 1t.0000D - 1 9.99:)0[' - 1 3.133ff3 ll.40~:7[-::
1.60002.'3 5.0000E - 1 9.0000'::: - 1 3.2rO'.;!:'3 6.3775E1
1.600023 S.OOOOE - 1 9. 900cr - 1 3. LIlf52r3 7.6323.::'0
1. GO 00 173 ,5.0000r: - 1 9.990CiE - 1 3.4Gl€i,'3 7.7SfGE-1
1.('000T.'3 5.0000[' - 1 9.9990J7-1 3.4632.:-'3 7.76'::OE 2
1. 600 0E'3 6.0000£ - 1 9.0000P-1 3 . 5 C 3 LI i:' 3 9.684721
1.600023 [,.OOOOE - 1 9.90r)O~ - 1 3.755123 :1 .1100r!
1. 6000E3 6.0000r. - 1 9 . 9 9 0 0 Z" - 1 3.7742L'3 1.1225£0
1.600023 6.0000'::: - 1 9.99902..'-1 3.7761 E3 1.12370 - 1
1.6000E3 7.00002 - 1 9.00001"-1 3.8319173 1.2669:'""2
1.6000F.3 7,00002 - 1 9.90002-1 4.0499T'3 1.3SSJF.1
1.6000E3 7.0000T.' - 1 9.9')002-1 4.0717~~ 1.3G02fO
1.6000E3 7.0000E - 1 9.9q~OF 1 1t.07391"3 1.~6P6L' 1
1. 600 OE 3 8.0000£' - 1 9.0000F - 1 4.0077L'3 1. 43!.iOT'2
1.6anOE3 8.0QOOE - 1 9.9000[; - 1 4.3311E3 1. 36lJ.1L'1
1. 6000E3 £3.0000E - 1 9.9900J:' - 1 4.3555£'3 1.3476EO
1.6000E3 O.OOOOJ.' - 1 9.9990[.'-1 4.3579T3 1. 3l1592-1
1.6000E3 9.0000E - 1 9.0000E - 1 4.33161:'3 1. 36G9£'2
1. 6 00 O}: 3 9.0000£' - 1 ~ . :) 0 0 ot' - 1 4.5998'::'3 9.9520['0
1.6000E3 9.0000r. - 1 9.9900;::"-1 4.e:67],:,3 9.4195['-1
1.6000E3 9.0000E - 1 9.99901' - 1 4.62~4},'3 9.36452 - 2
1.6000E'3 1.0000£'0 9.0000i:' - 1 11.5(iItR1'3 9.6(\3121
1.6000E3 1.0000L'0 9.9000F - 1 4.057373 1.2008EO
1. 600 OE3 1.0000EO 9.990 OZ:'-l It. 880['3 1.2350£ ::
1. 6000E3 1.0000EO 9.9990:: 1 4.8£397['3 1. 23762 - 4
TA -
ETA -
INT -
Air Inlet Temperature of
Efficiency
Burner Intensity Parameter
PHI - Equivalence Ratio
TB - Combustion Temperature of
Table VII - 7
image:
-------
TA
:2.0000E3
2.0000E3
2.0000E3
2.0000E3
2.0000E3
2.0000E3
2.0000E3
2.0000E3
2.0000E3
2.0000E3
2.0000E3
2.000CE3
2.0000E3
2.0000E3
2.0000E3
2.0000E3
2.00001'3
2.0000E3
2.0000E3
:2 . 000 OE 3
2.0000E3
2.0000E3
2.0000E3
2.0000E3
2.0000E3
2.0000£'3
2.0000E3
2.0000E3
2.0000E3
2.0000E3
2.0000E3
2.0000E3
:2.0000E3
:2.0000L'3
2.0000E3
:2.0000E3
2.0000E3
2.0000E3
2.00001:.'3
2.0000E3
THEORETICAL BURNER ANALYSIS
Effect of Equivalence Ratio and Efficiency On
Temperature and Intensity Parameter
Air Temp. = 20000r
PHI
1.0000E'-1
1.0000E-1
1.0000E-1
1. OOOOE~l
2.0000E-1
2.0000c;-1
2.00001:;-1
2.0000E-1
3.0000E-1
3.0000E-1
3.0000E-1
3.0000£'-1
4.0000E-1
'4.0000E-1
4.0000£'-1
4.0000E-1
5.0000£'-1
5.0000E-1
5.0000E-1
'5.0000F-1
6.0000E-1
6.0000r-1
6.0000r-1
6.00001'-1
7.0000E-1
7.00001'-1
7.0000.7-1
7.0000E-l
8.0000E-1
8.0000r-l
8.0000E-l
8.0000E-l
9.0000£'-1
9.000017-1
9.0000E-l
9.0000E-1
1.0000EO
1. OOOOEO
1.00001'0
1.0000EO
ETA
9.0000£'-1
9.9000E-l
9.9900E-l
9.9990E-1
9.000QE-1
9.9000F-l
9.9900r-1
9.9990E-1
9.0000E-1
9.9000E-1
9.9900P-1
9.9990E-1
9.0000'::'-1
9.,9000£-1
9.9900P,-1
9.9990E-1
9.0000r-1
9.90COL' 1
9.9900E-1
9.9990P-1
9.0000E-l
9.90COE-1
9.990uE'-1
9.9990E-1
9.0000r-l
9.9000E-1
9.9'3001F1
9.9990E-l
9.0000E-1
9.9000[-1
9.9900;;-1
9.9990E-l
9.0000E-1
9.9000E 1
9.9900D-1
9.99901'-1
9.0000E-1
9.9000E 1
9.9900E-1
9.9990E-1
TB
2.3~99E'3
2.3959/,'3
2.39~)5E'3
2.39913:':3
2.6978L'3
2 . 76 7 2:: 3
2.7741!:'3
2.7748':-:'3
3.01G3::3
3.1169£'3
,3.1270E'3
3.12nOT'3
3.3174I:3
3 . 4 4 7 5 .:..' 3
3.4604£3
3.4r,17E3
3.6027L:3
3.76082:3
3~77C6;::3
3.7782£:3
3.8738~'3
4.0S87,773
LI.0772E3
4.079H'3
4.1318:-:3
4 . 3 II 2 F. D 3
4.3637E3
4.3658E3
4.3777D3
'+.6137E3
4.6374r3
4.6398L'3
4. r,124:"3
ll.8727173
4.8'H19P3
4.9015;;'3
4.8369E'3
5.1241E3
5.1531£3
5.1560E3
INT
6.01f.6J,'O
6.2951i.' 1
f.3251E-2
6.3282Z-3
1. 92:9E1
2.1415EO
2.1645E-1
2. if, f) 8'~- 2
4.4326E1
5.0493I:~
5.1129£ 1
5.1192E-2
8.13'j7El
0.25<::5EO
~J.371!iE 1
9.3827Z-:
1. 2Ei 16E2
1.4080E1
1 . ll21 7 EO
1.4231E 1
1.7059£2
1. C3'~7E1
1.8446[:'0
1.0455.:'-1
2.0431E2
2.0€30E1
2~OS9SEO
2.0590;':-1
2.1f.04E2
1.9486;"1
1.n59fO
1.9125[.'-1
1. ~4 B1E2
1.35171:.'1
1. 273820
1.2659E-1
1.3093E2
1.5013EO
1.60971'-2
1.6125[.'-4
TA - Air Inlet Temperature or
ETA - Efficiency
INT - Burner Intensity Parameter
PHI - Equivalence Ratio
TB - Combustion Temperature or
Table VII - 8
image:
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[1]
[2]
[3J
[4J
[5 ]
[6 J
[7J
[8J
[9J
VSTABILITY[O]V
V STABILITY;I
'1'IL+460+ 0 400 800 1200 1600 2000
A/lSR+OpO
1+1
'1'I+'1'IL[I]
BURN
ANSR+ANSR.(.ANS)
, , .
I+IU
+(I1.pTIL)/4
v
VDURN[U] V
V BURN;I;.!
ANS+ 12 5 pO
+(PRIN'1'=O)/SXIP
,
[1J
[2J
[3J
[4J
[SJ
[ 6)
[7]
[8]
[9]
(10)
[11 )
[12)
[13)
[14)
[15)
[16)
[17)
(18)
(19)
(20)
(21)
(22)
V
'1'1 - '; (TI-460);' of'
ETA '1'11
PHI
SXIP:PHA+0.1x\10
.7+1 .
.7UP:PH+PHA[.7)
COUN'1'+O
E+0.3+0.05x\14
I'1''1':COU/l'1'+COUNT+1
CAL
INTM+r/IN'1'
I+INT\I/l'1'N
+(1=1) /OUT
+(COUN'1'=3)/OU'1'
E+E[I-1)+(O.1*COUN'1'+1)x\10
+1'1''1'
OU'1':+(PR1N'1'-O)/S'1'OR
12 3 12 4 12 1 12 6 DF'1' PH.E[1].('1'B[I)-460).1NTr1J
S'l'OR:ANS[J;)+«'1'I-460).PH.E(1).('1'E[!)-460).1NT[1)x1-1
.1+.7+1
+(.11.10 )/JUP
INT
Table VII-9
image:
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THEORETICAL BUJafER ANALYSIS
Stability Limits
TI = 0 of
PIlI E7'A ,,,..., I;~"'T
.Li..
0.100 0.9480 494.1 O.OOOO'JO
0.200 0.9390 940.2 0.000el0
0.300 0.9250 1338.3 0.003139
0.400 a.noo 1695.4 0.08Q9S!:i
0.500 0.8';) E'O 2019. r, 0.70010'J
0.600 0.8790 2306.2 2.936463
0.700 0.8500 2555.6 8.03(!9(;5
0.800 0.32')0 274~1.7 1(;.408577
0.900 0.G000 ?90~),R 27.0838(,5
1.000 0.7600 3004.9 38.E6CJ8:;
PI = 400 of
PilI E':'A PI: IlIT
0.100 0.8900 840.4 0.000003
0.200 0.8980 1255.5 0.001949
0.300 0.8900 1627.6 6.073046
0.400 0.8770 1960.5 0.7156:31
0.500 0.8600 2254.6 3.347339
0.600 0.8450 2523.7 9.n.50050
0.700 0.8200 2740.1 21.800524
0.800 0.7990 2939.1 38.516837
0.900 o.nGO 3074.3 57.941062
1. 000 0.7280 3162.3 77.320775
TI = 800 op
PHI ETA ",... IliT
. L';
,, 0.100 0.7900 1170.8 0.001762
0.200 0.83130 1559.3 0.074312
0.300 0.8400 1904.2 0.805498
0.400 0.8300 2209.8 4.038581
0.500 0.8200 2490.0 12.647126
0.600 0.8000 2724.2 29.034448
0.700 0.7000 2931.6 53.657546
0.800 0.7550 3099.8 84.558451
0.900 0.7200 3210.6 118.1G0823
1.000 0.6870 3299.2 150.905892
TI - Air Inlet Te8peHture of
PHI - Equi.alence Ratio
ETA - Bumer Efficiency
TB - Co8buad.on T8IIPerature OF
lIT - Oombuation Intenaity Parameter
..... - No Critical Conditions Aria.
Table VII - 10
image:
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THEORETICAL BURNER ANALYSIS
Stability Limits
7:I = 1200 of
PliI D7'A PI': I,'m
l~ J.
0.100 O.5~00 14C2.3 0.126897
0.200 0.7480 1044.3 1.11817'J
0.300 0.7700 21f4.'J 5.476:?56
0.400 0.7700 2447.3 17.2333L~6
0.500 0.7I:'OQ 2695.13 40.177244
0.60C 0.7480 ~919.4 75.838458
(). 7 00 0.72130 3102.'J 1 ~ ~ . C I~ 5197
D.800 ().7000 3240.9 176.5513030
0.900 0.6700 3347.? 232.570(,LI9
1.000 0.63'30 3425.2 2G6.23913~;
'j"I = 1C80 oF'
j) i!1' ETA TI" . T~1m
....l. ~
0.100 ***"* ".",,* ...""
0.200 0.51300 2074.2 9.724018
0.300 0.5570 239LI. 4 27.133C38
O. 4,00 0.6870 266:.3 60.721746
0.500 0.606C 21387.9 113.124843
0.600 O.57G0 3083.G 183.183256
0.700 0.G590 3245.6 26E.4063B3
0.800 0.6360 3372.0 356.503031
0.900 0.6('90 3405.3 447.141329
1. 000 0.5800 3530.4 533.26t36()1
TI = 2000 OF
,7'HI ETA m':'"' INT
.i.J
0.100 ".."" *"*"* It*"..
0.200 "".." ***". .it"".
0.300 0.4060 2458.5 113.805829
0.400 0.54CO 2801.9 1'30.508831
0.500 0.5700 3019.4 295.597717
0.600 0.5700 3192.6 4 2 2 . 1 L~ 2 911
0.700 0.5650 33u5.7 562.614364
0.800 0.5450 345G.8 708.456281
0.900 0.5270 3540.1 851. 9~.69.71
1. 000 0.5000 3587.8 988.1011951
TI - Ail' Inlet T8111p8l'atU1"8 of
PHX .. EQuiv.18nol ~tio
ETA.. JUfftU J:ft1ailftoy
TI .. ConIbU8don T..,.ratUN .r
1'" .. Combut1on Int.n.1ty '.r..tll'
..... .. No CrIt10al ConditIon. ArL..
Table VII
....1.
image:
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[1)
[2)
[3)
[4]
[5)
[6)
[7)
[8)
[9)
[10)
[11)
v.
VIllTPLOT[[j] v
V INTPLOT
170+1
PINT+OpO
PE+OpO
PIIN+0.1)( \10
E+ 0.01 0.025
ITT:PH+PHN[NO)
CAL
PINT+PINT ,IlIT
PE+PE,E
NO+NO+1
+(NO~10)/ITT
,0.05)(\20
Table VII - 12
image:
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THEOJETICAL BlmfER AMALYSIS
co~1n U!; T I r.t! H:TEUS lTY PJlPI'.tTTH' H~T(TJ, r, PH)
TI = 200~ F
E. ~~ 0.1 0.2 0.3 a.1I 0 r: o.G 0.7 0.8 0.9 1.0
.J
0.011 921.08 ~22.'(, ?~3.7 921J.79 n~. 74 92(.5( ~;:'7.2( 9~7.83 o21?29 ?2C.(~
0.025 i "1~.92 '2f.5~ '3:;.7~ 1I~2.53 l:611.n9 47(.f5 48E.3S 119~.:=:3 ~1().2? "5?:),.(5
t
0.05 r 212."5 230.(:3 2'9.1;.1 2(j7.9l 2~(..7( 30~.66 321~.G~ 3l:JoCE 3f2.3b. 380.83
0.10 . 112.37 13" 1!;8.on 18lJ.~8 211.C8 241.33 272.4C <,...; l~ r:"O 337.8 371.92
. ...J -" .. ~_. ~
0.15 I; 78."23 102.72 131.25 1IJ3.92 200.(./1 2111 .?7 :,85.(9 333.()( 383.34 1I3f.13
0.20 I 61.1101 67.61;( 120."3 1~9.92 20(.19 25:'.11 310.4( 3C3.14 1152.87 52(.91
0.25 50.978 78.92" 115.CS H:.32 21f!.r4 20lJ.71 3(0.11 l!li3.33 533.66 r2~). 75
0.30 . 113.809 73.227 IH.13 H7.50 2311.1~ 3i3.f9 1:0 ~ .11 2 5C7.17 517.51 734.1~
.
0.35 . 38.11511 t;9.1 113.73 173.95 250.53 3LJ3.17 "5" .119 5(~.31 (97.11 830.28
0."0 I. 311.192 65.783 113.7!: 180.25 266.15 370. 7E 1I~1.P,3 624.7:- 7(.5.53 908. E5 .
0."5 30.616 f.2.P.211 1l3.': 18~.(' 279.6 3)lJ.27 526.15 ((8.82 21(..45 961.71
0.50 t 27. "e 59.92' 1l2.83 18).21 2P.9.5~ IIll.6l1 550.4( (97.4 f44.59 932.46
0.55 . 2".62" 5".8f.(; 111."~ 19r..3) 2911.89 1121.01 5F2.12 7j)7~14 84~.1)5 9E7.C7
0.60 I 21.938 ~).lIn 107.~1 1eC.1I7 294.42 420.75 ::5Q.02 (95.71 818.72 911:.33
0.65 19.3"3 "!'.C2 lCJ.ll H~.e!) 287.17 II09.~2 539.71 (.(-1.:.8 lt2."P ?OC.7f! 32~.7r ')?2."2 2(;'>.71
0.90 (;.01192 19.212 "1I.2~J R1.122 12(..1f IT':.l'P 2"t.9t: 2}( .1!7 J-:'5.~2 130.~J
0.95 ~ 3.1005 10.201 23.P3 "3.7rl ~7.152 fl9.122 103.r2 10].('" 23.023 Y .44~
1.00 0 I) j t) c c r, " " r
TI - AIR DIIEf TEIIPEJtA'n8 8r
lIlT - c(.lIn.6TI~ IftEIISITY PAlWE1"D
PH - EQmVAlDCE 1tATIG-
E - COIIIUSTICII EmCIDlC'f
Table VII - 13
image:
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VIII.
CORRELATION OF THE EXPERIMENTAL DATA NITH A THEORETICAL HODEL
The experimental data obtained in this program would be
of value by itself without additional theoretical analysis, since it
shows the remarkably low emissions which can be obtained by
proper operation of the Paxve burner. The value of this data,
however is irnrneasureably increased by our ability to interpret
it in the light of the theoretical burner analysis presented in
Secion VII of this report. We have been able to use this.
analytical background as the basis for data correlations. Nith
those correlations, we can predict performance of burners having
widely different sj,zes and operating conditions. Such cC?rre1ations
and the theoretical understanding of burner operation are of
particular value when new operating conditions are of interest.
The Paxve burner tested here had a maximum air flow rate
of 180 Ibs/hr. The highest flow rate normally tested was
approximately 140 Ibs/hr. At the nominal operating condition for
the burner (f/a = 0.038) this yields ap~roximately 100,000 BTU/hr
of heat release. The volume of the burner was on the order of .
0.03 ft3 and hence the nominal heat release rate was approximately
3 x 106 BTU/hr. ft3.
The main thrust of the EPA program, of which this
research work was a part, deals with burners of considerably'
larger heat release; on the order of 2,500,000 BTU/hr. The
first task of data correlation, therefore is to be able to
predict the influence of increasing the scale of the burner by
at least a factor of 25. There is also a great deal of
interest at the present time in low emission burners for
application to gas turbine engines. Gas turbine burners
operate at higher inlet pressures and temperatures than the burner
under test here. It is therefore desirable to have a means for
designing a burner which will have low emissions at elevated
pressures and temperatures and to be able to predict the
influence of these parameters as well as scale si~e on both burner
stability and emission characteristics.
In order to accomplish the goals outlined above, several
types of experimental data correlations were investigated. The
stability data was correlated with the theoretical prediction
of the burner theory outlined in Section VII. The corr~lation
is presented herein. The carbon monoxide and hydrocarbon emissions
from the burner were correlated in terms of the efficiency
predictions of the burner theory outlined in Section VII above.
Correlation of the oxides of nitrogen data is discussed herein. The
combustion temperatures used in that correlation are those predicted
by the combustion theory.
A.
Correlation of the E~erimental Stability Data
Figure 20 of Section VI, shows the experimental blowout
data from the Paxve burner plotted against air flow; this data can
be compared directly with the pre~ictions of the burner theory
image:
-------
discussed in Section VII. In order to accomplish such a
comparison, a computer program, PREDICT, was written which
examines all of the lean burning experimental runs in terms
burner theory outlined previously. .
of the
1.
Program PREDICT
Program PREDICT is shown in Table 1. An
examination of this program will be helpful in discussing the
experimental data correlations which are to follow. Because of
the limitations of the analysis, only equivalence ratios of 1
or less were considered. For each of the lean runs, a value
of the combustion intensity parameter, INTD, at which the burner
was tested was computed. Using the burner air inlet temperature
and equivalance ratio, a subroutine, Program LIMIT was called.
Program LIMIT, shown in Table 2, finds the limiting
value of the intensity parameter INTL corresponding to the stability
limit of the burner. Program LIMIT in turn called CAL, discussed
previously, which finds values of combustion temperature and
combustion intensity parameter as a function of the burner
efficie~cy. Program LIMIT performs essentially the same
calculation as that performed by Program BURN described previously.
Program LIl1IT returns values of the limiting intensity parameter,
INTL and the efficiency and burner temperature which exist at the
blowout limit, EL and TBL.
