Sealing structures for gas turbine engines

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

1994-08-31

1995-11-28

Kwon, John T.

Rotary kinetic fluid motors or pumps

With passage in blade, vane, shaft or rotary distributor...

416116, F01D 518

Patent

active

054701988

ABSTRACT:
A cooling and sealing arrangement in a gas turbine engine comprises a seal assembly extending between nozzle guide vanes and combustion chamber discharge nozzles. The nozzle guide vanes have platforms having extensions which in one embodiment overlap the downstream ends of the discharge nozzles. Cooling air is supplied to the upstream edge portions of the platforms through holes in flanges on the discharge nozzles. The seal assembly defines a chamber adjacent the platform extensions which is supplied with cooling air through metering holes in the seal assembly which provides part of a boundary for a cooling air chamber, the boundary of the chamber having cooling air holes for metering cooling air into the chamber to cool the upstream portion of the nozzle guide vane outer platforms. Cooling air exits the chamber through holes in the platform extensions to film cool them.

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