Systems And Methods For Controlling An Inlet Air Temperature Of An Intercooled Gas Turbine Engine

Abstract: The present application and the resultant patent provide an intercooled gas turbine engine. The intercooled gas turbine engine may include a low pressure compressor configured to produce a compressed flow of air, an intercooler, a low pressure compressor configured to produce a compressed flow of air, a high pressure compressor, a second air line positioned between the intercooler and the high pressure compressor and configured to direct the first portion of the compressed flow of air toward the high pressure compressor, and a bypass air line positioned between the low pressure compressor and the high pressure compressor and configured to direct a second portion of the compressed flow of air to the second air line. A related method of controlling a temperature of an incoming flow of air supplied to a core engine of an intercooled gas turbine engine also is provided. FIG.2

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