Cooling apparatus for aircraft gas turbine engine exhaust nozzle

Details Cooling apparatus for aircraft gas turbine engine exhaust nozzle Cooling apparatus for aircraft gas turbine engine exhaust nozzle

1997-07-23

1998-07-07

Jordan, Charles T.

Fluid sprinkling, spraying, and diffusing

Reaction motor discharge nozzle with jacketed or hollow...

2391273, 23926539, 60 3932, 60261, 60267, B64D 3304, B05B 1200, F02C 720, F02K 310

Patent

active

057755892

ABSTRACT:
The present invention provides coolable exhaust nozzle flap and seal assemblies having liners that are spaced inward and apart from their respective flap and seal cool walls, to form a cooling passage therebetween that converges in the axial downstream flow direction. One embodiment provides single wall multi-hole film cooled nozzle flap and seal liners particularly for use individually or in combination on convergent and divergent hollow flaps and seals for variable exhaust nozzles. Flap and seal coolable assemblies may be unitary structures that are integrally fabricated or formed such as by casting.

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