| 摘要 |
A mixer assembly (100) for use in a combustion chamber (62) of a gas turbine engine (10) including a pilot mixer (102), a main mixer (104), and a fuel manifold (106). The pilot mixer (102) includes: an annular pilot housing (108) having a hollow interior; a primary fuel injector (110) mounted in the pilot housing (108) and adapted f or dispensing droplets of fuel to the hollow interior of the pilot housing (108 ); a plurality of axial swirlers (112,114) positioned upstream from the primary fuel inject or (110), each of the plurality of swirlers (112,114) having a plurality of vanes for swirling air traveling through the respective swirler to mix air and the droplets of fuel dispensed by the primary fuel injector (110); and, a plurality of secondary fuel injection ports (134) for introducing fuel into the hollow interior of the pilot housing (108). The main mixer (104) further includes: a main housing (124) surrounding the pilo t housing (108) and defining an annular cavity (126); a plurality of fuel injection ports (128) for introducing fuel into the cavity (126); and, at least one swirler (130) positioned upstream from the plurality of fuel injection ports (128), each o f the main mixer swirlers (130) having a plurality of vanes for swirling air traveling through the respective swirler to mix air and the droplets of fuel dispensed by the main mixer fuel injection ports (128). The fuel manifold (106) is in flow communication with the plurality of secondary fuel injection ports (134) in the pilot mixer (102) a nd the plurality of fuel injection ports (128) in the main mixer (104).
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