Apparatus for operating gas turbine engine combustors

Details Apparatus for operating gas turbine engine combustors Apparatus for operating gas turbine engine combustors

F - Mech Eng,Light,Heat,Weapons

02

C

F02C 1/00 (2006.01) F23R 3/02 (2006.01) F23R 3/28 (2006.01) F23R 3/60 (2006.01)

Patent

CA 2464847

A fuel injector for a gas turbine engine combustor includes a centerline axis. The fuel injector also includes a fuel inlet coupled to a cooling air source, an injection tip for discharging fuel into the combustor in a direction that is substantially parallel to the combustor centerline axis, and a body extending between the inlet and the injection tip. The body includes at least one air inlet and at least one air outlet. The air inlet is for receiving cooling air within the body. The outlet is for discharging cooling air external to the combustor.

Un injecteur de carburant pour chambre de combustion de turbine à gaz comporte un axe central. Cet injecteur de carburant comprend aussi une arrivée carburant accouplée à une source d'air de refroidissement, une buse d'injection pour injecter le carburant dans la chambre de combustion dans un sens sensiblement parallèle à l'axe central de la chambre de combustion, et un corps occupant l'espace compris entre l'entrée et la buse d'injection. Ce corps comprend au moins une entrée et une sortie d'air. L'entrée d'air sert à recevoir l'air de refroidissement à l'intérieur du corps. La sortie sert à injecter l'air de refroidissement extérieur dans la chambre de combustion.

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