| 摘要 |
A combustor (30) for a gas turbine engine having an annular combustion chamber (32) includes a plurality of main fuel injection and air swirler assemblies (36) and a plurality of pilot fuel injection and air swirler assemblies (38) disposed in a circumferential ring extending about the circumferential expanse of a forward bulkhead (34). The plurality of pilot fuel injection and air swirler assemblies (38) are interspersed amongst and disposed in the circumferential ring of main fuel injection and air swirler assemblies (36). Fuel being supplied to the combustor (30) is selectively distributed between the plurality of main fuel injection and air swirler assemblies (36) and the plurality of pilot fuel injection and air swirler assemblies (38) in response to the level of power demand on the gas turbine engine. The air swirlers (44) of the plurality of main fuel injection and air swirler assembles (36) are adapted to impart a lower level of swirl of air passing therethrough relative the air swirlers (56) of the plurality of pilot fuel injection and air swirler assemblies (38). |
