GAS TURBINE COOLING AIR SUPPLY SYSTEM Russian patent published in 2006 - IPC F02C7/12 F01D11/02 

FIELD: mechanical engineering; gas turbines.

SUBSTANCE: in proposed systems cooling air from high-pressure source is delivered inside gas turbine and is directed into radial accelerators. Radial accelerators cause tangential acceleration of air indirection of circular motion of rotor surface. After acceleration of cooling air to peripheral speed of rotor, air gets into radial holes. Then cooling air is discharged into hollow rotor at accordingly reduced radius of outlet. System contains labyrinth seal in combination with brush seal to separate chamber delivering air into radial holes from chamber communicating with front space of rotor of turbine first stage by forming intermediate chamber which prevents mixing of flows owing to leaks from axial-flow compressor with flow of cooling air from accelerators. Labyrinth seal in combination with brush seal is adapted to separate pressure side of compressor from chamber communicating with front space of rotor in turbine first stage. Brush seal is arranged after labyrinth seal in direction of flow.

EFFECT: increased total efficiency of system.

3 cl, 2 dwg