-------
TABLE A-12. TEST PLAN
I. Baseline performance with petroleum fuel.
A. Engine break-in.
B. Run engine to determine mechanical and pumping losses
for correlation of data.
C. Collect part load and emissions data at:
1. 2200 RPM - rated speed
2. 1400 RPM - peak torque
Data taken at load points equivalent to the 0, 50%, and 100% BMEP
points.
II. Performance with shale-derived DFM - repeat step I-C.
A. With same timing and rack setting.
B. With rack and timing adjusted to the same power as in step 1-3.
III. "OBSERVED" shale-derived DFM comparison - steps I-C and II repeated
for personnel from Naval Ship Research and Development Center.
9. PROJECT STATUS
Testing conducted in April 1980; results documented on 12 May 1980.
10. RESULTS
Performance and emissions for both fuels were compared and found to be
the same with the exception of 2.5 to 4.0 percent lower thermal efficien-
cy with the shale-derived DFM. Results are presented in Table A-13.
Additional part load performance tests and advanced timing performance
tests also showed no significant differences in either performance or
emissions for both fuels.
11. REFERENCES
"Diesel Engine Test, 12 May 1980", supplied by C. H. Hershner, David W.
Taylor Naval Ship R&D Center, Annapolis Laboratory (Code 2705). Annapolis,
nU 9 I L. pp«
Telephone communication to C. H. Hershner, U.S. Department of the Navy,
?7 March °" P R&° Center* AnnaP°lis> MD> to s- Quinlivan,
A-46
-------
TABLE A-13. SUMMARY OF TEST RESULTS
Petroleum Shale
I.
II.
III.
IV.
2200 rpm - max load (fixed rack @ .440)
BMEP* (psi)
BSFCt (lb/bhp-hr)
BSEC? (btu/bhp-hr)
Smoke
HC (gr/bhp-hr)
NOV (gr/bhp-hr)
A
2200 rpm - idle
HC (gr/bhp-hr)
NOY (gr/bhp-hr)
A
1400 rpm - max load (fixed rack @ .440)
BMEP* (psi)
BSFCt (lb/bhp-hr)
BSECf (btu/bhp-hr)
Smoke
HC (gr/bhp-hr)
NOY (gr/bhp-hr)
A
1400 rpm - idle
HC (gr/bhp-hr)
NOV (gr/bhp-hr)
X
125
.447
8,194
.03
.09
1.17
.09
.22
142
.411
7,534
.08
.12
.57
.05
.12
126
.448
8c n "3 f o Q°/-^ \
, D(J6 ( o . o/o> )
.03
.03
1.25
.15
.16
142
.406
7,706 (2.3%>)
.11
.12
.51
.06
.11
BMEP = brake mean effective pressure.
fBSFC = brake specific fuel consumption.
^BSEC = brake specific energy consumption.
A-47
-------
TEST 13
NAVY CV-60 CLASS BOILER EMISSION MEASUREMENTS
1. FUELS TESTED
Synfuel: shale-derived diesel fuel marine (MIL-F-16884G).
Reference fuel: petroleum-derived diesel fuel marine (DFM).
2. TEST EQUIPMENT
U.S. Navy CV-60 Class ship's propulsion steam generator (see Table A-14
for description).
TABLE A-14. CV-60 STEAM GENERATOR-OPERATIONAL PARAMETERS
Number 1
Class CV-60
Boiler Manufacturer Babcock & Wilcox (B&W)
Operating Pressure 1200 psig
Superheated Steam Temperature 950°F
Steam Generated @ Full Power 261,450 Ib/hr
Oil Burner @ Full Power 20,000 Ib/hr
Combustion Gas Pressure 2 psig
Boiler Type Natural Circulation
Water Cooled Furnace Yes
Furnace Frontwall and Floor Materials Refractory
Superheater Type Horizontal
Number of oil Burners 7
Burner Type *
Automatic Combustion Control Yes
*
B&W Iowa Registers with mechanical vented plunger atomizers.
3. TEST SITE
Naval Ship Systems Engineering Station, Philadelphia, Pennsylvania.
A-48
-------
4. TEST OBJECTIVE
§ To perform comparative emissions measurements between petroleum-
derived diesel fuel marine (DFM) and shale-derived DFM for comparison
with EPA stationary source steam generator standards.
5. SPONSORING AGENCY
David W. Taylor Naval Ship R&D Center
Annapolis Laboratory, Code 2705
Annapolis, MD 21402
Project Officers: Carl H. Hershner and Robert M. Giannini
Telephone No: 301-267-2674
6. CONTRACTOR
NAVSSES, Philadelphia, Pennsylvania.
7. TEST CONDITIONS
Boiler operating conditions presented in Table A-15. It was originally
intended to conduct the emissions testing at boiler loading conditions of
10, 25, 50, 75, 100, and 120 percent of full power. However, due to lack
of a full complement of forced draft blowers, rates of 63 percent or
lower were obtained (see Table A-15).
8. ENVIRONMENTAL MONITORING (See Figure A-8)
S02, N0x, CO, HC, C02, 02, and smoke.
9. PROJECT STATUS
Project began in March 1980 and completed in September 1980.
10. RESULTS
Pollutant emission results summarized in Table A-15. No significant dif-
ferences observed between emissions resulting from use of petroleum-
derived DFM or shale-derived DFM for any boiler load condition. It is
noteworthy that:
• Shale-derived DFM sulfur oxide emissions were generally somewhat lower
than petroleum-derived DFM at the same operating rates, due to the
lower initial sulfur content of the shale DFM vs. petroleum DFM (0.02
v 0.16 percent).
• Petroleum-derived DFM oxides of nitrogen exceeded those of shale-
derived DFM.
A-49
-------
TABLE A-15. CV-60, PETROLEUM-DERIVED/SHALE-DERIVED DFM EMISSIONS COMPARISON
Operating Rate,
Sulfur Dioxide,
PPM, Measured
Theoretical
Sulfur, PPM
EPA - Units,
lb; Per 106
BTU
Oxides of Ni-
trogen, PPM,
teasured
EPA - Units,
rbs Per 106
BTU
Carbon Mono-
xide, PFM
Hydrocarbons,
•J" PPM, as
tji Methane
O
Carbon Dio-
xide, *
Smoke, Kingel-
mann Number
Oxygen. 1,
Excess Air
OFG
Ibs Fuel Oil
Pressure
Fuel Oil Rate,
HR
% of Ful 1 Power
Time/Date
Coiment
11
DFM
2
-
-
9
_
1500
140
1.2
<1
14.2
-
-
65
2137
11
1030
5/16/80
White
Smoke
DFM
3
93.5
0.005
10
0.012
800
30
1.2
*'
11.6
112
207
65
2137
11
1100
5/16/80
Trace
Stack
Shale
0
11.7
0
9
0.011
200
15
3.5
•O
11.4
109
206
64
2400
12
1200
5/29/80
Normal
Opera-
tion
12
Shale
0
12.01
0
50
0.060
200
20
4.5
cl
10.2
83
201
65
2400
12
1430
5/29/80
Normal
Opera-
tion
25
Shale
0
11.80
0
15
0.018
350
15
3.6
*'
11.1
100
205
64
2400
12
1500
5/29/30
Normal
Opera-
tion
DFM
10
99
0.016
60
0.071
30
-
-
«!
7.1
48
195
120
5150
25
1110-
5/9/80
Normal
Opera-
tion
DFM
1
99
0.002
.
_
0
3
0
-------
ECONOMIZER
I
tn
TRANSMISSOMETER
(OPACITY SMOKE METER)
I ^HEAT EXCHANGER
CHEMICAL DRTER
ZERO
GAS ANALYZERS
BACK FLUSH AIR
PRE FILTER
(GLASS VOOL)
CVA-60
STEAM GENERATOR
(HAVSSES! TRAILER
Figure A-8. Source Emissions Instrumentation Schematic Diagram
-------
Pollutant levels (i.e., sulfur oxides, nitrogen oxides, and smoke) were
.all found to be below EPA stationary source standards.
11. REFERENCES
"Shale Fuel Oil Emissions Measurement: Interim Report", Memorandum Series
3242, 24 August 1980, supplied by C. H. Hershner, David W. Taylor Naval
Ship R&D Center, Annapolis Laboratory (Code 2705), Annapolis, Maryland,
12 pp..
Telephone communication of C. H. Hershner, U.S. Department of Navy, David
W. Taylor Naval Ship R&D Center, Annapolis, Maryland, to S. Quinlivan,
TRW, 17 March 1981.
A-52
-------
TEST 14
U.S. NAVY DDG-15 CLASS BOILER EMISSIONS MEASUREMENTS
1. FUEL TESTED
Synfuel: shale-derived diesel fuel marine (DFM), MIL-F-16884G.
Reference fuel: petroleum-derived diesel fuel marine (DFM), MIL-F-16884G
2. TEST EQUIPMENT
U.S. Navy DDG-15 Class propulsion steam generator (see Table A-16 for
description).
3. TEST SITE
Naval Ship Systems Engineering Station, Philadelphia, Pennsylvania.
4. TEST OBJECTIVE
• To perform comparative emissions measurements between petroleum-
derived diesel fuel marine and shale-derived DFM for comparison with
EPA stationary source steam generator standards.
5. SPONSORING AGENCY
David W. Taylor Naval Ship R&D Center
Annapolis Laboratory, Code 2705
Annapolis, MD 21402
Project Officers: Carl H. Hershner and Robert M. Giannini
Telephone No: 301-267-2674
6. CONTRACTOR
NAVSSES, Philadelphia, Pennsylvania.
7. TEST CONDITIONS
Comparative emissions data on petroleum-derived and shale-derived DFM
obtained over an operating range of 12 to 106 percent of full power.
Other boiler operating conditions presented in Table A-17.
A-53
-------
TABLE A-16. GENERAL DDG-15 BOILER DESCRIPTION
Class
DDG-15
Boiler Manufacturer
Operating Pressure
Superheated Steam Temperature
Steam Generated @ Full Power
Oil Burner @ Full Power
Combustion Gas Pressure
Boiler Type
Water Cooled Furnace
Furnace Frontwall and
Floor Materials
Superheater Type
Number of Oil Burners
Burner Type
Automatic Combustion Control
Combustion Engineering
1200 psig
950°F
137,500 Ib/hr
10,980 Ib/hr
2 psig
Natural Circulation
Yes
Refractory
Vertical
4
C.E./Wallsend
Steam Assist Burner
Yes
A-54
-------
TABLE A-17. DDG-15, PETROLEUM-DERIVED/SHALE-DERIVED DFM EMISSIONS COMPARISON
cn
tn
Kal«j I UH1 ' l>m SHAM! IIFM
Sulfur
II Ion Me,
Tlioor 1 I Icnl
Siilfni ',_ ffm
KI'A-lliilts,
Ihs I'or
III'1 P.11I
Oxlih-s of
HI ir.T.i'".
r.l'A-lliilts.
Ilia IV r
10 ' inn
Carbon
llydror-nrhitna ,
IHi.xlilG.X
Siw.kn, Klnp.iH-
M.IIIII Number
Km OSM Air
ID 10 9
58 58 57
0.027 0.027 0.026
25 25 28
0.051 0.0ril 0.057
200 200 200
55-
8.0 8.0
Clear Clo.ir Clc.ir
9.8 10.0 10.1
HO 81 m
31ft 118 141
6 6 6 66
6.5 6 6.5 6.5 -
0.018 0.019 0.018 0.019 -
27 27 25 10 36
0.060 0.061 0.060 0.06? -
00000
55622
Clenr Clcnr Clenr Clenr Clr;
_L> .- .1 __1JL_L_ .11- ?__ J.2.- .P__r ..
9/ 102 97 100
If.H 178 UH 171
5J 52 52 50
0.028 0.029 0.029 0.028
40 40 10 43
O.OU'I 0.092 0.092 0,10
7500 15(10 1500 10
35 35 30
ft. 4 -
r Snick
_1 K 7 1 2_10 12.0 42.7
911 101 101 110
1/0 179 179 392
6666
0.015 0.016 0.016 0.016
35 36 42 42
11.0110 0.090 0.090 0.09C
0 0 100 100
1 1 I 1
5.0 5.0 5.8 5.8
Clenr Clear Clenr Clear
mo no no 110
171 192 192 19?
10 11 10 10
51 61 59 57
0.027 0.032 0.028 0.0
23 28 28
0.047 0.056 0.0
100 ncg ncK nei;
*5 5 5 ' 10
9.0 9.6 9.6 7.'i
Trace Trace
Clenr Stack Stack Cle
9_. 2 10. 1 9J _1_0_.
71 H3 77 83
119 142 J10 341
SIIAI.K
J 5 55
- 7 - 7
29 - 0.014 - 0.015
38 37 32 33
i6 - 0.076 - 0.071
neg nog neg neg
1 121
4.0 4.0 4.0 4.0
ir Clear Clear Clenr
1 :_ 10 J_^_iP_..6
^ 83 - 88
142 - J51
(Continued)
-------
TABLE A-17. (Continued)
en
-------
TABLE A-17. (Continued)
I
cn
—i
Kale. Z
Kul fur
Dloxl tie
jipar wnouri.'*)
lln-iirfl li:nl
Sn 1 f ur j I'J"*
KI'A-UnUn,,
Ilis IV r 10 '
irm
OxI.K-s of
N 1 1 i nr.cn ,
IH'W, BM>,-isurCMl
KJ'A-llnlls,
11,9 IV i 10
imi
C.i r l,c. II
Mom, .Me,
[>!•»
Ityilrorflflioiia ,
|>|,l>, .IB
nvllumn
C.-ii him
Dioxide, Z
r.nnkr. Rhi|(,-|-
HIJIIII NiialuT
.. .
Ilicyi;'1"! I
IIKH
5228
55 57 55 51
0.0)5 0.006 0.006 U.025
50 18 52 55
0.110 O.OHO 0.110 o.no
200 - 310 TiO
5 10 , 20 10
i
I.I 8.B | , 0.4 9,1
Trace ClPnr Clpnr (Me/ir
<1 <1 '1
10.9 10. 2 10.9 12.0
SIIAI.K
f. 5.5 5.5
6 6
0.020 (1.020
15 1U 35
0.1199 • 0.091
000
1 1 0
, V
5.0 4.8 4.9
Clenr L'lonr (llenr
<1
-------
TABLE A-17. (Continued)
O|N»rnt InR
H.itf, Z
Kxn-nn Air
lift:
llm Fuel
Ul 1 I'rensiire
Z of Kull
1'iiWRr
Tine/
li.ile
1 of
Itiirner*
ruMHttlt
m :
IIFN
91 81
•J'ifl l/i 1
7071 7073
70 70
0950 Kimi
6/J3/00 ^
4 'i
Trace
SI nrk
*"
92 100
15H 3/1
7073 7071
70 70
1015 1100
4 4
SIIAI.K i
112 112
414 414
7451 7453 7451
68 68 6H
1045 1055 1105
9/IO/HO
444
KXI
om
KM 98 107
174 370 387
10810 10810 10830
1OO 100 100
1110 1330 1400
6/25/80
4 44
106
SIIAI.K
112 132
434 434
11790 11790
106 106
1435 1445
9/3/80
4 4
1.1 nht
Trace
Stuck
i
cn
CO
NOTK: - • InetniMpnt not In o|>nr*it1iHi
n.c.* not rtfleuIntPd
-------
8. ENVIRONMENTAL MONITORING
S02> CO, C0£, NOX, HC, Q^* ancl smoke emission levels were monitored by
the NAVSSES Mobile Source Emissions Unit (see Figure A-9 for schematic)
which was positioned adjacent to the DDG-15 boiler.
9. PROJECT STATUS
Testing performed intermittently between June and September 1980.
10. RESULTS
Pollutant emission results summarized in Table A-17. No significant
differences observed between emission resulting from use of petroleum-
derived DFM or shale-derived DFM for any boiler load condition. However:
• Shale-derived DFM, sulfur oxides emissions were generally lower than
those of petroleum-derived DFM at the same operating rates due to
lower initial sulfur content of shale fuel versus petroleum (0.02 per-
cent vs. 0.16 percent). In addition, shale DFM excess air values
tended to be higher-than those of petroleum DFM, consequently diluting
stack sulfur dioxide emissions further.
• Petroleum-derived DFM oxides of nitrogen emissions were slightly higher
than those of shale-derived DFM, at the same rate of combustion.
t Hydrocarbon emissions were generally low. Carbon dioxide emissions
from petroleum-derived DFM tended to be unusually higher than those
of shale-derived DFM at 12, 50, and 70 percent of full power, due in
part to incomplete setting of boiler operating condition and the ad-
justment of excess air settings after the onset of data taking. Carbon
monoxide emissions from the petroleum fuel were also higher than those
from shale fuel which were in most cases negligible.
Pollutant levels all found to be below EPA stationary source standard.
11. REFERENCES
"Shale Oil Fuel Measurement, DDG-15 Boiler Interim Report", 18 February
1981, supplied by C. H. Hershner, David W. Taylor Naval Ship R&D Center,
Annapolis Laboratory (Code 2705), Annapolis, MD. 7 pp.
Telephone communication of C. H. Hershner, David W. Taylor Naval Ship R&D
Center, Annapolis, MD, to S. Quinlivan, 17 March 1981.
A-59
-------
ECONOMIZER
i
CT>
O
TRAKSUISSOKETER
(OPACITT SMOKE METER)
HEAT EXCHANGER
CHEMICAL
ZERO CAS
CAS ANALYZERS
PRE FILTER
(CLASS WOOL)
CVA-60
STEAM GENERATOR
(HAYSSES) TRAILER
Figure A-9. Source Emissions Instrumentation Schematic Diagram
-------
TEST 15
U.S. NAVY FF-1040 CLASS BOILER
PRESSURE-FIRED EXHAUST EMISSIONS MEASUREMENTS
1. FUELS TESTED
Synfuel: shale-derived diesel fuel marine (DFM), MIL-F-16884G.
Reference fuel: petroleum-derived fuel marine (DFM), MIL-F-16884G.
2. TEST EQUIPMENT
U.S. Navy FF-1040 Class pressure-fired steam generator (see Table A-18
for description).
3. TEST SITE
Naval Ship Systems Engineering Station, Philadelphia, Pennsylvania.
4. TEST OBJECTIVE
• To perform comparative emissions measurements between petroleum-
derived and shale-derived DFM for comparison with EPA stationary
source steam generator standards.
5. SPONSORING AGENCY
David W. Taylor Naval Ship R&D Center
Annapolis Laboratory, Code 2705
Annapolis, MD 21402
6. CONTRACTOR
NAVSSES, Philadelphia, Pennsylvania.
7. TEST CONDITIONS
Boiler conditions are presented in Table A-19. It was originally in-
tended to conduct the emissions testing over the full operating range of
the FF-1040; due to mechanical problems, data acquisition was limited to
the operating condition 20 to 60 percent of full power.
A-61
-------
TABLE A-18. GENERAL BOILER DATA
Class
FF-1040
en
ro
Boiler Manufacturer
Operating Pressure
Superheated Steam Temp.
Steam Generated @ Full Power
Oil Burner @ Full Power
Combustion Gas Pressure
Boiler Type
Water Cooled Furnace
Furnace Frontwall and
Floor Materials
Superheater Type
Number of Oil Burners
Burner Type
Automatic Combustion
Control
Foster-Wheeler
1200 pslg
950°F
126,000 Ib/hr
9,740 Ib/t.r
up to 60 pslg
Pressure Fired
Yes
Can type - refractory
No Frontwall
Horizontal - Ring Tube Type
3
TODD triplex mechanical
pressure atomizer
Yes
-------
TABLE A-19. FF-1040, PETROLEUM-DERIVED/SHALE-DERIVED DFM EMISSIONS COMPARISON
cr>
u>
Rate. Z
Sulfur
DIo«Ue,
PP«. ncasured
Tlienrctlcol
Sulfur, rP»
EPA- Units.
Ibn p«r 10
BTV
Oxides of
Nitrogen, rpm
ETA-Ilnit..,
Ibs per 10
BTU
Carbon
Monoxide, pjin
Hydrocarbon*,
ppuit an
>e thane
Carl'on
Dioxide, Z
Smoke, Rlnnel
•ann Number
Oxygen ,Z
Excess Air
19.5 20
2 0
57
21 62
0.090
200 10
5 1
5.4 7.2
Trace
White Clear
13.3 10.1
83
^
19 19 20 20
0010
8787
0.027
66 65 64 61
1 t
0.120 0.133 0.125 0.125
0000
8 7 - 10
10.0 B.8
Clear Clear Clear Clear
8.9 9.8 9.2 9.7
68 81 71 79
25
0
61
60
0.110
10
0
9.0
Clear
9.0
70
26
0
7
67
0.130
200
125
8.8
Clear
9.0
70
33
2.5
64
0.068
6)
0.110
0
0
8.7
Clenr
8.7
63
33
0.5
6
0.015
72
0.156
0
45
14.0
Clear
10.9
92
'.5
2
61
O.OS'i
65
0.125
0
0
10.0
Clear
9.2
71
48
2
7
0.05ft
77
0.160
100
285
8.6
Clenr
10.3
85
56 56
3 4
64 64
1
0.076 0.102
92 92
0.170 0.170
0 0
0 0
10.5
Clt'.ir Clear
8.7 8.7
63 63
58
2
8
0.052
120
0.227
50
200
9.2
Clear
8.9
68
(Continued)
-------
TABLE A-19. (Continued)
en
Ope rut Ing
Rntc. Z
UKC
F.K-1 Oil
Rate. Hr
1-St.iR*
Burner
firman
I of full
Power
Tl«c/
Date
19. S 20 19 19 20 20 25 26 33 33 45 48 56
341
1906 19C4
550/55 550/50
19.5 20
1455 1440
9/17/80 9/17/B(
114 318 319 334
IBftO 1880 2000 2000
550/40 550/40 550/50 550/5(
19 19 20 20
1245 1145 1200 1215
) 9/23/BO 9/23/80 9/23/80 9/23/1
318
2448
) 545/9f
25
1400
W 9/17/(
318
252;
54B/TO
26
1245
10 9/18/8
104
1232
'> 552/1
11
1126
0 9/17/
159
1136
»5 54': /H
11
1200
BO 9/IB/fl
119
4391
5 575/K
45
1250
0 9/l//f
346
4681
5 562/440
48
1130
10 9/1K/JO
104
5315
Sf.0/545
135
.SIIALK
56 58
104
5515
560/545
135
56 • 56
1135 : 1200
9/17/80 9/17/80
314
5617
555/545
115
18
1045
9/18/80
Tf»c«
Uliltr
Saokr
Frui
Stuck
{-) " Instrument Inopcriitlvc
-------
8. ENVIRONMENTAL MONITORING (See Figure A-10)
S02, NOX, CO, HC, and smoke.
9. PROJECT STATUS
Data acquired on three operating days (17, 18, and 23 September 1980).
10. RESULTS
Pollutant emissions summarized in Table A-19. No significant differences
observed between emissions resulting from use of petroleum-derived or
shale-derived DFM for any boiler load condition. It is noteworthy that:
• Petroleum-derived DFM sulfur emissions slightly exceeded shale fuel
emissions under the same operating conditions.
• Shale fuel nitrogen oxide emissions slightly exceeded petroleum-
derived emissions under the same operating conditions.
Pollutant levels (i.e., Sulfur oxides, nitrogen oxides, and smoke) all
found to be below EPA stationary source standards.
!
11. REFERENCES
"Shale Fuel Oil Emissions Measurement, FF-1040 Boiler, Interim Report",
18 February 1981, Memorandum Series 3037, supplied by C. H. Hershner,
David W. Taylor Naval Ship R&D Center, Annapolis Laboratory (Code 2705),
Annapolis, MD. 6 pp.
Telephone communication of C. H. Hershner, U.S. Department of Navy, David
W. Taylor Naval Ship R&D Center, Annapolis, MD, to S. Quinlivan, 17 March
1981.
A-65
-------
ECONOMIZER
CT>
CT>
TRAKSWISSOMETER
(OPACITY SMOXEMETER1
LIGHT SOURCE
Mt
I •«-HEAT EXCHANGER
CHEMICAL DRIER
ZERO CAS
GAS ANALYZERS
IACK FLUSH AIR
CO CO, CO, .0, 0,
xoit ion rut CHU Utci
PRE FILTER
(GLASS WOOD
PART ICIII AT ES
FILTER
8ACX FLOSH
AIR
HEATED flO
HYDROCARBON ANALYZER
CVA-60
STEAM GENERATOR
(X/tVSSES) TRAILER
Figure A-10. Source Emissions Instrumentation Schematic Diagram
-------
TEST 16
EVALUATION OF SHALE-DERIVED JP-5 TYPE FUEL
IN AN ALLISON T63-A-5A ENGINE
1. FUELS TESTED
Synfuel: JP-5 fuel derived from shale oil (see Table A-20).
Reference fuel: JP-5 petroleum-derived fuel (see Table A-21).
2. TEST EQUIPMENT
Allison T63-A-5A turboshaft engine used in Army OH-58A and Navy TH-57A
helicopters. Consists of a combination six-stage axial flow, one-stage
centrifugal flow compressor directly coupled to a two-stage free turbine
which is coupled to a gas producer turbine.
3. TEST SITE
Naval Air Propulsion Test Center, Trenton, New Jersey.
4. TEST OBJECTIVE
• To evaluate the performance and emissions of JP-5 type fuel derived
from shale oil compared to petroleum-derived JP-5 in the sea level
operation of a T63-A-5A helicopter engine.
5. SPONSORING AGENCY
U.S. Navy
Naval Air Systems Command
Washington, D.C.
6. CONTRACTOR
Naval Air Propulsion Test Center
Fuels and Fluid Systems Division
Trenton, N.J.
Project Officer: J. Solash
Telephone No: 609-896-5841
7. TEST CONDITIONS
Emissions test cycle parameters are presented in Table A-22. This sequence
A-67
-------
TABLE A-20. LABORATORY ANALYSIS OF SHALE OIL DERIVED JP-5
:
Gravity, Specific 15.5/15. S'C
(60/60'F)
Gravity. "API. 15.5/15. S'C
(60/60'F)
DlatllUtlon. IBP, *C CF)
5Z Over *C CF)
10Z Over 'C CF)
20Z Over 'C CF)
30Z Over 'C CF)
40Z Over 'C CF)
50Z Over 'C CF)
60Z Over *C CF)
70Z Over *C CF)
801 Over 'C CF)
90Z Over 'C CF)
95Z Over 'C CF)
End Point, *F
Recovery Z Vol.
