AXIAL-FLOW COMPRESSOR

FIELD: aircraft industry; gas-turbine engines. ^ SUBSTANCE: invention relates to compressors of aircraft gas-turbine engines with highly-loaded wide-chord blades making it possible to reduce amplitudes of pressure oscillations after impeller with resulting reduction of vibration stress of structure. When compressor operates, owing to the fact that working blades 5 are installed at different pitch in circumferential direction, each blade interacts with guide vane assemblies 1 and 2 in different phase, and effect of generation of oscillations is reduced owing to mismatch of blade interaction phases. Owing to the fact that guide vane assemblies 1 and 2 are shifted circumferentially relative to each other, each working blade 5 interacts, in turn, with guide vane assemblies, and effect of reduction of amplitude of acoustic vibrations increases. Making of guide vanes 3 and 4 curved in radial direction provides gradual interaction of each working blade 5 with vanes when blade passes by guide vane assembly at rotation which decreases amplitude of acoustic vibrations. ^ EFFECT: reduced dynamic action on compressor. ^ 2 cl, 4 dwg