Patent ID: 7878000

Claim:
A mixer assembly for a gas turbine engine, comprising: (a) a primary fuel injector having a central axis for injecting a primary fuel spray into a primary air stream, wherein fuel is provided at a desired rate and droplets of said fuel spray are within a desired size range, said primary fuel injector further comprising: (1) a fuel passage in flow communication with a fuel supply; (2) a heat shield adjacent said fuel passage; and (3) an annular fuel manifold positioned at a downstream end of said primary fuel injector in flow communication with said fuel passage, wherein fuel is injected by said primary fuel injector at a flow number of at least approximately 10, where the flow number is defined as flow speed divided by the square root of change in pressure; (b) a secondary fuel injector positioned radially outwardly of said primary fuel injector for injecting a secondary fuel spray into a secondary air stream spaced radially outwardly of and surrounding said primary air stream; and, (c) a primary air jet positioned between said primary fuel injector and said secondary fuel injector to direct a portion of an incoming air stream between said primary air stream and said secondary air stream.