To enhance mixing of fuel and air in a combustor for a gas turbine.
The annular combustor 14 suitable for use in the gas turbine engine 10 is disclosed, which has a plurality of fuel injectors 73 and a plurality of apertures 62, 64 circumferentially arranged within inner and outer liners 32, 34 of a combustor chamber 24. Further, each aperture 62 of the inner liner 32 is disposed on one side of a center line An of each fuel injector 73, and each aperture 64 of the outer liner 34 is disposed on the other side of the center line An of each fuel injector 73. In this way, air exhausted from the apertures 62, 64 advantageously opposes a direction of swirl of fuel and air mixture that is injected from the fuel injectors 73, thereby providing enhanced mixing of the fuel and air within the combustor chamber 24, increased residence time and reduction of hot streaks in the inner and outer liners 32, 34.
ONDAS MICHAEL S
NORRIS JASON W
