Sliding joint between combustor wall and nozzle platform

Details Sliding joint between combustor wall and nozzle platform Sliding joint between combustor wall and nozzle platform

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 9/02 (2006.01) F01D 9/04 (2006.01)

Patent

CA 2549162

An assembly for a gas turbine engine (10), the assembly comprising a combustor (16) and a vane assembly (22) downstream from the combustor (16). The vane assembly (22) includes at least one airfoil (24) radially extending between an inner and outer platform (26,28) defining an annular gas path (23) therebetween. At least the outer platform (28) forms a first sliding joint connection (36) with an adjacent outer combustor wall (32) such that radial sealing between the outer platform (28) and the outer combustor wall (32) is provided at engine operating temperature, while permitting relative axial displacement there between.

L'invention porte sur un ensemble pour moteur de turbine à gaz (10), lequel ensemble comprend une chambre de combustion (16) et un ensemble aubes (22) en aval de la chambre de combustion (16). L'ensemble aubes (22) comprend au moins un profil aérodynamique (24) s'étendant entre une plate-forme interne et une plate-forme externe (26,28) qui définissent une trajectoire de gaz annulaire (23) entre elles. La plate-forme externe (28) au moins forme une première connexion de joint coulissant (36) avec une paroi de chambre de combustion externe adjacente (32), de telle manière qu'à la température de fonctionnement du moteur, une étanchéité radiale se forme entre la paroi de la plate-forme externe (28) et la paroi externe (32) de la chambre de combustion, qui permet néanmoins un déplacement axial relatif de l'une par rapport à l'autre.

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