Patent ID: 7975487
Filing Date: 2011-07-12
Classification: F23R,Y02T

Abstract:
1. A method of operating a combustor assembly of a gas turbine engine, the method comprising: flowing compressed air received from a compressor into a combustor housing; flowing a first portion of the compressed air into an annular passage of an impingement dome assembly; flowing the first portion of the compressed air from the annular passage of the impingement dome assembly onto a dome; flowing the first portion of the compressed air from the dome to a plurality of fuel injectors configured to inject fuel for combustion; flowing a second portion of the compressed air from the combustor housing to the fuel injectors for combustion; and flowing a third portion of the compressed air from the combustor housing to a liner assembly of the combustor, wherein at least a portion of the third portion flows through a passageway in the liner assembly and through an orifice in the liner assembly into an exit cone.