Program PREDICT now. 'compares the intensity parameter
at which the burner was operating with the value of the intensity
parameter at the stability limit. A stability prediction
parameter is. formed given by
INTR = INTD
INTL
INTR greater than 1.0 implies that the burner will not stay lit.
The air flow rate and hence INTD exceeds the limiting value for stable
operation. INTR less than or equal to 1.0 implies .that stable
burner operation should occur.
We must now compute the operating efficiency and burner
temperature. To accomplish this Program PREDICT uses, EL, INTL,
and INTD to make an estimate of the operating efficiency of the
burner. It then calls Program CAt and uses this estimated
efficiency to compute new values for burner intensity parameter
and operating temperature. The new value of intensity parameter,
INT, is compared .with INTD and the estimate of efficiency
revised. The process is iterated until the value of INT agrees
to within 1% with INTD. The efficiency EFF and operating
temperature TP of the burner are now stored for this run and the
next set of operating data is examined. The process is repeated
until all of the data has been exhausted.
type s .
The results of Program PREDICT are seen to be of several
First, we obtain a value of INTR for every lean run, and
VIII-2
image:
-------
1-
hence a prediction of whether or not the burn~r will be stable.
Secondly, for those conditions where the burner will be stable,
we obtain values of EFF and TP: the predicted effic~ency and
operating temperature of the burner. Finally, for all runs
including both stable and unstable runs, we obtain values of
the efficiency and combustion temperature at the stability limit.
The use of Program PREDICT for comparison of burner
stability limits with theory requires some ingenuity as to how
one should present the data. In this regard it was decided that
a plot of the experimental observations of burner operating
condition versus INTR would be of some interest. A variable
named BURN was devised to assist in making this comparison.
For those runs in which the burner was considered to be operating
normally, a value of 2 was assigned to BURN. For those runs for
which the burner was definitely going out in a reasonable period
of time (less than five minutes), a value of 0 was assigned
to BURN. Those runs for which the burner was operating in an
erratic fashion, or for which the burner eventually went out
. after a long period of time, were assigned a value of BURN equal
to 1.
Figure 1 shows a plot of BURN versus INTR. The upper
line represents conditions for which the burner was stable. The
middle line represents stability limit operation. The bottom
line represents test runs for which the burner was going out.
Clearly the assignment of a value to BURN is a matter of judgment,
and hence it is not surprising that there is some scatter in the
data.
Figure 1 shows a surprisingly good correlation for
the predictions from the values of INTR and the BURN = 0 and
BURN = 2 lines. Virtually all of the BURN = 2 values lie below
INTR - 1.0. Of the runs for which BURN = 2, only 12 of these
have values on INTR greater than 1. The highest is run No. 223 for
which INTR = 1.96. Similarly, of the runs for which BURN = 0
was assigned, only one run, No. 391 had a value of INTR below
1.0. For run No. 391, INTR = 0.84.
The runs for which BURN = 1 was assigned do not show
quite such good correlation. Here there are lean limit runs for
which It~R = 0.25 and other lean limit runs for which INTR = 2.5.
Most of these lean limit discrepancies appear to be a result
of the difficulty associated with obtaining accurate fuel/air
ratio data. While the volumetric gas analysis equipment is
quite accurate for normal burning runs, it becomes less
valuable near a blowout condition. When the burner is near
blowout, the efficiency of the burner may drop to as low as
90%. Under these conditions, the fuel/air ratios based on the
volumetric data should be in error by about 10%. While this
may seem like a small error, a change of burner temperature of
200°F has a pronounced effect on the computed value of INTR.
2.
Stability Tests From Program PREDICT
The stability predictions obtained from
VIII-3
image:
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Program PREDICT are tabulated in Tah1es 3 through 18. The first
column in each of these tables shows the run number. Next we see
volume of the burner under test, then the inlet temperature and the
air flow rate. In Column 5, the equivalence ratio at which the
burner was operated is shown. This is based on the nominal fuel/air
ratio discussed previously. Column 6 shows the burner intensity
parameter based on the flow rate and volume of the burner.
Column 7 shows the limiting value of intensity parameter at lean
blowout as, computed from the equivalence ratio and air inlet
temperature. From these the stability parameter INTR in Column 8
is computed. Column 9, labeled BURN, shows the estimate of burner
stability provided by the burner operator or the data in the
burner notebook. As explained above, 2 represents stable operation
of the burner, 1 represents lean limit operation and 0 corresponds
to operating conditions for which the burner will go out.
Examination of Table 3 through 18 provides additional
into the validity of the burner stahility theory. We see
many instances where it was difficult to judge how close
to the stability limit, the value of INTR is in fact close
insight
that in
we we re
to 1.
Another interesting observation from the Table deals
with those values for which the burner was at or near lean limit
operation while the value of INTR is low. Here, the computer
program predicts that the burner will have some considerable margin
of stable operation, while in fact it was near or at its blowout
limit. These were usually runs at low air flow rates in test
Stand 2. This burner is more subject to heat loss than the other
burners tested., The influence of heat loss on the stability of the
burner can be significant, par~icu1arly at low air flow rates.
Since the burner stability analysis program did not take this
heat loss into account, it is not surprising that there are some
differences between the prediction and the experiment at the low
flow rates.
3. Correlation of Stability Data with
Theoretical Stability Curves
In addition to the information obtained from
Program PREDICT, the stability limit data previously obtained from
Programs STABILITY and BURN can be used to correlate burner blowout
data.
Figures 20, 21, 22, 24 and ,25 in section VI
show blowout data for the paxve Burner. Superimposed on these
figures are theoretical stability limit curves based on the analyses
of Section VII. It is clear that the theoretical limit curves
agree well with the experimental data. The propane curves are more
complete than the kerosene curves because it was easier to run the
propane tests. Figure VI 20 is for propane at ambient temperature
in a 33 cu. in. burner. This figure shows that all of the blowout
points (squares) lie to the left of the theoretical limit line,
while all but two of the stable burning points (circles) lie
to the right of the line. The lean limit points showing marginal
stability (triangles) are scattered around the theoretical limit
VIII-4
image:
-------
line.
Another way of showing the same information is to plot
the data on a curve of equivalence ratio versus burner intensity
parameter. Figure 2 shows such a plot for the ambient temperature
data. Superimposed on the data is the theoretical limit line for
75°F inlet temperature; we again see that the data and the
theory are in substantial agreement.
4. Final Comments on Burner Stability
Correlation
The experimental stability data from the Paxve
burner agrees quite well with the predictions obtained from the'
burner theory, particularly at high flow rates. There are several
matters which bear further investigation.
a. The stability of the burner is particularly
sensitive to extraneous heat loss. Incorporation of a heat loss
term in the stability analysis should improve the correlation
between the experimental and theoretical predictions, particularly
at low flow rates. The interpretation of such a burner heat loss
parameter in terms of burner construction considerations would be of
great value in the improvement of burner design.
b. The burner stability 'prediction program
assumed that the fuel entering the burner was at ambient
temperature. A correction was made for the heat input necessary to
raise the fuel to the air inlet temperature. During many of the
runs, particularly those with kerosene, the fuel was at an
elevated temperature. This seems to increase the burner stability.
The burner stability prediction program could be readily modified
to take into account the fuel inlet temperature.
c. The burner analysis was limited to lean
operation. This was primarily a result of the limited funding
available for this effort and a corresponding limited interest
in this area of burner operation for automotive application. Some
industrial processes utilize staged combustion with rich mixtures in
the first stage. An extension of the present work to investigate
rich operation may reveal procedures that would assist in reducing
the level of pollutants emitted from these sources.
d. The stability of the burner as well as its
emission characteristics are influenced by the uniformity of the
fuel/air distribution within the burner. Burners which have highly
homogenous fuel/air mixtures at the. inlet are generally somewhat
less stable than burners which have non-uniform fuel/air distribu-
tions. This is due to the fact that the flame can stabilize in a
locally rich portion of the flow and then spread through the rest
of the stream.
~.:
.",1",
Non-uniform fuel/air distribution is also a factor ~n
burner emissions. The problems of hydrocarbon emissions from the
top of the vapor generator stack, which caused so much trouble during
VIII-S
image:
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the course of this program, was finally traced to a badly distorted
fuel/air profile in the air/fuel mixture ahead of the burner inlet.
Once this non-uniform fuel/air condition -had been corrected, the
hydrocarbon emission problem was immediately cleared up.
Unfortunately it is not possible at this time to go back and
establish a uniformity of the fuel/air mixture during the early
stability tests.
If the indicated improvements in the burner theory were
made, it seems clear that the theoretical analysis will be more than
adequate to serve as a basic tool in burner design and development.
The burner stability theory predicts the influence not only of
flow rate and burner volume, but a180 air inlet temperature and
pressure. Verification of the validity of this analysis at high
inlet pressure and temperature is a task of great importance. That
work was beyond the scope of this program.
B.
Correlation of the Oxides of Nitrogen Data
It is clear from an examination of the experimental
data that the oxides of nitrogen emissions from the Paxve burner ex-
haust are a strong function of fuel/air ratio and not strongly dependent
on air flow rate through the burner. An examination of comparable
data from cold air and hot air runs shows somewhat higher NOx levels
at the elevated inlet temperatures. Although the data scatter makes
an exact comparison difficult, it appears that the influence of
inlet temperature is what one would expect if the NOx were a function
of combustion temperature only. Figure VI-l9 shows all of the NOx
data from the burner plotted against burner temperature. Despite'
the scatter it is' clear that a correlation between these two
variables exist.
It seems reasonable to presume that the oxides of nitrogen
in the burner exhaust are formed in the burner by a chemical
reaction whose rate is given by an Arrhenius type equation
~ (NO)= I< [02] a
Vol e-E/RT
\'here:
NO = Nt of NO formed
Vol = burner volume
E = activation energy of the over-all reaction
Since the NOx concentration in ppm is the ratio of the NOx weight
flow to the air weight flow, we might expect that the NOx in
parts per million would be given by an equation of the form
[NO] = 1<[02]a e-E/RT
WA/vol
I. .
Exa~ination of the data, however,' shows that the predicted
inverse dependence of NOx with air flow rate either does not exist,
VIII-6
image:
-------
or else is
dependence
be further
reciprocal
suppressed by the data scatter. The predicted
on temperature however, is clearly evident, and
characterized by plotting the NOx concentration
combustion temperature.
can
against
Figure 3 shows such a plot for all of the data~ Figure
4 shows a similar plot for the small sample of the data in which the
fuel type and general operating conditions were relatively fixed. In
both cases, we can draw a straight line through the data and obtain
an empirical correlation.
Paxve has examined several approaches to the
correlation of the NOX data obtained during this program. The
possibility in involving the air flow, and the oxygen concentration
in the result was investigated. We found that a better correlation
could be obtained by using the combustion temperature alone than
could be obtained by including these other factors. The ambient
temperature data appears to be well fitted by an equation of the
form
NOx = 4.38 X 105 x e-E/RT
with
E = 36.7 K cal/mole
Figure 5 shows this equation superimposed on the summary NOX
curve, using the theoretical flame temperatures for 70°F and
400°F inlet temperatures. It is clear that the curves give
a reasonable fit to the data, although the 400°F curve is
somewhat conservative as compared to the bulk of the high
temperature data. . .
C.
Correlation of the CO Emissions Data
The theoretical burner analysis described in Section
VII of this report provides a basis for correlating the CO
emissions from the burner. The theory yields values for the burner
efficiency as a function of the inlet temperature and the burner
intensity parameter. If we subs tract the efficiency, from
1.0, we obtain the unreactedness, 6, which should be proportional
to the emissions of unburned or partially burned material in the
burner exhaust. Program PREDICT gave an evaluation of each lean
test point. Tables showing ~1e predicted burner efficiency,
the predicted emissions, and the acutal values of the CO, HC, and
NOx emissions, are presented in Tables 19 through 31. Examination
of the data in those tables show that the CO emissions are generally
less than the predicted values.
In order to examine this further we have taken some
typical sets of CO gm/Kg emissions data and superimposed the
predicted emission levels based on .the analysis. Figure 6 shows
the CO emissions from the burner for the small burner (33 cu. IN.)
on test stand 1 with ambient air and propane. The CO emissions are
obviously strongly influenced by the air flow rate. Curves
VIII-7
image:
-------
through the data for air flow rates of 25 lb/hr, 50 lb/hr, and
100 lb/hr have been drawn on the figure as solid lines. Predictions
based on the theoretical burner.analysis are shown on the figure
as dotted lines. Two of these theoretical prediction lines are
shown, one for 25 lb/hr, the other for 100 lb/hr.
Figure 7 shows a similar set of data for later runs in
test stand 2 burning kerosene with elevated inlet temperatures.
again, the predicted values are substantially higher than the
experimentally determined CO emission levels.
Once
We do not have a simple explanation for the low levels
of CO emissions observed. We suspect, however, that this is a
consequence of the oversimplification involved in arriving at
the predicted values. The theoretical analysis was based on the
assumption that the unreactedness (the combustion inefficiency)
was represented by vaporized but unburned raw fuel. The predicted
heat release was therefore reduced directly with the unreacted-
ness. Experimentally, however, the unburned material which is
most significant in the combustion chamber under lean operating
conditions is not raw fuel, but rather carbon monoxide. In
order to correlate the CO data, we therefore assumed that the
CO levels would be equal to. the predicted unreactedness. This
is clearly inconsistent. If we had refined our analysis to allow
for partially reacted material leaving the chamber (the fuel
converting into water vapor and carbon monoxide), then the
heat release used in the analysis at low efficiency points
would have been greater and the predicted emissions would have
been less as the blowout limits were approached. A revision
of the analysis to account for this partial reaction process
would be desirable, but it was not feasible within the
financial limitations of the present contract. In any case,
it seems clear that the CO emissions to be expected from the
Paxve burner will be less than those predicted by the present
theory. This gives us a method for obtaining CO emission
estimates which will be conservative for burner application
studies.
Figure 6 also shows the dramatic reduction in CO
emissions which occur as the exhaust gases pass through the
vapor generator stack. This is undoubtedly a result of the
continued oxidation of the CO to C02 which occurs as the gases
cool off during their passage through the heat exchanger. The
rate of the CO oxidation reaction is still substantial at
temperatures over 2000oF. As the gases cool, there is time
for the combustion reaction to come closer to completion.
There is also time for CO which arises from the high temperature
equilibrium dissociation reaction to recombine as the equilibrium
shifts during cooling. The theoretical predictions are thus.
even more conservative for a burner coupled to a heat exchanger.
VIII-8
image:
-------
<
...
.....,
~~
....
BURNER STABILITY CORRELATION
BURlIJIG
LIMIT
BLOWOUT
2.0
1.0
Q
0.5
...-. ---- - - .
. ..-..-. --.-. . .-
o
0.5
BURNER STABILITY PREDICTION PARAMETER
1.0 1.5 2.0 2.5
.. .
. . .
. .
.
..
.
.
.
..
. ... .
.
. .
1.0 1.5 2.0 2.5
BURNER STABILITY PREDICTION PARAMETER
INTR
3.0
.
3.0
INTR
3.5
3.5
4.0
.
4.0
image:
-------
o ca..
H
5
,6
.
~
> 0.6
S
a
w
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Q
.
<
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0.2
o
0.001
~: I", "'I]""'_::;-~- -
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.'
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-"j! ji~ '.H! 11 .~-=-..:... --- ........:~.!,d;.jJi....
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INTENSITY PARAMETER ::~~ ;~~. ~:" ..
VS " .,:' - -I--..._~. . "I' :rt ~~ ' . ;':~;
1 ~' EQUIVALENCE RATIO :
~,:, :'::IFI" : -;...:..c~ --" .' I -. =--."-. :.::, ....~".::,
n+ . . b. - ... ,'PI' ' . . " .., ,.
: :_- - -:"" -.- '; ,,~;~ ~I
,,' ;f.1:" ,:, '-, """":: I,' .'" ,.~- ",,;.;:, :' ,. ..,
,I '" ~~:, . ~-~: -- I~, ... ,::" ,:-- ':" :,,: ,::.:"
; ~ " , ~,::;,,:::;.'-~~<=~~:~ .-~.~- ;.:.' ~ ;-~-- h~'; ,:,,"
.,-!; ,.; '. i.. :: I '1 '1'
': :>':;:,': ,'''':,,: ~~ ~~~-~~ --~I:~- .-' -~t~~ :~:-'i:'::;
"., " ", -=- =:.::_-= 111-'-'"" -.':' "ill~'::'.: .:.::.
'::'. --- rlli/, --. 8 '. .
., , ' . - -. -. --- 1- . 1 '
I: 'j .' -'. ..Ij . .
,i - - ~ H 'r" - -
~,~I .. -.. a-r='-' 1=- " - -. -" "::.:
. - t . . - - " I ' -- - ~ ' ,
".' --
, ,II' I. ~ --- - J ~ -.--.--
,.
BURNER STABILITY CORRELATION
"
'..
"
.
.. -... ----
.
.- -
-
..,.
-~'.. ...-
. .-
-. -- ---- -
.
.. -
---- _.~. _u-
-. -
I I
..
"
.f
--. --
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'. ::v:: ::::I:~:~-
-I.
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-
0..' ....-
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--
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_::: ::::::~:::t
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.
.-n ....
-
-.-- ..
0.- .nO
-
u.
!$
+ ii! -I"-
Titt~1:; "
Iii,
::::;:_:-=t~i :::: :_::h ~
<--On
h.
nO---' -
...
0-.-
h- ..
h
,.
--.
--.
..
::: :-;.-t
-.
0.01
0.1
INTENSITY PARAMETER IHTD
1.0
10
image:
-------
rot
I
'"
o
II
rot
~
,.
I
o
rot
I
I' ~
I
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15
~
I:!
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....
t;
:>
01:
:IE
o
U
~
i
Do
....
U
./il
coaaUATION Of' QJU~S (:# HITII05EN Dl'TA
VITH aECIPaocAL COMIUSTIOH T~eIATu.e
.
.
. .
.
. .
.'
. .
.. .
. .
, .
.:-
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...' .:::
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.. . 8. .
.
. . . .
. . .
. .
.
.
. . .
. .
0.01 0.10 1.00 10.00 100.00
OXIDES O~ NITROGEN EMISSIONS FROM THE BvaNE.
1000.00
NDB PPM
rlc.
VIII;'!
rot
I
a:
o
..'
II.GO.f+
..
,.
o
rot
I
II .
~
~
50;
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3.1
z
o
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ft
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0..
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to:
'f;!
3.5
I
2.50t
I/TE'~P
COR.fLATICN (:# OXIDfS ~ NITP.OGfN DATA
, .
ICF.ItOS eNf'--+tOT--fI UPHER DATA
~ .
0.1
0.22 .
10
0.116
1.0
2.15
11.611
!fOX COJ8CDf'!Uno" /fOB
PP/f
ri~.
VIII-II
image:
-------
a..ELATION OF BURNER OXIDES OF NITROGEN DATA
0.10
(X10) CORRELATING PARAMETER
0.22 0.-6 1.00 2.15
NOX/02
4.64
10.00
-.0
2.7
r4
I.G
0
r4
.
... 3.7
-
~
0 .
r4
.
~l
~ .
~ 3.5
(oJ
~
~, .
:;r;
c
....
... 3.2
(I)
'::>
~
0
u
~ .
<
u
~ 3.0
It
....
u
t!
<
"""'1
.... ...
......
. .
(II
I
2.5~
I/TEMP
. 0.10
I I I ,
0.22 0._6 1.00 2.15
(X10) CORRELATING P~P.AMETER
I
It.fiIt
NOX/02
I
]0.00
image:
-------
10"
1.0
- - = ~ ~FFof='~ ~ - :~; -- --- :P n- - -- 1- } 1 - -;:-;-1
: -- u :eEf:'-LLJi"- oj? - -- ,- -- - --r- - -01 H J fU~--f-
-. -- COG EMISSIONS DATA FROM THE PAXVE BURNER' -- +-1 : :-1
, !"UEL IPROPANE :: -- --,. -;~f-~~-:
AIR TEMP :UNDER 250 F -- tl' -1;- '-I!
BURNER VOLUME I 133.0 CU IN -'~ -f j- -i -[-,--;-.-.
