COMPRESSOR OF GAS-TURBINE ENGINE (VERSIONS) Russian patent published in 2007 - IPC F04D25/00 

FIELD: aircraft industry.

SUBSTANCE: invention can be used in gas-turbine, particularly, in compressor building. In proposed compressor with diagonal stage thrust bearing installed on rotor shaft is arranged so that axis passing through centers of rotation for antifriction bearing or through center of thrust ridge of shaft for sliding bearing intersects with axis of rotor shaft at distance H from place of intersection of axis of rotor shaft and extension of generatrix of conical surface of periphery of working vane. According to first and second design versions, efficiency of compressor with diagonal stage and with curvilinear generatrix of periphery of vane and reliability are increased owing to provision of optimum arrangement of thrust bearing on rotor shaft and minimum clearance between vanes of wheels and stator of compressor.

EFFECT: increased efficiency and reliability in operation.

3 cl, 2 dwg