GAS TURBINE ENGINE Russian patent published in 2011 - IPC F02C7/18 

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine includes compressor with add stages with annular bleeding cavity located behind them. Bleeding cavity is connected to air bypass cavity with bypass flaps located in it. From bypass cavity in front of flaps there made is at least one air bleeding channel. Channel is connected by means of pipelines to air blowing cavities of turbine and compressor housings. Surface area of the opening between cavities is less than the surface area of the opening in bypass cavity before flaps by 1.1…2.0 times. Air bleed for blowing of turbine and compressor housings is made at an angle of α=90°…180° from flow direction to air bypass cavities.

EFFECT: invention allows improving reliability and reducing the engine manufacturing cost by controlling radial gaps between stator and rotor.

2 cl, 4 dwg