Reeldue Z Vol.
Loee, Z Vol.
CUB, Exl*tent. «J/100 «1
Sulfur, Z Wt.
F.I. A Saturates, Z Vol.
Olafins. Z Vol.
Aruiutlcs, Z Vol.
Aniline Point, *C
Aniline Crevlty, Conetant
Hut of Coabuetlon. MJ K*"1
(STU/lb)
Corroelon, Copper Strip
Saoke Point, en
Freeie Point, *C CF)
Flaeh Point, *C CF)
Vlecoeltv, «2a"1 X 10~* (eke).
.-34. S'C (-30'F)
Contaalnatlon, agl~
Thertul Stability t 260. 0'C
(SOO'F) (JFTOT)
Water Separonecer Teat, Modified
Oil Shale
0.8058
44.1
171.1 (340)
185.5 (366)
191.0 (376)
199.0 (390)
205.5 (402)
212.0 (414)
219.0 (426)
225.5 (438)
2)3.5 (452)
242.0 (468)
254.5 (490)
265.5 (510)
282.0 (540)
97.8
1.0
1.2
81.7
0.05
71.76
2.29
25.95
61.8
6,315
43.105
(18,532)
1-a
22
-22.5 (-28)
65.5 (150)
Froien
164.20
Fall
76
MIL-T-5624J
Requirement*
Average
JP-5 (a) Nintanni Naxlvuai
0.8170 0.788 0.845
41.7 M.O *8.0
_ -
_ -
197.0 (387) - 204.5 (400)
-
-
-
216.5 (422)
-
-
.
243.0 (469)
-
263.5 (506) - 288.0 (550)
_
1.5
1.5
1.3 - -7
0.096 - 0.4
-
0.8 - 5.0
16.0 - 25.0
62.5
6.059 4.500
43.091 42.565
(18,526) (18.300)
1-b
22.2 19
-49.0 (-56) - -46.0 (-51)
60.0 (140)
10.5 - 16.5
. - 1.0
Paaa - Paea
94 85
(n) Mlnerel Indue try Survey•, Avlntlon Turbine Fueli, 1973 Reference.
A-68
-------
TABLE A-21. LABORATORY ANALYSIS OF PETROLEUM-DERIVED JP-5
FOR T63-A-5A ENGINE TEST
Gravity, Specific 15.5/13.5'C
(60/60'F)
Gravity. 'API. 15.5/15.5*C
(60/60'F)
Distillation. IBP. *C CD
5Z Ov«r 'C CF)
10X Over 'C CD
201 Over *C (*P)
301 Over 'C CF)
401 Over *C CF)
501 Over 'C CF)
601 Over 'C CF)
701 Over 'C CF)
801 Over 'C CF)
901 Over "C CF)
951 Over *C CF)
End Point, *F
Recovery Z Vol.
Residue Z Vol.
Lots. Z Vol.
CUB, Existent, mg/100 ml
Sulfur, Z Ut.
F.I.A Saturates, Z Vol.
Oleflns. Z Vol.
Aromatics, Z Vol.
Aniline Pol.it, *C
Aniline Gravity, Constant
Heat of Conbuatton, HJ Kg"1
(BTTJ/lb)
Corroalon, Copper Strip
Saoke Point, "m
Freete Point. *C CF)
Flaah Point, *C CF)
Vlacoslty, B2a'1 X 10"6 (cU).
38.0'C (100'F)
Viscosity, mV1 X 10"6 (cks).
-34.5*C (-30°F)
Contaaloat loo, mgf1
The raj 1 Stability 9 260. O'C
(500'F) OFTOT)
Water Scparoneter Test, Modified
Average
JP-5 Used JP-5 (it)
0.811* 0.1170
42.9 41.7
176. S (350)
188.0 (370)
192.0 (378) 197.0 (387)
198.0 (388)
202.0 (396)
208.0 (406)
213.5 (416) 216.5 (422)
216.5 (422)
223.5 (434)
229.0 (444)
238.0 (460) 243.0 (469)
245.5 (474)
258.0 (496) 263.5 (50t)
98.5
1.0
0.5
0 l.J
0.06 0.096
80.86
0.95 0.8
18.10 16.0
61.7 62.5
6,139 6.059
43.170 43.091
(18,560) (18,526)
1-a ,
28 22.2
-50.0 (-58) -49.0 (-56)
63.5 (146)
1.55
9.40 10.5
1.80
Pass Pass
98 94
M1L-T-5624J
Requirements
Minimi* Haxlmua
0.788 0.845
36.0 48.0
-
-
204.5 (400)
-
-
-
-
-
-
-
-
-
288.0 (550)
-
1.5
1.5
- . 7
0.4
-
5.0
25.0
-
4,500
42.565
(18,300)
1-b
19
-46.0 (-51)
60.0 (140)
16.5
1.0
Pass
85
(A) Min«r«l Industry Surveys, Aviation Turbin* Fuel*, 1973 Reference.
A-69
-------
TABLE A-22. EMISSIONS TEST CYCLE
Engine Power Rating
Cold Start
Maximum Power (nil)
Normal Rated Power (NR)
902 NR
60% m
402 NR
Flight Idle
Ground Idle
Tine (Minutes^
10
10
10
10
10
10
10
TOTAL TIME
70
was repeated to provide duplicate data. Throughout the test program, the
power turbine was kept at 538 RPS (35,000 RPM) except at ground idle.
8. ENVIRONMENTAL MONITORING
CO, C02, NO, N02, and total hydrocarbons (THC).
9. PROJECT STATUS
The study was completed in May 1976. It was recommended that other labo-
ratory tests should be initiated to measure other performance factors of
the shale derived JP-5 (e.g., material compatibility, cleanliness, addi-
tive requirements, flammability, etc.).
10. RESULTS
f The performance of the JP-5 type fuel derived from oil shale was
equivalent to that of petroleum-derived JP-5. Although the shale oil
A-70
-------
JP-5 was highly contaminated with solid particles, no effect on engine
performance was observed. Most of the solid matter was collected by
two in-line filters and a filter upstream of the engine fuel pump.
• The CO and THC emissions were equivalent for both fuels. NOX emission
levels were higher for the oil shale derived JP-5, due to the higher
levels of organic nitrogen compounds present in the oil shale derived
JP-5 (see Figure A-11).
• The shale oil JP-5 was not recommended for use in flight operations,
due to failure to meet standard specifications.
12. REFERENCES
Solash, J., C.J. Nowack, and R.J. Delfosse. "Evaluation of a JP-5 Type
Fuel Derived from Oil Shale", Navy Air Propulsion Test Center, Trenton,
NJ. NAPTC-PE-82, May 1976, 44 pp.
Telephone communication of C.J. Nowack, Navy Air Propulsiton Center,
with S. Quinlivan, TRW, 3 March 1981.
A-71
-------
70
60
50
AO
§
o
55
O
o
X
o
30
20
10
0.010
O JP-5
D SHALE OIL JP-5
I
0.015
FUEL/AIR RATIO
0.020
Figure A-ll. Exhaust Emissions of Oxides of Nitrogen (NO ) for T63-A-5A ENGINE.
A-72
-------
TEST 17
DEVELOPMENT OF ALTERNATE SOURCES OF JP-5 FUEL, ENDURANCE AND
EMISSION TESTS OF A T63-A-5A ENGINE USING A TAR SANDS DERIVED JP-5
1. FUELS TESTED (see Table A-23)
Synfuel: unifined kerosene-derived from Athabascan Tar Sands.
Reference fuel: petroleum-derived JP-5 fuel.
2. TEST EQUIPMENT
An Allison T63-A-5A turboshaft engine. Free turbine type used in the
Army OH-58A and Navy TH-57A helicopters.
3. TEST SITE
Naval Air Propulsion Test Center,
Trenton, New Jersey
4. TEST OBJECTIVES
• Investigation of the suitability of JP-5 fuel derived from alternate
sources for Navy use.
5. SPONSORING AGENCY
Department of the Navy
Naval Air Propulsion Test Center
Trenton, New Jersey
Prepared by: C. J. Nowack
Telephone No: 609 -896-5841
6. CONTRACTOR
-Department of the Navy
Naval Air Propulsion Test Center
Trenton, New Jersey
Author: C. J. Nowack
Telephone No: 609-896-5841
7. TEST CONDITIONS
The T63-A-5A engine was installed in a sea level test cell using a three-
point mounting system. Engine inlet air and fuel temperatures during the
A-73
-------
TABLE A-23. PROPERTIES OF UNIFINED KEROSENE, AVERAGE JP-5 AND NAPTC JP-5
(T63 ENGINE CALIBRATION FUEL)
Gravity, Specific, 60/60 °F
Gravity, °API, 60/60 °F
Reid Vapor Pressure, Ib/in^
Distillation, I.E. P. °F
5% over °F
10% over °F
20% over °F
30% over °F
40% over °F
50% over °F
60% over °F
70% over °F
80% over °F
90% over °F
95% over °F
End poing °F
Recovery % vol .
Residue % vol .
Loss % vol.
Gum, Existent, mg/100 ml
Sulfur, % wt.
F.I, A. Saturates, % vol.
Olefins, % vol.
Aromatics, % vol .
Aniline Point, °C
Aniline - Gravity Constant
Heat of Combustion, Btu/lb
Corrosion, Copper Strip
Smoke Point, mm
Freeze Point, °F
Flash Point, °F
Water Tolerance
Viscosity, cks. , 100°F
0°F
-30°F
Contamination, mg/ liter
Thermal Stability (JFTOT)
Total Acid Number
Doctor Test
Water Separometer Test, Modified
Uni fined
Kerosene
0.8328
38.4
0.00
366
380
388
398
408
418
428
436
448
462
480
500
546
98.1
1.4
0.5
1.2
0.01
77.06
3.67
19.27
59.8
5,361
18,436
la
20.0
-64
154
#1 (1.0)
1.74
6.38
12.85
0.11
Pass
0.007
Sweet
95
NAPTC JP-5
0.8142
42,3
--
356
374
380
386
394
400
410
418
430
442
460
480
508
99.0
1.0
0.0
--
0.05
75.98
3.65
20.37
61.5
6,036
18,551
la
21
-58
154
--
--
--
9.34
0.33
Pass
—
—
--
MIL-T-5624J
Requirements
Min Max
0.788 0.845
36.0 48.0
"~ "" — ~
"* ~ "• •"
— — — —
400
-— __
— . _
--
— —
—
--
--
--
--
550
—
1.5
1.5
7
0.4
-_
5.0
25.0
__
4,500
18,300
Ib
19
-51
140
__
—
__
16.5
1.0
Pass
0.15
Sweet
85
A-74
-------
between 70 and 90°F. The studies were conducted according to
the following test sequences:
Fuel Test Sequence Time/Hours
JP-5 Pre-test Engine Calibration 3
Unifined Kerosene Engine Performance/Endurance Studies 54
JP-5 Post-test Engine Calibration/Exhaust 1
Emissions
Unifined Kerosene Post-test Engine Exhaust Emissions 1
Throughout the test program, the power turbine was kept at a constant
speed of 35,000 RPM except at ground idle. The engine power ratings
designated for the emission survey were selected as being representative
of a typical Army helicopter duty cycle. (Performance ratings are de-
tailed in the reference report.)
8. ENVIRONMENTAL MONITORING
Carbon monoxide, nitrogen oxide and unburned hydrocarbon emissions.
9. PROJECT STATUS
The Naval Air Propulsion Test Center investigation of the suitability for
Navy use of JP-5 derived from alternate sources was originally authorized
on June 1974 under NAVAIR AIRTASK No. A330-33-C/052B/5F571-571-301. It
was recommended that various laboratory tests be continued on a low
priority basis and that further engine testing be delayed.
10. RESULTS
• Unifined Kerosene as derived from Athabascan Tar Sands by GCOS is a
satisfactory substitute for petroleum derived JP-5 in the sea level
operation of the T63-A-5A engine under the environmental conditions
tested. There was no visual degradation of fuel system materials or
hot end components after 55 hours of engine performance.
• The carbon monoxide (CO) and total unburned hydrocarbon (THC) emis-
sions were higher at low engine fuel-air ratios (lower power) for JP-5
than were obtained with Unifined Kerosene (see Figures A-12 and A-13).
• The nitrogen oxide (NO,,,) emission was slightly higher at all fuel-air
ratios when using Unifined Kerosene than with JP-5 (see Figure A-14).
A-75
-------
1000 .
CO
(ppm)
800 -
600 -
400 •
200 •
I
.01
.015
Fuel/Air Ratio
i
.02
D - Unif ined Kerosene
O - JP-5
Figure A-12, Carbon Monoxide Emissions, ppm
T63-A-5A Engine (S/N 401331)
A-76
-------
500 -,
400 -
300 -
THC
(ppm)
200
100 -
i
.015
Fuel/Air Ratio
—!
.01
D - Unifined Kerosene
O - JP-5
Figure A-13. Total Unburned Hydrocarbon Emissions
T63-A-5A Engine (S/N 401331)
—r-
.02
A-77
-------
60
50-
40-
(ppm) 30 |
20-
10-
0«7
i
.01
.015
.02
Fuel/Aiif Ratio
D - Unifined Kerosene
O - JP-5
Figure A-14. Nitrogen Oxide Emissions
T63-A-5A Engine (S/N 401331)
A-78
-------
11. REFERENCE
Memo No. PE71:CJN:er, 10340, Ser F1002, "NAVAIR Work Unit Plan No. NAPTC-
812, Development of Alternate Sources of JP-5 Fuel, Report on Endurance
and Emission Tests of a T63-A-5A Engine Using a Tar Sands Derived JP-5",
26 June 1975, 18 pp.
A-79
-------
TEST 18
U.S. ARMY'S ENERGY AND SYNTHETIC FUELS PROGRAMS
1. FUELS TESTED
Previously tested fuels are shown in Table A-24. Future testing is
scheduled to focus on fuels from oil shale, direct coal liquefaction,
and biomass.
2. TEST EQUIPMENT
A wide variety of powerplant systems must be satisfied if synfuels are
to be adopted. These range from 2-cycle spark-ignition engines to large
2-cycle and 4-cycle compression ignition engines found in self-propelled
guns and tactical support equipment.
3. TEST OBJECTIVES
The Army Energy Plan establishes the basis for reducing energy consump-
tion, reducing dependency on conventional hydrocarbon fuels, and tasks
the Army to obtain a position of energy leadership. One of the major
programs of the plan is the alternative fuels program, which is directed
towards minimizing potential loss of military effectiveness from a dis-
ruption of energy supplied under foreigh control.
4. SPONSORING AGENCY
U.S. Army
5. CONTRACTOR \
This information for many individual
tests are described in separate
abstracts.
6. TEST SITE
7- TEST CONDITIONS
8. ENVIRONMENTAL MONITORING
9. PROJECT STATUS /
The Army has evaluated the suitability of several synfuels for use in
Army equipment (Table A-24).
A-80
-------
The current thrusts within the U.S. Army's Alternative and Synthetic
Fuels Program encompasses the following efforts: Develop Capability
for Using Synthetic and Alternative Fuels; Develop New, Accelerated
Fuel-Engine Qualification Procedure Methodology; and Conduct Gasohol
Evaluation in Tactical Equipment.
TABLE A-24. PREVIOUSLY EVALUATED SYNTHETIC FUELS
Syncrude
Source:
Coal
Tar Sands
Shale
Shale
Process :
C.O.E.D.(Pyrolysis)
Steam Extraction
(Gulf Canada)
Paraho (Above-
Ground Retort)
Paraho (Above-
Ground Retort)
Fuels:
Gasoline
Distillate
Aviation
Turbine
(JP-5)
Gasoline
Diesel
Aviation
Turbine
(JP-5/JET-A)
Aviation
Turbine
(JP-5 & JP-8)
Diesel
When
Tested:
1973-74
1975
1976-77
1979-80
Product
Quality:
Marginal
Marginal
Excellent
Marginal
Poor
Marginal
Satisfac-
tory
10. RESULTS
The product quality of fuels tested so far are shown in Table A-24. Test
results from individual tests are described in separate abstracts.
11. MISCELLANEOUS
The file described in this abstract contains four documents: (1) Army
Energy R&D Plan 1981, (2) a magazine article describing the Army's syn-
fuel program, (3) a photocopies set of overhead-projector transparencies
describing the Army Mobility Fuels Program, and (4) a progress report on
fuels and lubricants research during 1980.
A-81
-------
12. REFERENCES
Le Pera, Maurice E. The U.S. Army's Alternative and Synthetic Fuels
Program. Army Research, Development, and Acquisition Magazine. Septem-
ber-October 1980. pp. 18-20.
Department of the Army. Progress of Fuels and Lubricants Research During
FY 80. U.S. Army Mobility Equipment Research and Development Command
(MERADCOM), Fort Belvoir, Virginia. January 1981. 22 pp.
Department of the Army. Army Energy R&D Plan - 1981. U.S. Army Mobility
Equipment Research and Development Command, Fort Belvoir, Virginia.
March 12, 1981.
A-82
-------
TEST 19
EVALUATION OF MILITARY FUELS REFINED FROM PARAHO-II SHALE OIL
1. FUELS TESTED
Synfuels: shale-derived JP-5, JP-8, and marine diesel fuel (DFM) (see
Table A-25.
Reference fuels: JP-5, diesel fuel No. 2, and Jet A fuel derived from
petroleum.
2. TEST EQUIPMENT
In the gas turbine combustion performance test, the combustor used is
based on hardware from the Allison T-63 gas turbine engine used in several
Army helicopters.
In the diesel engine performance test, the four diesel engines used re-
present critical and widespread engines in the military tactical fleet:
the militarized version of the Detroit Diesel 6V-53T; the military-
developed LDT-465-1C; a single cylinder from the Teledyne-Continental
AVDS-1790 air-cooled diesel mounted on a CUE crankcase; and a commercially
configured Detroit Diesel 3-53 diesel engine (see Table A-26 for test
engine characteristics).
3. TEST SITE
U.S. Army Fuels and Lubricants Research Laboratory
Southwest Research Institute
San Antonio, Texas
4. TEST OBJECTIVES
• To evaluate JP-5, JP-8, and DFM produced from Paraho-II shale oil for
specification requirements and other properties, and to ascertain their
performance in Army engine systems as a part of the overall program to
develop a capability for consuming multisource fuels within the Depart-
ment of Defense.
A-83
-------
TABLE A-25. PROPERTIES OF FUELS DERIVED FROM SHALE OIL
Properties
Specific Gravity, 15.6/15.6"C
Gravity, 'API
Distillation, *C
IBP
10Z Recovered
20! Recovered
501 Recovered
90Z Recovered
End Point
Z Recovered
Z Residue
Z Loss
Flash Point, 'C
Viscosity at 37.B*C,cSc
Viscosity at -20*C,cSt
Aniline Point, 'C
Cloud Point, *C
Pour Point, *C
Freezing Point, *C
Existent Gum, mg/100«l
Total Acid Number, mg KOH/g
Neutrality
Aromatics, volZ (FIA)
Olefins, volZ (FIX)
Carbon, vtZ
Hydrogen, vtZ
Nitrogen, ppm
Oxygen, vtZ
'Sulfur, vtZ
Thermal Oxidation Stability (JFTOT)
at 260°C
tf, mm Hg
Tube rating, visual
TDR-spun
TDR-spot
Net Heat of Combustion, HJ/kg
Smoke Point , mm
Aniline-Gravity Product
Visual Appearance
Color, ASTM Rating
Accelerated Stability, mg/100 •!
Particulate Matter, ag/1
Ash, wtZ
Cetane Number
Carbon Residue on
10Z bottoms, wtZ
Demulsif ication, minutes
Ring Carbon
Mono-aromatlcs, wtZ
Di-aromatics, wtZ
Trl-aromatics, wtZ
GC Distillation, 'C
0.1 wtZ off
1 wtZ off
10 wtZ off
20 wtZ off
50 wtZ off
90 wtZ off
95 wtZ off
99 wtZ off
99.5 wtZ off
HPLC Aromatics, WtZ
HPLC Saturates, wtZ
JP-8
0.8044
44.4
178
187
189
201
227
257
98.5
1.0
0.5
57
1.30
4.19
62.4
-52
0.4
0.01
21
2
66.05
13.70
0.31
0.40
0.002
0
2
10.0
12.0
1A
42.82
20.2
6,407
Straw, clear
0.5
0.29
0.3
45
13.84
1.19
0.003
120.1
153.6
170.4
176.6
203.1
241.0
252.2
274.6
285.7
23.5
76.5
JP-8
0.775-0.840
37-51
205 max
300 max
1.5 max
1.5 max
38 Bin
8.0 mix
-50 max
7 max
0.015 max
25 max
5 max
13.5 mln
0,30 max
25 max
<3
IB max
42.8 mln
19 mln
1 max
186 max
— .-
330 max
JP-5
0.8081
43.6
179
189
192
202
228
248
98.5
1.5
0
62
1.38
4.68
60.4
-51
0
0
22
2
85.92
13.66
<1
0.38
0.005
0
1
2.0
8.0
2C
42.68
17.5
6,134
White, clear
<0.5
0.14
0.1
45
13.54
1.36
0.002
136.5
159.7
174.5
185.3
208.9
245.9
255.0
278.8
291.6
24.9
75.1
JP-5
Requirements
36-48
205 max
-——
290 max
1.5 max
1.5 nax
60 mln
8.5 max
-46 max
7 max
0.015 max
25 max
5 max
13.5 min
0.40 max
25 max
<3
~
42.6 min
19 mtn
4,500 mln
1 max
185 max
320 max
DFM
37.9
206
233
243
264
295
312
99
1
0
80
2.71
67.0
10
-18
0
0.001
Neutral
30
1
86.54
.3.36
<1
0.37
0.004
0
3
11.5
19
1A
42.50
16.5
White, clear
<0.5
0.20
0.5
0
49
0.04
5
11.58
4.03
0.045
103.4
152.3
214.0
236.2
271.8
316.5
323.3
336.1
342.1
27.8
72.2
DFH
Requirements
Record
— —
357 max
385 max
™
3 max
60 aln
1.8-4.5
Record
-1 max
-7 max
0.3 max
Neutral
— -
1.00 max
Clear, bright
3 max
2.5 max
8 max
0.005 max
45 mln
0.2 max
10 max
—
—
.»—
.
_
A-84
-------
TABLE A-26. TEST ENGINE CHARACTERISTICS
Manufacturer
Designation
Induction System
Combustion System
Strokes/Cycle
Number of Cylinders
Arrangement
Displacement
Bore and Stroke
Rated Power at Speed
kW(Hp) at rpra
Max Torque at Speed
Nm(lb-ft) at rpm
Compression Ratio
Fuel System
Detroit Diesel
6V-53T
turbocharged
direct
injection
2
6
60° V
5.21L
(318 in. )
9.84 x 11.43 cm
(3-7/8x4-l/2in.)
Detroit Diesel Teledyne Continental
3-53
normally
aspirated
direct
injection
2
3
in-line
2.61L
(159 in. )
LDT-465-1C
turbocharged
M.A.N.
4
6
in-line
7.83L
(478 in. )
9.84 x 11.43 cm 18.0 x 19.2
(3-7/8x4-l/2in.) (4.56x4.87 in.)
244(300) at 2800 67.1(90) at 2800 104(140) at 2600
834(615) at 2200 278(205) at 1800 556(410) at 1600
17 21 22
Teledyne Continental*
CUE-1790
simulated
turbocharge
direct injection
4
1
2.44L
(149.1 in. )
(5.75x5.75 in.)
N70 unit
injector
N50 unit
injector
Bosch PSB6A-90EH-
5337A3 with
ABD-355-124-7 nozzles
*Single cylinder from Teledyne-Continental AVDS-1790-2D engine adapted to a CUE crankcase by others.
-------
• Fuels were analyzed to determine their specification requirements,
storage stability, additive response, compatibility with petroleum-
based fuels, combustion performance, diesel engine performance, and
microbiological growth susceptibility.
5. SPONSORING AGENCIES
U.S. Army Mobility Equipment Research and Development Command
Ft. Belvoir, Virginia 22060
Contract Monitor: F.H. Schaekel
Telephone No: 703-664-6071
U.S. Department of Energy
Bartlesville Energy Technology Center
Bartlesville, Oklahoma 74003
Project Officer: Dr. D.W. Brinkman
Telephone No: 918-336-2400
6. CONTRACTOR
Southwest Research Institute
Energy Systems Research Division
San Antonio, Texas 78284
Principal Investigator: John N. Bowden
Telephone No: 512-684-5111
7. TEST CONDITIONS
Table A-27 presents the operating conditions which represent the air flow
rates in the actual engine for the six different power points (idle to
full power) investigated. Emission data were recorded at each power point
for each fuel.
Three diesel engines were used during maximum power output and specific
fuel consumption testing: the 6V-53T, the LDT-465-K, and the AVDS-1790.
The engines were mounted on dynamometer test stands and alternately
operated on the shale-derived JP-5 and DFM and the petroleum-derived re-
ference fuel - diesel fuel No. 2.
The 3-53 diesel engine was operated for 210 hours with shale-derived DFM
according to the Army/CRC wheeled-vehicle endurance cycle to evaluate the
wear and deposit formation tendencies of this fuel.
8. ENVIRONMENTAL MONITORING
CO, NO , unburned hydrocarbons, and smoke.
A
A-86
-------
TABLE A-27. T-63 COMBIJSTOR RIG OPERATING CONDITIONS
Mode
Ground Idle
—
Descent
Crui se
Cl imb/Hover
i>
5 Takeoff
Percent
Power
10
25
40
55
75
100
Burner
Inlet Air
Pressure,
kpa
230
283
329
369
418
477
Burner
Inlet Air
Temperature,
°K
422
452
478
294
518
547
Air Flow
Rate,
kg/s
0.64
0.75
0.86
0.93
1.02
1.10
Fuel Flow
Rate,
kg/m
0.42
0.54
0.68
0.93
1.01
1.30
Fuel /Air
Ratio
0.0109
0.0121
0.0131
0.0145
0.0166
0.0198
-------
9. PROJECT STATUS
Work was conducted from June 1979 through November 1980. Interim report
dated March 1981. Additional tests planned for FY 82 usino other types
of army equipment.
