A reverse-flow annular combustor with its casing diameter of 400 mm was developed using an uncooled liner made of a three-dimensional woven ceramic matrix composite. The combustor was tested using the TRDI high-pressure combustor test facility at the combustor maximum inlet and exit temperature of 723 K and 1623 K, respectively. Although both the material and combustion characteristics were evaluated in the test, this report focused on the combustion performance. As the results of the test, the high combustion efficiency and high heat release ratio of 99.9% and 1032 W/m3/Pa were obtained at the design point. The latter figure is approximately twice as high as that of existing reverse-flow annular combustors. Pattern factor was sufficiently low and was less than 0.1. Surface temperatures of the liner wall were confirmed to be higher than the limit of the combustor made of existing heat-resistant metallic materials.
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January 2003
Technical Papers
Combustion Test Results of an Uncooled Combustor With Ceramic Matrix Composite Liner
Y. Suzuki,
Y. Suzuki
Japan Defense Agency, Propulsion Division, 3rd Research Center, Technical Research & Development Institute (TRDI), 1-2-10 Sakae, Tachikawa, Tokyo 190-8533 Japan
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T. Satoh,
T. Satoh
Japan Defense Agency, Propulsion Division, 3rd Research Center, Technical Research & Development Institute (TRDI), 1-2-10 Sakae, Tachikawa, Tokyo 190-8533 Japan
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M. Kawano,
M. Kawano
Kawasaki Heavy Industries, Ltd., Research & Development Section 2, Aero Engine Research & Development Center, 1-1 Kawasaki, Akashi 673-8666 Japan
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N. Akikawa,
N. Akikawa
Kawasaki Heavy Industries, Ltd., Material Engineering Section, Aero Engine Engineering Department, Gas Turbine Division, 1-1 Kawasaki, Akashi 673-8666 Japan
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Y. Matsuda
Y. Matsuda
Kawasaki Heavy Industries, Ltd., Material Engineering Section, Aero Engine Engineering Department, Gas Turbine Division, 1-1 Kawasaki, Akashi 673-8666 Japan
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Y. Suzuki
Japan Defense Agency, Propulsion Division, 3rd Research Center, Technical Research & Development Institute (TRDI), 1-2-10 Sakae, Tachikawa, Tokyo 190-8533 Japan
T. Satoh
Japan Defense Agency, Propulsion Division, 3rd Research Center, Technical Research & Development Institute (TRDI), 1-2-10 Sakae, Tachikawa, Tokyo 190-8533 Japan
M. Kawano
Kawasaki Heavy Industries, Ltd., Research & Development Section 2, Aero Engine Research & Development Center, 1-1 Kawasaki, Akashi 673-8666 Japan
N. Akikawa
Kawasaki Heavy Industries, Ltd., Material Engineering Section, Aero Engine Engineering Department, Gas Turbine Division, 1-1 Kawasaki, Akashi 673-8666 Japan
Y. Matsuda
Kawasaki Heavy Industries, Ltd., Material Engineering Section, Aero Engine Engineering Department, Gas Turbine Division, 1-1 Kawasaki, Akashi 673-8666 Japan
Contributed by the International Gas Turbine Institute (IGTI) of THE AMERICAN SOCIETY OF MECHANICAL ENGINEERS for publication in the ASME JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Paper presented at the International Gas Turbine and Aeroengine Congress and Exhibition, New Orleans, LA, June 4–7, 2001; Paper 2001-GT-088. Manuscript received by IGTI, Dec. 2000, final revision, Mar. 2001. Associate Editor: R. Natole.
J. Eng. Gas Turbines Power. Jan 2003, 125(1): 28-33 (6 pages)
Published Online: December 27, 2002
Article history
Received:
December 1, 2000
Revised:
March 1, 2001
Online:
December 27, 2002
Citation
Suzuki , Y., Satoh, T., Kawano, M., Akikawa , N., and Matsuda, Y. (December 27, 2002). "Combustion Test Results of an Uncooled Combustor With Ceramic Matrix Composite Liner ." ASME. J. Eng. Gas Turbines Power. January 2003; 125(1): 28–33. https://doi.org/10.1115/1.1501916
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