Combustor turbine successive dual cooling

F - Mech Eng,Light,Heat,Weapons – 02 – C

Patent

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Details

F02C 7/12 (2006.01) F01D 5/00 (2006.01) F01D 25/26 (2006.01) F02C 7/18 (2006.01) F23R 3/00 (2006.01)

Patent

CA 2429425

The present invention is directed to a combustor/turbine successive dual cooling arrangement in which the combustor has a one-piece hot combustor wall and front and rear cold combustor walls, and cooling air is forced under pressure through perforations in the cold combustor walls and impinges on the annular front and rear sections of the hot combustor wall for the backside cooling of the hot combustor wall. The exhaust combustor backside cooling air is directed to gain access to the hot end of the engine, that is, the turbine section, to cool the turbine components.

La présente invention concerne un système de double refroidissement successif pour turbine/chambre de combustion dans lequel la chambre de combustion comporte une paroi chaude d'une seule pièce et des parois avant et arrière froides. L'air de refroidissement est forcé sous pression au travers des perforations dans les parois froides de la chambre de combustion et va heurter les parties annulaires avant et arrière de la paroi chaude de la chambre de combustion, ce qui refroidit le dos de la paroi chaude de la chambre de combustion. L'air de refroidissement qui s'échappe au dos de la chambre de combustion est dirigé vers l'extrémité chaude du moteur, c'est-à-dire vers la partie turbine, dont il va refroidir les organes.

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