Patent ID: 8789375

Claim:
A method, comprising: injecting fuel and air from an injection mechanism disposed in a combustion liner of an axial gas turbine combustor, the combustion liner disposed within a combustor housing and including an outer casing comprising a plurality of openings formed along a length and configured as compressed air inlets, an inner casing having a closed rear end and a combustion outlet and an air circulation path extending between and along the inner and outer casings, the injection mechanism including at least one fuel injector extending through the air circulation path, the at least one fuel injector having a fuel passage leading to a fuel injection opening and an air injection assembly leading to an air passage and an air injection opening, wherein the fuel injection opening and the air injection opening are disposed at an off-center position to provide injecting of the fuel and air toward the closed rear end of the inner casing in a direction counterflow to a generally lengthwise downstream flow of combustion products in the axial gas turbine combustor.