PERFORMANCE OF SEMI-TRANSPORTATION-COOLED LINER IN HIGH-TEMPERATURE-RISE COMBUSTOR.

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作者：
Wear, Jerrold D.
Trout, Arthur M.
Smith, John M.
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NASA Technical Paper | 1981年 / 1806期
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摘要：
A combustor liner fabricated from Lamilloy was tested at inlet air pressures to 8 atmospheres, an inlet air temperature of 894 K, and exhaust gas temperatures to 2430 K. Results obtained with the Lamilloy liner are compared with results obtained with a conventionally designed, film-cooled step-louver liner. Operation of the Lamilloy liner with counterrotating swirl combustor fuel modules with mixing venturis was possible to a fuel-air ratio of 0. 065 without obtaining excessive liner metal temperatures. At the 0. 065 fuel-air condition the average liner metal temperature was 140 kelvins and the maximum local temperature 280 kelvins above the inlet air temperature. Combustion efficiency, pattern factor, and smoke data are included.
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