-- -- t - .-- rl-11'1- i'-r_-, T:-u-- : -- -; ~;. : + -j~w- -P!~ ~ l
- Ii t i-" ,,- - "-, ..- - .: t~I-H!ii WiJ
103~~~ -~---~-~ - -. :.-- ,-<~::~_..- <~-=---- :--- ,i I :_' -~
- -- - - --, '-, -- -- ~- -- '?f:? ~~ -_:.- -- -. - n - I
8> -->-~<--~-' " -
--~;::_~._:--;- ~ -~--:~- --~n :;: -- I - --ltt.~:l+h- --.0..---
102 ::_:'i>:I~~ :", ".iIIi:1 ::"1~HHiJ.tOMO
I':" -' ';j- :.::, - ,I ;,'T": ,',f'J-,}l:., - "to ;~:iC Ow
~, -:;;, - --, ,,:e'(;~..;;.f '1'. :cF:
-- - -- - .- -. - -j _n -- --
-++: --- n- - - - -- -' UDder 40 + --,- ~- - - --: -- --
-i-1- -- -~ n- j 40 - 70 0 -- - - - ..-: - --
, - " " ..;,>- ~, -' illr :i!: g ,: _<'810...
-: ,;'~' ':'11,__- -' - P1t;'ti7W-;08t.j ~I ~~I::I' .'111~f: >:-1 o~
"" - i:A~--- - - 1--, J. I I' I
, " : . "I -':':, d : 1 !ilfl ! Iii j11'1: - ,: -, .-
~L ,- -u -- , :! I - 1,1 -
- u -- -- -- = . = : -- _:: ~ :-: - - -- =~~IIIT or THE GAS r -- I j I 'II.
, . " ,- lhtffFffl1mmnTffiTIII i ' ) II !
-
--
-
- - .-
--
~".-:'
I'" .,.,
-
- r:
n
-- -
--
o .,,,
.8
10
o.
0.02
0.0"
0.0&
0.08
9.10
0.12
0.1"
0.16
MOMMAL FUEL AIR RATIO FAt
Fia.
VIII-I
image:
-------
10
tIC
.¥
.....
~
.
i!:}
1-4
><
o.
i
:z:
~ 1.0
PAXVE BURNER
CARBON MONOXIDE DATA
KEROSENE DATA
VOLUME 52.3 cu in
AIR TEMP OVER 250 of
100
AIR FLOW
f/Hr.
Under 40
40 - 70
70 -120
120 -150
;-: Over 150
Flag indicates runs
from No. 282 ON
RUNS WITH !f0 CO DETECTED WERE
PLOTTED AS 5 PPM WHICH IS THE
RESOLtrrIOM LIMIT OF THE GAS
CHROMATOGRAPH
0.1
0.02
0.03
o.o~
0.05
0.06
NOMINAL FUEL AIR RATIO
FAN
+
o
~
o
o
1-
0.07
Fig.
VIII-7.
image:
-------
PROGRAM 1)RI:DICT
(1]
(2]
(3)
(~)
(5 ]
(6]
(7]
(8)
[9)
(10)
(11 ]
(12)
(13]
(n)
[15)
(16)
(17 )
(18)
(19)
(20)
(21 )
(22)
(23)
. V
V PREDICT;I;PH;TI;INTD;LIT;CA;CF;C~;TE~T
NL+ppnIG
1+1 -
INTD1+INTL+INTR+TBL1+EL+EFP+TP+(pPHIC)pO
GO:PH+PHIG[I]
TI+TAG(I]
WAD+flAG[I]
INTD1(I)+INTD+WADxCONST[I]
LIMIT
INTR[I)+INTD+INT
INTL[I]+1NT .
TBL1 [I]+T8
EL[1]+E
LIT+INTDsINT
+(LIT-O)/OUT
!RN: E+1- (l-E) x( INTDtINT)*l- (PTI=l) +2
CAL
'lfST+(1- I NTD+ IRT)
+«I'~ST»0.61)/BRN
OUT:EPF[I)+LITxE
'P(I)+('BxL1T)+(1-LI,)xTI-~60
I
1+1+1
+(IsRL)/GO
Table
VIII-l
PROGRAM LIMIT
I
I
I .
I,
[1)
(2)
(3)
[~)
(S)
(6)
(7]
(8)
(9)
[10)
[11 )
[12)
[13]
V
V LIM1T;1;COURT;INTM
COUNT+O
E+O.3+0.0Sx\11f
ITT:COUNT+COUNT+l
CAL
1NTN+r / nIT
1+1/1' \ 1N'/.I
+(I=l)/OUT
+(COUNTa3)/OUT .
E+E[I-1]+(O.1*COUNT+1)x\10
+ITT
OU':E+E[I]
1NT+1N1'(1)
TB+TB[I]
Table
VIII-2
image:
-------
COIIPABISO. 0' PB~DIcrD ~.D UPBRIIIB.rAL BURNER STABILITY DATA PAGE 1
BU. ..0£ £IR rop ~IR P£OJI "UI" IN'r DATA INT LIN INT RAT BURN
.0. I.*3 0' LBSI.. BArIO JI/VP*2 JI/VP*2 ID / IL
1 33.0 75 22.3 0."678 0.3244 0.5487 0.590.6 - 1
2 33.0 10 22.2 0.5309 0.3229 1.5621 0.2065 -1
3 33.0 15 "5.3 0."822 0.6585 0.7412 0.8875 -1
.. 33_.0 15 "5.3 0...52.. 0.6585 0.4299 1.5303 - 1
5 33.0 15 "7.0 0."&50 0.6830 0.5447 1.2526 - 1
I 33.0 II 51.1 0."501 0.8991. 0.4176 2.1505 -1
7 33.0 90 51.7 0...9..8 0.8974 0.9350 0.9588 -1
8 33.0 '0 &1.7 0.&32& 0.8974 5.4903 0.1633 2
9 33.0 90 &1.7 0.5073 0.8974 1.1420 0.7850 1
-10 33.0 90 &1.7 0."697 0.8974 0.6079 1.4747 0
11 33.0 90 61.7 0.5230 0.8974 1.4478 0.6192 1
12 33.0 90 51.7 0."322 0..8974 0.2935 3.0539 0
13- 33.0 '0 11.7 0.538& 0.8974 1. 8107 0.4951 - 1
1.. 33.0 90 &1.7 0.5073 0.8974 1.1420 0.7850 1
15 33.0 90 &1.7 0.5089 0.8974 1.1695 0.7666 2
16 33.0 90 71.1 0.5689 1.1362 2.6981 0.4207 2
17 33.0 90 78.1 0 . 51t1 7 1.1362 1.8890 0.6009 1 .
18 33.0 90 71.1 o. 551t1 1.1362 2.2311 0.5087 2
19 33.0 91 78.0 0.6115 1.1352 4.4320 0.2559 2
20 33.0 92 78.0 0 . 5377 1.1341 1.8009 0.6291 2
21 33.0 92 71.0 0."609 1.1341 0.5216 2.1721 0
22 33.0 93 77.9 0 . ..96.0 1.1331 0.9661 1.1716 0
23 33.0 93 77.9 0..5209 1.1331 1.4192 0.7976 1
2.. 33.0 93 77.9 0.5382 1.1331 1. 8199 0.6220 1
25 33.0 93 77.9 0.5631 1.1331 2.5330 0.4469 1
BURIl .. 2 --- srABLB- OPBBArIO. UNITS OF INT ARE LBS/SEC FT*3 A TM* 2
BUR. . 1 srABILIrr LIllIr
BUR. .. 0 - - - BUR .BR GOBS our
image:
-------
COMPARISON OF PREDICTED AND EXPERIMENTAL BURNER STABI LITf DATA PAGE 2
RUN VOL AIR TEMP AIR PLOil EQUIV INT DATA IlIT LIM INT RAT BURN
NO. IN*3 OF LBSIBR RATIO JlIVP*2 JlIVP*2 IDIIL
26 33.0 90 103.3 0.6937 1.5030 9.5186 0.1578 2
27 33.0 93 103.1 0.5794 1.4989 3. 097 3 0.4835 2
28 33.0 96 102.8 0.5227 1.491+9 1.4727 1.0140 0
29 33.0 97 102.7 0.5118 1. 1+935 1.2588 1.1852 0
30 33.0 97 102.7 0.5231 1. 4935 1.4887 1. 0022 1
31 33.0 102 120 . 9 . 0.5930 1.7583 3.7383 0.4699 2
32 33.0 105 120.6 0.5465 1. 7537 2.1285 0.8231 2
33 33.0 108 120.2 0.5158 1.7490 1. 3 937 1.2537 1
34 33.0 95 121. 6 0.5099 1.7691+ 1.2117 1.4587 0
35 33.0 102 120.9 0.5190 1.7583 1.4273 1.2307 1
36 33.0 112 153.8 0.5878. 2.2377 3.6370 0.6147 2
:p 33.0 117 153.2 0.5613 2.2280 2.6910 0.8272 2
38 33.0 120 152.8 0.5451 2.2222 2.201+1 1.0073 2
39 33.0 120 152.8 0.5299 2.2222 1.7910 1.2396 0
40 33.0 120 152.8 0.5135 2.2222 1. 41 0 5 1.5739 - 1
41 33.0 124 152.3 0.5470 2.2146 2.2941 0.9654 1
42 33.0 91 103.2 0.7565 1.5016 15.0328 0.0998 2
43 33.0 93 103.1 0.5222 1.4989 1.4474 1.0345 1
44 33.0 87 41.8 0.7529 0.6085 H. 5467 0.0418 2
45 33.0 85 41.9 0.6916 0.6096 9.2316 0.0660 2
46 33.0 84 41.9 0.6132 0.6096 4.4163 0.1379 2
47 33.0 82 42.0 0.5333 0.6113 1.6303 0.3745 2
48 33.0 82 42.1 0.4910 0.6121+ 0.81+97 0.7199 2
49 33.0 80 42.1 0.1+"97 0.6124 0.3988 1.5337 0
50 33.0 80 42.1 0.4997 0.6124 0.9710 0.6300 1
BURN = 2 --- STABLE OPERATION UNITS OF INT ARE LBSISEC FT*3 ATM* 2
BURN = 1 --- STABILITI LIMIT
BURN = 0 --- BURNER GOES OUT
<
Ho-J
:::~
''''
~..
image:
-------
COIIPARISO. 0' PRBDICf'BD A.D BZPBRIIIB.f'AL 8UR.BR Sf'ABILIf'Y DAf'A PAGE 3
RUlI VOL AIR f'BIIP AIR 'LOll BQUIV I.f' DAf'A I.f' LIII I.f' RAf' BURN
.0. IlI*3 0' LBS IBR RAf'IO IIIVP*2 JlIVP*2 IDIIL
51 33.0 83 25." 0.6097 0.3688 ...2..0.. 0.0869 2
52 33.0 82 25." 0.5"06 0.3691 1.8068 0 .20U 2
53 - 33.0 82 25." 0."'''5 0.3691 0.5329 0.6919 1
n 33.0 83 25." 0'."510 0.3188- 0 . U"" 0.8888 1
55 1.0 83 "2.0 3.1753 -1.0000 -1.0000 -1.0000 -1
51 - 1.0 81 "2.1 2.6U2 -1.0000 -1.0000 -1.0000 -1
57 -1.0 12 "2.0 2.8966 -1.0000 -1.0000 -1.0000 1
58 1.0 85 "1.9 2.6510 -1. 0000 -1.0000 -1.0000 - 1
59 -1.0 85 "1.9 3.1812 -1..0000 -1.0000 -1.0000 - 1
60 1.0 90 "1.7 1.9"52 1.0000 .-1.0000 -1.0000 -1
61 - 1.0 90 ..1.7 1.9"52 - 1.0000 -1.0000 -1.0000 -1
62 -1.0 85 _1.9 2.6510 -1.0000 1.0000 -1.0000 -1
63 1.0 87 "1.8 3.1870 -1.0000 -1.0000 -1.0000 -1
6- - 1.0 85 _1.9 2.6510 -1.0000 -1.0000 -1.0000 - 1
65 - 1.0 88 "1.8 2.7692 -1.0000 -1.0000 -1.0000 - 1
66 - 1.0 85 "1.9 2.8585 1.0000 -1.0000 -1.0000 -1
67 -1.0 85 "1.9 2.7616 -1.0000 - 1.0000 -1.0000 -1
68 -1.0 78 25.5 2.5262 1.0000 - 1.0000 -1.0000 - 1
69 1.0 82 2".7 2.3985 -1.0000 - 1.0000 -1.0000 -1
70 - 1.0 85 25.3 2.9167 -1.0000 -1.0000 -1.0000 -1
71 - 1.0 86 25.3 3.06"6 -1.0000 -1.0000 -1.0000 - 1
72 - 1.0 90 11.7 2.3863 -1.0000 -1.0000 -1.0000 - 1
73 -1.0 93 61.5 2.""93 -1.0000 - 1. 0000 -1.0000 - 1
7.. 33.0 86 25.3 0.50"" 0.3677 1.0731 0.3"23 1
75 - 33.0 85 25.3 0.6219 0.3681 ".8599 0 .0757 2
BUR. .. 2 --- Sf'ABLE OPBRAf'IO. U.I'1'S OF INf' ARB LBSISBC FT*3 ATM*2
BURlI .. .1 --- Sf'ABILIf'Y LIllII'
BURR .. 0 u- BURliER GOBS OUf'
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CONPARISOII OF PREDIC'!ED AND EXPERIMENTAL BURN'ER S'!ABILIT! DA'!A PAGE 4
RUN VOL AIR TEMP AIR 'LOJI EQUIV IN'! DATA .. INT LIN IN'! RAT BURN
NO. III*3 of LBSIHR RATIO JlIVP*2 JlIVP*2 IDIIL
76 33.0 85 25.3 0.8339 0.3681 22.9747 0.0160 ~
77 33.0 85 25.3 0.9960 0.3681 41.5938 0.0088 2
78 33.0 90 51.7 0.5574 0.8974 2.3338 0.3845, 1
79 33.0 92 51.&' 0.6869 0'.8958 9.0511 0.0989 2
80 33.0 90 &1. 7 0.9927 0.8974 41.6033 0.0216 2
81 -1.0 92 11.6 1.4432 -1.0000 1.0000 -1.0000 -1
82 33.0 103 102.1 0.5050 1.4855 1.1611 1 .2781 2
83 33.0 105 101.9 0.7666 1.4829 16.5407 0.0896 2
84 33.0 100 102.4 0.7464, 1.4895 14.3647 0.1036 2
$5 33.0 103 102.1 0.9178 1.4855 33.8123 0.0439 2
86 -1.0 105 101.9 1.2812 -1.0000 -1.0000 -1. 0000 -1
87 33.0 300 59.3 0.5391 0.8628 3.8187 0.2259 2
88 33.0 300 59.3 0 .6869, 0.8628 15.3308 0'.0563 2
89 -1.0 300 59.3 1.1075 -1.0000 1. 0000 - 1.0000 -1
90 33.0 300 59.6 0.5770 0.8665 5.8483 0.1482 2
91 33.0 310 59.3 0.8222 0.8628 H.3220 0.0251 2
92 -1.0 300 59.3 1.1075 -1.0000 -1' . 0 0 0 0 - 1.0000 -1
93 52.3 250 165.3 0.4863 1. 5174 1.5676 0.9680 2
94 52.3 250 165.3 0.6478 1.5174 9.9126 0.1531 2
95 52.3 250 165.3 0 .8299 1.5174 31.5282 ,0.0481 2
96 52.3 250 132.9 ' 0.9885 1.2193 54.2496 0.0225 2
97 52.3 95 55.9 0.4881 0.5126 0.8554 0.5986 2
98 52.3 95 55.9 0.6175 0.5126 4.7821 0.1071 2
99 52.3 95 55.9 0.8087 0.5126 20.6232 0.0248 2
100, 52.3 100 55.6 0.9984 0.5103 42.9648 0.0119 2
BURN II 2 - -- STABLE OPERA'!IOII UNITS OF INT ARE LBSISEC FT*3 ATN*2
BURN. 1 --- STABILIT! LIllI'!
