STATOR OF COMPRESSOR OF GAS-TURBINE ENGINE Russian patent published in 1998 - IPC

FIELD: aviation industry. SUBSTANCE: stator of compressor of gas-turbine engine with system controlling radial clearances is intended to improve efficiency of system controlling radial clearances between stator and rotor and to eliminate effects of outer loads on inner frame of compressor. Stator of compressor has outer frame with fixture for attachment of engine to aircraft and elements of system controlling radial clearance. Outer frame is connected with resilient flanges to inner frame of compressor and with columns - to support of rotor. Inner frame of compressor with guiding apparatuses and working blades installed in it is connected via straightening apparatus of compressor to support. It is possible to use combination of resilient and rigid elements in nonrigid coupling of outer and inner frames of combustion chamber by means of radial supports. In this case power coupling of outer frame of compressor to support of rotor passes through rigid connection, straightening apparatus behind compressor and inner frame of combustion chamber. EFFECT: improved efficiency and elimination of effects of outer loads on inner frame of compressor. 3 dwg