초록 ▼

A combustor for a gas turbine engine is disclosed which is able to operate efficiently at inlet air flows having a high subsonic Mach Number. The combustor has an outer liner and an inner liner spaced therefrom, wherein a combustion chamber is defined therebetween. A dome inlet module is provided wh

A combustor for a gas turbine engine is disclosed which is able to operate efficiently at inlet air flows having a high subsonic Mach Number. The combustor has an outer liner and an inner liner spaced therefrom, wherein a combustion chamber is defined therebetween. A dome inlet module is provided which is in flow communication with compressed air flow from a compressor upstream thereof. The dome inlet module has an outer member fixed to the outer liner and an inner member fixed to the inner liner, wherein a flow passage is defined by the outer and inner members for the compressed air flow to flow freely from a compressor to the combustion chamber. Fuel atomizers are then utilized to inject fuel into the flow passage so that the fuel is mixed with the compressed air stream to form a fuel/air mixture which enters the combustion chamber.

대표청구항 ▼

A combustor for a gas turbine engine having a compressor providing compressed air flow, comprising: (a) an outer liner; (b) an inner liner spaced from said outer liner, wherein a combustion chamber is defined therebetween; (c) a dome inlet module in flow communication with said compressed air flow h

A combustor for a gas turbine engine having a compressor providing compressed air flow, comprising: (a) an outer liner; (b) an inner liner spaced from said outer liner, wherein a combustion chamber is defined therebetween; (c) a dome inlet module in flow communication with said compressed air flow having an outer member fixed to said outer liner and an inner member fixed to said inner liner, wherein a flow passage is defined therebetween for an air stream to flow from said compressor to said combustion chamber; (d) means for injecting fuel into said flow passage, wherein said fuel mixes with said air stream to form a fuel/air mixture which enters said combustion chamber; and (e) means for igniting and stabilizing a flame within said combustion chamber, said igniting and flame stabilizing means further comprising: (1) a trapped vortex cavity positioned immediately downstream of said dome inlet module; (2) means for injecting air into said trapped vortex cavity; (3) means for injecting fuel into said trapped vortex cavity; and (4) an igniter positioned adjacent to said trapped vortex cavity for igniting said fuel and air therein to produce pilot combustion gases.