BURN. 0 --- BURNER GOES OUT
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COItPARISO. or PRBDIcrBD A'D BZP~RINB.rAL BUR'ER srABILIrr DArA PAGE 5
RU' VOL AIR rBItP AIR FLOII BQUIV IlIr DArA I1Ir LIlt I.r RAr BURII
'0. Ill. 3 or LBS INR , RArIO IIIVP*2 flIVP*2 IDIIL
101 -1.0 102 55.5 1.1925 0.0000 0.0000 0.0000 -1
102 52.3 102 89.0 0.7520 0.8165 14.9787 0.0545 2
103 52.3 400 50.0 0'.8359 0."593 43.4487 0.0106 2
10.. 52.3 _00 50.0 0.5406 0."593 5.4104 0.0849 2
105 52.3 8.. 49.9 0.9250 0."581 33.4897 0.0137 2
106 52.3 85 49.9 0."888 0.4581 0.8290 0.5519 1
107 52.3 85 49.9 0.3925 0.4581 0.1159 3.9481 0
108 52.3 85 49.9 0.44"8 0~4576 0.3703 1.2345 2
109 52.3 85 49.9 0 .5563 0.4576 2.2581 0.2027 2
110 52.3 400 50.0 0."039 0.4593 0.7676 0.5984 2
111 52.3 400 50.0 0.3915 0.4593 0.6090 0.7543 2
112 52.3 400 33.2 0.4688 0.3048 2.1848 0.1395 2
113 52.3 ..00 33.2 0.3891 0.3048 0.5814 0.5243 2
114 52.3 400 33.2 0.3805 0.3043 0.4912 0.6194 2
115 52.3 400 33.1 0.3883 0.3040 0 . 5727 0.5309 1
116 52.3 400 82.7 0.5375 0.7587 5.2248 0.1"52 2
117 52.3 ..00 82.8 0.4312 0.7601 1.2303 0.6178 2
118 52.3 "00 82.8 0.3861 0.7601 0.5487 1.3851 0
119 52.3 400 126.8 0.4672 1.1634 2.1364 0.5446 2
120 52.3 ..00 127.0 0."279 1.1654 1.1641 1.0012 2
121 52.3 ..00 126.8 0.4469 1.163" 1.5783 0.7371 2
122 52.3 400 126.8 0.4010 1.1634 0.7272 1.5998 0
123 52.3 74 50.5 0.7951 0.4634 18.2890 0.0253 2
124 52.3 ,80 49.5 0.4743 0.4542 0.6308 0.7192 1
125 52.3 85 "7.6 0.4930 0.4369 0.8895 0.4906 - 1
BURN =. 2 --- srABLE OPBRArIOIl UNIrs OF INr ARE LBSISEC FT*3 ATM*2
BURN = 1 --- STABILI~r LINIT
BURN = 0 - - -BURliER GOES our
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CO/tlPARISOII OF PREDICTED AND EXPERIMENTAL BURliER STABILIT! DATA PAGE 5
RUN VOL AIR TE/tIP AIR 'LOJI EQUIV lilT DA TA lilT LI/tl INT RAT BURN'
NO. IN*3 of LBS/HR RATIO JI/VP*2 JI/VP*2 ID/IL
126 52.3 95 127.3 0.5049 1.1684 1.1230 1.0404 0
127 52.3 95 119.6 . 0.5687 1.0976 2.7371 0.4006 1
128 52.3 90 17.8 0.5411 0.6226 1.8745 0.3318 2
129 52.3 80 8&.2 0.5061 0.7910 1.0758 0.73"4 2
130 52.3 80 82.8 0.5822 0.7604 3.0707 0.2474 2
131 52.3 80 66.7 0.6869 0.6124 8.7686 0.0698 2
132 1.0 80 44.5 1.0553 0.0000 0.0000 0.0000 -1
q3 52.3 80 83.4 0.5628 0.76 55 2.4145 0.3167 2
134 52.3 80 66.7 0.7036 0.6121f 10.0334 0.0610 2
135 52.3 80 72.3 0.4347 0.6634 0.2940 2.2538 0
136 52.3 88 72.3 0.5318 0.6634 1.6320 0.4061 2
137 52.3 90 66.7 0.7036 0.6124 10.2913 0.0594 2
138 52.3 95 96.6 0.6404 0.8867 6.0209 0.1471 2
139 52.3 95 95.0 0.7260 0.8715 12.3178 0.0707 2
140 -1.0 95 91.1 1.0266 0.0000 0'.0000 0.0000 - 1
141 -1.0 95 77.3 1.2099 0.0000 0.0000 0.0000 -1
11f2 52.3 95 77.8 0.5389 0.7145 1.8518 0.3854 2
143 -1.0 95 77.8 1. 2013 0.0000 0.0000 0.0000 - 1
llf4 1.0 95 91.1 1. 0266 0.0000 0.0000 0.0000 -1
1It5 52.3 95 94.4 0.7302 0.8665 12.6988 0.0682 2
146 52.3 95 96.6 0.5433 0.8867 1.9651+ 0.1+507 2
11+7 52.3 95 98.3 0.4702 0.9019 0.6261+ 1.1+383 1
11+8, 52.3 95 90.5 0.7614 0.8310 15.6459 0.0531 2
149 1.0 95 53.6 1.2873 0.0000 0.0000 0.0000 - 1
150 52.3 95 56.9 0.1+388, 0.5219 0.341+7 1. 5126 2
BURN = 2 --- STABLE OPERATION UNITS OF INT ARE LBS/SEC FT*3 ATM*2
BURN. 1 -- - STABI LIT! LIJJIT
BURR = 0 --- BURNER GOES OUT
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COMPARISON OF PREDICTED AND EXPERIMENTAL BURNER STABILITY DATA PAGE 7
RUN VOL AIR TEMP AIR FLOW EQUIV INT DATA INT LIM INT RAT BURN
NO. IN*3 of LBS /lJR RATIO JI/VP*2 JI/VP*2 ID/IL
151 52.3 ..00 8".0 0.7066 0.7706 22.2613 0.0346 2
152 52.3 400 79.5 0.7"61 0.7297 28.1965 0.0259 2
153 52.3 360 111.2 0."703 1.0206 1.9112 0.5341 1
154 52.3 355 55.6 0.7013 0.5103 19.364" 0.0263 2
155 52.3 270 98.9 0.50"3 0.9081 2.1939 0."136 2
156 52.3 260 103.3 0."292 0.948" 0.6331 1. 4983 0
157 52.3 260 100.0 0.5856 0.9182 5.6586 0.1622 1
158 52.3 260 100 .6 0.6375 0.9232 9.3190 0.0990 2
159 52.3 265 97.3 0.7598 0.8929 22.6992 0.0393 2
160 1.0 270 90.7 1.2226 0.0000 0.0000 0.0000 - 1
161 - 1.0 275 89.6 1.2..18 0.0000 0.0000 0.0000 -1
162 -1.0 275 87.9 1.5592 0.0000 0.0000 0.0000 - 1
163 52.3 360 22.0 0.5..6.. 0.2018 5.0677 0.0398 1
164 52.3 370 22.0 0.7565 0.2018 27.9911 0 .0072 2
165 52.3 375 30.8 0.7925 0.2825 34.0641 0.0083 2
166 52.3 365 44.5 0.6641 0.4086 15.2380 0.0268 2
167 52.3 370 44.0 0.8406 0.4036 41.7926 0.0097 2
168 52.3 370 41. 2 0.9728 0.3784 64.4761 0.0059 2
169 52.3 345 55.0 0.7296 0.5045 22.6681 0.0222 2
170 52.3 325 69.8 0.5771 0.6407 6.3214 0.1013 2
171 52.3 305 78.1 0..5162 0.7164 2.9222 0.2450 2
172 52.3 275 97.8 0.4118 0.8980 0.4885 1.8383 0
173 1.0 -1 1.0 - 1.0000 0.0000 0.0000 0.0000 - 1
174 52.3 ..00 96.6 0.6507 0.8864 15.0295 0.0589 2
175 52.3 "OS 93.3 0.7925 0.8561 36.1910 0.0236 2
BURN = 2 - - - STABLE OPERATION UNITS OF niT ARE LBS/SEC FT*3 ATM*2
BURN = 1 --- STABILITY LIMIT
BURN = 0 --- BURNER GOES OUT
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COMPARISON OP PREDICTED AND EXPERIMENTAL BURNER STABILITY DATA PAGE 8
RUN VOL AIR TEMP AIR FLml EQUIV INT DATA INT LIM INT RAT BURN
NO. IN*3 OF LDS /llR RATIO W/VP*2 W/VP*2 ID/IL
176 52.3 405 93.1 0.8733 0.8547 50.6320 0.0169 2
177 52.3 405 98.6 0.4239 0.9049 1.1124 0.8135 2
178 52.3 405 95.9 0.5413 0.8806 5.5355 0.1591 2
179 52.3 350 133.7 0.8388 1. 2275 39.9028 0.0307 2
180 52.3 345 134.6 0.7140 1.2354 20.5484 0.0601 2
181 52.3 340 136.1 0.6205 1.2493 9.9945 0.1249 2
182 52.3 340 138.8 0.5458 1.2743 4.7161 0 .2700 2
183 52.3 335 139.0 0.4894 1. 2754 2.2792 0.5596 2
184 52.3 334 141.7 0.4435 1.3004 1.1318 1.1491 1
185 52.3 335 139.0 0.5014 1. 2754 2.6829 0.4754 2
186 52.3 335 139.0 0.5631 1.2754 5.6213 0.2269 2
187 - 1.0 -1 1.0 -1.0000 0.0000 0.0000 0.0000 - 1
188 52.3 430 77.9 0.6830 0.7145 20.4438 0.0349 2
189 52.3 430 79.0 0.5532 0.7252 6.8132 0.1065 2
190 52.3 430 79.0 0.4885 0.7252 3.2004 0.2266 1
191 52.3 400 66.9 0.5766 0.6144 7.8786 0.0780 2
192 52.3 405 56.0 0.6896 0.5137 20.1414 0.0255 2
193 - 1.0 410 51.6 1.2578 0.0000 0.0000 0.0000 -1
194 52.3 410 113.0 0.5463 1.0374 5.9429 0.1746 - 1
195 52.3 410 113.6 0.4858 1.0425 2.8719 0.3630 - 1
196 52.3 410 115.2 0.4920 1.0576 3.1155 0.3395 - 1
197 52.3 430 101. 4 0.5304 0.9309 5.3194 0.1750 - 1
198 52.3 360 41. 2 0.6579 0.3780 14.3547 0.0263 - 1
199 52.3 340 38.5 0.9818 0.3531 62.6358 0.0056 - 1
200 52.3 410 38.5 0.6616 0.3531 16.7434 0.0211 - 1
BURN = 2 - -- STABLE OPERATION UNITS OF INT ARE LBS/SEC FT*3 ATM*2
BURN = 1 --- STABILITY LIMIT
BURN = 0 --- BURNER GOES OUT
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COMPARISON OF PREDICTED AND EXPERIMENTAL BURNER STABILITY DATA PAGE 9
RUN VOL AIR TEUP AIR FLOW EQUIV INT DATA INT LIM INT RAT BURN
NO. IN*3 OF LBS/HR RATIO W/VP*2 W/VP*2 ID/IL
201 52.3 86 83.2 0.8221 0.7634 21.7050 0.0351 2
202 52.3 82 102.9 0.7187 0.9441 11.3179 0.0833 2
203 52.3 110 148.0 0.6216 1.3581 5.2160 0.2601 2
204 1.0 - 1 -1.0 -1.0000 0.0000 0.0000 0.0000 - 1
205 52.3 313 76.8 0.6978 0.7049 17.1035 0.0412 2
206 52.3 253 167.8 0.6498 1.5402 10.1619 0.1515 2
207 52.3 245 181.5 0.5601 1.6655 4.0754 0.4084 2
208 66.5 70 51. 5 0.8177 0.3718 20.5144 0.0181 - 1
209 66.5 70 49.9 0.9883 0.3598 39.6679 0.0091 -1
210 66.5 70 49.9 0.6666 0.3598 7.1656 0.0502 - 1
211 1.0 70 49.9 1.0852 0.0000 0.0000 0.0000 -1
212 66.5 70 102.9 0.6368 0.7425 5.4032 0.1373 -1
213 66.5 70 99.7 0.7865 0.7199 17.2529 0.0417 -1
214 1.0 70 96.6 1.0999 0.0000 0.0000 0.0000 -1
215 66.5 70 49.9 0.4845 0.3598 0.7215 0.4981 -1
216 66.5 70 48.2 0.6615 0.3479 6.8425 0.0508 - 1
217 52.3 80 83.8 0.6044 0.7689 3.9655 0.1937 2
218 66.5 100 91. 5 0.6187 0.6606 4.9179 0.1343 2
219 66.5 110 95.3 0.7845 0.6881 18.6383 0.0369 2
220 52.3 100 86.2 0.5854 0.7910 3.4036 0.2322 2
221 52.3 100 116.8 0.5761 1.0717 3.0495 0.3511 2
222 52.3 100 131.8 0.5105 1.2094 1.2482 0.9679 2
223 52.3 100 108.4 0.6205 0.9951 5.0047 0.1986 2
224 52.3 100 168.5 0.5562 1.5462 2.3779 0.6503 2
225 52.3 .100 151.8 0.6173 1.3932 4.8472 0.2874 2
BURN = 2 - - - STABLE OPERATION UNITS OF INT ARE LBS/SEC FT*3 ATM*2
BURN :: 1 --- STABILITY LIMIT
BURN = 0 --- BURNER GOES OUT
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COMPARISON OF PREDICTED AND EXPERIMENTAL BURNER STABILITY DATA PAGE 10
RUN VOL AIR TEMP AIR FLor.; EQUIV INT DATA INT LIM INT RAT BURN
NO. IN*3 of LDS/HR RATIO W/VP*2 W/ VP*2 ID/IL
226 52.3 100 177.9 0.5266 1.6330 1.5866 1.0293 1
227 52.3 76 55.8 0.5796 0.5121 2.935~ 0.1743 2
228 52.3 82 58.1f 0.5761 0.5358 2.8714 0.1864 2
229 52.3 85 57.6 0.5773 0.5288 2.9431 0.1795 2
230 52.3 433 57.6 0.5779 0.5284 8.7961 0.0601 2
231 52.3 420 60.8 0.5473 0.5579 6.2023 0.0900 2
232 52.3 ~10 90.9 0.5203 0.8346 ~.4305 0.1884 2
233 52.3 407 90.2 0.6172 0.8281 11.6716 0.0709 2
234 52.3 90 76.9 0 . 67 2.5 0.7062 7.9725 0.0885 2
235 52.3 92 77.3 0.5930 0.7094 3.620~ 0.1957 2
236 52.3 89 77.7 0.6003 0.7132 3.8997 0.1829 2
237 52.3 82 38.4 0.6353 0.3524 5.5154 0.0638 2
238 66.5 79 49.1 0.4880 0.3544 0.7973 0.4445 2
239 66.5 80 48.9 0.5391 0.3531 1.7569 0.2010 2
240 66.5 82 48.9 0.6563 0.3528 6.7467 0.0523 2
241 66.5 82 48.8 0.7266 0.3522 11.9947 0.0294 2
242 66.5 78 49.2 0.7617 0.3554 15.0894 0.0236 2
243 66.5 80 48.8 0.8945 0.3522 29.7059 0 .0119 2
244 66.5 79 98.1 0.5043 0.7082 1.0409 0.6796 2
245 66.5 80 97.6 0.5994 0.7043 3.7461 0.1878 2
246 66.5 80 60.5 0.6393 0.4364 5.7049 0 .076 5 -1
247 1.0 75 - 1.0 0.4609 0.0000 0.0000 0.0000 - 1
248 66.5 85 47.2 0.5625 0.3404 2.4459 0.1390 - 1
249 66.5 75 49.2 0.8476 0.3554 24.0592 0.0148 - 1
250 66.5 85 48.8 0.8555 0.3522 25.4455 0.0138 - 1
BURN = 2 -- - STABLE OPERATION UNITS OF INT ARE LBS/SEC PT*3 ATM*2
BURN :r 1 --- STABILITY LIMIT
DURN = 0 --- BURNER GOES OUT
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COIIPARISO. or PBBDIcr.D A.D .ZPBBIII..~AL BUB..R S~ABI LI~r DA~A PAGK 11
BU. VOL AIR ~KIIP AIR rLOfI BQUIV III~ DA~A I.~ LIlt III~ RAT BURN
.0. I.*3 or LBS "R RA~IO fll VP* 2 flIVP*2 IDIIL
251 &1.5 85 100.8 0."183 0.7278 0.9702 0.7502 -1
252 16.5 90 100." 0.5006 0.72"5 1.0273 0.7052 -1
253 16.5 92 97.0 0.5172 0.6198 3.0094 0.2326 -1
25" 66.5 93 1 00.1 0.6"12 0.7225 6.0290 ~.1197 -1
255 52.3 93 90.0 0.6063 0.8260 4.2127 0.1959 2
25& 66.5 85 97.6 0.7188 0.10"3 11.4080 0.0617 , 2
257 66.5 85 97.6 0.78 52 0.70"3 17.6921 0.0398 2
258 &&.5 85 . 97.5 0.900" 0.7037 30.66-8 0.0229 2
259 &&.5 85 97." 1.0000 0.7030 _2.0062 0.0167 2
2&0 16.5 85 97.3 0.9609 0.702- 37.6931 0.0186 2
2&1 -1.0 89 97.2 1.1875 0.0000 0.0000 0.0000 -1
2&2 66.5 90 1.....- 0.5167 1.0"21 1.3178 0.7900 2
263 66.5 97 1-3.5 0.5957 1.0355 3.7940 0.2727 2
26- &6.5 85 -8.8 0.4951 0.3522 0.9199 0.3824 2
2&5 &&.5 85 "8.8 0.5820 0.3522 3.1141 0.1130 2
2&6 &6.5 96 143.0 0.5677 1.0319 2.7115 0.3802 2
2&7 &6.5 96 97.8 0.5045 0.7063 1.1193 0.630" 2
2&8 &6.5 9& 97.2 0.5817 0.7018 3.2131 0.2182 2
269 66.5 96 97.2 0 "6582 0.7018 7.1329 0.0983 2
270 66.5 96 97.1 . 0.6860 0.7011 9.0735 0.0772 2
271 &6.5 180 1"".1 0.5576 1.0"02 2. ..183 0.4297 2
272 66.5 100 141.7 0.6618 1.0231 7."548 0.1371 2
273 66.5 100 143.1 0.6745 1.0328 8.3279 0.1239 2
27.. 66.5 100 1"3.5 0.7565 1.0355 15.3389 0.0675 2
275 66.5 95 1"3.7 0.825" 1.037" 22."802 0.0"61 2
BUR. ." 2 --- srABLB OPERA~IOII UNITS OF INT ARE LBSISEC FT*3 ATM*2
BURN = 1 --- srABILIrr LIIII'r
BURII = 0 --- BURIIBR GOBS our
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COHPARISO' 0., PR~DIC'1'~D AlID ~XPERIN~''1'A£ BUR'ER S'I'ABI£I'1'l,DA'I'A PAGE 12
RUlI VOL AIR '1'KIIP AIR .,1.011 KQUIV II'! DA'I'A II'!' 1.111. liT RAr . BURII
110. 111*3 0' I.BSIBR RATIO 1I1VP*2 III VP*Z IDIIL
271 -1.0 -1 130.0 -1. 0000 0.0000 0.0000 0.0000 -1
277 -1.0 -1 1"0.0 -1.0000 0.0000 0.0000 0.0000 -1
.278 -1.0 -1 -1..0 -1. 0000 .0.0000 0.0000 0.0000 -1
279 52.3 10' 91.0 0.5791 0.83 53 3.251t9 0.256" 2
280 52.3 110 90.9 0.6808 0.83'" 9.0216' 0.092" 2
281 52.3 110 111.3 0.5932 1. 0217 3.8"30 0.2656 2
282 52.3 94 "G.4 0.6072 0."258 ".2688 0.0997 2
283 52.3 100 47.3 0.602" 0."338 4.1303 0.1050 2
284 52.3 105 "6.5 0.4239 0."268 0.2659 1.6031 2
285 52.3 116 136.5 0."873 1. 2529 0.9210 1.3590 .2
286 66.5 82 58.8 0.5010 0...2..6 1.0009 0."237 2
287 66.5 92 14".0 0.5260 1.039" 1.5258 0 .6812 2
288 66.5 90 1"".3 0.5654 1.0"13 2.5809 0.4030 2
289 66.5 95 1"3.6 0.6016 1.0366 ".0261 0.2572 2
290 66.5 99 1.42.9 0.7193 1.0318 11.8468 0.0870 2
291 1.0 73 66.0 1.3984 0.0000 0.0000 0.0000 -1
292 -1.0 75 "9.1 1. 5625 0.0000 0.0000 0.0000 -1
293 -1.0 82 "7.1 1.359" 0.0000 0.0000 0.0000 -1
29.. -1.0 90 51.1 1.2578 0.0000 0.0000 0.0000 -1
295 1.0 72 "9.2 1.3203 0.0000 0.0000 0.0000 -1
296 -1.0 81 "8.6 1. 3..38 0.0000 0.0000 0.0000 -1
297 1.0 92 "8.3 1...1..1 0.0000 0.0000 0.0000 -1
298 -1.0 95 48.2 1.2813 0.0000 0.0000 0.0000 - 1
299 1.0 96 87.2 1.3750. 0.0000 o~oooo 0.0000 -1
300 - 1.0 85 49.3 0.0000 0.0000 0.0000 -1
1.1719
BURlI . 2 --- STABLBOPERATIon UNITS OF INT ARE LBSISEC FT*3 ATM*2
BURII . 1 --- STABILITl LIMIT
DURN. 0 --- BURlIBR GOES OU'!'