10. RESULTS
Specification Analysis
t The shale-derived fuels met virtually all the military specifications
with the exception of the failure of JP-5 to meet copper corrosion re-
quirement and DFM to meet maximum limit for pour point as seen in
Table A-25.
Storage Stability Tests
• Storage stability of the shale-derived fuels was equivalent to that of
petroleum products at 43°C for 32 weeks. Accelerated stability at 80°
and 150°C indicated instability at the lower temperature, but none at
150°C.
Compatibility, Additive Response, and Microbiological Growth Tests
• Compatibility tests with JP-5 and DFM petroleum- and shale-derived
fuels indicated that the fuels are compatible with each other. JP-5
and DFM synfuels responded to the addition of a centane improver
additive in a manner similar to that of a petroleum-based fuel. The
addition of a corrosion inhibitor incrementally improved the corrosion
tendencies of JP-5 and DFM but did not affect the JP-8. Microbiolo-
gical growth susceptibility tests showed that growth of C1 adosporiurn
resinae was supported by shale-derived JP-5 and OFM.
Gas Turbine Combustion Performance
t In general, the combustion properties of synthetic JP-5 and DFM are
not significantly different from the respective petroleum-derived
fuel (see Table A-28).
• Combustion inefficiency is determined by CO and UHC in the exhaust.
Figure A-15 shows that DFM gives slightly higher CO emissions than
JP-5 and Jet A. Contrary to its fuel properties, DFM gave somewhat
lower UHC emissions than the other fuels as seen in Figure A-16.
• NOX emissions shown in Figure A-17 were essentially the same for both
shale fuels and Jet A at all operating conditions.
t Exhaust smoke indices for the shale-derived fuels were higher than
the respective Jet A fuel.
A-88
-------
TABLE A-28. SUMMARY OF GAS TURBINE COMBUSTION RESULTS
Power
Point
100
100
100
75
75
75
55
55
55
40
40
40
25
25
25
10
10
10
Fuel
No.
0
1
2
0
1
2
0
1
2
0
1
2
0
1
2
0
1
2
Fuel Flame
Type Radia.
Jet A
JP-5
DFM
Jet A
JP-5
DFM
Jet A
JP-5
DFM
Jet A
JP-5
DFM
Jet A
JP-5
DFM
Jet A
JP-5
DFM
42.8
59.7
60.1
37.0
48.9
50.7
31.9
43.7
48.1
26.7
37.4
43.2
23.3
30.0
39.2
17.8
26.2
31.9
Smoke
No.
28.9
48.7
45.2
32.1
38.1
41.0
15.8
19.7
22.6
12.0
25.2
27.9
11.7
21.2
29.9
7.9
17.7
23.2
Smoke
mg/M
4.3
13.2
10.8
5.1
7.1
8.46
1.8
2.4
2.9
1.3
3.4
4.0
1.27
2.6
4.5
0.84
2.06
3.0
NO
X
E.I.
7.2
7.2
6.7
5.5
5.7
4.7
4.7
4.6
4.3
4.7
4.7
4.7
3.1
3.6
3.3
1.3
3.3
3.1
CO
E.I.
9.5
9.1
13.8
30.3
30.8
34.3
48.3
47.7
50.1
59.6
59.9
65.4
82.3
75.8
102.3
113.6
107.9
118.0
UBH
E.I.
0.2
0.4
0.4
2.0
1.9
2.9
7.1
7.3
7.0
11.7
13.3
12.5
35.9
30.7
33.7
71.5
82.9
69.0
Combustion
Efficiency
99.79
99.78
99.67
99.31
99.28
99.13
98.64
98.59
98.54
98.14
97.97
97.91
95.57
96.13
95.35
92.37
91.52
92.42
A-89
-------
120
100
o>
x"
iu
Q
Z
' Z
o
w
5
LU
8
80
60
40
20
1 JP-5 (SHALE)
2 DFM (SHALE)
0 JET A (PETROLEUM)
20 40 60 80
PERCENT OF FULL POWER
100
Figure A-15. Effect of Fuel on Carbon Monoxide Emissions
100
90
, 80
l
70
60
* 50
Q
Z
Z
o
30
20
10
0
1 JP-5 (SHALE)
2 DFM (SHALE)
0 JET A (PETROLEUM)
0,1.2
20 40 60 80
PERCENT OF FULL POWER
100
Figure A-16. Effect of Fuel on Unburned Hydrocarbon Emissions
A-90
-------
10
LLJ
D
u.
u.
O
0>
X~
Q
2
§
to
e/2
I
UJ
+2
JP-5 (SHALE)
DFM (SHALE)
0 JET A (PETROLEUM)
20 40 60 80
PERCEMT OF FULL POWER
100
Figure A-17. Effect of Fuel on NO Emissions
A
Diesel Engine Performance
• In the power output and specific fuel consumption tests of the three
diesel engines using shale-derived JP-5 and DFM and petroleum-derived
diesel fuel, the only observable difference between the fuels were
those attributed to differences in heat of combustion. The percent
change in observed horsepower and volumetric fuel consumption for the
three test engines are summarized in Tables A-29, A-30, and A-31.
0 Results of the 210-hour endurance test showed no power loss during the
test nor evidence of distress or component failure; and piston deposits
and component wear were acceptable. The results of the shale-derived
DFM in this test were indistinguishable from those obtained using a
petroleum-derived diesel fuel.
11. REFERENCE
Bowden, J.N., et al. Military Fuels Refined From Paraho-II Shale Oil.
Prepared by Southwest Research Institute for U.S. Army (MERADCOM), Interim
Report AFLRL No. 131. March 1981.
A-91
-------
TABLE A-29 PERCENT CHANGE IN OBSERVED HORSEPOWER AND VOLUMETRIC
FUEL CONSUMPTION IN DETROIT DIESEL 6V-53T
Engine Speed
1800
2000
2200
2400
2600
2800
Average
From DF-2
Power
-0.8
-1.4
-1.8
-1.8
-1.5
-2.4
-1.7 ± 0.5
to DFM
Fuel*
1.5
1.5
1.1
1.1
1.2
0.9
1.2 ± 1.0
From DF-2
Power
-3.4
-5.1
-5.3
-6.2
-7.3
-8.4
-6.0 ± 0.5
to JP-5
Fuel*
5.8
4.2
3.8
5.5
5.5
6.6
5.2 ± 1.0
Brake specific volumetric consumption (Gal/BHP-hr).
TABLE A-30. PERCENT CHANGE IN OBSERVED POWER AND VOLUMETRIC
FUEL CONSUMPTION IN CUE-1790
Engine Speed,
rpm
1800
2000
2200
2400
Average
Std Dev
From DF-2
Power
+2.7
+1.4
+3.7
+1.8
+2.4
1.0
to DFM
Fuel*
-1.1
-1.4
-3.0
-2.9
-2.1
1.0
From DF-2
Power
-2.9
-4.6
-1.1
-2.3
-2.7
1.5
to JP-5
Fuel*
7.0
0.3
1.8
3.8
3.2
2.9
Brake specific volumetric consumption (Gal/BHP-hr).
A-92
-------
TABLE A-31. PERCENT CHANGE IN OBSERVED POWER AND
FUEL CONSUMPTION IN LDT-465-1C
(From Diesel Fuel to DFM)
Engine Speed,
rpm
1600
2100
2600
Average
Change in
Max Power, %
-1.9
-0.6
+0.4
-0.7
Change
Full Power
+1.3
-0.1
+ 1.0
+1
in Fuel*, %
3/4 of Full Power
+0.8
+1.8
+2.7
.3
Brake specific volumetric consumption (Gal/BHP-hr).
A-93
-------
TEST 20
EVALUATION OF FUEL CHARACTER EFFECTS ON
FT01 ENGINE COMBUSTION SYSTEM
1. FUELS TESTED
Reference fuels: thirteen non-synfuels were tested; i.e., a typical
JP-4; five blends of JP-4 with a single ring aromatic concentrate; a
double ring aromatic concentrate, and a light oil; a typical JP-8; five
blends of JP-8 with the same three compounds used for the JP-4 blends;
and a Number 2 diesel fuel. The thirteen fuels incorporated systematic
variations in hydrogen content (12.0 to 14.0 weight percent), aromatic
type (monocyclic or bicyclic), initial boiling point (285 to 393 K by
gas chromatograph), final boiling point (532 to 679 K also by gas chroma-
tograph), and viscosity (0.83 to 3.25 cSt at 300 K).
2. TEST EQUIPMENT
General Electric F101 turbofan engine main combustion system elements.
A sector rig and a full-annular rig were used to generate the combustion
data. Separate rigs were used to obtain carboning and nozzle fouling
data on the fuels.
3. TEST SITE
General Electric test facility, Evendale, Ohio.
4. TEST OBJECTIVES
• To determine the effects of broad variations in fuel properties on
the performance, emissions, and durability of the F101 combustion
system.
• The rationale for selection of the test fuels was to span systematical
ly the possible future variations in key properties that might be
dictated by availability, cost, the use of nonpetroleum sources for
jet fuel production, and the possible change from JP-4 to JP-8 as the
prime USAF aviation turbine fuel.
A-94
-------
5. SPONSORING AGENCIES
Air Force Aero Propulsion Laboratory (SFF)
Air Force Wright Aeronautical Laboratories
Wright-Patterson AFB, Ohio 45433
Government Project Engineer: T.A. Jackson
Telephone Number: 513-255-2008
Additional funding and technical guidance was provided by the Environ-
mental Sciences Branch of the Environics Division in the Research and
Development Directorate of HQ Air Force Engineering and Services Center
located at Tyndall Air Force Base, Florida.
6. CONTRACTOR
General Electric Company
Aircraft Engine Group
Cincinnati, Ohio 45215
Project Officer: C.C. Gleason (and T.L. Oiler)
Telephone Number: 513-243-3207
7. TEST CONDITIONS
Test fuels were evaluated in: (a) 13 high pressure/temperature full-
annular combustor performance/emissions/durability tests; (b) 13 atmos-
pheric pressure/high temperature full-annular combustor pattern factor
performance tests; (c) 13 high pressure/temperature single fuel nozzle/
swirl cup carbon deposition tests; (d) 14 low pressure/temperature 54-
degree sector combustor cold day ground start/altitude relight tests;
(e) 15 high temperature short duration fuel nozzle fouling tests; and
(f) 0 high temperature longer cyclic fuel nozzle valve gumming tests.
8. ENVIRONMENTAL MONITORING
NO , CO, smoke, and unburned hydrocarbons.
A
9. PROJECT STATUS
Testing and analytic activity occurred from August 1977 through September
1978. Final report submitted June 1979.
10. RESULTS
• As expected, gaseous emissions and smoke levels were strongly depen-
dent upon operating conditions for all fuels tested.
A-95
-------
• Low power emissions of CO and UHC were only significant at idle, and
decreased sharply with increasing power level. Levels of CO were
readily correlated with power level; UHC exhibited more variability
while following a similar trend.
• Oxides of nitrogen were primarily a high power emission and, for fuels
with negligible amounts of fuel-bound nitrogen, correlated readily
with power level.
• At high power conditions, fuel hydrogen content was found to have a
very significant effect on annular liner temperature, smoke, and NOX
levels. While smoke levels decreased with increasing hydrogen content,
the levels were very low with all the fuels (i.e., smoke levels of 0.4
to 3.2, which are on the threshold of smoke measurement system accu-
racy).
t At low power operation, CO and UHC correlated with the 10 percent dis-
tillation recovery temperature and with relative spray droplet size
(a function of fuel viscosity, surface tension, and density).
• Cold day ground start and altitude relight correlated with fuel atomi-
zation/volatility parameters.
t Combustor liner life analyses yielded relative life predictions of
1.00, 0.72, 0.52, and 0.47 for" fuel hydrogen contents of 14.5, 14.0,
13.0, and 12.0 percent, respectively. At the present state of turbine
stator development, no fuel effect on life is predicted.
• Extended cyclic fuel nozzle valve gumming tests revealed significant
effects of fuel type and temperature on nozzle life. The results cor-
related with laboratory thermal stability ratings of the fuels based
on tube deposits alone.
11. REFERENCE
Gleason, C.C., T.L. Oiler, M.W. Shayeson, and D.W. Bahr. Evaluation of
Fuel Character Effects on the F101 Engine Combustion System. AFAPL-TR-
79-2018, CEEDO-TR-79-07, U.S. Air Force, Wright-Patterson AFB, Ohio,
June 1979. 199 pp.
A-96
-------
TEST 21
EVALUATION OF FUEL CHARACTER EFFECTS ON
J79 SMOKELESS COMBUSTOR
FUELS TESTED
Reference fuels: thirteen refined and blended non-synfuel fuels were
tested; i.e., a current JP-4, five blends of the JP-4, a current JP-8,
five blends of the JP-8, and a No. 2 diesel fuel. These fuels incorpo-
rated systematic variations in hydrogen content (11.9 to 14.5 weight
percent), aromatic type (monocyclic or dicyclic), initial boiling point
(298 to 409 K by gas chromatograph), final boiling point (554 to 646 K,
p
also by gas chromatograph), kinematic viscosity (0.90 to 3.27 mm /s as
294.3 K), and thermal stability breakpoint (518 to 598 K by JFTOT) for
evaluation.
2. TEST EQUIPMENT
The J79-17C turbojet engine main burner as represented by two single can
combustor rigs and a fuel nozzle rig.
3. TEST SITE
General Electric test facility, Evendale, Ohio.
4. TEST OBJECTIVES
• To determine the effects of broad variations in fuel properties on
the performance, emissions, and durability of the combustion system
identified above.
• Compare results to those previously obtained in similar tests of the
J79-17A and F101 combustion systems.
• Test fuels were selected to represent variations in properties that
can be expected to affect the combustion system; ranges of property
variations were set to represent broad limits that may be anticipated
in using fuels refined from an expanded portion of the petroleum re-
source and from non-oetroleum hydrocarbon sources.
• The combustion system was selected because it represented a redesign
of a system in wide usage by the USAF (as well as one which was tested
under a preceeding fuels program, the J79 standard configuration).
A-97
-------
This provided an opportunity to compare two different combustion
systems designed for the same engine.
5. SPONSORING AGENCY
Aero Propulsion Laboratory (AFWAL/POSF)
Air Force Wright Aeronautical Laboratories (AFSC)
Wright-Patterson AFB, Ohio 45433
Government Project Engineer: Jeffrey S. Stutrud
Telephone No: 513-255-2008
Partial funding and technical support in the area of the measurement and
analysis of gaseous emissions and smoke data were provided by the Envi-
ronmental Sciences Branch of the Environics Division in the Research and
Development Directorate of HQ Air Force Engineering and Services Center.
6. CONTRACTOR
General Electric Company
Aircraft Engine Business Group
Technology Programs and Performance Technology Dept.
Cincinnati, Ohio 45215
Principal Investigator: C.C. Gleason (and T.L. Oiler)
Telephone No: 513-243-3207
7. TEST CONDITIONS
The fuels were evaluated in: (a) 14 high pressure/temperature combustor
cold-day ground start/altitude relight tests; (b) 14 low pressure/temper-
ature combustor cold-day ground start/altitude relight tests; and (c) 7
high temperature cyclic fuel nozzle fueling tests.
8. ENVIRONMENTAL MONITORING
NO , CO, smoke, and unburned hydrocarbons.
A
9. PROJECT STATUS
The period of performance for this effort, including testing and analysis,
was July 1, 1979 through June 1, 1980. Final report is dated November
1980.
10. RESULTS
• As expected, gaseous emissions and smoke levels were strongly depen-
dent upon operating conditions for all fuels tested.
A-98
-------
• Low power emissions of CO and UHC were only significant at idle, de-
creasing sharply with increasing power level. Levels of CO were readi-
ly correlated with power level; UHC exhibited more variability while
following similar trends.
• Oxides of nitrogen were primarily a high power emission and, for fuels
with negligible amounts of fuel-bound nitrogen, correlated readily
with power level.
• Smoke increased with power level but for the system tested (a low smoke
combustor) the emission was below 20 Smoke Number. This is below
visible and also in a range where the accuracy of the measurement sys-
tem is suspect.
At
be
high power operating conditions, fuel hydrogen content was found to
a very significant fuel property with
flame radiation, smoke, and NO emission
respect
levels.
to liner temperature,
0 At idle and cruise operating conditions, CO and HC emission levels
were found to be dependent on
spray droplet size.
both fuel hydrogen content and relative
0 At cold-day ground start conditions, lightoff correlated with the
relative fuel droplet size.
0 Altitude relight limits at low flight Mach numbers were fuel dependent
and also correlated with the relative fuel droplet size.
0 Combustor liner life analyses, based on the test data, yielded relative
life predictions of 1.00, 0.93, 0.83, and 0.73 for fuel hydrogen con-
tents of 14.5, 14.0, 13.0, and 12.0 percent, respectively.
0 High temperature cyclic fuel nozzle fouling tests revealed significant
effects of fuel quality and operating temperature on nozzle life. The
results correlated with laboratory thermal stability rating of the
fuels.
11. REFERENCE
Gleason, C.C., T.L. Oiler, M.W. Shayeson, and M.J. Kenworthy. Evaluation
of Fuel Character Effects on J79 Smokeless Combustor. AFWAL-TR-80-2092,
ESL-TR-80-46, U.S. Air Force, Wright-Patterson AFB, Ohio, 1980. 178 pp.
A-99
-------
TEST 22
EVALUATION OF FUEL CHARACTER EFFECTS ON
J79 ENGINE COMBUSTION SYSTEM
FUELS TESTED
Reference fuels: thirteen non-synfuels were tested; i.e., a typical JP-
4; five blends of JP-4 with a single ring aromatic concentrate, a double
ring aromatic concentrate, and a light oil; a typical JP-8; five blends
of JP-8 with the same three compounds used for the JP-4 blends; and a
Number 2 Diesel fuel. The thirteen fuels incorporated systematic varia-
tions in hydrogen content (12.0 to 14.5 weight percent), aromatic type
(monocyclic or bicyclic), initial boiling point (285 to 393 K by gas
chromatograph), final boiling point (532 to 679 K also by gas chromato-
graph), and viscosity (0.83 to 3.25 cSt at 300 K).
2. TEST EQUIPMENT
J79 turbojet engine main combustion system elements. Two single can test
rigs were used to generate combustion data at high and low pressure points
A fuel nozzle rig was used to obtain nozzle fouling data on the test
fuels.
3. TEST SITE
General Electric test facility, Evendale, Ohio.
4. TEST OBJECTIVES
t To determine the effects of broad variations in fuel properties on the
performance, emissions, and durability of the J79 combustion system.
• The rationale for selection of the test fuels was to span systematical-
ly the possible future variations in key properties that might be
dictated by availability, cost, the use of nonpetroleum sources for
jet fuel production, and the possible change from JP-4 to JP-8 as the
prime USAF aviation turbine fuel.
A-100
-------
5. SPONSORING AGENCIES
Air Force Aero Propulsion Laboratory (AFWAL/POSF)
Air Force Wright Aeronautical Laboratories
Wright-Patterson AFB, Ohio 45433
Government Project Engineer: T.A. Jackson
Telephone No: 513-255-2008
Additional funding and technical guidance was provided by the Environ-
mental Sciences Branch of the Environics Division in the Research and
Development Directorate of HQ Air Force Engineering and Services Center
located at Tyndall Air Force Base, Florida.
6. CONTRACTOR
General Electric Company
Aircraft Engine Group
Cincinnati, Ohio 45215
Project Officer: C.C. Gleason (or T.L. Oiler)
Telephone No: 513-243-3207
7. TEST CONDITIONS
Test fuels were evaluated in: (a) 14 high pressure/temperature combustor
performance/emissions/durability tests; (b) 14 low pressure/temperature
combustor cold-day ground start/altitude relight tests; and (c) 18 high
temperature fuel nozzle fouling tests.
8. ENVIRONMENTAL MONITORING
NO , CO, smoke, and unburned hydrocarbons.
9. PROJECT STATUS
Testing and analytical activity occurred from June 1977 through August
1978. Final report is dated June 1979.
10 RESULTS
• Fuel hydrogen content strongly affected smoke, carbon deposition, liner
temperature, flame radiation and moderately affected NOX emissions.
Hydrogen content is, therefore, probably the single most important fuel
property, particularly with respect to high power performance and
emission characteristics and combustor durability (life).
t
Fuel volatility (as indicated by initial boiling range) and viscosity
effects became evident at low power operating conditions. Cold day
A-101
-------
starting and altitude relight capability are highly dependent upon
these properties.
• Within the range tested, neither aromatic type (monocyclic or bicyclic)
nor final boiling range produced any direct effect on emissions or
combustor performance.
• None of the fuel properties produced any measurable effect on combus-
tor exit temperature distribution (profile and pattern factor), idle
stability, fuel nozzle fouling tendency, or turbine life.
t The fuel nozzle fouling tests were indeterminate. More sophisticated
long-term tests are needed to determine the effects of fuel thermal
stability on fuel supply/injection system components.
11. REFERENCE
Gleason, C.C., T.L. Oiler, M.W. Shayeson, and D.W. Bahr. Evaluation of
Fuel Character Effects on 079 Engine Combustion System. AFAPL-TR-79-
2015, CEEDO-TR-79-06, U.S. Air Force, Wright-Patterson AFB, Ohio, June
1979, 197 pp.
A-102
-------
TEST 23
FUEL CHARACTER EFFECTS ON CURRENT, HIGH PRESSURE RATIO,
CAN-TYPE TURBINE COMBUSTION SYSTEMS
1. FUELS TESTED
Reference fuels: twelve fuels were tested including a baseline JP-4, a
baseline JP-8, and five blends of each baseline fuel. Hydrogen content,
aromatic type, distillation range, and viscosity were varied by blending
JP-4 and JP-8 fuels with a mineral seal oil and two types of aromatic
solvents. The fuel matrix incorporated systematic variations in hydrogen
content (12.0 to 14.4 percent wt.), aromatic type (single or multi-ring),
10 percent distillation point (353 to 464 K by gas chromatograph), final
boiling point (541 to 612 K by gas chromatograph), and viscosity (0.888
to 2.305 centi-stokes at 298 K).
2. TEST EQUIPMENT
A single can combustor rig, simulating a 36° segment of the mainburner
of the TF41 turbofan engine, was used to generate high and low pressure
data. A special fuel nozzle rig was used to generate combustor carboning
and nozzle fouling data.
3. TEST SITE
Detroit Diesel Allison, Indianapolis, Indiana.
4. TEST OBJECTIVES
• The purpose of this program was to determine the effects of fuel pro-
perty variations on the performance, exhaust emission, and durability
characteristics of the TF41 turbofan engine combustion system. The
system was selected because it is one of two high pressure ratio,
connular system in use by the Air Force.
• The rationale for selection and testing of test fuels was to study the
operational and performance characteristics that might occur with the
ultimate use of non-petroleum-derived fuels in the TF41 turbofan
engine.
A-103
-------
5. SPONSORING AGENCY
Air Force Aero Propulsion Laboratory
Air Force Wright Aeronautical Laboratory
Air Force Systems Command
Wright-Patterson AFB, Ohio 45433
Government Project Engineer: T.A. Jackson
Telephone No: 515-255-2008
Partial funding and technical support in the area of the measurement and
analysis of gaseous emissions and smoke data were provided by the Envi-
ronmental Sciences Branch of the Environics Division in the Research and
Development Directorate of HQ Air Force Engineering and Services Center
(HQ AFESC/RDVC).
6. CONTRACTOR
Detroit Diesel Allison (DDA)
Division of General Motors Corporation
Indianapolis, Indiana 46206
Project Officer: Dennis Troth
Telephone No: 317-242-5000
7. TEST CONDITIONS
Performance tests were accomplished at idle, altitude cruise, dash, and
takeoff conditions. Sea level and altitude ignition tests were also
completed. Carboning and fuel nozzle fouling tests were conducted under
accelerated failure conditions.
8. ENVIRONMENTAL MONITORING
NO , CO, smoke, and unburned hydrocarbons.
A
9. PROJECT STATUS
Test and analytical activity were conducted from June 15, 1978 through
June 15, 1979. Final report is dated April 1980.
10. RESULTS
• Fuel fouling and carboning characteristics were established. Combustor
operating parameters such as liner temperature, pattern factor, igni-
tion fuel/air ratio, lean blowout fuel/air ratio, and exhaust emissions
were correlated to fuel properties.
A-104
-------
• This program did have a problem with fuel-to-fuel contamination. As a
result, two fuel data files were created: one file for high pressure
tests, the other for low pressure tests. High pressure combustor data
such as performance, exhaust emissions and durability were correlated
with fuel information identified as high-pressure fuel data. Altitude
relight and stability measurements were correlated with low-pressure
fuel data.
• Hydrogen content, total aromatic content, and multi-ring aromatic
content were found to strongly affect CO and smoke emissions, combus-
tion efficiency, and liner wall temperatures at high power operation.
• None of the fuel property characteristics produced any measurable
effect on combustor exit temperature distribution (pattern factor or
radial profile), idle performance or emissions, or hot section hardware
life.
• Maximum achievable ignition altitude was most strongly influenced by
total aromatic content and hydrogen content. Once ignition was
achieved, combustor stability was controlled by 10 percent boiling
point, viscosity, vapor pressure, and surface tension.
11. REFERENCE
Vogel, R.E., D.L. Troth, and A.J. Verdouw. Fuel Character Effects on
Current, High Pressure Tatio, Can-Type Turbine Combustion Systems. AFAPL-
TR-79-2072, ESL-TR-79-29, U.S. Air Force, Wright-Patterson AFB, Ohio,
1980. 148 pp.
A-105
-------
TEST 24
LOW NO HEAVY FUEL COMBUSTORS CONCEPT
y\
1. FUELS TESTED
Synfuel: middle distillate SRC-11 fuel.
Reference fuels: low quality petroleum residual, and petroleum reference
distillate fuel (see Table A-32).
TABLE A-32. FUEL PROPERTIES
Hydrogen, wt %
Carbon, wt %
Nitrogen (FBN)
wt%
10%. Dist.
6F (K)
End point
°F (K)
Pour point,
6F (K)
Petroleum
Distillate
(ERBS)*
12.88
87.05
0.013
375 (464)
645 (614)
-35 (236)
Petroleum
Residual
(RESID)
11.24
87.39
0.27
572 (573)
1026 plus
(825)
40 (278)
Synthetic-CDL
(SRC-II)
8.81
85.84
0.83
410 (483)
597 (587)
-50 (228)
*Experimental Referee Broad Specification
2. TEST EQUIPMENT
Air-staged combustor with rich burning zone followed by quench zone and
a lean reaction and dilution zone; sized for use with Detroit Diesel
Allison Model 570-K industrial gas turbine.
