Gas turbine engine combustor with improved cooling

Details Gas turbine engine combustor with improved cooling Gas turbine engine combustor with improved cooling

F - Mech Eng,Light,Heat,Weapons

23

R

F23R 3/06 (2006.01)

Patent

CA 2583400

A gas turbine engine combustor liner having a plurality of holes defined therein for directing air into the combustion chamber. The plurality of holes provide a greater cooling air flow in regions intermediate each diffuser pipe than in other areas of the combustor liner.

L'invention porte sur un revêtement de chambre de combustion de turbine à gaz muni d'une pluralité d'ouvertures conçues pour diriger l'air vers la chambre de combustion. L'éventail d'ouvertures permet d'acheminer un plus grand flux d'air de refroidissement dans des zones situées entre chaque tuyau de diffuseur plutôt que dans d'autres secteurs du revêtement de la chambre de combustion.

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