SYSTEMS AND METHODS FOR CONTROLLING AN INLET AIR TEMPERATURE OF AN INTERCOOLED GAS TURBINE ENGINE

摘要

The present application relates to an intercooled gas turbine engine. The intercooled gas turbine engine comprises: a low pressure compressor configured to produce a compressed flow of air; an intercooler; a first air line positioned between the low pressure compressor and the intercooler and configured to direct a first portion of the compressed flow of air to the intercooler; 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.