Gas turbine combustor exit duct and hp vane interface

Details Gas turbine combustor exit duct and hp vane interface Gas turbine combustor exit duct and hp vane interface

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 11/00 (2006.01) F01D 9/02 (2006.01) F02C 7/28 (2006.01) F23R 3/42 (2006.01)

Patent

CA 2601934

An assembly for a gas turbine engine includes a combustor and a vane assembly disposed downstream thereof. A portion of an outer platform of the vane assembly defines an axial sliding joint connection with the combustor, and includes a plurality of depressions located in an outer circumferential surface thereof opposite the combustor. The depressions are disposed in regions of expected higher thermal growth about the circumference of the outer platform such that thermal growth of the entire outer platform is substantially uniform circumferentially therearound.

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