Gas turbine combustor with quench wake control

A method for controlling temperature deviations in the exhaust gases exiting an annular combustion chamber defined between an inner circumferentially extending liner and an outer circumferentially extending liner spaced radially outboard of and coaxially circumscribing the inner liner, each of the inner circumferentially extending liner and the outer circumferentially extending liner having a heat shield mounted to a shell, wherein combustion dilution air is admitted into the combustion chamber through a plurality of relatively large dilution air admission holes disposed in a circumferentially extending row in each of the inner liner and the outer liner;

• the method comprising the steps of:
• providing a plurality of relatively smaller quench air admission holes in a circumferential row in at least one of the inner and outer liners at a location downstream of the row of relatively large dilution air admission holes, each of said plurality of relatively smaller quench air admission holes including a respective hole in the shell and a corresponding hole in the heat shield of said at least one of the inner and outer liners;
• arranging the plurality of relatively smaller quench air admission holes relative to the plurality of relatively large dilution air admission holes upstream thereof such that there is associated with each relatively large dilution air admission hole a first quench air admission hole and second quench air admission hole, the first quench air admission hole and a second quench air admission hole, the first quench air admission hole being offset laterally in a first lateral direction and the second quench air admission hole being offset laterally in a second lateral direction opposite to the first direction;
• and
• admitting quench air into the combustion chamber through said plurality of quench air admission holes.