Systems and methods for controlling an inlet air temperature of an intercooled gas turbine engine

A method of controlling a temperature of an incoming flow of air supplied to a core engine of an intercooled gas turbine engine, the method comprising:

• producing a compressed flow of air with a low pressure compressor;
• directing a first portion of the compressed flow of air to an intercooler for cooling therein;
• directing a second portion of the compressed flow of air to bypass the intercooler;
• mixing the first portion of the compressed flow of air and the second portion of the compressed flow of air downstream of the intercooler to form the incoming flow of air;
• and
• directing the incoming flow of air to the core engine.

An intercooled gas turbine engine, comprising:

• 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;
• 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 combustor in communication with the high pressure compressor;
• and
• a high pressure turbine in communication with the combustor.