TECHNICAL PAPERS: Gas Turbines: Combustion and Fuels

Combustion Test Results of an Uncooled Combustor With Ceramic Matrix Composite Liner

[+] Author and Article Information
Y. Suzuki, 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, Y. Matsuda

Kawasaki Heavy Industries, Ltd., Material Engineering Section, Aero Engine Engineering Department, Gas Turbine Division, 1-1 Kawasaki, Akashi 673-8666 Japan

J. Eng. Gas Turbines Power 125(1), 28-33 (Dec 27, 2002) (6 pages) doi:10.1115/1.1501916 History: Received December 01, 2000; Revised March 01, 2001; Online December 27, 2002
Copyright © 2003 by ASME
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Miyake,  M., 2000, “Engine Development in Japan Defense Agency,” J Gas Turb. Soc. Jpn., 28 (5), pp. 352–356 (In Japanese).
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Nishino,  K., Igashira,  K.-I., Take,  K., and Suemitsu,  T., 1999, “Development of a Combustor Liner Composed of Ceramic Matrix Composite (CMC),” ASME J. Eng. Gas Turbines Power, 121, pp. 12–17.
Kawano, M., et al., 1994, “Development of Reverse-Flow Annular Combustor for Small Turboshaft Engines,” Proceedings of the 34th Conference on Aerospace Propulsion, Japan Society of Aeronautical and Space Science, Tokyo, Japan, pp. 170–175 (In Japanese).
Matsuda, Y., Akikawa, N., and Satoh, T., 2001, “Manufacturing of 3-D Woven SiCf/SiC Composite Combustor Liner,” Ceramic Engineering and Science Proceedings, American Ceramic Society, Westerville, OH, 22 , No. 3, pp. 463–470.
Society of Automotive Engineers, Inc., 1980, “Procedure for the Continuous Sampling and Measurement of Gaseous Emissions From Aircraft Turbine Engines,” Aerospace Recommended Practice, Paper No. ARP 1256A.
Lefebvre, A. H., 1988, Gas Turbine Combustion, McGraw-Hill, New York.


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Cracks near dilution holes on the inner liner
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Surface temperature of the inner liner
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Pattern factor against parameter ϕ
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Temperature distribution at combustor exit
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Pressure loss against corrected air mass flow
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Combustion efficiency against 0 parameter
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Surface temperature measuring points. (▴=the measuring points in axial location, •=fuel nozzle point in circumferential location, ○=point between fuel nozzles in circumferential location.)
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Cross section of the combustor installed in the test facility, including arrangement of sensors
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Air-blast-type fuel injector
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Three-dimensional woven ceramic matrix composite
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Ceramic matrix composite liners, (a) outer liner, (b) inner liner
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Cutaway view of the combustor
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Comparison of the heat release rate of the present combustor with other reverse flow combustors
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Cross section of the KSX combustor



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