COMPRESSOR FAN STAGE (VERSIONS) Russian patent published in 2007 - IPC F04D29/38 

FIELD: aircraft industry; compressors.

SUBSTANCE: invention relates to axial-flow stages of compressors of double-flow aircraft turbojet engines. According to invention, through holes made in from of different-type perforation or row of slots made on surfaces of working blades, higher pressure air is fed to boundary layer and into holes (slots) made in trailing edges of blades which equalize distribution of velocity and pressure in pitch of blade rim in outlet section. Higher pressure air is fed to holes made on surface of trailing edges of blades along inner channels of blades not from low-pressure compressor, but from under-rotor space of impeller communicating with surrounding atmosphere. For this purpose, tubes are installed in hub of impeller increasing length of inner channels of blades to axle of rotation of compressor. Holes are made on negative pressure surface of blades, being at angle of α<45° to surface of blade in direction of air in interblade channel of impeller, and, as a version, disk with channels is installed in hub of impeller, said channels being extensions of inner channels of blades to axle of rotation of compressor.

EFFECT: enlarged range of stable operation, improved aerodynamic and acoustic characteristics of compressor.

3 cl, 6 dwg