Combustion Test Results of an Uncooled Combustor With Ceramic Matrix Composite Liner
Author:
Suzuki Y.1, Satoh T.1, Kawano M.2, Akikawa N.3, Matsuda Y.3
Affiliation:
1. Japan Defense Agency, Propulsion Division, 3rd Research Center, Technical Research & Development Institute (TRDI), 1-2-10 Sakae, Tachikawa, Tokyo 190-8533 Japan 2. Kawasaki Heavy Industries, Ltd., Research & Development Section 2, Aero Engine Research & Development Center, 1-1 Kawasaki, Akashi 673-8666 Japan 3. Kawasaki Heavy Industries, Ltd., Material Engineering Section, Aero Engine Engineering Department, Gas Turbine Division, 1-1 Kawasaki, Akashi 673-8666 Japan
Abstract
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.
Publisher
ASME International
Subject
Mechanical Engineering,Energy Engineering and Power Technology,Aerospace Engineering,Fuel Technology,Nuclear Energy and Engineering
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2 articles.
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