Counter swirl annular combustor

摘要

An annular combustor 14 suitable for use in a gas turbine engine having a plurality of fuel injectors 73 and a plurality of apertures 62, 64 circumferentially arranged within the inner 32 and outer 34 liners of the combustion chamber 24 is disclosed. Further, each of the apertures 62 of the inner liner 32 are disposed on one side of the centerline An of each of the fuel injectors 73 and each of the apertures 64 of the outer liner 34 are disposed on the opposing side of the centerline of each of the fuel injectors 73. In this way, air exhausted from the apertures 62, 64 advantageously opposes the direction of swirl of the fuel and air mixture that is injected from the fuel injectors 73 thereby providing enhanced mixing of the fuel and air within the combustion chamber 24, increased residence time and the reduction of hot streaks in the inner and outer liners 32, 34. <IMAGE>