Patent ID: 8171735

Claim:
A mixer apparatus for a gas turbine engine combustor, comprising: (a) a generally cylindrical primary fuel injector with upstream and downstream ends, the primary fuel injector including: (1) a hollow central portion configured to pass a first air stream therethrough; (2) an annular fuel passage positioned at the downstream end of the primary fuel injector, the fuel passage configured to discharge an annular first fuel stream surrounding the first air stream; (b) an annular splitter surrounding the primary fuel injector, the splitter configured to pass a second air stream surrounding the first fuel stream; (c) an annular first housing surrounding the primary fuel injector and the splitter, the first housing having an exit positioned axially downstream of the primary fuel injector and the splitter; and (d) a plurality of fuel injection ports positioned in a radial array outside the first housing, the fuel injection ports disposed in communication with a fuel supply and positioned to discharge a second fuel stream into a third air stream at a position axially upstream of the exit of the first housing.