Sealing structures for gas turbine engines

Details Sealing structures for gas turbine engines Sealing structures for gas turbine engines

F - Mech Eng,Light,Heat,Weapons

02

C

F02C 9/16 (2006.01) F01D 9/02 (2006.01) F01D 11/00 (2006.01)

Patent

CA 2117240

A cooling and sealing arrangement in a gas turbine engine comprises a seal assembly (42,30) extending between nozzle guide vanes (20) and combustion chamber discharge nozzles (22). The nozzle guide vanes (20) have platforms (34,36) having extensions (34A,36A) which in one embodiment overlap the downstream ends of the discharge nozzles (22). Cooling air is supplied to the upstream edge portions of the platforms through holes (26,28C) in flanges (24,28) on the discharge nozzles (22). The seal assembly (42,30) defines a chamber (58,70) adjacent the platform extensions which is supplied with cooling air through metering holes (56.68) in the seal assembly. Cooling air exits the chamber (58,70) through holes (34B,36B) in the platform extensions to film cool them.

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