Gas turbine combustor, particularly for an aircraft engine

Details Gas turbine combustor, particularly for an aircraft engine Gas turbine combustor, particularly for an aircraft engine

F - Mech Eng,Light,Heat,Weapons

23

R

F23R 3/42 (2006.01) F23R 3/04 (2006.01) F23R 3/08 (2006.01) F23R 3/26 (2006.01)

Patent

CA 2381395

A gas turbine combustor, in particular for an aircraft engine, has at least one chamber, through which combustion gas flows in use, and which is defined by a lateral wall with channeling for feeding cooling air into the chamber and cooling the lateral wall; part of the channeling is defined by at least one double wall for guiding a relative stream of cooling air into the chamber in a tangential direction with respect to the lateral wall.

L'invention concerne une chambre de combustion de turbine à gaz, particulièrement pour un moteur d'aéronef, dans laquelle un gaz de combustion circule en service, et qui est définie par une paroi latérale munie d'une canalisation pour acheminer de l'air de refroidissement dans la chambre et refroidir la paroi; une partie de la canalisation est définie par au moins une double paroi pour guider un courant relatif d'air de refroidissement vers la chambre dans une direction tangentielle par rapport à la paroi latérale.

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