Patent ID: 8920109

Claim:
A thermal management arrangement in a gas turbine engine, comprising: a conduit-arrangement providing fluid communication between a compressor section and: a relatively thermally responsive portion of a turbine vane carrier; and a relatively thermally unresponsive portion of the turbine vane carrier, the conduit-arrangement comprising: a general cooling flow outlet disposed proximate the relatively thermally responsive portion of the turbine vane carrier and configured to discharge a general cooling flow; and an impingement flow outlet disposed proximate the relatively thermally unresponsive portion and configured to discharge an impingement flow onto the relatively thermally unresponsive portion; wherein the thermal management arrangement is configured such that a flow rate of the impingement flow is effective to accelerate a thermal response of the relatively thermally unresponsive portion toward a thermal response of the relatively thermally responsive portion and wherein the turbine vane carrier comprises a discrete ring disposed within an outer casing of the gas turbine engine and comprising the relatively thermally responsive portion and the relatively thermally unresponsive portion.