The purpose of this continuing research was to investigate the effects of combustion chamber geometry on exit temperature fields using a validated ambient pressure test rig. Rig test conditions were set to simulate an engine operating condition of 463 km/h (250 kn) at 7620 m (25,000 ft) by matching Mach number, equivalence ratio, and Sauter mean diameter of the fuel spray. Using a thermocouple rake, high resolution temperature measurements were obtained in the combustion chamber exit plane. Following the previously published procedures, a three-dimensional laser scanning system was used to quantify geometric deviations from two populations of combustion chambers. These populations differed in that one had a significantly higher allowable engine operating temperature for continuous cruise condition. Geometric deviations of both populations were compared with the reference model. The relationship between combustion chamber exit temperature profile and geometric deviation of each population was then compared. The main conclusion of this research was that the temperature profile degradation of both populations due to geometric deviations followed similar trends. These results highlighted that the difference in operating limitations of these populations did not significantly affect component performance.

1.
Henderson
,
R. E.
, and
Blazowski
,
W. S.
, 1978, “
Turbopropulsion Combustion Technology
,” The Aerothermodynamics of Aircraft Gas Turbine Engines, Report AFAPL-TR-78–52, Wright Patterson Air Force Base, OH.
2.
Kotzer
,
C.
,
LaViolette
,
M.
, and
Allan
,
W.
, 2009, “
Effects of Combustion Chamber Geometry Upon Exit Temperature Profiles
,”
ASME
Paper No. GT2009-60156.
3.
Lefebvre
,
A. H.
, 1999,
Gas Turbine Combustion
,
2nd ed.
,
Taylor and Francis
,
London
.
4.
Bicen
,
A.
, and
Tse
,
D.
, 1990, “
Combustion Characteristics of a Model Can-Type Combustor
,”
Combust. Flame
0010-2180,
80
, pp.
111
125
.
5.
Sjöblom
,
B.
, 1980, “
Some Aspects on Increasing Gas Turbine Combustor Exit Temperature
,”
ASME
Paper No. 80-GT-73.
6.
Lefebvre
,
A.
, 1984, “
Fuel Effects on Gas Turbine Combustion: Liner Temperature, Pattern Factor, and Pollutant Emissions
,”
J. Aircr.
0021-8669,
21
(
11
), pp.
887
898
.
7.
Povey
,
T.
,
Chana
,
K.
,
Jones
,
T.
, and
Hurrion
,
J.
, 2007, “
The Effect of Hot-Streaks on HP Vane Surface and Endwall Heat Transfer: An Experimental and Numerical Study
,”
ASME J. Turbomach.
0889-504X,
129
, pp.
32
43
.
8.
Rizk
,
N.
,
Oechsie
,
V.
,
Ross
,
P.
, and
Mongia
,
H.
, 1988, “
High Density Fuel Effects
,” Wright-Patterson Air Force Base, Aero Propulsion Laboratory, Technical Report No. AFWAL-TR-88-2046.
9.
Freiman
,
V.
, and
Tul’skii
,
V.
, 1985, “
Reducing Unevenness in the Temperature Field After the Combustion Chamber of a GTK-10 Gas Turbine Unit
,”
Energomashinostroenie
0131-1336,
6
, pp.
3
5
.
10.
Rollbuhler
,
R.
, 1987, “
Combustion Characteristics of Gas Turbine Alternate Fuels
,”
National Aeronautics and Space Administration
Technical Report No. DE-AI01-85CE50111.
11.
Ng
,
D.
, 1999, “
A New Method to Measure Temperature and Burner Pattern Factor Sensing for Active Engine Control
,”
National Aeronautics and Space Administration
Technical Report No. NASA/TM-1999-209090.
12.
Friedman
,
R.
, and
Carlson
,
E.
, 1955, “
A Polar Coordinate Survey Method for Determining Jet-Engine Combustion-Chamber Performance
,” National Advisory Committee for Aeronautics, Lewis Flight Propulsion Laboratory, Technical Report No. 3566.
13.
George
,
B.
, and
Cox
,
J.
, 1975, “
Predicting Exit Temperature Profile From Gas Turbine Combustors
,”
J. Aircr.
0021-8669,
13
, pp.
630
636
.
14.
Lefebvre
,
A.
, 1984, “
Fuel Effects on Gas Turbine Combustion: Liner Temperature, Pattern Factor, and Pollutant Emissions
,”
ASME
Paper No. AIAA-84-1491.
15.
Saravanamuttoo
,
H.
, 1990, “
Recommended Practices for Measurement of Gas Path Pressures and Temperatures for Performance Assessment of Aircraft Turbine Engines and Components
,” Advisory Group for Aerospace Research and Development, Technical Report No. AGARD-AR-245.
16.
Guy
,
S.
, and
Allan
,
W.
, 2006, “
Scaling of a Gas Turbine Combustion Chamber Test Rig to Simulate Operating Conditions
,”
Combustion Institute/Canadian Section, Spring Technical Meeting
, Waterloo, ON, pp.
4
-1–4-
6
.
17.
Taylor
,
D.
, 1999, “
A Turbomatch Model of the Allison T56-A15 Engine
,” MSc thesis, Cranfield University School of Mechanical Engineering, Swindon, UK.
18.
2003, “
Flight manual-C-130 Airplanes Equipped With T56-A-15 Engines C-12-130-000/MB-003
,” Issued Under the Authority of the Chief of Defence Staff.
19.
Odgers
,
J.
,
Kretschmer
,
D.
, and
Pearce
,
G.
, 1991, “
The Combustion of Droplets Within Gas Turbine Combustors: Some Recent Observations on Combustion Efficiency
,” Combustion Laboratories, Laval University, Technical Report No. 104.
20.
Odgers
,
J.
,
Kretschmer
,
D.
, and
Pearce
,
G.
, 1993, “
The Combustion of Droplets Within Gas Turbine Combustors: Some Recent Observations on Combustion Efficiency
,”
ASME J. Turbomach.
0889-504X,
115
, pp.
523
532
.
21.
Kretschmer
,
D.
, and
Odgers
,
J.
, 1996, “
Fuel Correlations for Combustion Purposes: A Summary of Progress Within the Past Fifteen Years
,” Technical Report No. 1025.
22.
2008, “
USAF Technical Order 2J-T56-53
,” Published Under Authority of the Secretary of the Air Force.
23.
2008, “
Flight Manual-C-130 Airplanes Equipped With T56-A-15 Engines C-12-130-000/MB-001
,” Issued Under the Authority of the Chief of Defence Staff.
24.
Kotzer
,
C.
, 2008, “
Effects of Combustion Chamber Geometry Upon Exit Temperature Profiles
,” MS thesis, Royal Military College of Canada, Kingston, ON.
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