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COIIPARISO. 0., PREDIC'rED A.D EZPERIIiEIt'rAL BURliER S'rABILI'rI DATA PAGB 13
RU. .,0£ AIR 'rBIiP AIR PLOJI EQUIV IIt'r DATA I.'r LIII IltT RAT BURIt
.0. I.*3 oP LBS1BR RA'rIO JlIVP*2 JlIVP*2 IDIIL
301 - 1.0 81 118.5 1.2188 0.0000 0.0000 0.0000 -1
302 - 1.0 92 96.9 1.11219 0.0000 0.0000 0.0000 -1
303 - 1.0 711 98.5 .1:2813 0.0000 0.0000 0.0000 -1
301t - 1.0 87 1111.5 1.31138 0.0000 0.0000 0.00.00 -1
305 - 1.0 100 12".2 1.3750 0.0000 0.0000 0.0000 -1
306 - 1.0 100 139.8 1.1719 0.0000 0.0000 0.0000 -1
307 -1.0 101t 9".3 1.1953 0.0000 0.0000 0.0000 -1
308 52.3 90 "6.6 0.5"69 0.,.279 2.0293 0.2109 2
309 52.3 98 "7.5 0.5052 0."362 l.n05 0.3820 2
310 52.3 9.. 118." 0.3"36 0."""3 0.0318 13.9791 -1
311 52.3 385 1t9.11 0.5886 0."533 8."696 0.0535 2
.312 52.3 388 "8.3 0 . 5098 0."1132 3.6137 0.1226 2
313 52.3 395 "7.2 0.39"5 0."331 0.6289 0.6887 2
31.. 52.3 3..0 88.2 0.5392 0.809" ".3720 0.1851 2
315 52.3 36" . 93.1 0."726 0.85"7 2.0056 0."261 2
316 52.3 ..00 90.5 0.50"3 0.8310 3.5181 0.2362 2
317 52.3 ..35 90.0 0."059 0.8259 0.9363 0.8821 2
318 52.3 350 137.1 0."935 1. 2582 2.5"85 0."937 2
319 52.3 350 137.2 0."150 1.2589 0.7"28 1.69"9 2
320 52.3 351 13".5 0.6..8.. 1. 23..0 13.0187 0.09"8 2
321 52.3 litO 89.8 0.5978 0.8238 "."""9 0.1852 2
322 52.3 115 90.0 0."857 0.8259 0.8930 0.92"0 2
323 52.3 105 90.0 0.""77 0.8259 0."32" .1.9101 1
32.. .52.3 95 135.5 0.58"7 1. 2..36 3.3180 .0.37"" 2
325 52.3 105 137.3 0 . 5181 1.26014 1."278 0.8827 2
BURIt = 2 --- STABLE OPBRATIOII UNITS OF INT ARE LBS/SEC FT*3 ATM* 2
BURN = 1 --- STABILITI LINIT
BURN = 0 - -- BURNER GOES OUT
image:
-------
COMPARISON OF PREDICTED AND EXPERINENTAL BURNER STABI LITr DATA PAGE 14
RUN VOL AIR TEMP AIR FLOW EQUIV INT DATA INT LIN INT RAT BURN
NO. IIf.3 of LBS/BR RATIO JI/VP.2 JI/VP.2 ID/IL
326 52.3 110 138.7 0.4796 1.2732 0.7905 1.6107 1
327 52.3 1f12 48.2 0.6017 0.4"20 10.3270 0.0428 2
328 52.3 395 47.3 0.4641 0.4338 2.0023 0.2166 2
329 . 52.3 390 47.1 0.3821 0.4318 0.4819 0.8961 2
330 . 52.3 407 90.3 0.5955 0.8288 9.6208 0.0862 2
331 52.3 400 92.7 0.4834 0.8511 2.6750 0.3182 2
332 52.3 1f35 89.7 0.1+059 0.8231 0.9363 0.8791 1
333 52.3 392 135.'- 0.1+1+01 1.2411 1.3715 0.9050 2
334 52.3 395 140.3 0.3843 1.2877 0.5173 2.4893 1
335 52.3 92 91.3 0.5556 0.8383 2.2910 0.3655 2
336 52.3 90 92.6 0.1+667 0.8498 0.5751 1.4759 1
337 52.3 90 48.5 0.5434 0.4447 1.9337 0.2297 2
338 52.3 90 49.6 0.5899 0.4548 3.4713 0.1309 2
339 52.3 100 136.7 0.5685 1.2547 2.77 70 0.4511+ 2
340 52.3 395 138.3 0.4997 1.2691 3.2593 0.3891+ 2
341 52.3 150 92.4 0.5245 0.8483 1.8563 0.4566 2
342 52.3 90 93.3 0.5472 0.8563 2.0349 0.4204 2
343 52.3 102 91.3 0.5273 0.8381 1.6153 0.5189 2
341+ 52.3 100 91.9 0.4688 0.8439 0.6253 1.3496 2
345 52.3 102 135.3 0.5445 1.2414 2.0530 0.6047 2
346 52.3 105 138.2 0.1+898 1.2682 0.9186 1. 3806 2
347 52.3 105 134.5 0.6523 1.2343 6.9392 0.1779 2
348 52.3 i07 90.1 0.6022 0.8274 4.2116 0.1963 2
349 52.3 100 91.9 0.5137 0.8431 1.3105 0.6427 2
350 52.3 101 136.4 0.5697 1.2514 2.8268 0.4423 2
BURN. 2 --- STABLE OPERATION UNITS OF INT ARE LBS/SEC FT.3 ATM*2
BURN = 1 --- STABILITr LIMIT
BURN. 0 --- BURNER GOE.#) OUT
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COIIPARISOII OP PR~DICr~D AIID EZPERIMEN'J'AL BURliER SrABILIrr DArA PAGE 15
RUN VOL AIR rEIIP AIR PLOJI E{/UIV III'!' DArA III'J' LIN IRr RAr BURN
~O. III*3 0' LBS/BR RArIO JI/VP*2 JI/VP*2 ID/IL
351 52.3 105 92." 0.6311 0.8..n 5.6528 0.1500 2
352 52.3 110 93.1 0.,5036 0.85"8 1.1679 0.7312 . 1
353 52.3 120 137.7 0.1311 1.2636 5.9076 0.2137 2
354 52.3 It 30 81." 0 . 5379 0.7"71 5.1838 0.1292 2
355 52.3 438 82.0 0.lt309 0.7528 1.1t"11t .0.5223 2
356 52.3 It 50 1t3.8 0.5570 O. ..018 1.5311 0.0531t 2
357 52.3 1ltO 180~5 0.5053 1.6565 1.350" 1.2255 2
358 52.3 110 "6.8 0 ...673 0.4299 0.6363 0.6750 2
359 . 52.3 120 138.2 0.5022 1.2686 1.1888 1.0661 2
360 52.3 380 92.6 0.5322 0.Bltge ".6028 0.18lt6 2
361 52.3 1t00 90.9 0.lt673 0.8339 2.1392 .0.3898 2
'362 52.3 1t05 89.8 0.6305 0.82115 12.9777 0.0635 2
363 52.3 1105 90.8 0.lt981t 0.8332 3.3250 0.2506 2
3611 52.3 ..05 118.7 0 . 5691 O...lt71 7.lt2lt3 0.0602 2
365 52.3 1t05 "8.0 0.62"" O...ltO.. 12.3lt31 0.0357 2
366 52.3 _10 "7.9 0."309 0."393 1.278- 0.31136 2
367 52.3 ..05 137.0 0.5100 1. 2571 3.8"35 0.3271 2
368 52.3 -10 137.1 0."309 1.2578 1.2781t 0.9839 2
369 52.3. 1t00 136.3 . 0 . 5691 1.2507 7.3129 0.1710 2
370 52.3 1t03 90.9 0.5lt75 0.8339 5.8881 0.1"16 2
371 52.3 ..21 137.1 0.5738 1.2582 8.2811 0.1519 2
372 52.3 "25 138.7 0.5lt38 1. 2732 6.0652 0.2099 1
373 52.3 1t25 90.9 0.5325 0.83"6 5.3562 .0.1558 2
371t '52.3 -30 90.3 0.lt913 - 0.8288 3.3181 0.2lt98 1
375 52.3 1t00 91." 0."618 0.8388 1.9765 0.lt2"" 1
BUR' . 2 --- STABLE OPERArIO' UIII'!'S OP III'J' ARE . LBS/SEC PT*3 ATN*2
BUR' = 1 --- S'!'AaILI'!'r LIllI'!'
aURN . 0 --- BURIIBR GOES OU'!'
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CONPARISON OF PREDICTED AND EXPERIMENTAL BURliER S'1ABILITI DATA PAGE 16
RUN VOL AIR TENP AIR FLOfl . EQUIV I.r DATA lilT LIN INr RAT BURN
NO. 18*3 of LiJSIHR RATIO W/VP*2 fI/VP*2 ID/IL
316 52.3 1+00 90.3 0.1+711 0.8288 2.2577 0.3671 1
377 52.3 1+05 "8.3 0.1+838 0...1t32 2.71t0" 0.1617 2
378 52.3 "28 "5.5 0."875 0"1+173 3.1372 0.1330 1
379 52.3 375 "7.0 0.1+650 0."311 1.8751+ . 0.2299 1
380 52.3 ..12 1+5.7 0."395 0 . ..198 1.4789 0.2839 1
381 52.3 411 138.5 0.4507 1.2710 1.71t98 0.726" 1
382 52.3 ..11 138.7 0."501 1.2728 1.7336 0.7342 1
383 52.3 403 47.1 0.4725. 0."320 2.3309 0.18 53 1
38" 52.3 76 91. It 0.5775 0.8390 2.8643 0.2929 1
385 52.3 90 91.6 0.5625 0.81+10 2.4911 0.3376 2
386 52.3 91 89.8 0.528" 0.8245 1.5705 0.5244 1
387 52.3 80 47.8 0.5255 0."389 1.""50 0.303" 1
388 52.3 81 IU.5 0.5337 0.4180 1.6331 0.2557 1
389 -1.0 85 48.2 1.233" 0.0000 0.0000 0.0000 -1
390 52.3 90 80~9 0.5"00 0.7428 1.8470 0."021 1
391 52.3 93 80.5 0."900 0.7384 0.8741 0.8439 2
BURN. 2 --- S'1ABLE OPERATION UNITS OF INT ARE LBS/SEC FTfr3 ATNfr2
BURII . 1 --- STABILITI LINIT
BURN. 0 --- BURNER GOES OUT
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COIIPABISO. 0,. PRDIcrU .UB... I.1l,.'ICI..C7 A.D .ZPERINBliTAL E1USSIOliS DATA PAGE 1
RU. BUB. AIR 'U.1, AIR IlflUIV COlI. PII.D PB.D COG HCG NOBG NOTG
.0. ~"P ~DlP ,UJJI .A~IO ~DIP ."'1 ... BNN ENN ENN ENN
0' 0' I,.S/.. 0' G/¥-G G/KG G/KG G/KG G/KG
1 -1 75 71 22.3 0."171 2107 0.1'71 32.1552 - 1. 0000 - 1.0000 - 1.0000 -1.0000
2 -1 10 71 22.2 0.5301 23... 0~1813 10.7091 - 1.0000 - 1. 0000 - 1.0000 1. 0000
3 - 1 85 72 "5.3 0."122 2011 0.1325 17.5205 -1.0000 - 1. 0000 - 1. 0000 -1.0000
.. - 1 15 73 "S.3 0 ."52" 112" 0.1170 103.0000 -1. 0000 - 1. 0000 - 1.0000 1.0000
5 - 1 IS 73 "7.0 0."150 I1n 0.1100 110.0000 1..0000 -1.0000 - 1. 0000 - 1. 0000
6 - 1 II 7.. 11.1 0."501 1111 0.1170 103.0000 - 1.0000 -1.0000 -1.0000 -1.0000
7 - 1 '0 75 11.7 0."'''1 2101 0.11"1 15.1116 -1.0000 1. 0000 - .1. 0000 -1. 0000
8 2 '0 73 11.7 0.1321 27"2 0.1111 10.111'7 -1.0000 -1.0000 - 1.0000 1.0000
, 1 90 7.. 61.7 0.5073 2215 0.1"51 n.ll07 -1.0000 - 1.0000 -1.0000 - 1'.0000
10 0 90 7.. 11.7 0."697 1"''' 0.1100 110.0000 -1.0000 - 1. 0000 - 1.0000 - 1. 0000
11 1 90 7.. 11.7 0.5230 2303 0.'111 31.9..5..' 1.0000 - 1.0000 - 1.0000 -1.0000
12 0 90 7.. 11.7 0."322 115.. 0.1000 100.0000 -1.0000 -1.0000 - 1.0000 -1.0000
13 - 1 90 7.. 11.7 0.5311 2371 0 . "'01 21.1793 -1. 0000 -1. 0000 - 1.0000 -1.0000
14 1 90 75 11.7 .0.5073 2215 0 . '''51 5".9107 1.0000 -1.0000 - 1.0000 1.0000
15 2 - '0 7.. 11.7 0.501' 2225 0.'''73 52.7310' - 1.0000 - 1.0000 - 1. 0000 - 1.0000
16 2 '0 75 71..1 0.5689 2..11 0.1'7"3 25.703" - 1.0000 - 1.0000 - 1. 0000 - 1.0000
17 1 90 75 71.1 0.5"17 2369 0.9115 38.5179 - 1.0000 - 1.0000 - 1.0000 -1~0000
18 -2 90 73 71.1 0.551t1 2_27 0."82 31.7835 - 1.0000 - 1.0000 - 1. 0000 - 1. 0000
l' 2 11 73 71.0 0.6115 2659 O. ''''1 15.9106 - 1.0000 -1.0000 - 1.0000 -1.0000
20 2 92 7- 71.0 0!,5377 2352 O. 9S11 "0.1180 - 1.0000 -1.0000 - 1.0000 1.0000
21 0 92 7- 78.0 0._609 1'''& 0.1100 110.0000 - 1. 0000 -1.0000 - 1. 0000 -1.0000
22 0 93 72 7.7.9 0."960 2013 0.1890 111.0000 - 1. 0000 1.0000 - 1.0000 - 1.0000
23 1 93 72 77.9 0.5209 2258 0.9"21 57.9"- - 1. 0000 - 1.0000 - 1.0000 - 1.0000
2.. 1 93 7- 77.9 0.5312 2356 0.9597 _0.29"3 - 1.0000 - 1. 0000 - 1. 0000 -1.0000
25 1 93 75 77.9 0.563,1 2_70 0 .9726 27.""82 - 1.0000 -1.0000 - 1.0000 - 1.0000
26 2 90 72 103.3 0.6937 293.. 0.1887 11.3""" -1.0000 1. 0000 - 1.0000 - 1.0000
27 2 93 73 103.1 0.57111 2517 0 .9688 31.1919 - 1.0000 - 1. 0000 - 1.0000 -1.0000
28 0 96 73 102.8 0.522'7 2133 0.8800 120.0000 - 1.0000 - 1.0000 - 1.0000 - 1.0000
29 0 97 73 102.7 0.5118 211.. 0.8870 113.0000 - 1.0000 - 1.0000 - 1.0000 - 1.0000
30 1 97 711 102.7 0.5231 2136 0.8800 120.0000 - 1.0000 - 1.0000 -1.0000 - 1.0000
BURN= 2- --STABLB PRED B~N = 1000-(1-81'1'7) .Oll - BURNER DATA FOR NOX
BURN=1- --LINIT PRED EPP7 PRON THBOR7 liar - NOX FROM VAPOR GENERATOR EXH.
< 'QUR1i=O---GOIIIG OUT
H~
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COl.fPARISON OF PREDICTED BURNER INEFFICIENCY AND EXPERIMENTAL EMISSIONS DATA PAGE 2
RUN BURN AIR FUEL AIR EQUIV COMB PRED PRED COG HCG NOBG NOTG
NO. TEMP TElrlP FLOW RATIO TEMP EFFY EMM EMM EMM EMM EMM
of of LDS/HR of G/KG G/KG G/KG G/KG G/KG
31 2 102 75 120.9 0.5930 2569 0.9690 31.0396 -1.0000 -1.0000 -1.0000 - 1.00')')"
32 2 105 75 120.6 0.5465 2339 0.9353 64.7047 -1.QOOO -1.0000 - 1.0000 -1.000~
33 1 108 77 120.2 0.5158 2120 0.8800 120.0000 - -1.0000 -1.0000 - 1. 0000
1.0000
34 0 95 75 121.6 0.5099 2106 0.8870 113.0000 .-1.0000 - 1. 0000 -1.0000 - 1.0000
35 1 102 73 120.9 0.5190 2126 0.8800 120.0000 -1.0000 - 1.0000 -1.0000 - 1.0000
36 2 112 74 153.8 0.5878 2530 0.9563 43.7293 -1.0000 - 1.0000 -1.0000 -1.0000
37 2 117 74 153.2 0.5613 2392 0.9325 67.4910 -1.0000 -1.0000 -1.0000 - 1.0000
38 2 120 74 152.8 0.5451 222~ 0.8790 121. 0000 -1.0000 - 1.0000 -1.0000 - 1.0000
39 0 120 75 152.8 0.5299 2175 0.8800 120.0000 -1. 0000 -1.0000 - 1.0000 - 1.0000
40 - 1 120 75 152.8 0.5135 0.8800 120.0000 -1.0000 -1.0000 -1.0000 - 1. 0000
2122
41 1 124 75 152.3 0.5470 2282 0.9021 97.9472 -1.0000 -1.0000 -1.0000 - 1.0000
42 2 91 75 103.2 0.7565 3127 0.9915 8.5202, 2.3336 -1.0000 -1.0000 - 1.0000
43 1 93 75 103.1 0.5222 2140 0.8850 115.0000 -1.0000 -1.0000 - 1.0000 - 1. 0000
44 '2 87 73 41.8 0.7529 3127 0.9965 3.4990 -1.0000 -1.0000 -1.0000 - 1.0000
45 2 85 75 41.9 0.6916 2941 0.9954 4.5711 -1.0000 - 1.0000 -1.0000. - 1.0000
46 2 84 75 41.9 0.6132 2678 0.9918 8.1577 -1.0000. - 1.0000 -1.0000 - 1.0000
47 . 2 82 75 42.0 0.5333 2373 0.9791 20.8626 -1.0000 -1.0000 - 1.0000 - 1. 0000
48 2 82 74 42.1 0.4910 2170 0.9542 45.8251 0.2371 - 1.0000 - 1.0000 - 1.0000
49 0 80 72 42.1 0.4497 1913 0.8980 102.0000 22.3454 - 1.0000 -1.0000 - 1.0000
50 1 80 73 42.1 0.4997 2215 0.9619. 38.1283 10.1863 - 1.0000 -1.0000 - 1. 0000
51 2 83 73 25.4 0.6097 '2673 0.9950 5.0074 -1.0000 - 1.0000 -1.0000 - 1.0000
52 2 82 73 25.4 0.5406 2420 0.9892 10.7788 -1.0000 - 1.0000 -1.0000 - 1.0000
53 1 82 73 25.4 0.4645 2083 0.9584 41.5690 -1.0000 -1.0000 - 1.0000 - 1.0000
54 1 83 73 25.4 0.4510 1992 0.9356 64.3729 -1.0000 - 1.0000 -1.0000 - 1.0000
55 - 1 83 73 42.0 3.1753 0.0000 0.0000 -1.0000 - 1.0000 -1.0000 - 1.0000
1492
56 - 1 81 73 42.1 2.6412 0.0000 0.0000 -1.0000 - 1.0000 - 1.0000 - 1.0000
1798
57 - 1 82 73 42.0 2.8966 0.0000 0.0000 6.4517 - 1.0000 -1.0000 - 1.0000
1639
58 - 1 85 75 41.9 2.6510 0.0000 0.0000 109.9697 -1. 0000 -1.0000 - 1.0000
1794
59 - 1 85 75 41.9 3.1812 0.0000 0.0000 50.9444 -1.0000 -1.0000 - 1.0000
1490
60 - 1 90 75 41.7 1.9452 0.0000 0.0000 53.2602 - 1.0000 -1.0000 - 1.0000
2447
.,
BURN=2---STABLE PR ED EMM = 1000x(1-EFFY) NOB - 8URliER DATA FOR NOX
BURN=1---LIMIT PRED EFFY FROM THEORY NOT - NOX FROM VAPOR GENERATOR EX H.
BURN=O---GOING OUT
Table
VIII-20
image:
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COIIPABISO. 0' PBDIcrD 'U.'.. I.."ICI..C7 A'D '8ZP..III..rA£ .IIISSIO.6 DArA PAG. 3
RU' BUR' AIR '0.£ AIR .IIUIV COli. PRD PR.D COt; BCG ,OBG .0rG
'0. rap rap '£011 RArIO rnp .", .1111 .,,11 .1111 81111 BIIII
0' 0' £.8/.. 0' G/IG G/IG G/IG GlIG G/XG
61 -1 90 75 "1.7 1.9"52 2....7 0.,0000 0.0000 125".8720 - 1.0000 -1.0000 - 1.0000
12 -1 15 72 1Itl.9 2.6510 179.. 0.0000 0.0000 1135.752" - 1.0000 0.0013 -1.0000
13 - 1 87 72 ."1.1 3 .1870 nil 0.0000 0.0000 3.5209 - 1. 0000 0.0023 -1.0000
I" -1 85 72 "1.9 2.1510 179.. 0.0000 0.0000 910. ..0..7 - 1. 0000 0.0004. -1.0000
65 -1 II 75 "1.1 2.7192 1717 0.0000 0.0000 -1.0000 - 1.0000 - 1.0000 1. 0000
II -1 15 75. "1.9 2.1515 1661 0.0000 0.0000 - 1. 0000 - 1.0000 .-1.0000 -1. 0000
17 1 15 75 "1.9 2.7111 1720. 0.0000 0.0000 284.03"5 - 1.0000 0.0013 1.0000
II -1 71 75 25.5 2.5212 1875 0.0000 0.0000 1.0000 - 1.0000 - 1.0000 - 1. 0000
69 - 1 82 75 2".7 2.3985 1971 0.0000 0.0000 1272.6096 122.4420 0.0016 -1.0000
70 - 1 85 71 25.3 2.9117 1629 0.0000 0.0000 104.1. ..344 472.0"85 0.0007 1.0000
71 -1 81 78 25.3 3.01"1 151tl 0.0000 0.0000 1.0000 1.0000 - 1.0000 - 1.0000
72 1 90 78 11.7 2.3813 1993 0.0000 0.0000 1200.7858 151.4368 0.0006 - 1. 0000
73 - 1 93 71 11.5 2.""93 19..2 0.0000 0.0000 1.0000 -1.0000 - 1.0000 - 1. 0000
7.. 1 8& 73 25.3 0.50"" 2278 0.9821 17.9200 1. 21 04 9.5854 0.0014 - 1.0000
75 2 85 73 25.3 0.6219 2717 0.9955 .. ...671 0.1944 - 1.0000 0.1023. .. 1. 0000
76 2 85 75 25.3 0.8339 3339 0.9981 1.9035 0.3193 4.9987 0.4057 -1. 0000
77 .2 85 75 25.3 0.9910 3558 0.9877 12.30"1 6.6866 2.3294 0.3974 -1.0000
78 1 90 75 11.7 0.557" 2"59 0.977" 22.6080 101.7531 57.3660 0.0119 1.0000
79 2 92 79 11.6 0.6869 2921 0.9931 1.8177 0.9586 1.4905 0.2489 -1.0000
80 2 90 79 11.7 0 ~ 9927 3555 0.9812 18.7995 21. 5030 - 1.0000 0.3622 -1.0000
81 - 1 92 80 11.6 1.""32 31..3 0.0000 0.0000 188.0142 - 1. 0000 0.0000 1. 0000
82 2 103 75 102.1 0.5050 209& 0.8878 '113.0000 105.3359 7.7417 0.0000 - 1.0000
83 2 105 78 101.9 0.7611 3165 0.9920 7.9883 2.7654 3.4637 0.3348 - 1.0000
8.. 2 100 72 102." 0.7"6.. 310.. 0.991" 8.6103 3.5505 3.9463 0.4516 - 1.0000
85 2 103 77 102.1 0.9171 3..93 0.9899 10.1318 12.6460 1.3655' 0.4084 - 1. 0000
86 -1 105 77 101.9 1.2812 ' '3502 0.0000 . 0.0000 866.5566 0.97 24 0.0264 - 1.0000
87 2 300 600 59.3 0.5391 2519 0.98 59 lIt.07'" 0.13..4 1.5420 0.0411 - 1.0000
88 . 2 300 100 59.3 0.6819 3071 0.9955 .....707 1.2088 0.2238 0.3218 - 1.0000
89 -1 300 600 59.3 1.1075 3658 0.0000 0.0000 "76.8417 0.8592 0.0356 - 1.0000
90 2 300 720 59.6 0.5770 2108 0.990" 9.5539 0.4080 0.5712 0.2221 - 1.0000
BURII=2---STAB£'8 PR'8D '11111 = 1000-(1-BFF7) 'OB - BURNER DATA FOR BOX
BURBzl---LIIIIT PRBD 'IFF' FRON THEOR7 'OT - 'OX FRON VAPOR GENERATOR EXB.