3. TEST SITE
Detroit Diesel Allison high pressure test facility, Indianapolis, Indiana.
A-106
-------
4. TEST OBJECTIVES
t Assess the capability of Model 570-K turbine to function in an environ'
mentally acceptable fashion on the three fuels described above.
0 Emission and performance goals are shown in Table A-33.
TABLE A-33. EMISSIONS AND PERFORMANCE GOALS AND TEST RESULTS*
Emissions and Performance
Parameters
FBN content, wt %
Maximum EPA NO. ppm at 15% 09
X L.
Program NO goal, ppm at 15% 09
X C.
Minimum NO measured, ppm at 15% 09
X c.
Program smoke goal, SAE smoke number
Measured smoke, SAE smoke number
Program combustion efficiency goal, %
Demonstrated combustion efficiency, %
ERBS
0.013
180
90
49
20
5
99
99.9
Test Fuels
Residual
0.27
230
230
53
20
3
99
99.9
SRC-II
0.88
230
230
50
20
3
99
99.9
Rich-zone equivalence ratio at minimum
measured NO,
1.25
1.40
1.35
Measured CO, ppm at 15% 02
Measured unburned hydrocarbons, ppm at
15% 00
22
24
25
25
Rich-zone maximum metal temperature,°K
1,015
(1,366)
1,170
(1,644)
1,110
(1,541)
k
Operating conditions: Rich/quench/lean (RQL) combustor
6% pressure drop
0.60 lean-zone equivalence ratio
Maximum continuous power conditions
A-107
-------
5. SPONSORING AGENCIES
U.S. Department of Energy
Office of Coal Utilization
Heat Engine and Heat Recovery Division
Project Officer: Warren Bunker
Telephone No: 301-353-2816
NASA-Lewis Research Center (Technical Program Management)
Cleveland, Ohio 44135
Project Officer: J. Notardonato
Telephone No: 216-433-4300, Ext. 6132
6. CONTRACTOR
Detroit Diesel Allison
Indianapolis, Indiana
Project Manager: A.S. Novick
Telephone No: 317-242-5428
7. TEST CONDITIONS
Combustor inlet temperature: 300°F and 575°F
Lean zone equivalence ratios: 0.45 to 0.50, and 0.55 to 0.60
Total mass flow: rated airflow and 125% rated airflow
Combustor was operated at maximum continuous power, as well as idle power
and 50% and 70% load power.
8. ENVIRONMENTAL MONITORING
Carbon monoxide, unburned hydrocarbons, nitrogen oxides, carbon dioxide,
smoke.
9. PROJECT STATUS
Project was begun in 1980 and completed in October 1981.
10. RESULTS (See Table A-33)
• The combustor was able to achieve low NOX with significantly different
fuels and levels of fuel-bound nitrogen at 50% and 70% load" power and
maximum continuous oower.
t High NOX levels (approximately 260 ppm at 15% 02) were obtained with
SRC-II fuel at idle power due to burn-through in the combustor dome,
which shifted the rich zone equivalent ratio below stoichiometric or
to full lean conditions.
A-108
-------
• Unburned hydrocarbons measured at all power levels were all below 25
ppm.
t Both CO and smoke varied directly with rich zone equivalence ratio and
inversely with lean zone equivalence ratio. Higher inlet temperatures
reduced CO and smoke emissions. Smoke levels were usually below 10
smoke number.
11. MISCELLANEOUS
Project is part of a multiple contract effort sponsored by DOE to develop
low NO combustor technology. Other participating contractors are:
A
Westinghouse, General Electric, United Technologies Corporation, and
Solar Turbine International.
12. REFERENCE
Novick, A.S. and D.L. Troth. "Low NOX Heavy Fuel Combustor Concept Pro-
gram". Detroit Diesel Allison Division of General Motors. DOE-NASA-014B-1,
NASA CR-165367, October 1981.
A-109
-------
TEST 25
LOW NO HEAVY FUEL COMBUSTOR CONCEPT
/\
1. FUELS TESTED
Synfuel: SRC-11 fuel oil.
Reference fuels: low quality petroleum residual and petroleum reference
distillate fuel. :
2. TEST EQUIPMENT
The combustion configurations and their variations evaluated in this
study are described below.
A. Rich Burn - Lean Burn Concept
The baseline configuration is the rich-lean (rich burn-quick quench)
staged combustion system. This concept consists of a metered primary
zone airflow tube which provides the capability of varying the burner
front end equivalence ratio within a pre-mix pre-vaporized fuel prepara-
tion system or an airblast fuel nozzle centered in a 45-degree recessed
air swirler fuel preparation device, a rich burning combustion zone where
fuel and air are burned at equivalence ratios greater than 1.3, and a
quench zone where secondary air is introduced and mixed for further oxida-
tion in a lean combustion zone.
Variations to the rapid quench section were made by replacing the baseline
hardware (3-in. diam.) with 2-inch or 4-inch diameter sections. A third
variation addressed the feasibility of using uncooled non-metallic mate-
rials for the rich zone combustor. The material chosen for this section
was a cylinder of carbon compound. Another variation to the baseline
concept was the use of externally controlled plungers to vary the pressure
drop in the rapid quench zone of the baseline combustor.
B. Graduated Air^Addition Configuration
This configuration contains two rich zones of combustion (primary equi-
A-110
-------
valence ratios of greater than 2.0 and about 1.6) followed by the lean
burn zone.
C. Rich Product Recirculation
This configuration utilizes a large diameter mixing chamber as the rich
combustion zone. Secondary air is then added by one of two methods. The
first utilizes the rapid quench zone of the base rich burn-lean configura-
tion. The second method uses a quenching tube where air is introduced
into the center of the large mixing chamber through a necked down region
at the chamber exit through a 60° swirler.
D. Pre-burner Fuel Preparation
The pre-burner configuration consists of a small chamber with an air
boost fuel nozzle upstream of the primary zone in which a small amount of
fuel is burned to supply heat to vaporize the remaining fuel injected in
a necked down region of the pre-burner exit. The vaporized fuel then
travels into an aerodynamic swirler where vigorous mixing takes place.
Operation downstream of this section is the same as in the baseline rich
burn-lean burn configuration.
E. Rich-Lean Annihilation Combustor
This configuration consists of an air boost nozzle for fuel atomization
in the front end of the combustor, a rich burn module, a lean burn module,
an annihilation module, a rapid quench module, and a lean burn module.
3. TEST SITE
Pratt and Whitney Aircraft, West Palm Beach, Florida.
4. TEST OBJECTIVE
• Computer evaluation of several combustor concepts for achieving low
NOX emissions with high-nitrogen fuels (including SRC-II) in utility
gas turbine engines application without the use of water injection.
5. SPONSORING AGENCIES
U.S. Department of Energy
Office of Coal Utilization
Heat Engine and Heat Recovery Division
A-lll
-------
Project Officer: Warren Bunker
Telephone No: 301-353-2816
NASA-Lewis Research Center (Technical Program Management)
Cleveland, Ohio 44135
Project Officer: D. Schultz
Telephone No: 216-433-4000
6. CONTRACTOR
Power Systems Division
United Technologies Corporation at
Pratt and Whitney Aircraft
Government Products Division
West Palm Beach, Florida
Project Manager: G. W. Beal
Telephone No: 305-840-2000
7. TEST CONDITIONS
Conditions of the tests run are shown in Table A-34.
8. ENVIRONMENTAL MONITORING
NO , CO, and smoke.
/\
9. PROJECT STATUS
Modeling of individual configurations has been completed and performance
characteristics with respect to combustor flow fields and emission cha-
racteristics predicted. Preliminary test results for some configurations
are available and are described in Table A-34. These only include tests
with the baseline configuration and variations to the fuel preparation,
primary rich zone length and quench zone diameter.
10. RESULTS
The results of tests completed as of this paper's publication date are
shown in Table A-34. As predicted, the values of NO were reduced for the
smaller diameter quench zone and increased for the larger diameter quench
zone. The results indicate the rich burn-lean burn staged combustion
system can meet the emissions goals of the EPA standard.
11. MISCELLANEOUS
Project is part of a multiple contract effort sponsored by DOE to develop
A-112
-------
TABLE A-34. TEST SUMMARY
Configuration Description
1. •
•
t
1A. •
t
•
IB. 0
•
•
•
1C. •
«
•
•
2A. •
»
*
Rich-Lean Burn
(Rich Burn Quick Quench)
18-in. (45.7 cm) Rich Zone
Length
Premix Tube
Rich-Lean Burn
18-in. (45.7 cm) Rich Zone
Length
Recessed Air Swirler
Rich-Lean Burn
18-in. (45.7 cm) Rich Zone
Length
Recessed Air Swirler
Copper Cooling Coil
Rich-Lean Burn
18-in (45.7 cm) Rich Zone
Length
Recessed Air Swirler
Thicker Liner Material
Rich-Lean Burn
12-in. (30.5 cm) Rich Zone
Length
Recessed Air Swirler
Win. N0x/Rich Approximate
Fuel Equiv. Ratio Run Hours Comments
ERBS 35/1.4 5 Burned hole in rich zone at
high pressure.
SRC-II 35/1.8 7.5 Burned hole in rich zone.
25/1.9
ERBS 20/1.7 1 Burned hole in rich zone.
ERBS ' 25/1.6 8 S.A.E. Smoke numbers 5.0 to 8.
Overheated Rich Zone
SRC-II 44/1.6
Resid. 78/1.7
SRC-11 52/1.6 13 S.A.E. Smoke numbers 2.0
74/1.6 3.0 on No. 2 & SRC-II.
50/1.7 Overheated rich zone.
(Continued)
-------
TABLE A-34. (Continued)
Configuration Description
Min. N0x/Rich Approximate
Fuel Equiv. Ratio Run Hours
Comments
2B. • Rich-Lean Burn
• 12-in. (30.5 cm) Rich Zone
Length
• Recessed Air Swirler
• Improved Liner Cooling
2C. • Rich-Lean Burn
• 12-in (30.5 cm) Rich.Zone
Length
• Recessed Air Swirler
e Improved Liner Cooling
3A. • Rich-Lean Burn
• 18-in. (45.7 cm) Rich Zone
Length
• Recessed Air Swirler
• Improved Liner Cooling
• Small Dia. Quench Zone
4A. • Rich-Lean Burn
9 18-in. (45.7 cm) Rich Zone
Length
t Recessed Air Swirler
ERBS
42/1.5
ERBS 58/1.8
Resid. 95/2.0
(0.3% FBN)
Resid. 90/1.8
(0.4% FBN)
Resid. 100/1.9
(0.5% FBN)
Resid. 58/1.6
(0.3% FBN)
Resid. 70/1.6
(0.4% FBN)"
Resid. 85/1.6
(0.5% FBN)
Resid. 57/1.6
(0.3% FBN)
Resid. 49/1.6
(0.4% FBN)
10
15
15
Burned hole in rich zone at high
pressure due to loss of coolant
flow.
No cooling problems.
No cooling problems.
No cooling problems.
Heavy coking at entrance of rich
zone.
(Continued)
-------
TABLE A-34. (Continued)
Configuration Description
• Improved Liner Cooling
• Large Dia. Quench Zone
8A. 0 Rich-Lean Burn
• 18-in (45.7 cm) Primary
• Recessed Air Swirl er
• Improved Liner Cooling
t Variable Quench Zone
5A. • Rich-Lean Burn
• 18 Inch (45.7 cm) Primary
• Recessed Air Swirl er
• Non-Metallic Liner
r . Min. NCL/Rich
^uel Equiv. Ratio
Resid.
(0.5% FBN)
ERBS
Resid.
(0.3% FBN)
Resid.
(0.4% FBN)
Resid.
(0.5% FBN)
SRC- 1 1
ERBS
ERBS
ERBS
50/50
ERBS/Resid.
Resid.
(.3% FBN)
Resid.
(.5% FBN)
58/1.6
184/1.54
250/1.60
73/1.59
108/1.56
78/1.60
36/1.55
30/2.09
26/1.57
39/1.65
50/1.60
77/1.66
80/1.54
Approximate
Run Hours Comments
No cooling problems. Variable area
stuck at low temps.
12
Fuel Nozzle Tip Bent.
Smoke Number 13.8 @ 4> . = 2.0
13 No Cooling Problems (600°F Inlet)
(2 Hr. High (315°C).
Pressure)
180 PSIA (1290 kPa).
Smoke Number 21.9 A - = 2.0
Non-Metallic Liner Ablated.
Started in Cone Exit ~6 Hrs. into
Testing After Blow Out Instability
at 300°F (150°C) Inlet Condition
with Residual Fuel .
-------
low NO combustor technology. Other participating contractors are:
A
Westinghouse, Detroit Diesel Allison Division of General Motors, General
Electric Company, and Solar Turbine International.
12. REFERENCE
Russell, P.L., G.W. Beal, R.A. Sederquist, and D. Schultz. "Evaluation
of Concepts for Controlling Exhaust Emissions from Minimally Processed
Petroleum and Synthetic Fuels", ASME Paper No. 81-GT-157. Paper pre-
sented at the Gas Turbine Conference and Products Show, March 9-12, 1981,
Houston, Texas.
A-116
-------
TEST 26
LOW N0v HEAVY FUEL COMBUSTOR CONCEPT
A
1. FUELS TESTED
Synfuel: middle distillate SRC-11 fuel oil.
Reference fuels: low quality petroleum residual, and petroleum reference
distillate fuel (see Table A-35).
TABLE A-35. FUEL PROPERTIES
Spec. grav. @ 289/289 K
Hydrogen content,
percent
Sulfur content, percent
Net heat of combustion,
MJ/kg
Viscosity, m2/s @ 311 K
Nitrogen content,
percent
Surface tension, N/M
Surface tension, N/M
Pour point, K
Vanadium, ppm by wt
ERBS
0.8377
12.95
0.085
42.5
1.36xlO"6
0.0054
244
—
SRC II
0.9796
9.07
0.20
38.1
3.55xlO"6
0.87
255
—
Residual
0.9440
11.52
0.49
41.3
1. 345x1 O"3
0.23
3.29xlO"2 @ 339 K
3.06xlO"2 @ 366 K
294
26
Experimental Referee Broad Specification (ERBS) petroleum distillate fuel.
2. TEST EQUIPMENT
Seven 20-cm diameter experimental combustors of varying designs (see
Table A-36).
A-117
-------
TABLE A-36. DESCRIPTION OF TEST COMBUSTORS
Combustor #
Type
Characteristics
Rich-Lean Combustor
with Premixing
Rich-Lean Combustor
with Multiple
Nozzle
Rich-Lean Combustor
Series-Staged Lean-
Lean Combustor
Series-Staged Lean-
Lean Combustor with
Premixed Main Stage
Parallel-Staged
Lean Combustor,
Combustor 6
Lean Burning
Catalytic Com-
bustor, Combustor 7
3-part combustor consisting of single-
fuel nozzle and swirl cup in a premixing
tube ahead of the rich stage to provide
uniform mixing of fuel and air and avoid
smoke production, a necked-down quench
zone where secondary air is introduced,
and a. lean stage.
Consists of eight fuel nozzles and swirl
cups in the head of a rich stage, followed
by a quench zone and lean stage. Differs
from Combustor 1 in multiple nozzle head
end.
Same as Combustor 2 except for differen-
ces in design of the mixing passages
between rich and lean stages, where secon-
dary and dilution air are introduced and
mixed with the products of combustion of
the rich stage in minimum time to generate
minimum additional NOX.
Consists of pilot stage with single-air
atomizing fuel injector and two-stage
counter-rotating swirl cups, and main
stage which employs eight single-stage
swirlers and air atomizing fuel injectors.
Design minimizes long gas residence times
associated with recirculating zones that
generate thermal NOX.
Consists of pilot stage having six dual
counter-rotating swirlers arranged in an
annulus around a main stage premixing duct.
Main stage fuel is introduced into the
forward end of the duct and mixed with air
prior to entering the combustion zone
through twelve axial slots at the aft of
the premixing duct.
Has low velocity pilot stage with a single
swirl cup and air atomizing fuel injector
at the dome end. Main stage has annular
high-velocity dome with six swirl cups and
fuel injector in a concentric arrangement
around the discharge end of the pilot
stage.
Designed to demonstrate ultra-low thermal
NOX performance. Includes a fuel prepa-
ration section preceding the catalytic
reactor main stage containing seven fuel
nozzles. Main stage catalytic reactor con-
sists of an MCB-12 Zironia-spinel substrate
coated with a proprietary VOP noble metal
catalyst. Reactor is followed by a down-
stream pilot stage section for ignition,
acceleration and part-load operation to
50 percent load, at which point lightoff
occurs for further load increase to full
power.
A-118
-------
3. TEST SITE
General Electric test facilities, Evendale, Ohio.
4. TEST OBJECTIVES
• Evaluation of several combustor concepts for achieving low NOX emis-
sions with high-nitrogen fuels (including SRC-II fuels) in utility gas
turbine engines application without the use of water injection.
t Emissions and performance goals presented in Table A-37.
TABLE A-37. EMISSIONS AND PERFORMANCE GOALS
Pollutant
Maximum
Level
Operating
Condition
(a) Emissions Goals
Oxides of nitrogen
Sulfur dioxide
Smoke
Performance Goals
(b)
Combustion efficiency
Total pressure loss
Outlet temperature
pattern factor
Combustor exit radial
temperature profile
75 ppm at 15% 0
150 ppm at 15% 0
S.A.E. no. = 20
All
All
All
99% at all operating conditions
6% at base power load
0.25 at base load and load
power
Equivalent to production comb.
values
5. SPONSORING AGENCIES
U.S. Department of Energy
Office of Coal Utilization
Heat Engine and Heat Recovery Division
Project Officer: Warren Bunker
Telephone No: 301 - 353-2816
NASA-Lewis Research Center (Technical Program Management)
Cleveland, Ohio 44135
Project Officer: J. Notardonato
Telephone No: 216 -433-4000, Ext. 6132
A-119
-------
6. CONTRACTOR
General Electric Company
Evendale, OH 45215
Project Manager: M. B. Cutrone
Telephone No: 513-243-2000, Ext. 3651
7. TEST CONDITIONS
Engine conditions (ignition to peak load): fuel-air ratios (0.0054 to
0.025), combustor inlet pressures (ambient to 1.166 mPa), combustor inlet
temperature (ambient to 609°K), and reference velocity (11.3 to 43.6
m/sec).
8. ENVIRONMENTAL MONITORING
Carbon monoxide, nitrogen oxides, and unburned hydrocarbon (UHC) emis-
sions.
9. PROJECT STATUS
Program begun in May 1979. To date, results available for testing per-
formed on combustors 1, 2, 4, and 6 (see Table A-38); additional testing on
combustors 1 and 2, as well as on combustors 3 and 5 recently completed;
results will be published in August 1981. Combustor 7 currently being
fabricated and tests planned for summer 1981. Program to be completed
by November 1981.
10. RESULTS
Combustor 1 (only ERBS fuel tested)
9 The high NOX emissions (20.0 to 24.0 g/kg NOX fuel) experienced due to
nozzle misalignment; significant NOX reduction experienced after
nozzle correction and increased rich stage equivalence ratio (12.0
g/kg NOX fuel).
• Smoke emissions exceptionally low (approximately 0-5 SAE smoke number).
• Combustible emissions (CO and UHC) were well within program goals (see
Table A-37).
Combustor 2
« NOX emissions with SRC-II and residual fuels higher than program goals
(see Table A-37) (certain modifications reduced NO emissions consider-
ably). x
A-120
-------
TABLE A-38. TEST MATRIX
Combustor No.
4
6
i
1
2
ERBS RESID SRC II
x x+ x
A X X
vt
X
xf x x
See Table A-36 for description of combustors.
Fuel doped with pyridine to increase fuel-bound nitrogen.
• Excellent smoke performance with SRC-II fuel (SAE smoke number was 18
at an air/fuel ratio of 0.029).
• Combustible emissions (CO, UHC) within program goals (see Table A-37)
for SRC-II and residual fuels; CO emissions were approximately 20 ppm
at baseload conditions.
Combustor 4
• NOX emissions approximately 10 percent above program goals (see Table
A-37) at 4-1/2 percent pressure drop with the ERBS and residual fuels.
• With SRC-II fuel, NOX emissions were well above program goals.
• Smoke levels well below goals (see Table A-37) at base and peak level
conditions with all three types of fuel.
Combustor 6
• NOX levels approximated program goals (see Table A-37) at base load
conditions with ERBS fuel and residual fuel, but were 37 percent above
the goal with SRC-II fuel.
t Low smoke levels observed for all fuels tested (*v20 SAE smoke number).
11. MISCELLANEOUS
Project is part of a multiple contract effort sponsored by DOE to develop
low NOX combustor technology. Other participating contractors are:
Westinghouse, Detroit Diesel Allison Division of General Motors, United
Technologies Corporation, and Solar Turbine International.
A-121
-------
12. REFERENCES
Cutrone, M.G., M.B. Hilt, et al. "Evaluation of Advanced Combustors for
Dry NOX Suppression with Nitrogen Bearing Fuels in Utility and Industrial
Gas Turbines", ASME Paper No. 81-GT-125. Presented at 26th International
Gas Turbine Conference, Houston, Texas, March 9-12, 1981. 10 pp.
Telephone communication to J. Fairbanks, U.S. DOE, Washington, D.C., with
S. Quinlivan, TRW, March 24, 1981.
Telephone communication to J. Notardonato, NASA Lewis Research Center,
with S. Quinlivan, TRW, May 20, 1981.
A-122
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TEST 27
LOW NOV HEAVY FUEL COMBUSTOR CONCEPT
/\
}. FUELS TESTED
Synfuel: middle distillate SRC-11 fuel.
Reference fuels: low quality petroleum residual and petroleum reference
*
distillate fuel (ERBS) and natural gas.
2. TEST EQUIPMENT
Two basic combustor approaches were tested including a staged combustor
with a rich primary zone and a lean secondary zone, and a lean-lean com-
bustion system. Three variations of the rich-lean combustor configuration
were tested including a longer primary zone (Configuration 1), a shorter
primary zone (Configuration 2), and a convectively cooled primary zone
(Configuration 3). Only one configuration of the lean-lean combustor
system was tested.
3. TEST SITE
Solar Turbine International, San Diego, California.
4. TEST OBJECTIVES
• Evaluation of several combustor concepts for achieving low NOX emis-
sions with high-nitrogen fuels (including SRC-II) in utility gas
turbine engines application without the use of water injection.
• Emission goals and performance standards for this work are shown below
in Table A-39.
5. SPONSORING AGENCIES
U.S. Department of Energy
Office of Coal Utilization
Heat Engine and Heat Recovery Division
*
Experimental Referee Broad Specification.
A-123
-------
TABLE A-39. COMBUSTOR EMISSION GOALS AND PERFORMANCE STANDARDS
Goal/Standard Level
NO
x
NO
x ERBS* fuel.
Combustion efficiency >99 percent.
Pressure drop <6 percent.
Pattern factor 0.25.
75 ppm corrected to 15 percent Q£ for
FBN levels up to 1 percent (wt).
37 ppm corrected to 15 percent 02 for
*
*
Experimental Referee Broad Specification.
Project Officer: Warren Bunker
Telephone No: 301 - 353-2816
NASA-Lewis Research Center (Technical Program Management)
Cleveland, Ohio 44135
Project Officer: H.G. Yacobucci
Telephone No: 216-433-4000
6. CONTRACTOR
Solar Turbine International
San Diego, California
Telephone No: 714-238-5500
7. TEST CONDITIONS
Lean-Lean
ERBS Fuel:
Inlet Air Temperature 260 & 371°C (500 & 700°F)
Inlet Air Pressure 586, 793 & 1200 kPa (85, 115 & 161
SRC-II Fuel:
Inlet Air Temperature 260 & 371 °F (500 & 700°F)
Inlet Air Pressure 308, 584 & 908 kPa (45, 85 & 132
Rich-Lean PS
Configuration 1 with Natural Gas:
Inlet Air Temperature 149, 177 & 204°C (300, 350 & 400°F)
Inlet Air Pressure 310 kPa (45 psia)
A-124
-------
Configuration 2 with ERBS Fuel:
Inlet Air Temperature 143 & 260°C (290 & 500°F)
Inlet Air Pressure 310 & 379 kPa (45 & 55 psia)
Configuration 3 with ERBS & SRC-II Fuel
Inlet Air Temperature 143 & 260°C (290 & 500°F)
Inlet Air Pressure 586 to 910 kPa (85 to 132 psia)
8. ENVIRONMENTAL MONITORING
NO , CO, unburned hydrocarbons, and smoke.
/v
9. PROJECT STATUS
The described combustor concepts were tested and recommendations for
further testing were made. Report presented in March 1981.
10. RESULTS
Lean-Lean
ERBS Fuel:
• The high thermal NOX is attributed to pre-mixing of the fuel and air.
Higher inlet temperatures increased the NOX emissions for a given
equivalence ratio, as did higher inlet pressure.
• The CO emission levels were consistently low at all conditions
evaluated.
• Unburned hydrocarbons were negligible and no smoke was detectable
throughout these tests.
SRC-II Fuel:
• For rich primary zone conditions, NOX emission levels were higher than
the emission goals. Increasing inlet pressure resulted in a decrease
in NOX emissions.
• CO emissions remained low using the SRC-II middle distillate fuel.
0 No smoke was detectable and unburned hydrocarbons were negligible
throughout these tests.
Rich-Lean Combustor
Configuration 1 with Natural Gas:
• NOX emissions were below 60 ppm and tended to decrease with decreasing
inlet temperature.
• Low CO and negligible unburned hydrocarbon emissions were observed at
all conditions evaluated.
Configuration 2 with ERBS Fuel:
• For rich primary zone conditions, NOX emissions dropped below 75 ppm
A-125
-------
(corrected to 15 percent 03) and Increased sharply as stolchlometric
primary zone conditions were approached.
t Low CO emissions were observed at all conditions evaluated.
Configuration 3 with ERBS Fuel:
• At each of four temperature and pressure conditions, the NOX emissions
appear to reach a minimum below the most stringent program goal, for
rich primary zone conditions.
• CO emissions levels were consistently low.
t No smoke was detectable and unburned hydrocarbon emissions remained
negligible throughout the tests.
