GAS-TURBINE ENGINE COMPRESSOR Russian patent published in 2013 - IPC F04D27/00 F04D29/56 

FIELD: machine building.

SUBSTANCE: gas-turbine engine compressor comprises blades with variable stagger angle including a vane connected to a support by a ring circuit plate (17) and held when rotating in the casing (14) hole. The blade plate comprises at least one notch (60) to tap air to the compressor flow which is aimed to be connected to the casing hole (62) to remove the tapped air when the blades are in the first position and which is blocked by the casing when the blades are in the second position. The tapped air flow depends on the blades' angle. The gas-turbine engine can be made as a turbojet, turboprop aviation engine, turboengine of a helicopter or a industrial vehicle.

EFFECT: required compressor stall margin is provided along with no engine performance degradation in other working modes.

12 cl, 10 dwg