BUR'aO---GOI'G OUT
Table
VIII-2l
image:
-------
COMPARISON OF PREDICTED BURNER INF.FFICIENCY AND EXPERIMENTAL EMISSIONS DATA PAGE 4
RUN BURN AIR FUEL AIR EQUIV COMB PRED PRED COG HCG NOBG NOTG
NO. TEMP TE1.fP FLOW RATIO TEMP EFFY EMU EMM EMM EMM EMM
OF of LBS/HP of G/KG G/KG G/KG G/KG G/KG
91 2 310 720 59.3 0.8222 3440 0.9967 3.3125 1.7928 0.0851 0.3795 - 1.0000
92 - 1 300 720 59.3 1.1075 i 3658. 0.0000 0.0000 -
699.7134 0.1234 0 .0915 1. 0000
93 2 250 440 165.3 0.4863 2176 0.9011 98.8889 51.3433 - 1.0000 0.0128 -1.0000
94 2 250 485 165.3 0.6478 2900 0.9890 11.0026 .4.0006 - 1.0000 0 . 1154 1.0000
95 2 250 510 165.3 0.8299 3416 0.9937 6.2930 9.3111 - 1.0000 0.5037 - 1.0000
96 2 250 520 132.9 0.9865 3636 0.9817 18.2715 207.8635 - 1.0000' 0.4010 - 1.0000
97 2 95 77 55.9 0.4881 2192 0.9648 35.1657 - 1.0000 - 1.0000 0.3787 - 1.0000
98 2 95 77 55.9 0.6175 2705 0.9936 6.3709 - 1.0000 - 1.0000 0.4642 -1.0000
99 2 95 77 55.9 0.8087 3283 0.9974 2.6068 - 1.0000 - 1.0000 0.4747 1.0000
100 2 100 77 55.6 0.9984 3565 0.9841 15.8934 - 1.0000 - 1.0000 0.3623 - 1.0000
101 - 1 102 77 55.5 1.1925 3485 '0.0000 0.0000 - 1.0000 -1.0000 0.3553 - 1.0000
102 2 102 77 89.0 0.7520 3132 0.9954 4.5716 - 1.0000 1. 0000 0.4443 - 1. 0000
103 2 400 770 50.0 0.8359 3525 0.9984 1. 6190 - 1.0000 - 1.0000 - 1.0000 -1.0000
104 '2 400 800 50.0 0.5406 2666 0.9946 5.4009 - 1.0000 - 1.0000 - 1.0000. 1.0000
105 2 84 88 49.9 0.9250 3503 0.9964 3.6101 - 1. 0000 - 1.0000 - 1.0000 - 1. 0000
106 1 85 95 49.9 0.4888 2194 0.9687 31. 2602 3.9308 - 1.0000 0.0049 - 1.0000
107 0 85 89 49.9 0.3925 1729 0.9060 94.0000 - 1.0000 - 1. 0000 - 1.0000 - 1.0000
108 2 85 92 49.9 0.4448 1900 0.8980 102.0000 - 1.0000 - 1.0000 -1.0000 - 1.0000
109 2 85 98 49.9 0.5563 2477 0.9890 11.0324 - 1.0000 - 1.0000 - 1.0000 -1.0000
110 2 400 730 50.0 0.4039 2115 0.9606 39.3993 16.3425 - 1.0000 0.0030 1.0000
111 2 400 730 50.0 0.3915 '2044 0.9450 55.0286 47.2658 - 1.0000 0.0832 - 1.0000
112 2 400 720 33.2 0.4688 2407 0.9919 8.0925 0.1555 - 1.0000 0.7380 - 1.0000
113 2 400 725 33.2 0..3891 2072 0.9677 32.3190 17.5557 - 1.0000 0.1116 - 1.0000
114 2 400 730 33.2 0.3805 2027 0.9598 40.1876 11.5914 - 1.0000 0.2476 - 1.0000
115 1 400 720 33.1 0.3883 2068 0.9672 32.8187 - 1. 0000 - 1.0000 0.0186 - 1.0000
116 2 400 710 82.7 0.5375 2647 0.9906 9.3964 - 1.0000 - 1.0000 - 1.0000 - 1.0000
117 2 400 710 82.8 0.4312 2209 0.9573 42.7243 - 1.0000 - 1.0000 - 1.0000 - 1.0000
118 0 400 730 82.8 0.3861 1916 0.8790 121. 0000 68.5008 - 1.0000 0.0125 - 1.0000
119 2 400 720 126.8 0.4672 2346 0.9623 37.7045 - 1.0000 - 1.0000 0.0308 - 1.0000
120 2 400 475 127.0 0.4279 2041 0.8700 130.0000 -1.0000 - 1. 0000 - 1.0000 - 1.0000
BURlJ=2- --STABLE PRED El,!M = 1000)(1-EPF1) NOD - BURNER DATA FQR NOX
BURli=l- - -LIMIT PRED EPFY PROU THEORY NOT - NOX FROM VAPOR GENERATOR SXH.
T"IRN=O---GOING OUT
;S~
Hili
HtJ'
.....
!\JCI
!\J
image:
-------
COIIPARISOB OF PREDICTED BURliER INEFFICIENCY AND EXPERIUENTAL EMISSIONS DATA PAGE 5
RUN BUR' AIR FUEL .AIR EQUIY COMB PRED PRED COG HCG NOBG NOTG
'0. TENP TENP FLOJI RATIO TENP EFFY EUN EIIII EMM Ellf.1 EIIN
OF OF LBSIBR of GIKG GIKG G/KG G/KG G/KG
121 2 ..00 ..50 126.8 0."469 2239' 0.9"32 56.7651 - 1.0000 -1.0000 - 1. 0000 -1.0000
122 0 ..00 450 126.8 0."010 1963 0.8770 123.0000 - 1.0000 -1.0000 - 1.0000 -1. 0000
123 2 7.. 70 50.5 0.7951 3236 0.9975, 2 . ".59 5 0.3215 -1.0000 0...28.. -1.0000
12" 1 80 78 "9.5 0.47"3 2112 0.9556 .......2..3 13.8280 -1.0000 0.0757 -1.0000
125 - 1 85 78 "7.6 0.4930 2218 0.9128 27.2300 11.26"7 1.0000 0.0582 -1.0000
126 0 95 78 127.3 0 . 5049 2092 0.8880 112.0000 12.3792 - 1.0000 0.2"59 -1.0000
127 1 95 18 119.6 0.5687 2498 0.9157 2".3086 16.0 litO -1.0000 0.2088 -1. 0000
128 2 90 100 67.8 0 . 5"11 2..11 0.9815 18...8..2 1. 0000 -1.0000 - 1. 0000 -1.0000
129 2 80 80 86.2 0.5061 2217 0.9515 ..8...529 - 1.0000 -1. 0000 - 1.0000 -1.0000
130 2 80 80 82.8 0.5822 2556 0.98 56 14.3664 - 1.0000 -1.0000 -1. 0000 -1.0000
131 2 80 80 66.7 0.6869 2923 0.9952 4.7632 - 1.0000 -1. 0000 1.0000 -1.0000
132 -1 80 80 "".5 1. 0553 3562 0.0000 0.0000 - 1.0000 -1.0000 - 1.0000 -1. 0000
133 2 80 80 83.4 0.5628 2"80 0.9819 18.0994 - 1.0000 -1.0000 -1.0000 -1.0000
134 '2 80 80 66.7 0.7036 2975 0.9957 ...3....2 - 1.0000 -1.0000 1. 0000 1.0000
135 0 80 80 72.3 0.4347 1864 0.9000 100.0000 - 1.0000 38.1951 - 1.0000 -1.0000
136 2 88 90 72.3 0.5318 2367 0.9770 23.0175 - 1.0000 95.3023 -1.0000 -1.0000
137 2 90 90 66.7 0.7036 2982 0.9957 ".2635 - 1.0000 0.9204 -1.0000' -1.0000
138 2 95 95 96.6 0.640" 2773 0.9907 9.3221 - 1.0000 - 1. 0000 0.3612 -1.0000
139 2 95 100 95.0 0.7260 3050 0.99"6 5.""36 - 1.0000 -1.0000 - 1.0000 -1.0000
140 - 1 95 100 91.1 1'.0266 .3569 0.0000 0.0000 - 1.0000 1. 0000 - 1.0000 -1.0000
141 - 1 95 100 77.3 1.2099 " 3..60 0.0000 0.0000 - 1.0000 - 1. 0000 - -1.0000
1.0000
142 2 95 100 77.8 0.5389 2399 0 . 91 &0 22.0132 - 1.0000 - 1.0000 -1.0000 -1. 0000
143 - 1 95 100 77.8 1.2013 3..72 0.0000 0.0000 - 1.0000 - 1. 0000 -1.0000
1. 0000
141t - 1 95 100 91.1 1.0266 ,3569 0.0000 0.0000 - 1. 0000 - 1. 0009 - -1.0000
1.0000
llt5 2 95 100 94.4 0.7302 3062 0.9947 5.3162 - 1.0000 - 1.0000' - -1.0000
1.0000
146 2 95 '100 96.6 0.5lt33 2..0.. 0.9732 26.8288 - 1.0000 - 1.0000 - 1.0000
1.0000
llt7 1 95 100 98.3 0.4702 1979 0.8900 110.0000 - 1. 0000 - 1.0000 - - 1. 0000
1.0000
1 1t8, 95 100 0.761" 3153 0.9954 1t.6212 - 1.0000 - - -1.0000
2 90.5 1.0000 1. 0000
149 - 1 95 100 53.6 1.2873 ,3356 0.0000 0.0000 - 1.0000 - 1. 0000 0.0000 -1.0000
150 2 95 100 56.9 0.4388 1887 0.8980 102.0000' - 1.0000 - 1. 0000 - 1.0000 - 1.0000
BURN=2---STABLE PREDEMH = 1000x(1-EFFY) NOB - BURNER DATA FOR NOX
BURN=l- --L'IMIT PRED EFFY FROM THEORY NOT - NOX FROM VAPOR GENERATOR EXH.
BURN=O---GOING OUT
Table
VIII-23
image:
-------
COMPARISON OF PREDICTED BURNER INEFFICIENCY AND EXPERIMENTAL EHISSIONS DATA PAGE 6
RUN BURN AIR FUEL AIR EQUIV CONB PRED PRED COG HCG NOBG NOTG
NO. TEI-IP TEMP r LOfI RATIO TENP EFFY EMM EMU EMM EMM EMM
of of LBSIHR of GIKG GIKG GIKG GIKG GIXG
151 2 400 160 84.0 0.7066 3197 0.9969 3.1313 - 1. 0000 - 1.0000 - 1.0000 - 1.0000
152 2 400 330 79.5 0.7451 3308 0.9974 2.6398 - 1.0000 0.1098 - 1.0000 - 1. 0000
153 1 360 300 111.2 0.4703 2329 0.9642 35.8068 - 1. 0000 0.0000 - 1.0000 - 1.0000
154 2 355 200 55.6 0.7013 3155 0.9977 2.2649 "':1.0000 - 1.0000 - 1.0000 - 1.0000
155 2 270 2'5 98.9 0.5043 2401 0.9743 25.7017 - 1.0000 :>.1179 - 1.0000 - 1.0000
156 0 260 255 103.3 0.4292 1963 0.8860 114.0000 - 1.0000 - 1.0000 - 1.0000 - 1.0000
157 1 260 290 100.0 2706 0.9896 10.3856 - 1.0000 0.0099 - 1.0000 - 1.0000
0.5856
158 2 260 317 100.6 0.6375 2884 0.9931 6.8859 - 1.0000 0.0700 - 1.0000 - 1.0000
159 2 265 350 97.3 0.7598 3257 0.9962 3.8282 - 1. 0000 0.0621 - 1.0000 - 1.0000
160 - 1 270 410 90.7 1.2226 0.0000 0.0000 - 1. 0000 - 1.0000 - 1.0000 - 1.0000
3546.
161 - 1 275 392 89.6 1.2418 :>.0000 0.0000 - 1.0000 0.0789 - 1.0000 - 1.0000
3525
162 - 1 275 480 87.9 1.5592 0.0000 0.0000 - 1.0000 6.4648 - 1.0000 - 1.0000
3096
163 1 360 110 22.0 0.5464 2663 0.9976 2.4453 - 1. 0000 63.1902 - 1.0000 - 1.0000
164 2 370 120 22.0 0.7565 3321 0.9993 0.7427 - 1. 0000 28.6829 - 1.0000 - 1.0000
165 2 375 120 30.8 0.7925 3415 0.9990 0.9942 - 1.0000 0.0721 - 1.0000 - 1.0000
166 2 365 140 44.5 0.6641 3051 0.9979 2.1090 - 1.0000 0.0337 - 1.0000 - 1.0000
167 2 370 150 44.0 0.8406 3518 0.9985 1.4867 - 1.0000 0.0336 - 1.0000 - 1.0000
168 2 370 170 41. 2 0.9728 3701 0.9950 4.9734 - 1.0000 0.0649 - 1.0000 -1.0000
169 2 345 180 55.0 0.7296 3230 0.9979 2.0617 - 1.0000 0.0260 - 1.0000 1.0000
170 2 325 190 69.8 0.5771 ;2733 0.9935' 6.5443 - 1.0000 0.0051 - 1.0000 - 1.0000'
171 2 305 195 78.1 0 . 5162 2491 0.98.51 14.8941 - 1.0000 0.0000 - 1.0000 - 1.0000
172 0 275 195 97.8 0.4118 1917 0.8870 113.0000 - 1. 0000 1.0630 - 1.0000 - 1.0000 .
173 - 1 -1 - 1 -1.0 - 1.0000 - 0.0000 0.0000 - 1.0000 - 1.0000 - 1.0000 - 1.0000
.
..
174 2 400 250 96.6 0 . 6507 3027 0.9954 4.6110 - 1.0000 0.0261 - 1.0000 - 1.0000
175 2 405 275 93.3 0.7925 3428 0.9971 2.9001 - 1.0000 0.0291 - 1.0000 - 1.0000
176 2 405 280 93.1 0.8733 3597 0.9967 3.3376 - 1. 0000 0.0308 - 1.0000 - 1.0000
177 2 405 200 98.6 0.4239 2145 0.9338 66.1992 - 1.0000 0.0000 0.2043 .- 1.0000
178 2 405 195 95.9 0.5413 2661 0.9896 10.4432 - 1.0000 0.0000 - 1.0000 - 1.0000
179 2 350 300 133.7 0.8388 3497 0.9954 4.5738 - 1.0000 0.0088 - 1.0000 - 1.0000
180 2 345 310 134.6 0.7140 3178 0.9947 5.3268 - 1.0000 0.0151 - 1.0000 - 1.0000
BURN=2-- -STABLE PR ED EMM = 1000x(1-EFFY) NOB - BURNER DATA F~R NOX
BURN=l-- -LIl4IT PRED EFFY PROU THEORY NOT - NOX FROM VAPOR GENERATOR EXH.
BURN=O---GOING OUT
Table
VIlI-24
image:
-------
COIIPARISOll OF PR8DIC'r6D BURlI8R IlIEFFICIElICr AND EXPERIIIElI'rAL EUISSIONSDA'rA PAGE 7
RUlI BURlI AIR PUEL AIR EQUIV COIIB PRED PR8D COG RCG NOBG NOTG
.0. '1'EIIP '1'EIIP PLOtl BA'1'IO '1'EIIP EFFY EMil E14M EMM EMM EMM
op op LBSIBR op G/KG G/KG G/KG G/KG G/KG
181 2 340 305 136.1 0.6205 2880 0 .9911 8.9491 - 0.0137 -1.0000 - 1.0000
1. 0000
182 2 340 303 138.8 0.5"58 2613 0.9821 17.8870 -1. 0000 0.0108 1.0000 - 1.0000
183 2 335 295 139.0 0."894 2372 0.9616 38.3977 0.0062 - 1. 0000 - 1.0000
1. 0000
18~ 1 334 280 141.1 0.4435 2053 0.,8170 123.0000 -1.0000 0.0069 0.1083 - 1.0000
185 2 335 320 139.0 0.5014 2427 0.9681 31.8877 - 1.0000 0.0240 -1.0000 -1.0000
186 2 335 340 139.0 0.5631 2674 0.9849 15.1181 - 1.0000 0.0000 0.4135 1.0000
187 -1 - 1 -1' -1.0 -1.0000 -1 0.0000 0.0000 - 1.0000 - 1.0000 - 1.0000 - 1.0000
188 2 430 340 71.9 0.6830 3t-.9 0.9970 3.0325 - 0.0077 - 1. 0000' - 1.0000
1.0000
189 2 ..30 320 79.0 0.5532 2727 0.9929 7.1253 - 0.0000 - 1.0000 - 1. 0000
1.0000
190 1 430 300 79.0 0.4885 2..88 0.9856 14.3782 -1.0000 0.0000 - 1.0000 - 1.0000
191 2 400 295 66.9 0.5766 2788 0.9947 5.2707 1.0000 0.0148 -1.0000 -1. 0000
192 2 405 295 56.0 0.6896 3153 0.9978 2.2005 - 1.0000 0.0039 1. 0000 -1.0000
193 - 1 410 360 51.6 1.2578 3587 0.0000 0.0000 - 1.0000 23.7001 - 1.0000 -1.0000
194 - 1 ..10 .. 20 113.0 0.5"U 2679 0.9883 11.6743 - 1.0000 0.0314 - 1. 0000 -1.0000
195 -1 410 410 113.6 0.4858 2446 0.9762 23.7640 - 1.0000 0.0353 - 1.0000 -1.0000
196 - 1 410 390 115.2 0.4920 2470 0.9778 22.1823 - 1.0000 8.9366 - 1.0000 1. 0000
197 - 1 430 340 101." 0.5304 2640 0.9884 11.5726 - 1.0000 0.9200 -1. 0000 - 1.0000
198 - 1 360 260 "1.2 0.6579 3028 0.9980 2.0329 -1.0000 0.0084 1. 0000 -1.0000
199 -1 340 320 38.5 0.9818 3690 0.9938 6.1932 1.0000 0.0380 -1.0000 -1.0000
200 -1 410 270 38.5 0.6616 3074 0.9983 1.6980 - 1.0000 0.5087 1.0000 -1.0000
201 2 86 82 83.2 0.8221 3307 0.9961 3.9168 - 1.0000 - 1. 0000 -1. 0000 1.0000
202 2 82 82 102.9 0.7187 3017 0.9938 6.2446 - 1.0000 - 1. 0000 - 1. 0000 -1.0000
203 2 110 100 1"8.0 0.6216 2704 0.9832 16.7514 1. 8195 0.0278 0.3728 - 1. 0000
204 -1 1 1 -1.0 -1.0000 -1 0.0000 0.0000 - 1.0000 - 1. 0000 - 1.0000 - 1.0000
205 2 313 77 76.8 0.6978 3114 '0.9966 3.3925 - 1. 0000 -1.0000 - 1.0000 -1.0000
206 2 253 77 167.8 0.6498 2909 0.9890 10.9588 - 1. 0000 - 1.0000 -1.0000 -1.0000
207 2 245 77 181.5 0.5601 2572 0.9728 27.2419 - 1.0000 - 1.0000 0.2588. 0.1527
-1 70 -1 51.5 0.8177 3292 0.9980 1.9506 - 1.0000 - - 1.0000 - 1.0000
208 1. 0000
209 -1 70 - 1 49.9 0.9883 3549 0.9904 9.5711 - 1.0000 - 1.0000 - 1.0000 - 1.0000
210 -1 70 -1 49.9 0.6666 2856 0.9968 3.2151 - 1.0000 - 1.0000 -1.0000 - 1.0000
BURN=2---STABLE PRED EMM = 1000IC(1-EFFY) NOB - BURNER DATA FOR NOX
BURN=1- --LIMIT PRED EFFY FROM THEORY NOT - NOX FROM VAPOR GENERATOR EXH.