Configuration 3 with SRC-11 Fuel:
• At each of four inlet conditions evaluated, the NOX emissions appear
to reach a minimum below the lower (large engine) NOX emission limit,
for rich primary zone conditions.
• The CO emissions level was consistently low.
0 No smoke was detectable and unburned hydrocarbon emissions remained
negligible throughout these tests.
11. MISCELLANEOUS
Project is part of a multiple contract effort sponsored by DOE to develop
low NOX combustor technology. Other participating contractors are:
Westinghouse, Detroit Diesel Allison Division of General Motors, United
Technologies Corporation, and General Electric Company.
12. REFERENCE
White, D.J., A. Batakis, R.T. LeCren, and H.G. Yacobucci. "Low NOX Com-
bustion Systems for Burning Heavy Residual Fuels and High-Fuel-Bound
Nitrogen Fuels", ASME Paper No. 81-GT-109. Presented at the Gas Turbine
Conference and Products Show, March 9-12, 1981, Houston, Texas.
A-126
-------
TEST 28
LOW NO HEAVY FUEL COMBUSTOR CONCEPT
rt
FUELS TESTED
Synfuel: middle distillate SRC-II fuel.
Reference fuels: low quality petroleum residual, and petroleum reference
distillate fuel (see Table A-40), and various blends of these fuels.
TABLE A-40. FUEL PROPERTIES
Gravity, °API (15.6°C)
Specific Gravity
Hydrogen, wt %
Nitrogen, wt %
Sulfur, wt %
Ash, wt %
Pour Point, °C (°F)
Viscosity, cst
@ 37.8°C(100°F)
Distillation Temp. °C (°F)
IBP
10%
50%
90%
FBP
Net Heat of Combustion
Btu/lb
ERBS*
38.2
.8338 @ 15.6°C
12.55
.008
.09
<.0002
-45.6(-50)
1.87
126 (259)
180 (356)
224 (435)
330 (620)
408 (766)
18,343
Petroleum SRC-II Middle
Residual Distillate
—
.9533 (@ 22°C)
11.43
.22
.48
.03
13.3
.9772
9.19
.79-. 8
.25
.0015
23.9(+75) -59.4(-75)
>835 (furol sec)
180 (356)
250 (482)
358 (676)
445 (833)
490 (914)
17,609
4.03
110 (230)
190 (374)
242 (486)
295 (563)
370 (698)
16,674
*Experimental Referee Broad Specification (ERBS) petroleum distillate fuel
A-127
-------
2. TEST EQUIPMENT
Several different combustion configurations were built for this test
(Table A-41). The combustion configurations selected for development and
design involved staged combustion (rich-lean) utilizing diffusion flames
and stated catalytic combustion. Detailed descriptions and illustrations
of each combustor are presented in the referenced report.
3. TEST SITE
Westinghouse Electric, Madison, PA.
4. TEST OBJECTIVES
• Evaluation of several combustor concepts for achieving low NOX emis-
sions with high-nitrogen fuels (including SRC-II) in utility gas
turbine engines application without the use of water injection.
• Emissions and performance goals presented in Table A-42.
5. SPONSORING AGENCIES
U.S. Department of Energy
Office of Coal Utilization
Heat Engine and Heat Recovery Division
Project Officer: Warren Bunker
Telephone No: 301 -353-2816
NASA-Lewis Research Center (Technical Program Management)
Cleveland, Ohio 44135
Project Officer: J. Notardonato
Telephone No: 216 -433-4300, Ext. 6132
6. CONTRACTOR
Westinghouse Electric Co.
Synthetic Fuels Division
P. 0. Box 158, Waltz Mill Site
Madison, PA 15665
Telephone No: 412-722-5716
7. TEST CONDITIONS
The reported test conditions for the configurations tested are shown in
Table A-43.
A-128
-------
TABLE A-41. COMBUSTOR CONFIGURATION DESIGNED
AND BUILT FOR TESTING
Direct Injection - Rich-Lean
1. Direct Injection, Venturi Quench
2. Direct Injection, Vortex Quench
3. Direct Injection, Vortex Quench, Perforated Plate
4. Direct Injection, Vortex Quench, Catalyst
9. Multiannular Swirl Burner
11. Rolls-Royce Combustor
Premix Rich-Lean
5. Recirculating Counter Swirl, Venturi Quench
10. Perforated Plate, Venturi Quench
Rich Primary Catalytic - Lean Staged Combustion
7. Catalyst A, Venturi Quench
8. Catalyst B, Venturi Quench
Rich Hybrid Premix/Direct Injection
6. Hybrid Piloted Rich Burner, Venturi Quench
Lean Catalytic
12. Catalytic
Lean Hybrid Premix/Direct Injection
13. Hybrid Piloted Lean Burner
A-129
-------
TABLE A-42 LOW NOX HEAVY FUELS COMBUSTOR CONCEPT PROGRAM
' SUMMARY OF GOALS AND OBJECTIVES
A. Emissions Limits (All Operating Conditions)
1. Oxides of Nitrogen - 75 ppm @ 15% 02
2. Sulfur Dioxide - 105 ppm @ 15% 0
3. Smoke - S.A.E. No. = 20
B. Performance Specifications
1. Combustion Efficiency
2. Total Pressure Loss
3. Outlet Temperature
Pattern Factor
4. Combustor Exit
Temperature Profits
>99%(@ all operating conditions)
<6% (@ base load power)
<0.25 (@ base load and load power)
-Equivalent to typical
production engine
combustor values
C. General
1. Retrofitable to current production and field engines
2. Highly durable
3. Maintainable
4. Fuel Flexible - Capable of meeting emissions and performance
specification on liquid fuels including petroleum distillates
and residuals and synfuels from coal and shale
A-130
-------
TABLE A-43. TEST CONDITIONS FOR BURNER CONFIGURATIONS TESTED
Direct Injection - Rich-Lean
Venturi Jet Quench/Lean Burner
Burner outlet pressure: 165 psia (1.14 MPa)
Burner inlet temperatures: 600°F (316°C)
Burner outlet temperatures: 1950°F (1066°C)
Total air flow: 4.1 Ib/sec (1.86 kg/sec.)
Vortex Mixer/Lean Burner
Quench module with vortex mixer was tested under
similar conditions to those described above.
Vortex Mixer/Catalytic Lean Burner (typical expected operating conditions
at full pressure)
Catalyst inlet temperature: 1480°F (804°C)
Catalyst outlet temperature: 2100°F (1140°C)
Lean Catalytic Burner
Combustor inlet pressure:
Air inlet temperature:
180 psia (1.24 MPa)
720°F (382°C)
Rolls Royce Combustor (peak conditions)
Combustor inlet pressure:
Air flow:
Multiannular Swirl Burner
Combustor inlet pressure:
Combustor inlet temperature:
Air flow:
163 psia (1.13 MPa)
7.6 Ib/sec. (3.45 kg/sec)
11.2 atmos (1.19 MPa)
638°F (338°C)
5.2 Ib/sec. (2.36 kg/sec.)
A-131
-------
8. ENVIRONMENTAL MONITORING
Carbon monoxide, nitrogen oxides, unburned hydrocarbons, and smoke.
9. PROJECT STATUS
The combustion configurations which have been designed and built are
shown in Table A-41. Combustion emission sampling results available so far
are for configurations 1, 2, 4, 9, 11, and 12 using unblended fuels.
The study results were presented in March 1981.
10. RESULTS
Direct Injection - Rich-Lean
Ventori_ Jet_ Quenc_h/Lear[ Burnerj_
• Minimum NO values of 68-70 ppmv were obtained for the ERBS fuel.
X
• Minimum NO values of about 140 ppmv were obtained with SRC-II fuel.
/\
« Smoke measurements for this configuration for the ERBS fuel show SAE
smoke numbers of 20 and 26 for the primary equivalence ratio (1.6
which resulted in minimum NO emissions).
J\
• Smoke numbers were higher for SRC-II fuel oil (29 at a primary equiva-
lence ratio of 1.62).
Vpjrte_x_Mj_xe_r/_Lean_ B_u_rne_rj_
• NOX emissions of approximately 195 ppmv were obtained with the SRC-II
fuel.
• NOX emissions of approximately 120 ppmv were obtained with the ERBS
fuel.
j/o_rtex/Mj_xer/Caita, 1 y_tj_c_Lean_ J3u_rner:_
t NOX emission buds were about the same as described above for the vortex
mixer without the catalytic element for both fuels and did not appre-
ciably change over the range of equivalence ratios considered.
• FBN conversion in the SRC-II fuel was about 23 percent.
Lean Catalytic Burner
• NOX emission for the ERBS fuel was 2 ppm.
• Approximate NOX emissions and FBN conversions for the ERBS fuel with
pyridine added are shown below:
*
FBN - fuel bound nitrogen.
A-132
-------
FBN, Wt % NO,,, ppmv*"% Conversion of FBN
A • • —•—•—• • "• -
0.2 60 60
0.5 100 47
1.2 200 40
* • - - - - • . —
Corrected to 15 percent oxygen.
• NOX emissions from SRC-11 fuel were 190 and 200 ppmv.
• Conversion efficiency of FBN from the SRC-II fuel in the lean catalytic
combustor was about 50 percent.
Rolls-Royce Combustor
• Emissions for
as follows:
Emission
Constituent
NOX
CO
Unburned
Hydrocarbon
Smoke No.
ERBS and SRC-II fuel
Emission Level -
ERBS (ppm)
91
8
2
5 & 11
at the peak design
Emission Level-
SRC-II (ppm)
280
16-37
2
7
condition were
Emission Level -
Petroleum
Residual (ppm)
120
• Conversion rates of FBN were about 40 percent for SRC-II fuel and 30-
40 percent for petroleum residual fuel.
Multiannolar Swirl Burner
t Preliminary results from this burner are shown below:
Fuel
ERBS
SRC-II
Petroleum
Residual
Temperature, °F (°C)
2035 (1113)
1948 (1064)
1995 (1091)
NO., (ppmv) Remarks
X
26
165
127
Central nozzle only
Central & radial nozzles
Central & radial nozzles
• FBN conversion for SRC-II fuel was 20 percent, which is lower than
that of a conventional burner.
A-133
-------
11. REFERENCE
Lew, H.G., S.M. DeCorso, G. Vermes, D. Carl, W.J. Havener, J. Schwab, and
J. Notardonato. "Low NOX and Fuel Flexible Gas Turbine Combustors", ASME
Paper No. 81-GT-99. Presented at the Gas Turbine Conference and Products
Show, March 9-12, 1981, Houston, Texas.
A-134
-------
TEST 29
SMALL SCALE COMBUSTION TESTING OF SYNTHETIC FUELS
1. FUELS TESTED (See Table A-44)
Synfuel: SRC-II middle distillate, heavy distillate, and three blends
of middle and heavy distillate fuel oils.
Reference fuels: No. 2 and No. 6 fuel oils.
2. TEST EQUIPMENT
A 20-hp, Johnston, three-pass, firetube boiler designed to transfer
roughly 670,000 Btu/hr.
3. TEST SITE
Combustion Technology Division, Pittsburgh Energy Technology Center,
Pittsburgh, Pennsylvania.
4. TEST OBJECTIVE
• To characterize exhaust emissions and boiler efficiencies from both
synthetic fuels and petroleum-based fuels burned under identical com-
bustion conditions, in order to assess any change in the environmen-
tal impact of industrial or utility boiler exhaust gases upon changing
from petroleum-based fuels to synthetic fuels.
5. SPONSORING AGENCY
U.S. Department of Energy
Pittsburgh Energy Technology Center
Analytical Chemistry Division and
Combustion Technology Division
Pittsburgh, Pennsylvania
Principal Investigator: G. A. Gibbons
Telephone No: 412-675-5804
6. CONTRACTOR
None.
A-135
-------
TABLE A-44. FUEL ANALYSIS
I
GO
SRC-II "Blends"
Fuel,
%
Carbon
Hydrogen
Nitrogen
Sulfur
Ash
Oxygen (diff)
Heating Value
(Btu/lb)
No. 2
Fuelt
Oil
87.3
12.5
--
0.21
--
--
19,840
No. 6
Fuel
Oil
87.0
11.0
0.30
0.70
0.10
1.9
18,610
Middle
Distillate
(M)
85.9
9.0
0.9
0.3
0.10
3.8
17,260
Blend
No. 1
(3M:1H)
86.2
8.9
0.9
0.2
—
3.8
17,590
Blend
No. 2
(2M:1H)
87.5
8.5
0.9
0.4
0.60
2.1
17,140
Blend
No. 3
(1M:2H)
99.1
7.9
1.0
0.4
0.3
1.3
17,130
Heavy
Distillate
(H)
88.9
7.3
1.1
0.5
0.6
1.6
17,050
Typical analysis of No. 2 fuel oil.
Mixtures of middle and heavy distillate; blend No. 1 received already mixed.
-------
7. TEST CONDITIONS
To date, eight runs have been made with No. 6 oil: five at about 23 per-
cent excess air and three at about 11 percent excess air. Two runs have
been completed on No. 2 oil: one at 11 percent excess air and one at 20
percent excess air. Five SRC-II fuels have been tested: a heavy dis-
tillate, a middle distillate, and three blends. The initial blend of
SRC-II was approximately three parts middle distillate to one oart heavy
distillate. Six runs, three at each of two conditions, were made with
this blend. Subsequently, separate supplies of middle and heavy distil-
late were obtained, and two blends were prepared: one of two parts middle
to one part heavy distillate and the second of one part middle to two
parts heavy distillate. Three tests were run on each blend. Single tests
were run on the middle distillate and heavy distillate alone (see Table
A-45).
8. ENVIRONMENTAL MONITORING
NO , S0?, CO, HC, particulates, and polynuclear aromatic hydrocarbons
}\. (-
(qualitative).
9. PROJECT STATUS
Tests with SRC-II fuel oils and baseline petroleum fuel oils were con-
ducted from October 1979 through October 1980. The Progress Report is
dated 1981. Additional tests are planned with other synfuels - H-coal,
Exxon Donor Solvent fuel, shale oil, and biomass fuel. The program will
run until October 1982.
10. RESULTS
The results of the test program are highlighted below and in Tables A-46
through A-49.
• In general, combustion performance was good in all the test runs.
Total particulate loadings in the stack were small, and CO and total
hydrocarbon levels were below 100 and 1 ppm, respectively.
t The levels of NOX and S02 produced were proportional to the amount of
nitrogen and sulfur in the fuel.
0 There appear to be two sources of trace organics in the exhaust gases:
small amounts of the fuel itself not burned during combustion, and the
A-137
-------
TABLE A-45. TEST CONDITIONS FOR THE SYNFUELS TEST PROGRAM
Run
No.
LSF-20
LSF-21
LSF-22
LSF-23
LSF-24
LSF-25
LSF-26
LSF-27
LSF-28
LSF-29
LSF-30
LSF-31
LSF-32
LSF-34
LSF-35
LSF-36
LSF-37
LSF-38
LSF-39
LSF-40
LSF-41
LSF-42
LSF-43
LSF-44
Fuel
No. 6 Fuel Oil
No. 6 Fuel Oil
No. 6 Fuel Oil
No. 6 Fuel Oil
SRC-II, Blend 1
SRC-II, Blend 1
SRC-II, Blend 1
SRC-II, Blend 1
SRC-II, Blend i
SRC-II, Blend 1
No. 6 Fuel Oil
No. 6 Fuel Oil
No. 6 Fuel Oil
No. 6 Fuel Oil
No. 2 Fuel Oil
No. 2 Fuel Oil
SRC-II, Mid. Dist.
SRC-II, Blend 3
SRC-II, Blend 3
SRC-II, Blend 3
SRC-II, Blend 2
SRC-II, Blend 2
SRC-II, Blend 2
SRC-II, Heavy Dist.
Excess
% o2 *
3.9
2.1
4.1
4.4
3.9
2.2
3.9
2.3
4.5
1.9
2.3
4.0
2.1
4.1
4.6
2.2
4.4
2.5
4.2
2.2
2.5
3.9
2.6
2.9
Fuel
Ratet
(Gal/Hr. )
5.6
5.4
5.4
5.4
5.4
5.4
5.4
5.6
5.2
5.6
5.4
5.4
5.4
5.4
5.2
5.1
5.3
5.6
5.7
5.3
5.6
5.3
5.6
5.5
Steam Production/
Gal Fuelf
(Ibs. Steam/Gal.)
—
—
—
—
—
—
—
107.5
117.6
-__
111.2
103.7
108.3
110.5
106.1
106.7
111.7
115.7
114.0
115.7
109.8
108.7
109.4
114.7
"Percent oxygen was set as an experimental condition; two levels were se-
lected: 2.0-2.5 percent 0« and 4.0-4.5 percent CL.
f
Fuel rates were set at approximately 5.4 gal/hr and adjusted slightly to
maintain the same Btu/hr input for the fuel.
*Pounds of. steam produced per gallon of fuel fired.
A-138
-------
TABLE A-46. NO EMISSIONS AS A FUNCTION OF FUEL NITROGEN CONTENT
Fuel
No. 2 Fuel Oil
No. 2 Fuel Oil
No. 6 Fuel Oil
No. 6 Fuel Oil
No. 6 Fuel Oil
No. 6 Fuel Oil
No. 6 Fuel Oil
No. 6 Fuel Oil
No. 6 Fuel Oil
No. 6 Fuel Oil
SRC-II, Blend #1
SRC-II, Blend #1
SRC-II, Blend #1
SRC-II, Blend #1
SRC-II, Blend #1
SRC-II, Blend #1
SRC-II, Blend #2
SRC-II, Blend #2
SRC-II, Blend #2
SRC-II, Mid. Dist.
SRC-II, Blend #3
SRC-II, Blend #3
SRC-II, Blend #3
SRC-II, Blend #5
Run %
LSF 35
LSF 36
LSF 20
LSF 21
LSF 22
LSF 23
LSF 30
LSF 31
LSF 32
LSF 34
LSF 24
LSF 25
LSF 26
LSF 27
LSF 28
LSF 29
LSF 41
LSF 42
LSF 43
LSF 37
LSF 38
LSF 39
LSF 40
LSF 44
% Excess Air
26.0
11.0
21.0
10.5
23.0
25.0
11.5
22.0
10.5
23.0
21.5
11.0
21.5
11.5
26.0
9.5
13.0
21.5
13.5
25.0
13.0
24.0
11.0
15.0
% N (Fuel)
0
0
0.3
0.3
0.3
0.3
0.3
0.3
0.3
0.3
0.9
0.9
0.9
0.9
0.9
0.9
0.9
0.9
0.9
0.9
1.0
1.0
1.0
1.1
N0x (ppm)*
193
178
329
261
364
353
292
350
312
331
599
456
493
517
548
434
480
604
528
590
557
576
549
622
*
Adjusted to a dry, 0% Excess Air Basis.
A-139
-------
TABLE A-47. S02 EMISSIONS AS A FUNCTION OF FUEL SULFUR CONTENT
Fuel
No. 2 Fuel Oil
No. 2 Fuel Oil
SRC-II, Blend #1
SRC-II, Blend #1
SRC-II, Blend #1
SRC-II, Blend #1
SRC-II, Blend #1
SRC-II, Blend #1
SRC-II, Mid. Dist.
SRC-II, Blend #2
SRC-II, Blend #2
SRC-II, Blend #2
SRC-II, Blend #3
SRC-II, Blend #3
SRC-II, Blend #3
SRC-II, Heavy Dist.
No. 6 Fuel Oil
No. 6 Fuel Oil
No. 6 Fuel Oil
No. 6 Fuel Oil
No. 6 Fuel Oil
No. 6 Fuel Oil
No. 6 Fuel Oil
No. 6 Fuel Oil
Run %
LSF 35
LSF 36
LSF 24
LSF 25
LSF 26
LSF 27
LSF 28
LSF 29
LSF 37
LSF 41
LSF 42
LSF 43
LSF 38
LSF 39
LSF 40
LSF 44
LSF 20
LSF 21
LSF 22
LSF 23
LSF 30
LSF 31
LSF 32
LSF 34
% Excess Air
26.0
11.0
21.5
11.0
21.5
11.5
26.0
9.5
25.0
13.0
21.5
13.5
13.0
24.0
11.0
15.0
21.0
10.5
23.0
25.0
11.5
22.0
10.5
23.0
% S (Fuel)
0.20
0.20
0.20
0.20
0.20
0.20
0.20
0.20
0.30
0.40
0.40
0.40
0.40
0.40
0.40
0.50
0.70
0.70
0.70
0.70
0.70
0.70
0.70
0.70
S02 (ppm)
272
194
233
204
221
203
200
—
213
301
312
310
372
381
376
463
—
—
369
446
434
421
448
364
*
Adjusted to a dry, 0% Excess Air Basis.
A-140
-------
TABLE A-48. CALCULATED EFFICIENCIES FOR SELECTED TESTS
Run #
LSF-32
LSF-34
LSF-35
LSF-36
LSF-37
LSF-41
LSF-42
LSF-43
Fuel
No. 6
No. 6
No. 2
No. 2
SRC-II, Middle Distillate
SRC-II, Blend of 2 Parts
Middle Distillate to
1 Part Heavy Distillate
% (A Enthalpy
Balance)
+1.2
+1.5
-0.32
+5.0
+5.35
+2.4
+5.6
+5.8
Effi
% (Heat Loss)
83.1
78.7
74.8
80.0
83.8
78.4
80.7
82.5
ciency
% (Input-Output)
81.2
77.4
75.1
74.0
78.5
75.6
74.6
76.4
-------
TABLE A-49. SUMMARY OF GC-MS DATA OBTAINED FROM
A SYNFUEL AS WELL AS A PETROLEUM BURN
Compound
Naphthalene
2-Methyl naphthalene
1 -Methyl naphthalene
Biphenyl
2-Ethylnaphthalene
2,6- & 2,7-Dimethylnaphthalene
1,3- & 1 ,7-Dimethylnaphthalene
1 ,5-Dimethyl naphthalene
1 ,2-Dimethylnaphthalene
Acenaphthene
Dibenzofuran
Fluorene
9-Methylfluorene
2-Methyl fluorene
1 -Methyl fluorene
Dibenzothiophene
Phenanthrene
Anthracene
Carbazole
1-Phenyl naphthalene
3-Methyl phenanthrene
2-Methyl phenanthrene
9- & 4-Methyl phenanthrene
1 -Methyl phenanthrene
2- Phenyl naphthalene
Fluoranthene
Benzo(def )dibenzothiophene
Pyrene
Retene
Benzo(b)fluorene
4-Methyl pyrene
2-Methyl pyrene
Benzo(a)anthracene
Chrysene/Triphenylene
n-Alkanes
Detected
SRC- 1 1
L
L
L
L
L
L
L
L
L
L
L
M
M
M
M
M
H
L
L
L
M
M
M
M
L
M
L
H
L
M
L
L
L
L
L
in Combustion Emission
No. 2 Fuel Oil
M
H
L
L
L
L
L
L
L
L
L
L
ND
ND
ND
L
H
L
ND
ND
ND
ND
ND
ND
ND
L
ND
L
ND
ND
ND
ND
ND
ND
H
ND = Not Detected
H = High
M = Medium
L = Low
Total Hydrocarbon = 1 ppm.
A-142
-------
products of combustion (note that No. 2 and No. 6 fuel oil are essen-
tially aliphatic). For the petroleum fuels, n-alkanes and polynuclear
aromatic hydrocarbons are seen in the exhaust gas; for the SRC-11
fuels, the alkanes are absent or present at very low levels, and poly-
nuclear aromatic hydrocarbons not seen in the petroleum exhaust gases
are present.
11. REFERENCE
Gibbons, G.A., et al. Small Scale Combustion Testing of Synthetic Fuels.
Progress Report prepared by Pittsburgh Energy Technology Center. 1981.
A-143
-------
TEST 30
EVAPORATIVE EMISSIONS FROM VEHICLES
OPERATING ON METHANOL/GASOLINE BLENDS
1. FUELS TESTED*
Non-synfuel: 10 percent methanol/90 percent gasoline (Indolene) blend.
2. TEST EQUIPMENT
Two light duty vehicles were tested. Vehicle A was a 1977 Chevrolet
Impala with a 305 CID engine and 2V carburetor; vehicle B was a 1977
Buick Skylark with a 231 CID engine and 2V carburetor. Both vehicles
had activated carbon canisters for vapors from fuel tank only.
3. TEST SITE
Bartlesville Test Center, Bartlesville, Oklahoma.
4. TEST OBJECTIVE
* To determine the influence of the addition of methanol to gasoline on
evaporative emissions from light-duty vehicles.
5. SPONSORING AGENCY
U.S. Department of Energy
Bartlesville Energy Technology Center
Bartlesville, Oklahoma
Project Manager: Ken R. Stamper
Telephone No: 918-336-2400
6. CONTRACTOR
None
7. TEST CONDITIONS
Tests were performed using EPA's Sealed Housing for Evaporative Determina-
~*
Because of the unavailability of synfuels, the fuels used in some of these
programs were not "true" synfuels (e.g., methanol-derived from natural gas was
used instead of coal-derived methanol). These studies, however, are included
in this report because they were conducted to show what might be expected from
the combustion of actual synfuels in the indicated combustion systems.
A-144
-------
tions (SHED) test procedure which focuses on the measurement of evapora-
tive losses generated in two operations: diurnal and hot soak. The
diurnal portion of the test simulates a condition in which the temperature
of the fuel is raised from 60°F to 84°F (16°C to 29°C), due to the daily
temperature cycle. The hot-sock portion of the test is designed to simu-
late evaporative emissions resulting from the rise in temperature of the
fuel in the carburetor bowl, typical of the temperature rise which occurs
after a fully warmed engine is turned off.
8. ENVIRONMENTAL MONITORING
Hydrocarbons (corrected for methanol) and methanol.
9. PROJECT STATUS
Tests completed, and paper presented October 20-23, 1980.
10. RESULTS
Results from these tests show that using a 10 percent methanol/90 percent
gasoline blend increases evaporative emissions by 130 percent for short-
term use and 220 percent for long-term use, relative to the evaporative
emissions produced using a reference gasoline. The evaporative hydrocar-
bon emissions produced when the vehicles were operating on the methanol
blend had a slightly higher photochemical reactivity than those produced
from the reference gasoline.
