HIGH-PRESSURE COMPRESSOR OF GAS-TURBINE ENGINE Russian patent published in 2004 - IPC

FIELD: aircraft industry.

SUBSTANCE: invention relates to gas-turbine engines of aircraft and ground application. According to invention, in high-pressure compressor of gas-turbine engine each stage of which includes impeller with bushing and guide vane assembly, bushings of impellers are arranged at angle α relative to axis of compressor with angle α stepless increasing from 0-5^o for first stage impeller to 12-20^o for zth impeller, and decreasing to 0^o for working blades of compressor last stage at n/z=2.5-4; n/m=4-7; F₁/F₂=5-7 where z is ordinal number of compressor impeller starting from its inlet; n is number of compressor working blades; m is number of compressor stages with turnable guide vane assemblies; F₁ is ring area of compressor passage part at inlet; F₂ is ring area of compressor passage part at outlet.

EFFECT: increased service life and efficiency owing to use of high-pressure intermediate stages of compressor with preservation of high gas dynamic stall margin of compressor.

3 dwg