Patent ID: 7685827

Claim:
A cooling system for a gas turbine engine that includes at least a first compressor, a second compressor, and a turbine, said cooling system comprising: an intercooler coupled downstream from the first compressor such that compressed air discharged from the first compressor is routed therethrough and channeled to an inlet of the second compressor, said intercooler having a working fluid flowing therethrough; an injection system coupled in flow communication with said intercooler; and an annular manifold extending circumferentially around one of the first compressor or the second compressor and comprising a plurality of nozzles, said injection system configured to channel condensate formed in said intercooler into said annular manifold to facilitate supplying a flow of condensate to said plurality of nozzles, said plurality of nozzles configured to eject condensate into one of the first compressor or second compressor to facilitate reducing an operating temperature of the gas turbine engine.