11. REFERENCE
Stamper, K.R. Evaporative Emissions from Vehicles Operating on Methanol/
Gasoline Blends. SAE Technical Paper 801360, Presented to Society of
Automotive Engineers, Fuels and Lubricants Division, Baltimore, Maryland,
October 20-23, 1980. 12 pp.
A-145
-------
TEST 31
EXPERIMENTAL RESULTS USING METHANOL AND METHANOL/GASOLINE
BLENDS AS AUTOMOTIVE ENGINE FUEL
FUELS TESTED
Non-synfuels: two unleaded gasolines (Indolene and a commercial fuel)
were used as base fuels. Test data were obtained for each base fuel used
alone and in a blend with 5, 10, and 15 percent methanol and for pure
methanol.
TEST EQUIPMENT
The test equipment included a fleet of 10 cars of varying size (Table
A-50) and a stand-mounted 1975 350-CID engine.
TABLE A-50. TEST VEHICLES OPERATED ON METHANOL/GASOLINE FUEL BLENDS
Vehicle
Designation
A
B
C
D
E
F
G
H
I
J
K
Year and Make
1974 Chevelle
1974 Ford Torino
1975 Maverick
(non catalyst)
1975 Vega
1975 Chevelle
1975 Granada
(non catalyst)
1975 Dodge Dart
(non catalyst)
1975 Impala
1975 Monza
1975 Plymouth
(non catalyst)
1972 Buick
Engine
Size, CID
350
351
250
140
350
351
318
454
262
318
350
Transmission Carburetor
Automatic 2 bbl
2 bbl
1 bbl
1 bbl
2 bbl
2 bbl
2 bbl
4 bbl
2 bbl
2 bbl
4 bbl
Because of the unavailability of synfuels, the fuels used in some of these
programs were not "true" synfuels (e.g., methanol-derived from natural gas was
used instead of coal-derived methanol). These studies, however, are included
in this report because they were conducted to show what might be expected from
the combustion of actual synfuels in the indicated combustion systems.
A-146
-------
3. TEST SITE
Bartlesville Energy Research Center, Bartlesville, Oklahoma.
4. TEST OBJECTIVE
• To determine the emission and fuel-economy characteristics of methanol
and methanol/gasoline blends as automotive fuels.
5. SPONSORING AGENCY
Energy Research and Development Administration
Bartlesville Energy Research Center
Bartlesville, Oklahoma
The work was done, in part, in cooperation with the EPA.
Project Leader: J. R. Allsup
Telephone No: 918- 336-2400
6. CONTRACTOR
None.
7. TEST CONDITIONS
On the stand-mounted engine, test variables and engine parametric adjust-
ments included engine speed, exhaust gas recirculation rate, air-fuel
ratio, ignition timing, and compression ratio for 5, 10, 15, and 100 per-
cent methanol/gasoline blend fuels. The test vehicles were tested on a
chassis dynamometer to determine the influence of ambient temperature
(20°, 75°, and 100°F) using 5 and 10 percent methanol fuels. Five of the
test vehicles were also tested to determine the effects of sustained use
(5000-7500 miles) of gasoline/methanol blends (10 percent methanol).
These vehicles were repetitively driven over a controlled test route
during both summer and winter seasonal periods.
8. ENVIRONMENTAL MONITORING
Steady-state engine emissions of the following compounds were measured:
hydrocarbons, methanol, aldehyde, nitrogen oxides, and carbon monoxide.
9. PROJECT STATUS
Tests are completed, and report is dated January 1977. A companion study
involving the physical properties of the methanol/gasoline mixtures was
A-147
-------
conducted concurrently and will be made available as a Report of Investi-
gations entitled "Physical Properties of Gasoline/Methanol Mixtures" by
B.H. Eccleston and F.W. Cox.
10. RESULTS
Emissions data are summarized in Tables A-51 and A-52.
• The data indicate that for both base fuels, at normal ambient tempera-
ture, the average HC emissions were increased by addition of methanol
and were further increased (up to 30 percent) at higher temperatures;
the change in HC emissions due to methanol may be the result of methanol
in leaning the air/fuel ratio or to its effect in increasing fuel vapor
pressure.
• In general, aldehyde emissions increased with higher concentration of
methanol in the fuel. Levels of NOX emissions were unaffected by the
amount of methanol in the fuel but were slightly reduced as the ambient
test temperature was increased and slightly increased at cold ambient
temperature.
• CO was substantially reduced by the addition of methanol to the base
fuel at cold and median ambient temperatures. At high ambient tempera-
ture, CO emission levels varied erratically. In general, the fuels
containing methanol produced higher CO levels than the base fuels.
• Results from the dynamometer tests suggest that emissions a(re generally
affected to the extent that methanol addition affects air-fuel stoi-
chiometry, fuel heat content, and fuel vapor pressure.
• Results from the road tests indicate that vehicle emissions and fuel
economy were essentially unchanged during approximately 7,500 miles of
road testing; no engine or fuel system component failures were encoun-
tered during that testing.
• Results from the bench-mounted engine suggest that operation with pure
methanol may allow use of high-compression engines to realize improved
fuel energy economy with relatively low oxides of nitrogen emission.
11. REFERENCE
Allsup, J.R. Experimental Results Using Methanol and Methanol/Gasoline
Blends as Automotive Engine Fuel. BERC/RI-76/15, Bartlesville Energy
Research Center, Energy Research and Development Administration, Bartles-
ville, Oklahoma, January 1977. 81 pp.
A-148
-------
TABLE A-51. EXHAUST EMISSIONS AND FUEL RATE - VEHICLES A-E
Emissions, g/tnile:
CO
HC
NOX
Aldehydes
Methanol
Fuel economy, rr.i/10 btu:
Erni s s i on cy cle.....
Hifrhway cycle
Emissions, g/raiie:
CO
HC
NO ,
.-v
Aldehydes . . „
Kethanol
Fuel economy, mi/ 10" btu:
Emission cvcle
Highway cycle
Ambient temperature, °F
20
Base
fuel
57.
Me OH
10%
MeOH
75
Base
fuel
5%
MeOH
10%
MeOH
100
Base
fuel
57.
MeOH
10%
MeOH
BASE FUEL -- INDOLENE
48.8
2.7
2.1
.09
.01
8.7
15.4
39.1
2.6
2.1
.11
.08
8.6
15.4
35.0
2.3
2.0
.13
.13
8.7
15.1
17.7
1.4
2.0
.10
.01
10.0
15.9
14.2
1.6
1.9
.12
.08
9.8
15.9
10.9
1.8
1.9
.13
.15
9.7
15.6
25.8
1.6
1.8
.09
.02
10.2
16.4
44.0
2.0
1.6
.10
.10
9.6
15.8
34.2
2.1
1.7
.09
.17
9.8
15.9
BASE FUEL -- COMMERCIAL GASOLINE
48.2
2.5
1.9
.10
.02
9.5
16.8
42.3
2.5
1.9
.11
.08
9.0
15.9
32.1
2.6
2.0
.16
.14
8.7
15.2
18.7
1.3
1.8
.10
.02
10.1
15.9
13.2
1.6
1.8
.10
.08
9,8
15.2
9.6
1.7
1.7
.12
.15
9.6
14.9
19.7
1.6
1.7
.10
.02
10.3
16.5
28.3
2.1
1.6
.11
.10
10.0
16.3
19.6
2.3
1.7
.13
.17
9.8
15.8
-------
TABLE A-52. EXHAUST EMISSIONS AND FUEL RATE - VEHICLES A-J -
COMMERCIAL GASOLINE BASE FUEL/METHANOL BLENDS
tn
o
Dni.ssions, g/:nile:
CO -
HC .
NO ,
1 x
Fuel economy, mi/10" btu:
Ambient t o.npera ture^ °
2!"!
Clear
fuel.
40.3
2.5
1.9
.11
.01
9.3
15.8
57=
Mf.GH
35.7
2.6
2.1
.13
.08
9.1
15.3
10/:.
MoOH
29.?
2.8
2.0
.16
.15
8.9
14.8
-'cj
Clear
fuel
13.5
1 .1
2.1
.10
.02
10.0
15.9
5X.
Me OH
10.1
1.3
/.O
.11
.07
9.7
15.2
10/1
MeOlt
8.2
1.5
1.9
.12
.13
9.7
14.8
100
Clear
iuel
13.2
1.2
2.0
.09
.02
10.4
16.0
57-
MeOH
18.3
1.6
l.R
.10
.08
10.0
15.9
10%
MeOH
13.2
1.8
1.8
.12
.14
10.0
15.7
-------
TEST 32
FLEET TRIALS USING METHANOL/GASOLINE BLENDS
1. FUELS TESTED*
Non-synfuels: 10 percent methanol/90 percent gasoline blends.
2. TEST EQUIPMENT
The seven automobiles used in this study are described below in Table
A-53. The fuel metering hardware of the vehicles was not changed,
TABLE A-53. FLEET DESCRIPTION
Vehicle
No.
161
162
163
164
176
175
190
Vehicle
Description
1977 Chevrolet Impala
1977 Buick Skylark
1977 Ford LTD II
1977 Plymouth Fury
1978 Volvo 242 DL*
1978 Ford Pinto*
1978 Ford Fairmont
Engine
Disp. , CID
305
231
302
225
130
140
200
Carb.
2V
2V
2V
2V
FI
2V
IV
Test
I.W., Ib.
4,000
3,500
4,500
4,000
3,000
2,750
3,000
Vehicles are equipped with 3-way catalytic converters and closed-loop
A/F control.
3. TEST SITE
Bartlesville Energy Technology Center, Bartlesville, Oklahoma.
*
Because of the unavailability of synfuels, the fuels used in some of these
programs were not "true" synfuels (e.g., methanol-derived from natural gas was
used instead of coal-derived methanol). These studies, however, are included
in this report because they were conducted to show what might be expected from
the combustion of actual synfuels in the indicated combustion systems.
A-151
-------
4. TEST OBJECTIVE
0 To provide information on the fuel economy, driveability, emissions,
and the engine and fuel-handling component deterioration associated
with extended use of methanol/gasoline blends in current-production
automobiles.
5. SPONSORING AGENCY
U.S. Department of Energy
Bartlesville Energy Technology Center
Bartlesville, Oklahoma
Telephone No: 918-326-2400
6. CONTRACTOR
Same as sponsoring agency.
7. TEST CONDITIONS
The vehicles were operated over a course designed to accumulate mileage
at a rate and duty cycle similar to automobiles used by the private
sector. Vehicle tests were run at each 5,000-mile accumulation interval
to determine the fuel economy and the mass of pollutant emissions gene-
rated.
8. ENVIRONMENTAL MONITORING
CO, NO , unburned fuel, evaporative emissions of hydrocarbons and
/\
methanol.
9. PROJECT STATUS
The tests described in this report have been completed, although further
tests were recommended.
10. RESULTS
• The data show consistent reduction in CO emissions associated with the
use of the 10 percent methanol blend (see Figure A-18).
• The influence of the methanol blend on NOX emissions did not show a
consistent effect on the individual test vehicles. However, the 1977
model-year fleet showed slightly increased NOX emissions relative to
the emissions generated while operating on indolene, and the 1978
model-year fleet showed slightly decreased NOX emissions compared to
those from indolene-operating engines (see Figure A-19).
A-152
-------
c
o
to
to
UJ
r
-O
X
o
O)
i
en
c
o
o
1978 MY Fleet
Indolene
Methanol Blend
Mil
10 20 30 40 SO
eage Accumulation Level (K miles)
Figure A-18.
CO Emission Rates From 1977-MY and 1978-MY
Vehicles Operated Over the FTP Urban Cycle
on Indolene and Methanol/Gasoline Blends
to
c
o
CO
to
UJ
O) •
C7>
o
i-
+J
1/1
O)
-a
X
o
1978 MY Fleet
0Indolene
^Methanol
Blend
30
0 10 20 30 40
Mileage Accumulation Level (K miles)
Figure A-19.
NOX Emission Rates From Vehicles Operated Over the FTP
Urban Cycle on Indolene and Methanol/Gasoline Blends
A-153
-------
• The emission rates of unburned fuel from the test fleet show slight
increases associated with the use of 10 percent methanol blend over
test results from the fleet operating on indolene (see Figure A-20).
• The data showed a significant increase in evaporative emissions asso-
ciated with short-term use of the methanol blends and an even greater
increase when the methanol blend is used for extended periods.
11. REFERENCE
Stamper, K.R. Fleet Trials Using Methanol/Gasoline Blends. In: Pro-
ceedings of the IV International Symposium on Alcohol Fuels Technology,
Sao Paulo, Brazil, October 5-8, 1980. Vol. II. pp. 563-571.
1.30
0 10 20 30 40 90
Mileage Accumulation Level (K miles)
Figure A-20. UBF Emission Rates From Vehicles Operated Over the
FTP Urban Cycle on Indolene and Methanol/Gasoline
Blends
A-154
-------
TEST 33
GASOHOL FLEET OPERATIONS
1. FUELS TESTED*
Non-synfuel: gasohol and gasoline.
2. TEST EQUIPMENT
110 Southwestern Bell Telephone fleet vehicles.
3. TEST SITE
Bartlesville Energy Technology Center, Bartlesville, Oklahoma.
4. TEST OBJECTIVES
• To obtain comparative field experience and laboratory emission data
with gasohol and gasoline in controlled tests with units of a commer-
cial service fleet.
5. SPONSORING AGENCY
U.S. Department of Energy
Bartlesville Energy Technology Center
P. 0. Box 1398
Bartlesville, Oklahoma 74003
Project Manager: Jerry All sup
Telephone No: 918-336-2400
6. CONTRACTOR
Same as sponsoring agency.
7. TEST CONDITIONS
Operators of SWBT vehicles observed and recorded information from vehicles
during use in normal field service. Service records provided information
*
Because of the unavailability of synfuels, the fuels used in some of these
programs were not "true" synfuels (e.g., methanol-derived from natural gas was
used instead of coal-derived methanol). These studies, however, are included
in this report because they were conducted to show what might be expected from
the combustion of actual synfuels in the indicated combustion systems.
A-155
-------
on fuel economy and fuel system problems. Emissions and fuel economy
data were obtained from tests of the vehicles at BETC using a chassis
dynamometer to run EPA-prescribed test routines.
8. ENVIRONMENTAL MONITORING
Regulated pollutants.
9. PROJECT STATUS
Project complete.
10. RESULTS
• On the average, emissions were lower for vehicles fueled with gasohol,
but data is inadequate to conclude real differences.
0 Fuel economy was found to be unchanged between fuels, while driveabili-
ty was somewhat poorer with gasohol.
11. REFERENCE
Allsup, J. The BETC Fleet Test Program. In: Proceedings of Conference
on Fleet Use of Unique Automotive Fuels; Report No. MED117, August 13-14,
1980.
A-156
-------
TEST 34
EVAPORATIVE EMISSIONS FROM METHANOL/GASOLINE BLENDS
1. FUEL TESTED*
Non-synfuel: unleaded low-octane indolene and a 10 percent methanol/90
percent indonene blend.
2. TEST EQUIPMENT
Two automotive vehicles.
3. TEST SITE
Bartlesville Energy Technology Center, Bartlesville, Oklahoma.
4. TEST OBJECTIVE
• To determine the effect of short-term and long-term canister service
on evaporative emissions from vehicles using the above indicated fuels.
5. SPONSORING AGENCY
U.S. Department of Energy
Bartlesville Energy Technology Center
P. 0. Box 1398
Bartlesville, Oklahoma 74003
Project Manager: Jerry Allsup
Telephone No: 918- 336-2400
6. CONTRACTOR
Same as sponsoring agency.
7. TEST CONDITIONS
The original canisters were aged by operating the vehicles on 10 percent
methanol blends over routine duty for an extended period. Additional
*
Because of the unavailability of synfuels, the fuels used in some of these
programs were not "true" synfuels (e.g., methanol-derived from natural gas was
used instead of coal-derived methanol). These studies, however, are included
in this report because they were conducted to show what might be expected from
the combustion of actual synfuels in the indicated combustion systems.
A-157
-------
tests were run on both test fuels using fresh canisters to determine
effects of short-term service with methanol blends.
8. ENVIRONMENTAL MONITORING
Evaporative emissions (hydrocarbons),
9. PROJECT STATUS
Project complete.
10. RESULTS
® Aged canisters resulted in a 90 percent increase in evaporative losses
over fresh canisters with the vehicle operating on the methanol blend.
t Data from the short-term use of methanol blends indicated that a 75
percent increase in evaporative emissions would result with the blend
over a straight gasoline.
t Effect of long-term canister service on evaporative emissions operating
on methanol blends indicated that either fuel modifications or emission
control design modification must be made before emissions standards can
be met with this type of fuel.
« There are indications that the "Sealed Housing for Evaporative Determi-
nation" test procedure employed was not completely adequate to simulate
in-use evaporative losses from light-duty vehicles.
11. REFERENCE
Allsup, J. The BETC Fleet Test Program. In: Proceedings of Conference
on Fleet Use of Unique Automotive Fuels Report No. MED117, August 13-14,
1980.
A-158
-------
TEST 35
PERFORMANCE EVALUATION OF ALCOHOL-GASOLINE BLENDS
IN LATE MODEL AUTOMOBILES
1. FUELS TESTED*
Non-synfuels: ethanol/gasoline fuel blends, and methanol/gasoline fuel
blends.
2. TEST EQUIPMENT
Fourteen test vehicles as indicated in Table A-54.
3. TEST SITE
Anaheim, California.
4. TEST OBJECTIVES
• Performance evaluation of alcohol-gasoline blends in late-model auto-
mobiles.
• Experimental evaluation of the effect of ethanol and methanol in
gasoline on: 1) exhaust emissions; 2) evaporative emissions; and
3) vehicle driveability.
5. SPONSORING AGENCIES
U.S. Department of Energy and
Coordinating Research Council (CRC)
Atlanta, Georgia
CRC Contract No. CM-125-1-79
Project Officer: Al Zingle
Telephone No: 404-396-3400
6. CONTRACTOR
Systems Control, Inc.
Environmental Engineering Division
421 E. Cerritos Avenue
Anaheim, California 92805
*
Because of the unavailability of synfuels, the fuels used in some of these
programs were not "true" synfuels (e.g., methanol-derived from natural gas was
used instead of coal-derived methanol). These studies, however, are included
in this report because they were conducted to show what might be expected from
the combustion of actual synfuels in the indicated combustion systems.
A-159
-------
TABLE A-54. TEST VEHICLE DESCRIPTION
CT>
O
VEHICLE
NUMBER
G-l
G-2
G-3
G-4
G-5
G-6
G-7
G-8
G-9
G-10
G-ll
G-12
G-13
G-14
MAKE
Plymouth
Plymouth
Dodge
Dodge
Volvo
Dodge
Buick
Buick
Chevrolet
Ford
Ford
Ford
Ford
Cadillac
MODEL
Horizon
Horizon
Omni
Omni
DL
Aspen
Century
Century
Impala
Pinto
Pinto
Pinto
Pinto
Eldorado
VEHICLE ID.
NUMBER
ML24AAD102722
ML24AAD186522
ZL24AAD230651
ZL24AAD230652
VC24245A1166691
NE41CAF150663
4L69AAZ116617
4L69AAZ1 16703
1L69HAC114146
OT10A149924
OT10A142387
OT10A152199
OT10A152198
6L57AE617086
ENGINE
SIZE
105
105
105
105
2.3L
225
231
231
305
2.3L
2.3L
2.3L
2.3L
3f.O
INERTIA
WEIGHT
2,625
2,625
2,625
2,625
3,000
4,000
3,500
3,500
4,000
3,000
3,000
3,000
3,000
4,250
ACTUAL
HORSEPOWER
6.8
6.8
6.8
6.8
12.5
11.6
11.3
11.3
10.3
9.7
9.7
9.7
9.7
11.8
CONTROL
SYSTEM
Open
Open
Closed
Closed
Closed
Open
Closed
Open
Open
Open
Open
Closed
Closed
Closed
-------
Program Manager: Richard Carlson
Telephone No: 714-956-5450
7. TEST CONDITIONS
This program is divided into a program start-up phase and two testing
phases (Phase I for ethanol/gasoline fuel blends and Phase II for methanol/
gasoline fuel blends).
8. ENVIRONMENTAL MONITORING
Ethanol, aldehyde, methanol, hydrocarbon, carbon monoxide, and nitrogen
oxides.
9. PROJECT STATUS
Work performed to date includes the following: 1) fuel and vehicle
acquisition; 2) vehicle preparation including 4,000 mile break-in; 3)
demonstration testing; and 4) Phase I emissions, fuel economy, and drive-
ability testing was completed in April 1981. Phase II of the program is
to be completed in 1982.
10. RESULTS
None reported to date. A draft final report is currently being prepared
for Phase I results and should be available by the end of 1981. A draft
final report for Phase II will be prepared in 1982.
11. REFERENCE
Carlson, R.R. "Performance Evaluation of Alcohol-Gasoline Blends in Late
Model Automobiles". In: Proceedings of Conference on Fleet Use of Unique
Automotive Fuels Report No. MED117, August 13-14, 1980.
A-161
-------
TEST 36
DETERMINATION OF INDIVIDUAL ALDEHYDE CONCENTRATIONS IN THE
EXHAUST OF A SPARK IGNITED ENGINE FUELED BY ALCOHOL/GASOLINE BLENDS
1. FUEL TESTED*
Non-synfuels: 100 percent Indolene; 20 percent ethanol/80 percent Indo-
lene (20E); 20 percent methanol/80 percent Indolene (20M); and 30 percent
methanol/70 percent Indolene (30M).
2. TEST EQUIPMENT
A 1963 four-cylinder Pontiac engine modified with a 1974 cylinder head
and camshaft. The compression ratio was 8.1:1.
3. TEST SITE
Department of Mechanical Engineering, University of Miami, Coral Gables,
Florida.
4. TEST OBJECTIVE
§ To measure and compare individual aldehyde emissions from an alcohol/
gasoline blend fueled engine operated at various fuel-air equivalence
ratios.
5. SPONSORING AGENCY
U.S. Department of Energy
Heavy Duty Transport and Fuels Utilization
1000 Independence Avenue, S.W.
Washington, D.C. 20585
Project Officer: Euqene Ecklund
Telephone No: 202 -252-8055
Because of the unavailability of synfuels, the fuels used in some of these
programs were not "true" synfuels (e.g., methanol-derived from natural gas was
used instead of coal-derived methanol). These studies, however, are included
in this report because they were conducted to show what might be expected from
the combustion of actual synfuels in the indicated combustion systems.
A-162
-------
6. CONTRACTOR
Department of Mechanical Engineering
University of Miami
Project Manager: Robert R. Adt, Jr.
Telephone No: 305-284-2571
7. TEST CONDITIONS
Engine was operated at steady-state conditions, 2000 rpm and minimum
spark advance for maximum torque with fuel-air equivalence ratios of
0.96, 0.90, and 0.82. During operation at 0.82, the engine experienced
lean-limit misfiring.
8. ENVIRONMENTAL MONITORING
Total aldehydes, formaldehyde, acetaldehyde, acetone, propionaldehyde,
and acrolein.
9. PROJECT STATUS
Project complete; final report presented in October 1979.
10. RESULTS
• Total aldehydes (including acetone) increase 25 percent in going from
Indolene to 20E, 10 percent to 20M, and 30 percent to 30M.
• Aldehyde concentrations in the engine exhaust are generally a stronger
function of fuel blend than equivalence ratio.
• Formaldehyde is the largest component of the total aldehydes; up to
70-90 mole percent of the total.
• The emissions of formaldehyde and acetaldehyde are strongly controlled
by the content of methanol and ethanol in the fuel, respectively.
t Acetone concentration increases as the lean misfire limit is approached
(* = 0.82).
• Acrolein concentration decreases slightly with increasing alcohol blend
level.
t Aldehydes are partially destroyed in the exhaust system and virtually
completely destroyed in the catalyst.
11. REFERENCE
Harrenstien, M.S., K.T. Rhee, and R.R. Adt. Determination of Individual
Aldehyde Concentrations in the Exhaust of a Spark Ignited Engine Fueled
by Alcohol/Gasoline Blends. SAE Paper No. 790 952. 1-4 October 1979.
A-163
-------
TEST 37
METHANOL AS A BOILER FUEL
1. FUELS TESTED*
Reference fuels: methanol, natural gas, and residual oil No. 6.
2. TEST EQUIPMENT
A small scale boiler test stand and a Babcock & Wilcox R-B95 utility
boiler with a rated capacity of 425,000 Ib/hr steam and a net capability
of 49 MW.
3. TEST SITE
Boiler test stand: Coen Co., Burligame, California.
Utility boiler: A.B. Patterson steam generating station, New Orleans,
Louisiana.
4. TEST OBJECTIVES
• Demonstrate the use of methanol in external combustion boiler systems.
0 Compare boiler performance and emissions of methanol and conventional
fuel combustion.
5. SPONSORING AGENCY
Vulcan Cincinnati, Inc.
Cincinnati, Ohio
Program Manager: R.W. Duhl
Telephone No: 513-281-2800
6. CONTRACTOR
None.
*
Because of the unavailability of synfuels, the fuels used in some of these
programs were not "true" synfuels (e.g., methanol-derived from natural gas was
used instead of coal-derived methanol). These studies, however, are included
in this report because they were conducted to show what might be expected from
the combustion of actual synfuels in the indicated combustion systems.
A-164
-------
7. TEST CONDITIONS
All fuels were tested at two excess air levels and at load levels of 100,
75, and 50 percent. Methanol firing required a centrifugal pump and
Babcock & Wilcox 85° "Y" type burner tips; no other changes were made.
8. ENVIRONMENTAL MONITORING
NOV, CO, and aldehydes.
X
9. PROJECT STATUS
Testing was conducted in 1972. Final report dated December 1972.
10. RESULTS
In the boiler stand test, combustion of methanol produced NO emissions
A
one-fourth and one-tenth of those produced by natural gas and No. 6 resi-
dual oil, respectively.
The results of the utility boiler test program are highlighted below and
in Figure A-21.
• No particulate or sulfur compounds were emitted during methanol com-
bustion.
t NO/ emission levels of methanol were 7-14 percent of those measured
during residual oil combustion.
• CO emission levels of methanol were less than 100 ppm and generally
less than those observed for the residual oil.
o Organic acids and aldehydes were generally less than 10 and 1 ppm,
respectively. These emissions, as well as hydrocarbon emissions, were
considered negligible.
