Nozzle diaphragm platform for gas turbine engine

Details Nozzle diaphragm platform for gas turbine engine Nozzle diaphragm platform for gas turbine engine

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 5/12 (2006.01) F01D 5/18 (2006.01) F01D 5/28 (2006.01)

Patent

CA 2412982

A high-pressure turbine nozzle-vane band for a gas turbine engine, the band comprising an inside surface (12) supporting at least one guide vane (14) having a trailing edge (14a) that is directed towards a downstream end (16) of the band (10), and an outside surface (18), opposite the inside surface, from which a flange (20) extends radially, defining firstly, upstream from the flange, a passage (21) for cooling-air, and secondly, downstream from the flange, a cavity (22), the inside surface (12) of the band being provided, between the trailing edge (14a) of the guide vane and the downstream end (16) of the band, with a coating (26) forming a thermal barrier enabling a temperature gradient generated in the band by the air spinning in said cavity to be increased.

Plate-forme d'aube de distributeur de turbine haute-pression pour moteur à turbine à gaz, comprenant un côté interne (12) supportant au moins une aube directrice (14) dont le bord de fuite (14a) est dirigé vers une extrémité aval (16) de la plate-forme (10), et un côté externe (18), opposé au côté interne, à partir duquel s'étend radialement une bride (20) définissant, d'une part en amont de la bride un passage (21) pour de l'air de refroidissement, et d'autre part en aval de la bride une cavité (22), le côté interne (12) de la plate-forme étant muni, entre le bord de fuite (14a) de l'aube directrice et l'extrémité aval (16) de la plate-forme, d'un revêtement (26) formant barrière thermique permettant d'accentuer un gradient thermique engendré dans la plate-forme par une giration de l'air dans ladite cavité.

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