Patent ID: 7568343

Claim:
A gas turbine engine comprising: a compressor connected to a rotor shaft; a turbine connected to the rotor shaft; an annular combustor positioned between the compressor and the turbine and encircling the rotor shaft; the annular combustor being defined by an outer wall and an inner wall; the annular combustor having an axial length greater than a distance between the outer wall and the inner wall; the annular combustor forming a primary combustion zone in a forward end of the combustor downstream from the compressor and a secondary combustion zone immediately downstream from the primary combustion zone; a first fuel injection means to inject a fuel into the primary combustion zone to produce a primary combustion swirl; a second fuel injection means to inject a fuel into the secondary combustion zone to produce a secondary combustion swirl in an opposite direction than the primary combustion swirl direction; the first and second fuel injection means injects both fuels from one of the outer or inner walls of the combustor, and the distance between the inner wall and the outer wall of the combustor is short enough so that the first and second fuels and air are impinged against an opposite wall to produce the swirl in the combustion chamber; the first and second fuel injection means includes a rotary cup injector rotatably fixed to the rotor shaft, the rotary cup injector includes a front face and a rear face; and fuel lines in association with the first and second fuel injector means such that the fuel is supplied onto the front face and rear face, and then discharged as a thin film into the primary and secondary combustion zone.