BURN=O---GOING OUT
Table
VIII-25
image:
-------
COJ.!PARISON OF PREDICTED BURNER INEFFICIEnCY AND EXPERIMENTAL EMISSIONS DATA PAGE 8
RUN BURN AIR FUEL AIR EQUIV CONB PRED PRED COG RCG NOBG NOTG
NO. TEMP TEMP .FLOW RATIO TEMP EPFY ENU ENN EMM EMM EMN
of of LBSIHR of GIKG GIKG GIKG GIKG GIKG
211 - 1 70 - 1 ~9.9 1.0852 35~~ 0.0000 0.0000 - 1. 0000 -1.0000 - -
1. 0000 1.0000
212 - 1 70 - 1 102.9 0.6368 27~6 0.9915 8.~514 - 1.0000 1.0000 - - 1. 0000
1.0000
213 - 1 70 - 1 99.7 0.7865 3208 0.9961 3.9081 - 1.0000 - 1.0000 - - 1.0000
1.0000
21~ - 1 70 -1 96.6 1.0999 3537 0.0000 0.0000 - 1.0000 - 1.0000 - 1. 0000 -1.0000
215 -1 70 - 1 ~9.9 0.~8~5 2175 0.9729 27.0681 - 1.0000 - 1.0000 - 1.0000 -1.0000
216 - 1 70 - 1 48.2 0.6615 2839 0.9968 3.2156 - 1.0000 - 1.0000 - 1.QOOO - 1. 0000
217 2 80 - 1 83.8 0.6044 2638 0.9885 11. 47~6 - 1. 0000 - 1.0000 -1.0000 -1.0000
218 2 100 70 91. 5 0.6187 2708 0.9919 8.1171 0.1629 -1.0000 0.0726 - 1.0000
219 2 110 70 95.3 0.7845 3228 0.9965 3.5301 5.5606 - 1.0000 0.9701 -1.0000 I
220 2 100 100 86.2 0.5854 2583 0.9863 13.6626 - 1.0000 0.3391 0.2876 0.2~31
221 2 100 100 116.8 0.5761 253~ 0 .9788 21.1727 - 1. 0000 0.3523 - -
1.0000 1.0000
222 2 100 100 131.8 0.5105 2156 0.9078 92.1901 - 1.0000 2.095~ - - 1.0000
1.0000
223 2 100 100 108.4 0.6205 2704 0.9877 12.3~88 - 1. 0000 0.5651 - 1.0000 - 1. 0.000
22~ 2 100 100 168.5 0.5562 2413 0.9555 ~~.532~ - 1. 0000 0.3447 - 1.0000. -1.0000
225 2 100 100 151.8 0.6173 2679 0.9817 18.2645 - 1.0000 0 . 9205 - 1.0000 -1.0000
226 1 100 100 177.9 0.5266 2149 0.8800 120.0000 - 1.0000 -1.0000 - 1.0000 -1.0000
227 2 76 82 55.8 0.5796 2554 0.9903 9.7308 0.1744 0.9677 0.7041 -1.0000
228 2 82 90 58.4 0.5761 2545 0.9896 10.4349 0.1755 0.4170 0.0989 - 1.0000
229 2 85 95 57.6 0.5773 2552 0.9899 10.0640 0.1751 0.6529 0.3103 - 1.0000
230 2 433 98 57.6 0.5779 2818 0.9959 4.1~52 - 1. 0000 0.4560 0.2053 -1.0000
231 2 420 100. 60.8 0.5473 2702 0.9941 5.8817 - 1. 0000 0.3310 0.1174 -1.0000
232 2 410 100 90.9 0.5203 2589 0.9878 12.1522 - 1.0000 0.2877 0.1879 -1.0000
233 2 407 100 90.2 0.6172 2925 0.9948 5.2052 - 1.0000 0.4614 0.5288
1.0000
234 2 90 82 7f..9 0~6725 2881 0.9941 5.9028 - 1.0000 1.5728 1.2813 -1.0000
235 2 92 89 77.3 0.5930 2608 0.9886 11.4415 - 1. 0000 2.6~91 0.8953 -1.0000
236 2 89 89 77.7 0.6003 2632 0.9892 10.7661 - 1.0000 2.97 69 0.5918 -1.0000
237 2 82 82 38.4 0.6353 2760 0.9961 3.8535 - 1.0000 2.9425
1.5835 1.9999
238 2 79 70 49.1 0.4880 2202 0.9763 23.7091 - 1.0000 - 1.0000 -
0.0637 1.0000
239 2 80 71 48.9 0.5391 2414 0.9894 10.5573 - 1. 0000 - 1.0000 -
0.1855 1.0000
240 2 82 71 48.9 0.6563 2830 0.9967 3.2991 - 1.0000 - 1.0000 0.4526 -
1.0000
BURN= 2- - -STABLE PRED EMU = 1000x(1-EFPY) NOB - BURNgR DATA F.OR NOX
BURN=1- - -LIi>1IT PRED EFPY FRON THEORY NOT - NOX FROU VAPOR GENERATOR EXR.
BURN=O---GOING OUT
Table
VIII-26
image:
-------
COHPARISOIt OF PREDICrED BURNER IlIEFFICIEIICr AND EXPERIMENTAL E/.!ISSIONS DArA PAGE 9
RUN BURN AIR FUEL AIR EQUIV CONB PRED PRED COG HCG NOBG NOTG
NO. rENP rEHP FLOJ/ RATIO TEMP EFFr EUlI EMN EMM EMM ENM
OF OF LBS/HR of G/KG G/KG G/KG G/KG G/KG
241 2 82 72 48.8 0.7266 3051, 0.9978 2.2394 - 1.0000 - 1.0000 -
1.9359 1. 0000
242 2 78 68 49.2 0.7617 3150 0.9980 2.0079 - 1. 0000 - 1.0000 1.8018 -1.0000
243 2 80 72 48.8 0.8945 3457 0.9978 2.-2083 - 1.0000 -
1.0000 2.6989 1. 0000
2 79 68 98.1 0.5043 2221 0.9570 43.0363 - 1.0000 - 1. 0000 -
244 0.1184 1. 0000
80 70 97.6 0.5994 2622 0 .'9890 10.9873 '- 1.0000 - -1.0000
245 2 1.0000 0.2608
246 -1 80 70 60.5 0.6393 2770 0.9953 4.6675 - 1.0000 - 1. 0000 - -1.0000
1.0000
- 75 70 -1.0 0.4609 2131 0.0000 0.0000 - 1. 0000 - - -1.0000
247 1 1.0000 1. 0000
248 - 85 70 47.2 0.5625 2507 0.9925 7.4574 - 1. 0000 - 1.0000 - -1.0000
1 1.0000
249 - 1 75 70 49.2 0.8476 3363 0.9981 1.8957 - 1.0000 - 1. 0000 -1.0000
0.1125
250 - 85 70 48.8 0.8555 3386 0.9981 1.8842 - 1.0000 - 1. 0000
1 1.2634 1.0000
251 - 85 ' 70 100.8 0.4983 2190 0.9502 49.7573 - 1. 0000 - 1.0000 -1.0000
1 0.0767
252 - 90 70 100.4 0.5006 2210 0.954,3 45.7280 - 1.0000 - -1.0000
1 1. 0000 0.0501
- 97.0 0.577 2 2549 0.9866 13.4016 - 1.0000 -1.0000 -1.0000
253 1 92 70 0.1275
- 93 70 100.1 0.6412 2779 0.9925 7.5138 - 1.0000 1.0000 -1.0000
254 1 0.2430
255 2 93 70 90.0 0.6063 2653 0.9882 11.7618 - 1.0000 - 1. 0000 -
1. 0000 , 1. 0000
256 2 85 70 97.6 0.7188 3024 0.9954 4.6069 - 1. 0000 - 1.0000 0.4797 -
1.0000
257 2 85 70 97.6 0.7852 3214 0.9963 3.7465 - 1. 0000 -1.0000 1.3082 -1.0000
258 2 85 70 97.5 0.9004 3466 0.9955 4.4843 - 1. 0000 - 1.0000 2.0235
1.0000
259 2 85 ,70 97.4 1.0000 3556 0.9804 19.6038 - 1.0000 - 1.0000 2.6256 -
1.0000
260 2 85 70 97.3 0.9609 3538 0.9915 8.5162 - 1.0000 - 1.0000 0.9896 -1.0000
261 - 1 89 70 97.2 1.1875 3482 0.0000 0.0000 - 1. 0000 - 1.0000
1.1944 1.0000
262 2 90 70' 144.4 0.5167 2244 0.9436 56.4055 - 1.0000 - 1. 0000 -
0.2285 1.0000
263 2 97 70 143.5 0.5957 2609 0.9835 16.4723 - 1.0000 - 1. 0000 -
0.3739 1.0000
264 2 85 73 48.8 0.4951 2240 0.9799 20.0719 0.1469 - 1.0000 0.1062 -
1.0000
265 2 85 73 48.8 0.5820 2577 0.9938 6.2279 0.1737 - 1.0000 0.4157 - 1.0000
266 2 96 70 143.0 0.5677 2498 0.9772 22.8177 0.2547 - 1.0000 - 1.0000 -1.0000
267 2 96 70 97.8 0.5045 2243 0.9611 38.9211 - 1.0000 - 1. 0000 '-1.0000
0.0970
96 70 97.2 0.5817 2569 0.9874 12.6322 - 1. 0000 -
26'8 2 1.0000 0.2692 1. 0000
96 72 97.2 0.6582 2838 0.9936 6.3814 - 1. 0000 - -
269 2 1.0000 0.6805 1.0000
270 2 96 72 97.1 0.6860 2929 0.9947 5.3297 - 1. 0000 - 1.0000 -1.0000
1.9372
BURN=2---STABLE PRED EMM = 1000x(1-EFFY) NOB - BURNER DATA FOR NOX
BURN=1- --LIMIT PRED EFFY FROM THEORY NOT - NOX FROM VAPOR GENERATOR EXH.
BURN=O---GOING OUT
Table
VIII-27
image:
-------
COMPARISON OF PREDICTED BURNER INRFFICIENCY AND EXPERIMENTAL EMISSIONS DATA PAGE 10
RUN BURN AIR FUEL AIR EQU1V CONB PRED PRED COG NCG NOBG NOTG
NO. TEMP TEMP FLOW RATIO TEMP EFFY Ell/.! EMM EMM EMU EMM
OF of LBS/HR of G/KG G/KG G/KG G/KG GIKG
271 2 100 75 144.1 0.5576 2459 0.9740 26.0316 - 1.0000 - 1. 000'0 0.1791 -1.0000
272 2 100 71 141.7 0.6618 2846 0.9909 9.1203 - 1.0000 -1.0000 0.5020 - 1.0000
273 2 100 70 143.1 0.6745 2888 0.9915 8.4565 - 1.0000 1. 0000 1.4659 -1.0000
274 2 100 70 143.5 0.7565 3140 0.9942 5.7548 0.4611 0.0000 0.3865 -1.0000
275 2 95 70 143.7 0.8254 3317 0;9947 5.2594 0.7331 - 1.0000 1.0296 -1.0000
276 - 1 - 1 - 1 130.0 - 1.0000 - 1 0.0000 0.0000 - 1. 0000 - 1.0000 - 1.0000 1. 0000
277 - 1 -1 - 1 140 .0 - 1.0000 - 1 0.0000 0 .0000 - - 1.0060 - 1.0000 -1.0000
1.0000
278 - 1 - 1 -1 - 1.0 - 1.0000 - 1 0.0000 0.0000 - 1.0000 - 1. 0000 -1.0000 1.0000
279 2 109 70 91.0 0.5791 2~64 0.9848 15.1737 0.1247 0.1994 0.3360 0.1639
280 2 110 70 90.9 0.6808 2920 0.9936 6.3889 0.2104 0.9399 0.7810 0.7188
281 2 110 70 111.3 0.5932 2610 0.9838 16.2'248 0.1216 0.0485 0.3316 0.1638
282 2 94 70 46.4 0.6072 2670 0.9942 5.7850 0.1187 0.0000 0.3665 0.3002
283 2 100 70 47.3 0.6024 2658 0.9939 6.0739 0.1196 0.0000 0.1101 0.0786
284 2 105 70 46.5 0.4239 1846 0.9000 100.0000 0.1727 0.0000 0.0624 0.0454
285 2 116 70 136.5 0.4873 2051 0.8890 111.0000 0.2450 0.0000 - 1.0000 0.0589
286 2 82 75 58.8 0.5010 2253 0.9771 22.8988 - 1.0000 - 1.0000 0.1097 - 1.0000
28,7 2 92 70 144.0 0.5260 2302 0.9548 45.1854 2.6202 0.0000 0.1586 - 1.0000
288 2 90 69 144.3 0.5654 2483 0.9757 24.2540 - 1.0000 0.0000 0.1849 - 1.0000
289 2 95 69 143.6 0.6016 2629 0.9843 15.7393' - 1.0000 0.0000 0.2559 - 1.0000
290 2 99 60 142.9 0.7193 3029 0.9934 6.6129 0.9138 0.3568 0.1304 - 1.0000
291 - 1 73 68 66.0 1.3984 3192 0.0000 0.0000 - 1.0000 - 1.0000 0.6409 - 1.0000
292 - 1 75 70 49.1 1.5625 2965 0.,0000 0.0000 0.1314 161.4518 0.4629 - 1.0000
293 - 1 82 70 47.1 1.3594 3251 0.0000 0.0000 1109.9767 1.0542 - 1.0000 - 1. 0000
294 - 1 90 70 51.1 1.2578 3393 0.0000 0.0000 764.7702 2.7660 - 1.0000 - 1.0000
295 - 1 72 70 49.2 1.3203 3297 0.0000 0.0000 961.B26'~ 0.911~9 1.1960 - 1.0000
296 - 1 86 73 48.6 1.3438 3274 0.0000 0.0000 944.0615 0.6170 1.6858 - 1.0000
297 - 1 92 71 48.3 1.4141 3183 0.0000 0.0000 1152.1380 0.5784 1.0119 - 1.0000
298 - 1 95 71 48.2 1.2813 3364 0.0000 0.0000 879.4185 0.8733 2~1113' - 1.0000
299 - 1 96 71 87.2 1.3750 3238 0.0000 0.0000 984.6333 0.9159 - 1.0000 - 1.0000
300 - 1 85 69 49.3 1.1719 3494 0.0000 0.0000 ,1013.6513 1.0314 0.8173 - 1.000n
BURN=2---STABLE PRED EMU = 1000x(1-EFFY) NOB - BURNER DATA FOR NOX
BURN=l- --L1141T PRED EFFY FROU THEORY NOT - NOX FROM VAP-OR GENERATOR EXH.
BURN=O---GOING OUT
Table
VIII-28
image:
-------
CtJIIPUZ80. 0' p.."zcrBD .U.... Z.."ZCZ..C7 A.D .ZP.Bz...rA£ .IIZ8SZ0.S DArA PAG. 11
.u. BUB. AZR 'U.£ AZR .QUzr C0II8 PR.D PB.D COG BCG .OBG .orG
.0. rDP rpp ,UJJ/ RArzo rBHP ."7 .. BIIII .11. .101 .1111
0' 0' £8./.B 0' G/XG G/KG G/XG G/XG G/XG
301 -1 18 19 '1.5 1.2181 3'"'' 0.0000 0.0000. 129.tt393 0.5725 2.3267 -1.0000
302 -1 12 70 11.1 1.'219 3172 0.0000 0.0000 1104."730 -1.0000 0.3230 -1~0000
303 -1 ,.. 18 11.5 1.2113 3352 0.0000 0.0000 , "2".""0 2. nOI 0.5779 -1.0000
3M -1 11 70 1'1.5 1.3'38 3275 0.0000 0".0000 950.9025 1.0133 0."252 -1.0000
305 -1 100 11 12'.2 1.3150 32U 0.0000 0.0000 1030.770" 0.8'''1 o. ..431 -1.0000
3- -1 100 'I 131.1 1.1711 3503 0.0000 0.0000' 510.8185 '.017' 0.6130 -1.0000
30' -1 10.. 'I '''.3 1.1153 3"" 0.0000 0.0000 551.1211 -1.0000 0.3189 -1.0000
308 2 '0 320 "'.1 0 . 5"" 2...., 0.1886 11.3115 1.9812 -1.0000 0 . 2088 0.0'79
309 2 18 350 "7.5 0.5052 2285 0.97'" 20.St38 2.1579 0.0000 0.0.,8 0.011"
310 -1 ,.. 310 "8." 0.3"31 1562 0.'100 90.0000 0.5925 0.1868 0.0529 0.0529
311 2 385 350 ..,... 0 ~ 5886 2820 o. I"" 3.,6311t 1.8390 0.0000 0.33'" 0.3061
312 2 388 nl "1.3 0.5011 25..6 0.9925 1."545 0.1It25 0.0000 0 .016" 0.0726
313 2 3'5 3110 117.2 0.3'115 2063 0.9522 117.1285 0.1861 0.0000 0.0092 0.03.35
31.. 2 3"0 1150 88.2 0.53112 2603 0.9883 11 .67'2 -1.0000 -1.0000 0.0883 0.1590
315" 2 3611 ..50 93.1 0."726 2357 0 .9727 27.2698 -1.0000 -1.0000 -1.0000 0.0507
316 2 1100 1160 10.5 0.50"3 2520 0.9n9 15.0668 0.1"41 0.0000 -1.0000 0.0332
317 2 ..35 460 90.0 0.405' 2085 0.9216 78.3522 0 ;1806 0.0000 ,0.005,9 0.0237
318 2 350 638 137.1 0."935 2408 0.9665 33.4715 0.1..7.. 0.0000 0.0378 0.08"8
319 2 350 620 137.2 0."150 1976 0.8800 120.0000 0.32"9 0.0000 0.0000 0.0319
320 2 351 600 13".5 0.6..8.. 2981 0.9928 7.1961 0.1838 0.0000 0.0673 0.1328
. 321 2 1..0 no 89.8 0.5978 2659 0.9"87 11.2516 0.3619 0.0000 0.0951 0.1367
322 2 115 "90 90.0 0."857 2115 0.9234 76.5982 0.5007 0.0000 0.0074 0.0394
323 1 105 530 90.0 0.11"" 1922 0.8960 10".0000' 5.1723 0.2758 -1.0000 0.0295
324 2 95 585 135.5 0.58"7 2555 0.9769 23.09"8 0.1235 0.0198 0.0588 0.11"4
325 2 105 550 137.3 ,0.5181 2229 0.9286 71."471 0.9387 0.0117 0.0184 0.0437
326 1 110 610 138.7 0...,96 2023 0.8900 110.0000 4.5562 0.2561 0.0050 0.0399
327 2 "12 77 48.2 0 .6017 2884 0~9170 3.0281 0."025 0.0286 0.1456 0.2342
328 2 395 90 47.3 0."641 2378 0.9871 12.8502 0.4998 0.0000 0.0320 0.0671
329 2 390 95 47.1 0 .3821 1968 0.924" 75'.6240 3.1701 0.0000 0.0000 0.0253
330 2 407 97 90.3 0.5955 2853 0.9939 6.0797 0.1211 0.0000 0.2646 0.3661
BlIRN: 2- - -STAiJLE PRED ENU = 1000x(1-EFFY) NOB - BURNER DATA FOR NOX
BURN=I- --LIMIT PRED EFFY FRON THEORY NOT - NOX FROM VAPOR GENERATOR EXH.
