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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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References

Figures

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

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