FIELD: manufacture of aircraft engines; compressors of gas-turbine engines.
SUBSTANCE: proposed stage of axial-flow compressor includes rotor blades 1 and circular wall of housing 2 with holes 3 and 4 which are communicated with gas-and-air passage 5 and are interconnected by separate pipe lines 6 forming waveguides. Holes 3 are made before leading edges of blades and holes 4 are made behind inlet blades.
EFFECT: reduction of vibration stresses in structural members of axial-flow compressor due to reduced amplitude of pressure fluctuations.
4 cl, 2 dwg
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