BURN=O---GOING OUT
Table
VIII-29
image:
-------
COMPARISON OF PREDICTED BURNER INEFFICIENCY AND EXPERIMENTAL EMISSIONS DATA PAGE 12
RUN BilRN AIR FUEL AIR EQUIV COMB PRED PRED COG BCG NOBG NOTG
NO. TEMP TEMP FLOW RATIO TEMP EFFY E [.JI.1 EMM E/tIM EMM EMM
of of' LBS/BR of G/KG G/KG G/KG G/KG G/KG
331 2 400 100 92.7 0.4834 2436 0.9798 20.1670 0.1506 0.0000 0.0891 0.0891
332 1 435 92 89.7 0 .4059 2086 0.9223 77.6826 358.7488 0.0000 0.0000 0.4155
333 2 392 95 135.2 0.4401 2160 0.9166 83.4309 4.7839 0.0000 0.0000 0.0573
334 1 395 100 140.3 0.3843 1908 0.8800 120.0000 - 1.0000 0.0000 0.0000 0.0408
335 2 92 590 91.3 0.5556 2457 6.9787 21.2564 0.1263 0.0000 0.0770 0.1287
336 1 90 630 92.6 0.4667 1964 0.8900 110.0000 9.0811 0.0631 0.0000 0.0597
337 2 90 610 48.5 0.5434 2432 0.9876 12.4134 0.1292 0.0000 0.1511 0.1019
338 2 90 660 49.6 0.5899 2605 0.9926 7.4003 0.1186 0.0000 0.0080 0.0565
339 2 100 660 136.7 0.5685 2492 0.9718 28.1970 - 1.0000 0.1976 0.1838 0.1580
340 2 395 90 138.3 0.4997 2478 0.9739 26..0525 0.1455 0.0121 0.0239 0.1076
341 2 150 100 92.4 0.5245 2378 0.9725 27.4705 0.1383 0.0000 0.0250 0.0955
342 2 90 85 93.3 0.5472 2419 0.9753 24.7073 0.1283 - 1.0000 0.0000 0.8349
343 2 102 100 91.3 0.5273 2344 0.9686 31.4349 0.1375 0.0000 0.0452 0.0949
344, 2 100 100 91.9 0.4688 1979 0.8900 110.0000 0.1555 0.6505 0.0077 0.0690
345 2 102 95 135.3 0.5445 2386 0.9606 39.3849 0.1330 0.0000 0.0240 0.1704
346 2 105 95 138.2 0.4898 2051 0.8890 111.0000 - 1.0000 0.1853 0.0000 0.0952
347 2 105 97 134.5 0.6523 2813 0.9882 11.7854 - 1.0000 0.0000 0.2097 0.4230
348 2 107 95 90.1 0.6022 2649 0.9882 11.8085 0.9708 0.0000 0.0275 0.5474
349 2 100 100 91.9 0.5137 2274 0.9592 40.7793 128.2549 2.5352 0.0070 0.1373
350 2 101 105 136.4 0.5697 2498 0.97,24 27.5751 13.6585 0.0998 0.0417 0.3315
351 2 105 810 92.4 0.6311 2749 0.9906 9.3830 0.1105 0.0000 0.0973 0.1707
352 1 110 815 93.1 0.5036 2230 0.9510 48.9656 0.1399 0.0000 0.0190 0.0138
353 2 120 790 137.7 0.6311 2749 0.9861 13.8546 0.1105 1.3118 0.1497 0.2070
354 2 430 630 81.4 0.5379 2672 0.9915 8.4997 0.1306 0.0000 0.1018 0.1588
355 2 438 610 82.0 0.4309 2251 0.9646 35.3630 0.1643 0.0000 0.0112 0.0432
356 2 450 625 43.8 0.5570 2762 0.9964 3.5851 0.1260 0.0000 0.1024 0.1531
357 2 140 690 180.5 0.5053 2111 0.8800 120.0000 0 . 1394 0.0000 0.0284 0.0779
358 2 110 690 46.8 0.4673 2116 0.9590 41.0407 0.1512 0.0000 0.1025 0.0795
359 2 120 730 138.2 0 . 5022 2097 0.8860 114.0000 0.1403 0.0000 0.0666 0.1014
360 2 380 570 92.6 0.5322 2608 0.9881 11.8535 0.1321 0.0000 0.1119 0.1649.
BURN= 2- - -STABLE PRED EJ.fM = 1000)«1-EPFY) NOB - BURNER DATA FOR NOX
BURN=1- --LIf!IT PRED EFFY FROU THEORY NOT - NOX FROU VAPOR GENERATOR EXH.
BURN=O---GOING OUT
Table
VIII-30
image:
-------
COIIPARXSO. 0' PR1lDXcr.D .U"" X..'PXCX..CY A.D .ZPBRx...rA£ E.ISSIO.S DA2'A PAGE 13
BU. BUR. AIR 'U.£ AIR .QUIr COII1I PR.D PR.D COG BeG ROBG N02'G
.0. rap rap '£Of! RArIO rap B'FY BN. BIIJI ENII ENN EMil
OP 0' £BSIBR 0' (;J~C C/~C G/KG G/XG G/XG
361 2 1100 620 10.9 0.11673 2370 0.97 50 211.9818 0.1512 0.0000 0.0154 0.0795
362 2 1105 670 89.8 0.6305 2967 -0.9952 11.7757. 0.11 06 0.0000 0.1986 0.3236
363 2 1105 6115 90.8 0.119811 2501 0.98110 1.6.01111 0.11114 0.0586 0.1774 0.2323
3611 2 1105 670 11'.7 o. 5691 2769 ,0.9960 11.0079 0.1232 0.4965 0.1836 0.1943
365 2 1105 670 11'.0 0.621111 2953 0.99711 2.12111 0.1118 0.0616 0.2725 0.1910
366 2 1110 660 117.9 0.11309 2255 0.97911 20.1335 0.16113 0.0000 0.0558 0.0648
367 2 1105 670 137.0 0.5100 2530 0.9782 21.7602 -1.0000 0.0000 0.0515 0.1270
368 2 1fI0 690 137.1 0.11309 2087 0.885 5 1111."709 0.1643 -1.0000 0.0279 0.0432
369 2 1100 690 136.3 0 .5691 . 27..8 0.9882 11.7979 0.2"64 0.0000 0.1502 0.2267
-
370 2 1103 710 90.9 0.5"75 2683 0.9907 9..3231 0.3745 0.1464 0.1043 1.0000
-
371 2 ..26 720 137.1 0.5738 2785 0.9893 10.1911 > 0.9111 0.0000 0.1572 1. 0000
372 1 ..25 700 138.7 0.5..3. 2676 0.9856 1".350" 1.1935 0.5236 0.0525 :1. 0.000 ;
373 2 "25 720 90.9 0.5325 26116 0.9898 10.2252 0.1320 0.0757 0.0984 1.0000
-
374' 1 ..30 700 90.3 0.11'13 2..95 0.9839 16.0altS. 5.8846 6.5336 0.0584 1. 0000
. -
375 1 1100 710 91.11 0."618 23116 0.9725 27.11727 25.2456 108.5867 0.0042 1.0000
-
376 1 400 710 90.3 0."711 2387 0.9766 23.3936 85.4441 180.1626 0.0041 1.0000
-1. 0000 - 1. 0000
377 2 1t05 705 "8.3 0.11838 21f62 0.9903 9.7117 0.7287 0.1335 -
378 1 1t28 730 1t5.5 0."875 2..96 0.9919 8.0865 3.3900 5.0370 0.0687 1.0000
-
379 1 375 720 "7.0 0."650 236- 0.9865 13.52"7 8.5'00 3.4403 0.0670 1. 0000
-
380 1 1t12 715 1t5.7 0.lt395 229.. 0.9.832 16.8192 27.7000 75.2300 0.0055 1. 0000
32.1684 - 1. 0000
381 1 411 728 138.5 0."507 2262 0.9438 56.1542. 66.5627 0.0037 -
382 1 411 721 138.7 0.lt501 2258 0.9"29 57.1028 "9.3421 156.2723 0.0053 1.0000
-
383 1 ..03 700 "7.1 0."725 2..18 0.9890 11. 0430 20.7706 57.4081 0.0710 1.0000
-
38.. 1 76 710 91." 0.5775 2531 0.9830 16.9827 0.4440 0.0488 0.0822 1.0000
- - 1. 0000
385 2 90 430 91.6 0.5625 2..83 0.98011 19.6011 1.0000 0.0402 0.1436 -
386' 1 91 "70 89.8 0.52'" 2339 0.9686 31.3526 32.2044 8.5927 0.0271 1.0000
-
387 1 80 740 47.8 0.5255 2353 0.9839 16.1210 4.0152 1.0001 0.0998 1.0000
-
'388 1 81 740 "5.5 0.5337 2389 0.9865 13.5103 53.5975 28.3174 0 . 00'6 7 1.0000
-
389 -1 85 390 "8.2 1.233" 3..23 0.0000 0.0000 1194.6713 18.0370 0.5425 1.0000
-
390 1 90 515 80.9 0 . 5..00 2397 0.9769 23.1205 0.1301 0.2117 0.2557 - 1.0000
391 2 93 550 80.5 0.4900 214.. 0.9388 61.1581 77.7172 19.0275 .0.0098 1.0000
BURR= 2- --S TABLE PRED EMN = 1000x(l-AFFY) ROB - BURNER -DATA FOR NOX
BURN=1- --LIMIT PIlED EFFY FROII THEORY ROT - ROX FROM VAPOR GENERATOR EXH.
RURN=O---GOING OUT
Table
U-31.
image:
-------
APPENDICES
image:
-------
REFERENCES
1.
Frank-Kamenetskii, D.A., 8Diffu8ion and neat Exchange in Chemical
Kinetics", Quoted by Frank-Kamanet.kii, Princeton University Press,
1955.
2.
Van't Hoff, .Etude. de Dynamique Chimique", Amsterdam, 1884.
LeChatelier, Quoted by Frank-Kamenet8kii after Jouget, 8Mechanique
des Explosifs", Paris 1937.
3.
4.
Sernenov, N.N., quoted by Frank-Kamenet8kii, Z. Thysik, Chem. 48,
571, 1928. .
5.
vulis, L.A., "Thermal Regime. of Combu8tion", McGraw Hill, 1961.
DeZubay, E.A., .Characteri8tic. of Di.c-Controlled Flame", Aero
Digest, July 1950.
6.
7.
~~~~~~~~'G:;Cstr::;~~ ~~~l~;::~~~U:~nP~~~::~~~ ~~~e and
Explosion Phenomena page 21, Willi... and Wilkin., 1949.
~~~~~~~ti~:.zo:::8~e;:.;8~.~~d.8:;~c:;:~i;~~I~~~ ~~~;f8:nodY
Symposium on Combu.tion. . .
8.
9..
ZwiCk, E.B., , Bjerklie, J.W., .The Mechani.m of Combu.tion
stabilization in Monoprepellant Reaction Chamber.-, Sund.trand-
Turbo, Paco!ma, 1958.
10.
Clarke, A.E., Harri.on, ".J., Od9er., J., .cOIIIbu.tion Stability
in a Spherical Combu8tor., pp 664, 7th Symp08ium on Combu8tion,
Buttorworth.~ 1'59.
11.
Jeff8, R.A., 8it 1'1... Stabilit~ Hea~~~ RaUi of Scme
can-Ty~Cambu8 on :....r8-,.. ympo. ua on 08bu.t on
pp ID'I1";"""Will1am8" lJtG'i';" 1960.
Williama,et al, 8The Cambu8tion of Methane in a Jet-Mixed
Reactor", 12th Symp08ium on Ccnbu.tion, pp 91J, 1'69. .
12.
13.
Clarke, A.E., 8Further Studies of CClllbu.tion Phenomena in a
~~;::1,C~~::~~-i9:~ Symp08ium on Combu.tion, pp 9B2,
Herbert, M.V., 8A Theoretical Ana~.i8 of Reaction Rai;
controlled S,stema Part ~I-, 8th ympo81um on Combu.t on,
pp 970-981, il1iama IItErn., 1960.
14.
15.
Hougen, 0., Watson, K., Ragatz, 8Ch8mical Proce88 Principles.,
J. wiley' Sons, 1947.
image:
-------
Colorimetrio r.'icrodatcrmil8lit. of rJitrcgon ~;oxide in ihG ntmosfibera
BERNARD E. SALTZMAN .
D,.,.,o" 01 $pec/" HHI" s.n.b, U. So 0....., '" HuItI.. u..otIo", .Well.,.. ("tel..", 01110
The determlnatlo.. or nltros"n dioxide In the atrn-
"here h..M heretofore I,.,en I..unpered by dim_hi"" ID
..."'ple nh,orptlon an,llack oC ."""Iraell,.. A new ope-
. rilie rengeDt h.a Iw.en de\'elo.-I &I"d demonatrated to'
.I-.rb effielenll,. in a mlelset Critt",1 bubbler &It \eye"
. below 1 p.p.m. The reallent la a mixture or auVanlUe
u.,jd. JV-(l-n&lphlll)'I)-elhylenedlamlno dlhydrochlo-
rid", ...,,1 1Ir.f!IICJ "d.l. A ..laMt! .lIre.'1 eolor I. pr...luClOd
with 11 lIen..ltlylty ..r n Cew INltla I"'r billion ror . 10-
",illllto "...nple ..l 0.1. liler Iter ...Inllte. (~....o I" liye-
r..I.1 "x«... nn.1 olhcr /:""". ill .t..nf..loI ex,,"'"" p..."'''co
on I,. IIlIsht later(erinr:; elTe""'1 'h"lM! n.a,. be ftd.,eed
(urther by me..... which .ate .I,'....rll....l.
.rOXIC oxitlrll of lIitrn~(,". lil".",t,,<1 dllring the IlIIe of ex-
pl08iyP.8, in weMinl; ol>", believed to pI:»' " vitnl role in tho creAtion 01 irritating
';1"11 (4, 10). TO'licoloJ:i.: ~t.udiel (8, 0, 16, II, I~) can attention
,) the r",1It \ ""I. nitro~"1\ dioxido iA \ho I1\OIIt toxio of the y",rioua
.MOI!en uxi.I"M by n Inr~o fllCt«, And that confll8ion in tho
1~llul\tion ,,' thc hcnlt.h llaznrde huA I'CIIIIlted from AnAlytical
:lI!thoda wi. "fnil to diITrrr.nt.inte \.hie oxide from '\.ho o\.hcra in
I mixt.ure. 111 terme of lIit.roJ:eo dioxide, 11 ligure 01 6 p.p.m. ia
'!Ie mAximum 88Ie nllow:ll>ie eoncc11lrl1tion propoeed (8, i).
IU th\'le coneiderationll r"'lIlire it. det.crmlnAtion In air at much
...c"r levr.18 than previo\J.h- UWllltht nOCC8Al)'.
The m",jor problem of ..3IIt analyiiealmethoda hu b8en the
';j!jMllty in ahtlorbin« the gill lrum a ItIftieiently IArp 8mJt1e.
:...ulta have loccn uncertain for leveIa below 6 p.p,m. Sampb
:\l1li\ be eoI1ec~ In lAI'K" bottl. for the woll known pb8d-
iioulronie acid meY"xI (8, (1), 110,1 tin,.. An! required for -p\etlt
....,.Uoa; 1<.. ft!8U1!A have I>(!p.n repnnr.d (16) nnd cunllrmed
. u... ,.,.,...,nt ltudy. 8i",illlr diffieulliCII ocmJr with &he m-'
iJk'lIolme\.hode (II, ~Ii). 11o&h determine all niLroccn odde8ln
'100 fotm of niLmle, rl\ther !.IIIUl nit.ropn dioxide lpCCifie:IIl,..
AlternI'll! have bcl'n OIad" to UIIC rcnpmta lor nitrite il'll, whleh
'<'IIIItIIM' NI..:cillc tor nilrog,'" .lin1ridc, but an abaorption efTlCieftey
.i oll'y I\hollt a% W811 rcp..rk,U (16) when a midp!t impin(lUr ....
.....1. How,'vcr, thcac rrngcnta wen found to be wry --
"',,",ot rnr i,;jtheJ' IcvdJl IlJline a ,1- ayrinp for c:oIleet.inI tile
'11"1'''' 11, 1:1, lit); 10'" I,'velll haft '-wi cletenninro Ulilll a
....., '. . . C""t.inU/llIM ",Implaa haye '-' colh1eted II,. tMilll
. Ii.. " ... lit,uid (lir lclll,.'t:ltlln!8 (1) ,. alkali IJUbbIen (II),
'. . . :.1'''' ""inl': f7l unkllf)Wn ,oflicieney.
,._t report dr",IM wi&h &he ~ment alld demoD-
. "II 01 a rmpnt whid, ie .pecifae lOT nltropn dioxide and
..1 for cont.inllOlIIl IllUnl.Jinl': wi&h a hich efIeicmey. The
..,,4oom '" .lclA'1'lIIilli",' ~ ~ ... ~
. II,,, r.'litle 01 a t- tenthe fII a
. ;0" million with a vllri"~lJn 01 ..... Ulan 17": "181'18f!1e1K
..' """ IinAlly devr.\nI>f..1 em.,enlen&ly prodllCr.fl" A."IIIe diree$
-Io.r .. I.i.'" I'IUI .... ............. """lIdl,. or ..-tmt"""'>n,;..trie8Jly. .
. 10.." ." ..~, ;';1' 1....1 II> It ,"""'.1, rtlttf!o' hI,.>I,..., ....1 IIIr ..
.,,,,.1.., ..t .. ",... 01 0." lill!l' .",r IlIiUlot.., a -'u.,Uy "I a ,...
.. ,,. I"'" Ioilli.... .. n,....h..... wiUt " \(I-minll'" I8IIIpIa. 'J'he ""ee$
i ....n.- i..',,",..rillll S- ... fCII....1 &0 .... "icbL
ArrARA",!!
Spectrophotometer, Heckmnn Morlnl DU. A I!e\ of ma~hed
.teA tubol, 22 X 176 111111., j::ivilll( nn opLical JiKbt pnt.h of 2.02
em. WIll ulled in a llpeeil11 holder liLt.cd to tho 8p""trnllhu'.'motcr.
Mld,et Flitted Bubbler., a11-~I:ulII, enpnelty IJI) mi., with "I'-
ward-foelil!!:, 8-mm. dinmet.er tritted .hake. When UllCd wilh
10 ml. of tho ab80Tbing reagent, drnwinl': Air throllllh lit tbc mte
of 0.4 liler per minute .hou1<1 prodllco 20 to 30 mi. of fine froth
ubl.vo thn 111,11111,,".
Grab-Sample Bottle. IlRving ~lnlld"rd-t"por p:I'I.urld.joint eoo-
ncetlon II) .wJloocke lllr OV"cu"U"n, with calihrAlcd volume.
vnrying from :10 to 250 ml. Orclinnry J:11I_.toppcred bora-
lilieule glnee bottlce Are .uitllhln. FifLy-millilit<)r gll18l ayrillilll
are convenient for moderulely hl!!:h coneolltrntione.
REAG Jo:N"rtI
All rOllicn... nrc moo.: (rom nnulytienl j;rl\lJo chmnieal. in nl-
trir...-fr"c willer 1""'fAred hy reulolll..r nn.1 .Im.. "&le
throuJdl " at the rate of 0.4 liler f"'" anillll"" IInti! M"ffaciont (!ow,
baa .1~ (ahout 10 minu,,"...). N.,'.. tho '.olnl Air volume
8IImillcd. run, pm ruhbOT Jlu..,p.'ull '" .i"l1 "'I\Y hr. ulod lor con-
~&i<1III without ao-. If IcnJ;~hJl/tr,' L,.,., 1I,;"II11tII.
. e.m,a., fer w.,el8 a1Ieve 1 P.P.M. /'1'11111,10 in nn oyacu-
a&C!i1 J",tLIe of aPf'MllriAte iii.. jllNt 'N.fflro ,:ampllni 1.. eliminate
any ullfJl!l1Alnty .wout IoaII of VII"IIUln. ,\ &lll'fIUollfny Y Itc'p-
cook eooneetion to tile YllCUum 1'11"'1' i~ c.......nlent:. In &h. Ii..
potoition &be but.tIo .. "_trcl Lt, t '10 y/t'''",,>TClllltirc H( tho nb-
lOTI'inc ft!II&Imt'" tlao adeanl V;"""II" i. I'CtIOI. In th" ICCPnd
pcNlltiotl tho -I "in« ,"oUl.. I. "1.,,,,..1 /lIMI 1."0 V"Mlllln pump
dmW'. air t.broa,di &he -Plilll( lin.. t.. ..h..roul!hh Ihuh It. 111
the thin! pllRUoo the 811mI'll", Ii"" i.. e..,nll'CIted to. ~: .,' t!\',.c:uatm
bo$&Io anti the -pie I. colloe&cll. J'"r ,'1( 1~1I1u&inn "I &he ",.ruple
.,oIumo &he v-re ia rwordcd at I.'''' dilTerCllC/! bt!twecn the .
IiIIed aaad "_&oct condllioM, al/ll till! voillme ia lI,at IIf tI'e
boWe pip tIta& of .,., COI1IICC&i