Patent ID: 7802431

Claim:
A combustor for a gas turbine engine comprising: an intake, an outlet, and at least one swirler assembly disposed there between; an inner wall partially defining a combustion zone, comprising an upstream end and a downstream end; an outer wall disposed about the inner wall, comprising an upstream end sealingly connected to the inner wall, spaced a distance therefrom to define a flow channel for passage of a cooling airflow, the flow channel comprising a flow-based upstream end and a flow-based downstream end; and an end-capping ring sealingly connected to the inner wall proximate the outlet and upstream of the outer wall downstream end, extending around the downstream end of the outer wall, and terminating upstream of the outer wall downstream end and downstream of the outer wall upstream end, forming with said outer wall downstream end a flow-reversing channel communicating with the upstream end of the flow channel, wherein at the flow channel downstream end the inner wall comprises a plurality of holes in fluid communication with the flow channel and the combustion zone, and, wherein during operation the plurality of holes is effective to control the cooling airflow into the combustion zone; and wherein the end-capping ring supports by rigid attachment thereto a spring clip assembly extending radially outward; the spring clip defining an inlet for the cooling airflow.