COMPRESSOR OF GAS-TURBINE ENGINE Russian patent published in 2007 - IPC F04D29/52 

FIELD: aircraft engineering.

SUBSTANCE: invention relates to compressors of gas-turbine engines of aircraft and ground application, and it can be used also mechanical drives and drives of electric generators. According to invention, in compressor of gas-turbine engine including stator with guide vanes and outer and inner housing of compressor forming ring closed space to take off air from compressor connected by channels with flow path of compressor, said channels are made tilted in direction of air flow in flow path of compressor and are displaced mainly to side of trailing edge of guide valve. Number of channels is equal to number of guide vanes of said stage. Axes of symmetry of channels are parallel to axes of symmetry of lock joints of guide vanes, being arranged at equal distance from them, and front wall of channel in direction of air flow from side of flow path with inlet section inclined in direction of air flow at β/α = 3...8 and Б/В = 5...10 where α is angle of tilting of wall of inlet section relation to wall of stator forming flow path of compressor between guide vanes; β is angle of tilting of channel axis to wall of stator forming flow path of compressor between guide vanes; Б is chord of guide vane; В is distance between trailing edge of guide vane and rear wall of channel in direction of flow from side of compressor flow path.

EFFECT: improved reliability, reduced overall dimensions of compressor at minimum hydraulic losses of taken-off air.

3 dwg