Patent ID: 8109098

Claim:
A can combustor for a gas turbine engine comprising: an intake, an outlet, and at least one swirler assembly disposed there between; a combustion liner comprising an inner wall that partly defines a combustion zone, wherein the combustion zone and the inner wall share a common longitudinal axis and the common longitudinal axis is disposed in the combustion zone, and an outer wall disposed radially outward of the inner wall with respect to the common longitudinal axis, the inner wall and outer wall defining there between a flow channel for passage of a cooling air flow; and a flow control ring directly connected to downstream ends of the inner and outer walls of the combustor proximate the outlet, wherein the flow control ring comprises a plurality of holes in fluid communication with the flow channel and the combustion zone effective to deliver a plurality of discrete flows of cooling fluid into the combustion zone, and wherein during operation the plurality of holes is effective to control the cooling air flow.