Gas turbine combustor having counterflow injection mechanism and method of use

A method, comprising:

• injecting fuel and air at an off-center position and in a direction counterflow to a generally lengthwise downstream flow of combustion products in a gas turbine combustor,
• wherein injecting fuel and air comprises injecting fuel and air from at least one fuel-air 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 at least one fuel-air mechanism extending through the air circulation path, the at least one fuel-air injection mechanism having a fuel passage leading to fuel injection opening and an air injection assembly leading to an air passage and an air injection opening, wherein the fuel and air injection openings are disposed at an off-center position position to inject fuel and air toward the closed rear end of the gas turbine combustor.

A method, comprising:

• injecting fuel and air at an off-center position and in a counterflow direction relative to a generally lengthwise downstream flow combustion products in an a gas turbine combustor,
• wherein injecting fuel and air comprises injecting fuel and air from at least one fuel-air injection mechanism disposed within a combustion liner, the combustor liner disposed within a combustor housing, an air circulation path extending between and along an inner casing and an outer casing of the combustor liner and having a generally lengthwise flow axis extending from a stagnation zone at a closed rear end of the gas turbine combustor to a combustion outlet of the gas turbine combustor, the at least one fuel-air injection mechanism having a fuel passage leading to fuel injection opening and an air injection assembly leading to an air passage and an air injection opening, the outer casing comprising a plurality of openings formed along a length and configured as compressed air inlets,
• wherein the fuel and air injection openings are disposed at an off-center position to inject fuel and air toward a the closed rear end of the gas turbine combustor and in a direction generally counterflow to a generally lengthwise downstream flow of combustion products in the gas turbine combustor.