GAS-TURBINE ENGINE HIGH-PRESSURE COMPRESSOR Russian patent published in 2007 - IPC F04D29/60 

FIELD: mechanical engineering; compressors.

SUBSTANCE: according to invention, in high-pressure compressor of gas-turbine engine each stage of which includes working blade and guide vane installed after working blade, both installed in passage part, ratio of area F_in.1 of compressor passage part at inlet of first working blade to area F_out.1 of passage part at outlet from first stage is 1.6-2.2, ratio of area F_in.2 of compressor passage part at inlet of second working blade to area F_out.2 of passage part at outlet from compressor is 2.5-3.2 and Z - number of stages of compressor following the first stage is 4-6.

EFFECT: improved reliability and increased efficiency of compressor, reduced cost of manufacture and repair owing to increased gas dynamic stability and minimization of number of stages of rotary guide vanes.

1 dwg