HIGH-PRESSURE MULTISTAGE COMPRESSOR OF GAS-TURBINE ENGINE Russian patent published in 2008 - IPC F04D29/00 

FIELD: aircraft engineering.

SUBSTANCE: invention relates to high-pressure multistage compressors of gas-turbine engines of aircraft and ground applications. In proposed high-pressure multistage compressor including compressor stages with rotary guide vanes and stages with fixed guide vane assemblies following rotary guide vane assemblies, according to invention flow path of nth stage of compressor with fixed guide vane assemblies is connected by channels with blow out space inner housing of compressor last stages whose number is found from relation Z/Z₁=2.4-4.0 at n=m+(1-3) where m is number of compressor stages with rotary guide vane assemblies, Z is total number of compressor stages, Z₁ is number of last stages of compressor with adjustable radial clearance between stator and rotor.

EFFECT: increased efficiency owing to adjusting radial clearance between stator and rotor without use of additional control systems and actuating mechanisms.

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