11. REFERENCES
t Hagen, D.L. "Methanol as a Fuel: A Review With Bibliography". Paper
No. 770792, Irr. Passenger Car Meeting, Detroit, Michigan, September
1977.
• Vulcan Cincinnati, Inc. "Methyl Fuel Combustion Test, Vol. I and II".
Report of Test at A.B. Paterson Plant, Restricted to the Sponsors.
December 15, 1972, 1000 pp.
• Duhl, R.W. and T.O. Wentworth (Vulcan Cincinnati, Inc.). "Methyl Fuel
From Remote Gas Sources". Am. Instit. Chem. Eng. Soc. Calif. Section
llth Annual Mtg., April 16, 1974, Los Angeles, CA.
A-165
-------
Duhl, R.W. (Vulcan Cincinnati, Inc.). "Methanol, A Boiler Fuel Alter-
native". Am. Inst. Chem. Eng., 8th Annual Mtg., Boston, Mass., Sept.
7-10, 1975.
Duhl, R.W. "Methanol as a Boiler Fuel". Submitted for Publication,
Chem. Eng. Prog., February 1976.
Duhl, R.W. (Vulcan Cincinnati, Inc.) and J.W. Boylan (A.M. Kinney,
Inc.). "Use of Methanol as a Boiler Fuel". IV A - Symposium Swedish
Academy of Engineering Sciences, Stockholm, Sweden, March 23, 1976.
31
-
3.30
jg.^0
CC
IU
°-.20
ffi
£.15
a.to
.05
METHANOL .
20 30 40 50 60
UNIT LOAD-MEGAWATTS
Figure A-21.
NOX Emission Levels of Methanol,
Natural Gas, and Oil
A-166
-------
TEST 38
CHARACTERIZATION OF EMISSIONS FROM METHANOL AND
METHANOL/GASOLINE BLENDED FUELS
1. FUELS TESTED*
Non-synfuels: M-20 fuel (methanol/Indolene clear fuel - 20/80 volume
percent); pure methanol, and Indolene clear fuel.
2. TEST EQUIPMENT
Vehicle test: 1975 Ford LTD with 400 CID engine; automatic transmission
and air conditioning operating during test.
Engine test: a 1975 Ford, 400 CID engine without EGR.
3. TEST SITE
Scientific Research Laboratory, Dearborn, Michigan.
4. TEST OBJECTIVES
• To develop techniques for the quantitative analysis of methanol in
vehicle exhaust.
• To compare the influence of fuel composition on the aliphatic, aroma-
tic, and oxygenated hydrocarbon emissions.
5. SPONSORING AGENCY
Ford Motor Company
Scientific Research Laboratory
Dearborn, Michigan
Telephone No: 313 - 322-3494
6. CONTRACTOR
None.
*
Because of the unavailability of synfuels, the fuels used in some of these
programs were not "true" synfuels (e.g., methanol-derived from natural gas was
used instead of coal-derived methanol). These studies, however, are included
in this report because they were conducted to show what might be expected from
the combustion of actual synfuels in the indicated combustion systems.
A-167
-------
7. TEST CONDITIONS
The vehicle was operated at steady state and over a Federal test procedure
CVS-C/H certification cycle on a chassis dynamometer. The engine was run
at steady-state conditions using the following speed/load map:
Point 1: Speed = 1000 rpm
Load = WOT
0 FA =1.1
Spark = MBT
Point 2: Speed = 1000 rpm
Load = 25 percent of WOT
0 FA = 0.95
Spark = MBT
Point 3: Speed = 3000 rpm
Load = WOT
0 FA =1.1
Spark = MBT
Point 4: Speed = 3000 rpm
Load = 25 percent of WOT
0 FA = 0.95
Spark = MBT
8. ENVIRONMENTAL MONITORING
Total hydrocarbons (as propane) and specific organics.
9. PROJECT STATUS
Project completed and presented in February 1981.
10. RESULTS
A summary of the results are presented in Figures A-22 to A-24; general
findings are listed below:
Vehicle Chassis Dynamometer Test
• M-20 fuel gave significantly higher hydrocarbon and aromatic emissions
than Indolene fuel without a catalyst. M-20 fuel gave only slightly
higher aliphatic hydrocarbon, aldehyde, and aromatic emissions than
Indolene in the presence of a catalyst.
Engine Dynamometer Test
• Methanol and aldehyde emissions from 100 percent methanol fuel com-
prised more than 98 mole percent of total measured hydrocarbons.
t Methanol comprised about 50 percent of the hydrocarbon emissions at
lower operating speeds of engine with M-20 fuel.
A-168
-------
I
CT)
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0
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EH3 20% METHANOL, 80% INDOLENE
d IOO% INDOLENE
P**%
^^ ^
Hi | 11 1 IS ft fc ra
TOTAL METHYL TOTAL TOTAL I-OCTANE TOTAL TOLUENE BENZENE
HC (C3) ALCOHOL ALDEHYDES ALKANES x 10 AROMATICS x 10 x 10
xl xlO xlO x5 xlO
Figure A-22. A Comparison of Tailpipe Emissions (Post-catalyst) From a
Vehicle Burning 20% Methanol/80% Indolene and 100% Indolene
(CVS C/H - Cycle #1)
-------
1500-
Q.
a
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Figure A-23. The Effect of Engine Parameters on Emissions
Using 100% Indolene Fuel
-------
1500-
a.
QL
z~ 1000-
o
cr
»-
z
Ul
o
z
o
10
LU
O
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500-
TOTAL
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Xl
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xi
TOTAL
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3000 RPM - WOT
300ORPM -25% LOAD
TOTAL
ALKANES
X5
I-OCTANE
x 10
TOTAL
AROMATICS
xtO
TOLUENE
xlO
BENZENE
xlO
Figure A-24. The Effect of Engine Parameters on Emissions Using
20% Methanol/80% Indolene Fuel
-------
• Total aldehyde emissions from pure methanol fueled engine were 2-3
times higher under most operating conditions than those emitted from
Indolene clear and M-20 fueled engines.
• In general, all hydrocarbon species decrease in concentration with
increasing exhaust temperatures (higher rpm).
11. REFERENCE
Schuetzle, D., T.J. Prater, and R.D. Anderson. "Characterization of Emis-
sions From Methanol/Gasoline Blended Fuels". SAE Technical Paper No.
810 430. 23-27 February 1981.
A-172
-------
TEST 39
COMPARATIVE MUTAGENICITY OF COMBUSTION EMISSIONS OF A
HIGH QUALITY NO. 2 DIESEL FUEL DERIVED FROM
SHALE OIL AND A PETROLEUM-DERIVED NO. 2 DIESEL FUEL
1. FUELS TESTED
Synfuel: diesel fuel marine (refined from Paraho crude by SOHIO).
Reference fuel: petroleum-derived No. 2 diesel fuel (see Table A-55)
TABLE A-55. FUELS ANALYSIS
Analysis
API Gravity
Density @ 15°C Kg/liter
% Sulfur
Cetane Index
% Carbon
% Hydrogen
% Nitrogen
Distillation Range
IBP
10%
50%
90%
EP
FIA
% Saturates
% Olefins
% Aromatics
Shale
38.8
0.8359
0.024
57.0
84.08
14.96
<0.01
395°F
450°F
503°F
553°F
574°F
61.6
4.1
34.3
Petroleum #lf
35.5
0.8469
0.16
48.0
84.59
14.81
<0.01
380°F
427°F
504°F
600° F
642°F
66.2
1.3
32.5
t
Hydrotreated Diesel Fuel Marine courtesy of Navy Shale Oil refining
run.
Local #2 diesel fuel from Phillips Petroleum, Couch V.
A-173
-------
2. TEST EQUIPMENT
Test vehicle was a prototype turbocharged diesel Volkswagen Rabbit
(European Golf). The vehicle was equipped with a 1.5 liter prototype
injection engine with a rated 70 hp at 4,800 rpm.
3. TEST SITE
U.S. Department of Transportation, Cambridge, Massachusetts.
4. TEST OBJECTIVE
• To determine the relative quantity of mutagenic materials contained
in diesel fuels from synfuels as compared to those prepared from
petroleum.
5. SPONSORING AGENCIES
U.S. Environmental Protection Agency
Environmental Research Center
Research Triangle Park, North Carolina
U.S. Department of Transportation
Transportation Systems Center
Cambridge, Massachusetts
Project Officer: J. Sturm
Telephone No: 617- 494-2716
6. CONTRACTOR
None
7. TEST CONDITIONS
The vehicle was repetitively operated on a chassis dynamometer to simulate
an actual driving pattern; the highway fuel economy test cycle (HWFET).
This cycle is 12.75 minutes long over 10.24 miles at an average speed of
48 miles per hour.
8. ENVIRONMENTAL MONITORING
HC, NOX, CO, particulates, particulate matter composition, and mutagenici-
ty of particulates (Ames test).
9. PROJECT STATUS
Project is completed. Paper presented June 23-24, 1980.
A-174
-------
10. RESULTS
Generally, the HC and CO emissions were found to be lower and NO levels
A
higher for the shale-derived fuel as compared to the petroleum-derived
fuel. The particle emission rate and fuel economy values were similar
with both fuels. The emissions from the shale-derived fuel were somewhat
higher in extractable organics.
The emissions were measured by DOT as 0.14/0.89/1.07 grams per mile of
HC/CO/NO , respectively. Using the Federal Test Procedure driving cycle,
,A
this vehicle emitted 0.17 grams of particles per mile, which would meet
the newly proposed EPA standard of 0.2 g/mile (the fuel used in these
tests was not specified).
The mutagenic activity of the organics from the particle emissions was
similar for the two fuels, but because the shale-fuel sample was somewhat
higher both in mutagenic activity and extractable organics, the rever-
tants/mile was greater for the shale-derived fuel (see Table A-56).
11. REFERENCE
Huisingh, J.L., et al. Comparative Mutagenicity of Combustion Emissions
of a High Quality No. 2 Diesel Fuel Derived From Shale Oil and a Petro-
leum Derived No. 2 Diesel Fuel. In: Proceedings of the Symposium on
Health Effects Investigation of Oil Shale Development, Sponsored by the
U.S. Environmental Protection Agency, Gatlinburgh, Tennessee, June 23-24,
1980. Ann Arbor Science Publishers, Inc., Ann Arbor, Michigan, 1981.
255 pp.
TABLE A-56. COMPARISON OF THE MUTAGENIC EMISSION RATE*
BETWEEN A PETROLEUM AND SHALE DERIVED FUEL IN
SALMONELLA TYPHIMURIUM TA98 WITHOUT ACTIVATION
Petroleum
Shale
Rev/
yg Org.
5.10
7.68
% Ext
17.8
21.4
Rev x 105/
gm Part.
9.08
16.43
Per
gm/mi
0.18
0.17
Revertants/
Mile
163,000
279,000
Turbocharged VW Rabbit diesel vehicle (56.4 mi/gal).
A-175
-------
TEST 40
REPORT ON THE METHANOL-POWERED BANK OF AMERICA VEHICLE FLEET
IN SAN FRANCISCO AND LOS ANGELES
1. FUELS TESTED*
Reference fuels: simple blends of methanol and gasoline ranging between
2 and 18 percent by volume.
2. TEST EQUIPMENT
93 vehicles from the Bank of America fleet. 44 were control vehicles, 49
were run on the blends.
3. TEST SITE
San Francisco and Los Angeles areas.
4. TEST OBJECTIVES
• To demonstrate the practicality of using the various kinds of blends.
5. SPONSORING AGENCY
Bank of America
San Francisco, CA (Headquarters)
6. CONTRACTOR
Carson Associates
4117 Robertson Boulevard
Alexandria, VA 22309
Project Manager: Mr. Gavin McGurdy
Telephone No: 703-780-8284
7. TEST CONDITIONS
Fleet tested in California from February 1980 to present.
*
Because of the unavailability of synfuels, the fuels used in some of these
programs were not "true" synfuels (e.g., methanol-derived from natural gas was
used instead of coal-derived methanol). These studies, however, are included
in this report because they were conducted to show what might be expected from
the combustion of actual synfuels in the indicated combustion systems.
A-176
-------
8. ENVIRONMENTAL MONITORING
CO, NO, and unburned hydrocarbons.
9. PROJECT STATUS
Intensive data gathering in November, December, and January (80-81).
Bank now expanding use of blends at 2 and 4 percent levels. The contrac-
tor is continuing to supply support.
10. RESULTS
• Use of 2 and 4 percent blends recommended.
• Blends are practical and economical, result in improved mileage in new
cars and decrease emissions of CO and unburned hydrocarbons.
• An operating cost decrease of l
-------
TEST 41
ADVANCED COMBUSTION SYSTEMS FOR
STATIONARY GAS TURBINE ENGINES
1. FUELS TESTED
Synfuel: shale-derived diesel fuel marine (DFM).
Reference fuels: No. 2 fuel, No. 2 fuel with 0.5 percent nitrogen.
2. TEST EQUIPMENT (See Figures A-25 and A-26)
Utilizing a Rich Burn/Quick Quench concept from bench scale model evalua^
tions, two configurations of a full-scale prototype (25 megawatt engine
size) gas turbine combustor were constructed and tested.
3. TEST SITE
Pratt and Whitney Aircraft, West Palm Beach, Florida.
4. TEST OBJECTIVES
• Identify, evaluate, and demonstrate alternative combustor design con-
cepts for significantly reducing the production of NOX in stationary
gas turbine engines.
• Program goals were 50 ppmv NOX (at 15 percent 03) for non-nitrogenous
fuels, and 100 ppmv NOX (at 15 percent 02) for oil or gas containing
0.5 percent nitrogen by weight. The goal for CO was 100 ppmv (at 15
percent 02).
5. SPONSORING AGENCY
U.S. Environmental Protection Agency
Industrial Environmental Research Laboratory
Office of Environmental Engineering and Technology
Research Triangle Park, NC
Project Officer: W. S. Lanier
Telephone No: 919-541-2432
6. CONTRACTOR
United Technologies Corporation
Pratt and Whitney Aircraft Group
Government Products Division
West Palm Beach, Florida
A-178
-------
I
WD
Figure A-25. Full-Scale Combustor Scheme FS-03A
Figure A-26. Full-Scale Combustor Scheme FS-04
-------
Program Manager: Robert M. Pierce
Telephone No: 305-840-2239
7. TEST CONDITIONS
Test conditions are summarized in Table A-57 below. (For a complete list
of test parameters, see referenced document.)
TABLE A-57. TEST CONDITIONS
Combustor
Configuration
FS-03A
FS-03A
FS-03A
FS-03A
FS-03A
FS-03A
FS-04B
FS-04B
FS-04B
FS-04B
Fuel Type
No. 2 fuel with 0.5% N
No. 2 fuel, No. 2 fuel
with 0.5% N
No. 2 fuel, No. 2 fuel
with 0.5% N
Shale DFM
Shale DFM
No. 2 fuel
Shale DFM
Shale DFM
No. 2 fuel
No. 2 fuel
Power
Level
100%
100%
100%
100%
100%
100%
Idle
50%
Idle
50%
Inlet Air
Temp., °F
400
450
575
475
570
570
320
550
320
550
Rig Pressure
psia
50
50
100
50
100
100
40
96
40
96
8. ENVIRONMENTAL MONITORING
NO , CO, and unburned hydrocarbons.
A
9. PROJECT STATUS
Research was conducted from 1 January 1978 through 12 April 1979. Final
report is dated January 1980.
10. RESULTS
The results of the Rich Burn/Quick Quench combustor emission tests are
summarized in Figures A-27 through A-34, and highlighted below.
A-180
-------
500
FS-03A 10)
D NOX No. 2 Fuel
OCO No. 2 Fuel
(Runs FS03A 1
NOX No. 2 Fuel
With 0.5% N
CO No. 2 Fuel
With 0.5% N
50 psm
450°F
500
0.1 0.2 0.3
Overall Equivalence Ratio
(Runs FS-03A-11-*-FS-03A-20)
I I
NOX No. 2 Fuel With 0.5% N
CO No. 2 Fuel With 0.5% N
50 psia
400°F
0.1 0.2 0.3
Overall Equivalence Ratio
Figure A-27.
Variation in Emission Concentrations with
Overall Equivalence Ratio for Scheme
PS-03A, First Test Series
Figure A-28.
Variation in Emission Concentrations with
Overall Equivalence Ratio for Scheme
PS-03A, Second Test Series
-------
500
00
rsi
NOX No. 2 Fuel
With 0.5% N
CO No. 2 Fuel
With 0.5% N
500
0.1 0.2 0.3
Overall Equivalence Ratio
50 psia
475°F
Shale DFM
0.1 0.2 0.3
Overall Equivalence Ratio
0.4
Figure A-29.
Variation in Emission Concentrations with
Overall Equivalence Ratio for Scheme
PS-03A, Third Test Series
Figure A-30.
Variation in Emission Concentrations with
Overall Equivalence Ratio for Scheme
PS-03A, Fourth Test Series
-------
500
3=.
i
co
OJ
100psia
570°F
Shale DFM
500
0
0.1 0.2 0.3
Overall Equivalence Ratio
0^400
c.
0.
C
o
u
c
o
O
c
o
E
LU
300
200
100
(Runs FS-03A-47
QNO
OGO
100 psia
570°F
No. 2 Fuel
0.1 0.2 0.3
Overall Equivalence Ratio
Figure A-31.
Variation in Emission Concentrations with
Overall Equivalence Ratio for Scheme
PS-03A, Fifth Test Series
Figure A-32.
Variation in Emission Concentrations with
Overall Equivalence Ratio for Scheme
PS-03A, Sixth Test Series
-------
(Runs FS-04B-8, 13. & 14)
CM
o
a
3
ruo
800
500
400
NO,, CO Damper Setting
Q Q — ldl«
£ V iov« Po*«'
Sh»l» DFM ^
.-
**s
O £f-
\
°o o.i 0.2 o.:
700
600
CM
O
ss
in
Z 500
E
Q.
a.
in
C
O
c
a.)
o
c
O
o
o
E
in
400
300
200
100
0
(R
! 1
uns FS-04B-6, 7, and 9 to 12)
i i i
NOX CO Damper Setting
O
A
f*~^
y
i
JL
/
i
i
i
i
v— ^
jf\
1 \
lo\
o
V
No. 2
7
Idle
50% Po\
Fuel
ner
Overall Equivalence Ratio
0 0.1 0.2 0.3 0.4
Overall Equivalence Ratio
0.5
Figure A-33.
Variation in Emission Concentrations with
Overall Equivalence Ratio for Scheme
FS-04B Firing Shale DFM
Figure A-34.
Variation in Emission Concentrations with
Overall Equivalence Ratio for Scheme
FS-04B Firing No. 2 Fuel
-------
• Both combustor configurations (longer and shorter primary zone resi-
dence lengths) met emission goals of the program on both non-nitro-
genous and nitrogen-bearing fuels.
• The Rich Burn/Quick Quench combustor also met the program emission
goal while operating on a shale-derived diesel fuel marine. This
indicates the potential for handling other alternative fuels (both
shale oil and coal derived) by this combustion concept.
• Variable geometry was successfully employed to vary the airflow ad-
mitted into the primary combustion volume. This demonstrated the
ability to meet the program emission goals over the range of operating
conditions experienced in a typical 25-Mw GTE.
• Unburned hydrocarbon emissions from combustor FS-03A ranged from 0.9-
7.3 ppmw for No. 2 fuel; 1.1-21.8 ppmv for No. 2 fuel with 0.5 percent
N; and 1.3-15.3 ppmv for shale DFM at 15 percent 02-
11. REFERENCE
Pierce, R.M., C.E. Smith, and B.S. Hintan. Advanced Combustion Systems
for Stationary Gas Turbine Engines: Volume III. Combustor Verification
Testing. Prepared by United Technologies Corp. for U.S. Environmental
Protection Agency. EPA-600/7-80-017c. January 1980.
A-185
-------
TEST 42
ADVANCED COMBUSTION SYSTEMS FOR
STATIONARY GAS TURBINE ENGINES
1. FUELS TESTED (See Table A-58)
Synfuels: SRC-II middle distillate fuel oil and shale-derived residual
oil.
Reference fuels: No. 2 fuel and an Indonesian/Malaysian residual oil.
2. TEST EQUIPMENT (See Table A-59)
A prototype full-scale (25 megawatt engine size) Rich Burn/Quick Quench
gas turbine with two combustor configurations.
3. TEST SITE
Pratt and Whitney Aircraft, West Palm Beach, Florida.
4. TEST OBJECTIVES
• Identify, evaluate, and demonstrate the effects of a Rich Burn/Quick
Quench combustor on NOX formation while burning synthetic liquid and
residual fuel oils.
• Program goals were 50 ppmv NOX (at 15 percent Q£) for non-nitrogenous
fuels, and 100 ppmv NOX (at 15 percent 02) for oil or gas containing
0.5 percent nitrogen by weight. The goal for CO was 100 ppmv (at 15
percent 02).
5. SPONSORING AGENCY
U.S. Environmental Protection Agency
Industrial Environmental Research Laboratory
Office of Environmental Engineering and Technology
Research Triangle Park, NC
Project Officer: W.S. Lanier
Telephone No: 919-541-2432
6. CONTRACTOR
United Technologies Corporation
Pratt and Whitney Aircraft Group
Government Products Division
West Palm Beach, Florida
A-186
-------
TABLE A-58. COMPARISON OF FUEL PROPERTIES FOR TEST FUELS"
Specific Gravity
Viscosity,
centi stokes
Surface Tension
dynes/cm
Heat of Combustion
(net) Btu/lbm
Pour Point, °F
Flash Point, °F
Ultimate Analysis
Carbon%
Hydrogen %
Nitrogen %
Sulfur %
Ash %
Oxygen %
Conradson Carbon,
Residue %
End Point, °F
Atmos. Distillation
Carbon/Hydrogen
Ratio (by wt)
Hydrogen/Carbon
Molar Ratio
No. 2
(Typical)
0.84
(60°F)
5.0
(60°F)
25.7
(60°F)
18,700
<5
>130
87.0
12.8
<0.02
0.04-0.48
<0.003
<0.09
<0.30
640
6.537
1.823
SRC-II
Middle
Distillate
0.97
(609F)
6.3
(60°F)
33.3
(60°F)
17,235
<-45
>160
85.77
9.20
0.95
0.19
0.001
3.89
0.03
541
9.323
1.278
Indonesian/
Malaysian
Res id
0.87
(210°F)
11.6
(210°F)
22. 6-1-
(210°F)
17,980
61
210
86.53
11.93
0.24
0.22
0.036
—
3.98
NA
7.253
1.643
Shale
Res id
0.82
(210°F)
3.3
(210°F)
20. 6f
(210°F)
18,190
90
(remains waxy)
235
86.71
12.76
0.46
0.03
0.009
0.03
0.19
700
6.795
1.754
7t
Fuel properties are given at stand delivery temperatures to be maintained in
test program.
Estimate on basis of fuel specific gravity.
A-187
-------
TABLE A-59. SUMMARY OF COMBUSTOR DESIGN FEATURES
Premized Configuration
(Scheme FS-05A/B)
Nonpremixed Configuration
(Scheme FS-07A)
High Temperature
Rise Configuration
^Scheme FS-08A)
Type Com bust or
I-ength (Primary)
length (Dilution)
length (O%'ernll)
Combustor Can. Convert ivp
Primflry Zone Codling. Finned
Serondnry Zone
19.0 in.
8.0 in.
48.0 in. (including transition
section to turbine inlet)
Copibustor Can. Convertivp
Primnrv Zone Cooling. Finned
Secondary /one
19.0 in.
8.0 in.
4.'t.2 in. (including transition
section to turbine inlet)
Combustor Can. Convpctive
Primarv 7,one Cooling. Finned
Secondary Zone
19.0 in.
8.0 in.
4:1.2 in. (including transition
section to turbine inlet)
Outer Diameter
!nner Diameter
Combustor Reference
Area (Primary)
11.2* in.
9.R in.
75.4 in. sq
11.25 in.
9.8 in.
75.4 in. sq
11.25 in.
9.8 in.
75.4 in. sq
Type Nozzle (Initial
Configuration)
Single-zone low-pressure
spr'aybars (12 with a total of
.1G holes at O.O.'tl dial
Sonicore Model 281T boost- Sonicore Model 281T boosl-
air no77lc. compressed ni- air no7.7.le. compressed ni-
trogen IHMISI supply trogen boost siipplv
Swirler (Initial
Configuntion)
.1.20 in. O.D.. 0.5fi in. I.D.. 15
constant soliditv vanes with
vented, flat centerhodv (2f>
deg swirl angle)
•I in in OH.. 1.75 in. I I).. 20 t.O.'t in. O.I).. 1.75 in. I.I).. 20
vane recessed swirler (45 deg vane recessed svvirler ()•"> deg
swirl angle) swirl angle!
Combu.itnr Material
Outer Liner
Inne' Liner
Tvpe :147 SST
Slellite Ml (X40I
Tvpe :i47 SST
Stellile :ll IX 10)
Tv(ie :! 17 SST
Stellile Ml (XlO)
Combu.ttnr Wall Thickness
Outer Liner
Inner Liner
O.OR25 in.
0.125 in. on diiimi'ler with
0.125 high IIns
O.(Hi2fi in.
O.IMVJ.'i in.
0.125 in. on diameter wilh 0.125 in. on diameter wilh
n.125 high fins 0.125 high fins
Design Point Cunditions
Fuel-Air Ratio
Volumetric Heal Release
0.01S9
2.05X10' Btu/lft'-hr-Atm)
001 Kit 0 ()•«)•_)
2.05* |(t« Hlu/ll'.hr-Atm) 2.05 • I0« Blu/Ci'-hr-Alml
Rate Hased on:
Inlet Pressure 188 psia 188 psia
Conibuslor Airflow :il.5th/s :tl 5 ttVs
Conibuslor Reference 2!) 0 f/s 2!>.OI's
Velocity ( Primary 1
Conibuslor Total 5..V, 55',
Pressure Loss
188 psia
20.4 Ib/s
29.0 f/s
5. 5',
A-188
-------
Program Manager: Robert M. Pierce
Telephone No: 305-840-2239
7. TEST CONDITIONS
Inlet air temperatures (in °F), inlet total pressures (in psia), and exit
equivalence ratios are given in Figures A-35 through A-42 of the results
section.
8. ENVIRONMENTAL MONITORING
NO , CO, unburned hydrocarbons, and smoke.
