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.

Issue Section:
Gas Turbines: Combustion and Fuels
Keywords:
combustion, testing, gas turbines, aerospace engines, protective coatings, composite materials, ceramics, temperature, heat of combustion
Topics:
Combustion, Combustion chambers, Design, Heat, Temperature, Ceramic matrix composites, Flow (Dynamics), Pressure
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