Patent ID: 7716931

Claim:
A combustor for a gas turbine engine, said combustor comprising: a combustor liner assembly comprising an outer combustor liner defining at least a portion of a combustion chamber, said outer combustor liner having a radially extending first end defining a combustion chamber input opening and an axially extending second end defining a combustion chamber output opening, said first end transitioning into said second end to define an arcuate cross-sectional shape of said combustor liner; a dome assembly coupled to said first end, said first end extending downstream from said dome assembly, said dome assembly comprising a cyclone positioned in flow communication with a discharge opening of a compressor of the gas turbine engine, said cyclone having a plurality of cyclone vanes positioned circumferentially about said cyclone, said cyclone vanes configured to direct a flow of compressed air from the compressor into a fuel-air mixer cavity, wherein a flow passage of an aft most cyclone vane of said plurality of cyclone vanes is larger than a flow passage of a forward most cyclone vane of said plurality of cyclone vanes; and a fuel nozzle positioned within the cyclone in a radial configuration.