公开(公告)号：CA1039196A

公开(公告)日：1978-09-26

申请号：CA249115

申请日：1976-03-26

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BROWN HENRY B ,  CANTOR EUGENE ,  DETOLLA FRANCIS L ,  VOLLINGER GARY J

IPC: F01D25/12

Abstract: TURBINE COOLING Apparatus for cooling the nozzle guide vanes in the turbine section of a gas turbine engine is disclosed. A plurality of guide vanes is cantilevered from the turbine case and extends radially inward across the path of working medium gases flowing through the turbine. A ring which is deformable in response to pressure forces is disposed between the vanes and the turbine case forming an annular chamber from which air is metered to the vanes during operation of the engine for cooling. In one embodiment platform cavities and airfoil cavities are alternately disposed between the vanes and the ring to isolate airfoil cooling air from platform cooling air.

公开(公告)号：CA1039195A

公开(公告)日：1978-09-26

申请号：CA249113

申请日：1976-03-26

Applicant: UNITED TECHNOLOGIES CORP

Inventor： VOLLINGER GARY J

IPC: F01D25/12

Abstract: TURBINE COOLING Apparatus for cooling the case and the nozzle guide vanes in the turbine section of a gas turbine engine is disclosed. A plurality of guide vanes is cantilevered from the case and extends radially inward across the path of working medium gases flowing through the turbine. A ring, which is deformable to provide radial sealing in operative response to pressure forces exerted by medium gases on the airfoil section of each guide vane, is disposed between the vanes and the case forming an annular chamber which is adapted to receive cooling air and from which the cooling air is flowable to the vanes during operation of the engine.