A
9. PROJECT STATUS
Research was conducted from 1 July 1979 through 12 October 1979. Final
report is dated January 1980.
10. RESULTS
The results are summarized in Figures A-35 through A-42, Tables A-60 and
A-61, and highlighted below.
• All exhaust emission goals of the program were met while burning the
test synfuels and Malaysian residual oil.
• Sufficient residence time - A trade-off was shown to exist between
primary zone residence time and attainable NOX emission concentrations.
This trade-off, however, appears to be asymptotic with increasing re-
sidence time. It is thought that the level of the asymptote (NOX) is
a function of the degree to which each of the critical features of the
concept were executed.
• It was also shown in this program that the Rich Burn/Quick Quench con-
cept essentially eliminates the adverse effect that increased pressure
can have on NOX formation (this effect is very evident in lean combus-
tion and is ordinarily found to be proportional to the square root of
the pressure ratio).
11. REFERENCE
Pierce, R.M., C.E.. Smith, and B.S. Hintan. Advanced Combustion Systems
For Stationary Gas Turbine Engines: Vol. IV. Combustor Verification
Testing (Addendum). Prepared by United Technologies Corp. for U.S. Envi-
ronmental Protection Agency, EPA-600/7-80-017d. January 1980.
A-189
-------
400
300
CM
o
=£
in
Q.
Q.
200
-------
CM
O
#
in
a
a
c
o
"•5
4—i
0)
o
c
o
O
c
o
'(0
52
E
in
Runs FS-05B-10to 15,
19 and 34 to 37
100psia
615°F
No. 2 Fuel
200
100
Overall Equivalence Ratio
Figure A-36.
Comparison of Variation in NOX Concentration With Overall
Equivalence Ratio for Schemes FS-05B, FS-03A, FS-04A, and FS-04B
A-191
-------
500
(Runs FS-05B-16 to 18 and FS-05B-20 to 24)
D NOX
Oco
100 psia
610°F
SRC II Middle Distillate
Overall Equivalence Ratio
Figure A-37. Variation in Emission Concentrations With Overall Equivalence
Ratio for Scheme FS-05B Using SRC-II Middle Distillate Fuel
A-192
-------
300
D NO
O UHC
Test No. FS-05B-25 Thru 33
tOOpsia, 600°F
0.2 0.3 0.4
Equivalence Ratio
0.5
Figure A-38.
Emission Signature of Scheme FS-05B
Firing Shale Residual
A-193
-------
300
250
CM
O
*- 200
o
O
O 150
a
ex
c
o
'o>
OT
UJ
100
50
n_
NOX
CO
UHC
Test No. FS-05B-38 Thru 43
100psia, 600° F
0.1 0.2 0.3
Equivalence Ratio
0.4
300
250
'cvi
O
10 200
o
U
O
1
Q.
Q.
W 100
c
0
'55
OT
"E
LU
50
n
1
|
\
\
§NOX
CO
UHC
| Test No. FS-07A-1 Thru 11
i 100psia, 600° F
' / — Nox FromSch
r on No. 2 Fue
i
1
1
1
1
F\ i
*— *\ 1
/\*1/^
X^AVS
^\V
' \
uu hrom bcneme
FS-05B
on No. 2
Fuel
(~?\.^~
/^
-&"^Lrn
— — — *^
erne FS-05B
i
0.1 0.2 v .3
Equivalence Ratio
0.4
Figure A-39.
Emission Signature of Scheme FS-05B
Firing Indonesian/Malaysian Residual
Figure A-40. Emission Signature of Scheme FS-07A
Firing No. 2 Fuel
-------
UD
CJ1
300
250
'cvi
O
- 200
o
(Corrected 1
en
o
1
Q.
Q.
g 100
O
CO
CO
E
LU
50
n
§NOX
CO
UHC
Test No: FS-07A-12 Thru 14
100psia, 600° F
X
§
£
r®
\zf^
300
250
'c\i
O
in
^- 200
0
T3
0)
t;
QJ
k-
E
Q.
Q.
S 100
o
co
E
LU
50
0
n
•
I
m NO*
«>?• ^
<^ CO
© UHC
I
Test No. FS-07A-15 Thru 17
100 psia, 600°
Vv"i
^>
0.1 0.2
Equivalence Ratio
0.3
0.4
0.1
0.2 0.3
Equivalence Ratio
0.4
0.5
Figure A-41
Emission Signature of Scheme FS-07A
Firing Indonesian/Malaysian Residual
Figure A-42.
Emission Signature of Scheme FS-07A
Firing SRC-II Middle Distillate
-------
TABLE A-60. SUMMARY OF SAE SMOKE NUMBERS
Fuel
No. 2 Fuel
SRC II
Middle
Distillate
Shale Resid
Combustor
Configuration
Premixed
Nonpremixed
Premixed
Nonpremixed
Premixed
Nonpremixed
Indo/Malaysian Premixed
Resid.
Nonpremixed
Equivalence
Test No.
FS-05B-36
FS-07A-1
FS-07A-6
FS-07A-11
FS-05B-22
FS-05B-23
FS-05B-24
FS-07A-16
FS-05B-32
FS-05B-33
—
FS-05B-42
FS-05B-43
FS-07A-14
* 1 — primary equivalence ratio near the bottom of the
Ratio
0.1265
0.1354
0.2629
0.1988
0.2134
0.2590
0.1269
0.2190
0.1818
0.2490
—
0.2370
0.2047
0.1949
NO, bucket
Approximate
Primary Zone
Condition *
3
3
2
1
1
2
3
1
1
2
—
2
1
1
SAE
Smoke No.
(ARP 1179)
1.8
0.7
43.5
13.9
9.9
44.9
1.6
31.0
14.0
42.6
Not tested
51.2
46.3
23.2
2 — primary equivalence ratio overly fuel rich
3 — lean
primary equivalence ratio
TABLE A- 61. SUMMARY
Fuel
SRC II
(0.95% N)
Shale Resid
(0.46 'V, N)
Indo/Malay. Resid
(0.24% N)
OF APPROXIMATE NITROGEN CONVERSION RATES
Scheme Scheme
FS-05B FS-07A
12% 9%
Complete Conversion of
Fuel N to NO, (15% O2)
424
12% Not Tested 185
24% 15%
102
ppmv
ppmv
ppmv
A-196
-------
TEST 43
EMISSION
ALCOHOL FUELS FOR USE IN STATIONARY COMBUSTION SYSTEMS
EVALUATION OF N0y EMISSION CHARACTERISTICS OF
J\
1. FUELS TESTED (See Table A-62)
Reference fuels: residual oil, distillate oil, natural gas, propane,
isopropanol, methanol, and 50 percent methanol and isopropanol.
2. TEST EQUIPMENT
An experimental refractory wall furnace designed and constructed by
Aerotherm/Acurex to maintain a nominal 87,864 watts and a Dowtherm-cooled
furnace designed and constructed by Ultrasystems, Inc., to incorporate
the significant features of a firetube package boiler (1 MW).
3. TEST SITE
Refractory wall furnace test: EPA (in house), IERL/RTP.
Package boiler test: Ultrasystems, Inc., Irvine, California.
4. TEST OBJECTIVE
t Evaluate combustion data on alcohol fuels in smaller stationary boilers
and furnaces and compare the emission characteristics to those gener-
ated from conventional fuels.
5. SPONSORING AGENCY
U.S. Environmental Protection Agency
Combustion Research Branch
Industrial Environmental Research Laboratory
Research Triangle Park, N.C.
Project Officer: G. Blair Martin
Telephone No: 919-541-7504
Because of the unavailability of synfuels, the fuels used in some of these
programs were not "true" synfuels (e.g., methanol-derived from natural gas was
used instead of coal-derived methanol). These studies, however, are included
in this report because they were conducted to show what might be expected from
the combustion of actual synfuels in the indicated combustion systems.
A-197
-------
TABLE A-62. FUEL PROPERTIES
Fuel
Chemical
Formula
Fuel Type
Higher Heating
Value 107 J/Kg
Refractory Wall Furnace Test
Distillate oil
Propane
Methanol
Isopropanol
50% Methanol and
isopropanol
Package Boiler Test
Residual oil
Distillate oil
Natural gas
Methanol
CH 1.78
0.025% N
0.035% S
CQHQ 90%
o o
CH3OH
Mixture
C/H = 0.633
0.36% N
C/H - 0.565
0.05% N
CH4+
CH3OH
Commercial
LPG
Chemical grade
Chemical grade
Blend of
chemical grade
Commercial
Commercial
Commercial
Commercial grade
4.58
5.303
2.27
3.314
2.79
6. CONTRACTOR
Ultrasystems, Inc.
Irvine, California
7. TEST CONDITIONS
The refractory wall furnace tests were conducted under the following
conditions: (1) nominal nozzle flow and water content of selected fuels
as shown in Table A-63; (2) 115 percent theoretical air for all runs;
(3) all fuels were run at swirl block positions 2, 4, 6, and 8 (increasing
tangential air); and (4) flue gas recirculation run at swirl block posi-
tion 4 with distillate oil, propane, methanol, and isopropanol.
The package boiler simulator tests were conducted under the following
conditions: (1) a baseline burner air distribution of 50 percent primary
A-198
-------
TABLE A-63. LIQUID FUEL NOZZLE SELECTION
Fuel
Distillate oil
Isopropanol
50% Isopropanol and 50%
Methanol
Methanol
Water Content
Mass % of Total Flow
0
21
32
42
54
0
29
0
0
Nominal Nozzle Flow
Rate x 10-6 cu.m./sec.
2.103
2.629
3.15
3.68
4.206
3.15
5.258
4.206
5.25
and 50 percent secondary air; (2) baseline excess air was chosen to be 17
percent with variations up to 90 percent; and (3) full load heat release
of 1 MW.
8. ENVIRONMENTAL MONITORING
NO , NO, CO, hydrocarbons, aldehydes.
/\
9. PROJECT STATUS
Project complete. Final report dated 1977.
10. RESULTS
The results of the refractory wall furnace tests are highlighted below
and in Figures A-43 through A-45.
• NO emission levels for the five fuels were as follows: distillate
oil > propane > isopropanol > alcohol mixture > methanol.
• NO emissions decreased with increasing tangential air swirl for the
alcohol fuels.
• NO trend for alcohol fuels is more similar to that for propane than
that for distillate oil.
A-199
-------
• NO emissions for all fuels decreased with increasing fraction of flue
gas recirculation.
• Theoretical flame temperature is an important factor in explaining
reduced NO phenomenon.
• CO and hydrocarbon emissions were always below 50 ppm and smoke was
not observed for any fuel.
The results of the package boiler simulator tests are highlighted below
and in Figures A-46 and A-47.
• NO emissions for methanol were virtually constant at about 50 ppm for
all primary air levels, which are lower than those for residual oil,
distillate oil, or natural gas.
• Residual oil MO emissions increased rapidly as excess 02 increased to
4 percent, then leveled off, while methanol NO emissions increased
linearly with increasing excess 02-
• Methanol transferred only 23.6 percent of the heat in the combustion
zone, while the residual oil transferred 36.4 percent in the same zone.
• Although there was considerable scatter in the data, aldehyde concen-
trations were around 10 ppm for methanol and there was no detectable
difference between methanol and natural gas aldehyde concentrations.
11. REFERENCE
Martin, G.B. and M.P. Heap. Evaluation of NOX Emission Characteristics
of Alcohol Fuels for Use in Stationary Combustion Systems. In: American
Institute of Chemical Engineers Symposium No. 165, Volume 73, 1977.
A-200
-------
no
no
X
e
u
£_ 100
ODBTILLATE OIL A eoraoMNoi • METNANOI
OPROPANE O H%BOPHOPANOl • NKMETHANOL
4 I
tWRl HOCK POSITION
Figure A-43.
Comparison of Baseline Nitric Oxide
Emissions for Various Fuels as a
Function of Swirl Parameter.
300
O DISTILLATE Oil
O PROPANE
ISOPROPANOL
O METHANOL
006
010 0.1S
FRACTION RECIRCUlATEO.t
OJO
07S
Figure A-44.
Effect of Flue Ras Recirculation
on Nitric Oxide Emissions for
Various Fuels.
-------
400
300
O
rxi
a.
O
O 100
u
5
9 DISTILLATE OIL WITH FOR
• DISTILLATE OIL EMULSIONS
* ISOPROPANOL
O 50% ISOPROPANOL • 60% METHANOL
OMETHANOL
ft ISOPROPANOL - WATER
0
1.900
1
1
1
\
>
S no
s
X
O
f
z
100
1.800 1.700 1.600 1.&00
THEORETICAL FLAME TEMPEBATURE. 103*C
1.400
A RESIDUAL OIL
• DISTILLATE OIL
« NATURAL GAS
METHANOL
40 10 M
PRIMARV AIR, % OF TOTAL
70
Figure A-45.
Comparison of Nitrix Oxide Emission
Reduction as a Function of Theoretical
Flame Temperature for Various Diluent
Addition Techniques.
Figure A-46.
Comparison of Baseline Nitric Oxide
Emissions for Various Fuels as a
Function of Burner Primary Air.
-------
400
-
oN
u
E
£
o
'U
O
O
u
t-
<_>
tu
E
C
O
U
g
O
X
o
K 100
200
*T
A RESIDUAL OIL
• METHANOL
PRIMARY AIR • 60% OF TOTAL
2 4 • •
FLUE CAS OXYGEN CONCENTRATION. %
10
Figure A-47.
Effect of Excess Air on Nitric Oxide
Emissions for "ethano! and Residual Oil
A-203
-------
TEST 44
THE CONTROL OF NITROGEN OXIDE EMISSIONS
FROM PACKAGE BOILERS
1. FUELS TESTED*
Reference fuels: methanol5 natural gas, and No. 5 residual oil.
2. TEST EQUIPMENT
An industrial watertube boiler and an industrial firetube boiler.
3. TEST SITE
Essex County Correctional Center, New Jersey.
4. TEST OBJECTIVE
• Evaluate NOX emission characteristics of alcohol and conventional
fuels in industrial boilers.
5. SPONSORING AGENCY
U.S. Environmental Protection Agency
Combustion Research Branch
Industrial Environmental Research Laboratory
Research Triangle Park, N.C.
Project Officer: G. Blair Martin
Telephone No: 919-541-7504
6. CONTRACTOR
Energy and Environmental Research Corporation
2400 Michel son Drive
Irvine, California
Principal Investigator: M. P. Heap
*
Because of the unavailability of synfuels, the fuels used in some of these
programs were not "true" synfuels (e.g., methanol-derived from natural gas was
used instead of coal-derived methanol). These studies, however, are included
in this report because they were conducted to show what might be expected from
the combustion of actual synfuels in the indicated combustion systems.
A-204
-------
7. TEST CONDITIONS
Excess air and load levels are reported in Figures A-48 through A-51 of
the results. Influence of flue gas recirculation was also tested.
8. ENVIRONMENTAL MONITORING
N0x
9. PROJECT STATUS
Project complete, report dated February 1977.
10. RESULTS
The effect of fuel type and excess air on NO emissions from these two
A
boilers is shown in Figures A-48 and A-49. The No. 5 fuel oil contained
approximately 0.1 percent nitrogen, which accounts for the higher emis-
sions of that fuel. The lower emissions of the watertube boiler can be
attributed to the lower volumetric heat release rate. The influence of
flue gas recirculation (FGR) for both boilers at constant excess air on
NO emissions is shown in Figures A-50 and A-51. As seen here, FGR was
X
capable of reducing methanol NO emissions. The effect of excess air
J\
level on thermal efficiency is shown in Figures A-52 and A-53.
11. REFERENCE
Cichanowicz, J.E., M.P. Heap, C. McComis, R.E. McMillan, and R.D. Zoldak
"The Control of Nitrogen Oxide Emissions From Package Boilers", February
1977. EPA Contract 68-02-1498.
A-205
-------
240
200
120
ro
o
o\
(lb.m/hr.)
• 8500 No. S oil
A 8500 No. S oil
o 7300 natural gas
010.000 mtthanol
96000
200
120
Load (Ib.m/hf.l
• 10.000 No. 6 oil
Q 8SOO natural gn
7 6SOO mMhanol
4 S
02%
03%
Figure A-48.
NOX Emissions From a Firetube Boiler
As a Function of Fuel Type and Excess
Oxygen.
Figure A-49.
From a Watertube Boiler
As'a Function of Fuel Type and Excess
Oxygen.
NOX Emissions
-------
240
i
ro
o
o
K
E
a
d
x"
O
Firetube
Flue Gas
Recircuiation
Load (Ib.m/hr.) Fuel (02)
• 6000 No. 5 oil 3.9
O 6000 Natural Gas 3.9
o 6000 Methanol 3.8
200
o
g 160
o
120
E
Q
O
*>
40
Load (Ib.m/hr.) Fuel (02)
• 7500 No. 5 oil 4.6
O 7000 Natural Gas 3.5
O 8500 Methanol 3.5
10 20 30 40 50
Flue Gas Recircuiation, mas %
10 20 30 40
Flue Gas Recircuiation, mass %
Figure A-50.
The Influence of Flue Gas Recircuiation
NO Emissions From a Firetube Boiler
X
on
Figure A-51.
The Influence of Flue Gas Recircuiation on
NOV Emissions From a Watertube Boiler
A
-------
IS3
O
00
85
80
75
Load (Ib.m/hr.) Fuel
• 10,000 No. 5 Oil
O 8,500 Natural Gat
» 8,500 Melhanol
DD
90
76
1 2 3 4 E 6
Excea 01, *
789
Load Fual
0 8.500 No. 6 Oil
O 7,300 Natural Gat
• 10,000 Methanol
O O
123459789
EXMB 03, *
Figure A-52.
The Effect of Excess Air Level and Fuel
Type on the Thermal Efficiency of a
Watertube Boiler
Figure A-53.
The Effect of Excess Air Level and Fuel
Type on the Thermal Efficiency of a
Firetube Boiler
-------
TEST 45
IMPACT OF GASOHOL ON AUTOMOBILE EVAPORATIVE
AND TAILPIPE EMISSIONS
1. FUELS TESTED* (see Table A-64)
Non-synfuels: Indolene clear (Fuel 1) ; Indolene with added ethanol (Fuel
2); summer-grade unleaded regular octane fuel with and without added
ethanol (Fuels 3 and 4); and blended gasohol with added ethanol (Fuel 5).
2. TEST EQUIPMENT
Descriptions of the two light duty vehicles tested are provided in Table
A-65.
3. TEST SITE
"Raleigh Road Route", North Carolina. EPA Environmental Research Center,
RTP, North Carolina.
4. TEST OBJECTIVE
a To examine the impact of gasohol on vehicle evaporative and tailpipe
emissions.
5. SPONSORING AGENCY
U.S. Environmental Protection Agency
Mobile Sources Laboratory
Research Triangle Park, North Carolina
Project Officer: Frank M. Black
Telephone No: 919 -541-3037
6. CONTRACTOR
Northrop Services, Inc.
Research Triangle Park, North Carolina
Because of the unavailability of synfuels, the fuels used in some of these
programs were not "true" synfuels (e.g., methanol-derived from natural gas was
used instead of coal-derived methanol). These studies, however, are included
in this report because they were conducted to show what might be expected from
the combustion of actual synfuels in the indicated combustion systems.
A-209
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TABLE A-64. TEST FUEL SPECIFICATIONS
Specification
RVP
IBP, °F
10
50
90
EP
Ethanol (% vol )
API gravity
FIA (% paraffin)
FIA (% olefin)
FIA (% aromatic)
1
9.15
91
138
238
322
341
1.4
59.8
69.7
0.4
28.5
2 3
9.10 9.85
101 89
129 124
212 231
320 361
359 405
6.2 0.86
58.7 57.5
67.5 52.1
0.6 17.2
25.7 29.8
4
9.65
95
121
213
356
413
8.1
56.5
46.4
16.6
28.9
5
9.40
94
124
242
362
408
10.1
52.6
37.7
17.6
34.6
TABLE
A-65.
VEHICLE SPECIFICATIONS
Specification
Make
Manufacturer
Engine Family
Emissions Control
Mileage
Inertial weight (pounds)
Fuel tank capacity (gallons)
Vehicle 1
Mustang II
Ford
302 CID
EGR, CAT, PCV,
single canister
(fuel tank)
10,000
3,000
16
Vehicle 2
LTD II
Ford
351 CID
EGR, AIR,
dual cani
(carb. &
400
4,500
21
CAT, PCV,
ster
fuel tank)
A-210
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7. TEST CONDITIONS
Each car was tested with Fuels 1-5 in sequential order. The vehicles
were driven on a standard road course 44 miles long involving 13 stops
and an average speed of 45 mph. One complete test included: a diurnal
evaporative test; an urban dynamometer driving test; and a hot-soak eva-
porative test. For complete details, see referenced report.
8. ENVIRONMENTAL MONITORING
Tailpipe exhaust samples: THC, CO, C0~, NOV, and ethanol.
£- X
Evaporative samples: THC and ethanol.
9. PROJECT STATUS
Project complete; report is dated February 1981.
10. RESULTS
Exhaust and evaporative emission results are summarized in Tables A-66
through A-69.
t With both vehicles, the addition of ethanol to gasoline resulted in a
decrease in THC and CO emissions, and an increase in NOX emissions
(lean shift in combustion due to oxygen content of ethanol).
• Use of gasohol in both cars substantially increased evaporative emis-
sions. The aggragate change, tailpipe plus evaporative, in hydrocarbon
emissions with gasohol varied from no significant change with Mustang
II to a maximum increase of about 50 percent with the LTD II.
11. REFERENCE
Lang, J.M. and F.M. Black. "Impact of Gasohol on Automobile Evaporative
and Tailpipe Emissions". SAE Paper No. 810 438. 23-27 February 1981.
A-211
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TABLE A-66. EXHAUST EMISSION RATES FOR 1977 MUSTANG II
Fuel
1
2
3
4
5
Gram/mi 1 e
THC*
3.83
2.82
3.15
1.72
2.66
CO
26.7
19.8
27.0
17.2
25.5
N0x
NA
1.53
1.27
1.72
1.48
Ethanol
0
0.026
0.002
0.024
0.044
Fuel Economy
15.5
14.7
14.3
17.1
12.8
*
Sum
of hydrocarbons
and ethanol.
TABLE A-67. EVAPORATIVE
EMISSIONS
FOR 1977
MUSTANG II
Fuel
1
2
3
4
5
HCD
0.42
0.32
0.42
0.34
0.51
HCHS
10.60
22.10
18.80
36.10
22.90
Grams
Total
11.02
22.40
19.22
36.44
23.41
Ethanol
0.05
5.59
0.29
7.80
6.51
HC + Ethanol
11.07
27.99
19.51
44.24
29.92
A-212
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TABLE A-68. EXHAUST EMISSION RATES FOR 1979 LTD II
Fuel
1
2
3
4
5
THC*
0.50
0.37
0.60
0.46
0.55
CO
12.7
9.2
10.3
5.7
7.8
Gram/mile
NOX
1.36
1.83
1.85
2.20
2.10
Ethanol
0
0.002
0
0.012
0.023
Fuel Economy
11.3
11.4
11.0
10.9
11.4
*
Sum
of hydrocarbons
TABLE A-69.
and
ethanol .
EVAPORATIVE EMISSIONS FOR 1979
LTD II
Fuel
1
2
3
4
5
HCD
0.47
0.86
0.86
0.74
1.22
HCHS
1.07
3.53
1.65
6.49
4.86
Grains
Total
1.54
4.39
2.51
7.23
6.08
Ethanol
0.03
0.55
0.07
0.94
0.91
HC + Ethanol
1.57
4.94
2.58
8.17
6.99
A-213
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TECHNiCAL REPORT DATA
(Please read Instructions on the reverse before completing)
1. REPORT NO.
EPA-600/7-82-015
3. RECIPIENT'S ACCESSION NO.
4. TITLE AND SUBTITLE „„,,,. ~, .. T-.
A Compendium of Synfuel End-Use Testing Programs
5. REPORT DATE
April 1982
6. PERFORMING ORGANIZATION CODE
7. AUTHOR(S)
Masood Ghassemi, Sandra Quinlivan, and
Michael Haro
8. PERFORMING ORGANIZATION REPORT NO.
9. PERFORMING ORGANIZATION NAME AND ADDRESS
TRW, Inc.
One Space Park
Redondo Beach, California 90278
10. PROGRAM ELEMENT NO.
11. CONTRACT/GRANT NO.
68-02-3174, Task 18
12. SPONSORING AGENCY NAME AND ADDRESS
13. TYPE OF REPORT AND PERIOD COVERED
EPA, Office of Research and Development
Industrial Environmental Research Laboratory
Research Triangle Park, NC 27711
13. TYPE OF REPORT
Final; 3-9/81
14. SPONSORING AGENCY CODE
EPA/600/13
15. SUPPLEMENTARY NOTES IERL-RTP project officer is Joseph A. McSorley, Mail Drop 61,
919/541-2827. '
16. ABSTRACT
report gives information on major, recently completed, current, and
planned synfuel end-use testing projects. It is intended to promote the flow of infor-
mation between synfuel testing programs , thereby reducing the duplication of effort
and enabling design and implementation of cost-effective and systematic approaches
to the collection of appropriate environmental data in conjunction with on-going and
planned performance testing projects. EPA plans to update this compendium to
include results from current and future testing programs. Projects described in the
compendium include testing of shale-derived fuels, SRC-IE middle distillates, EDS
fuel oils, H-coal liquids, and methanol/indolene mixtures in such equipment as util-
ity boilers, steam generators, diesel engines (laboratory and full scale), auto
engines, and other combustors. Published reports on testing and discussions with
test sponsors/contractors are the sources of data for the compendium. Agencies/
organizations providing input include DOD, DOE, NASA, EPRI, private synfuel de-
velopers, and engine manufacturers.
17.
KEY WORDS AND DOCUMENT ANALYSIS
DESCRIPTORS
b.IDENTIFIERS/OPEN ENDED TERMS
c. COSATl Field/Group
Pollution
Tests
Fossil Fuels
Synthetic Oils
Carbinols
Combustion
Pollution Control
Stationary Sources
Synthetic Fuels
Indolene
13 B
14B
21D,08G
11H
07C
21B
iTEMEN
Release to Public
19. SECURITY CLASS (ThisReport)
Unclassified
21. NO. OF PAGES
236
20. SECURITY CLASS (."hispage)
Unclassified
22. PRICE
EPA Form 2220-1 (9-73)
A-214
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