Patent ID: 7272933

Claim:
A method for operating a gas turbine engine, including a first compressor, a second compressor, and a turbine, coupled together in serial flow arrangement, said method comprising: channeling compressed airflow discharged from the first compressor through an intercooler having a cooling medium flowing therethrough; operating the intercooler such that the compressed airflow is facilitated to be cooled and condensate is formed in the intercooler from the compressed airflow; channeling the cooled compressed airflow and the condensate from the intercooler to an inlet of the second compressor to facilitate reducing an operating temperature of the gas turbine engine, wherein channeling the condensate comprises: channeling the condensate from the intercooler to an annular manifold using an injection system coupled in flow communication between the intercooler and the manifold, wherein the injection system facilitates supplying the condensate to a plurality of nozzles coupled to the manifold; and ejecting the condensate from the plurality of nozzles to an inlet of the second compressor.