Fan exit guide vane thermal management system for conventional gas turbine engines

A method for cooling a hot fluid from a thermal management system of a gas turbine engine, comprising:

• receiving the hot fluid from the thermal management system of the gas turbine engine through at least one inlet connected to a first end of at least one first channel defined within at least one fan exit guide vane of the gas turbine engine;
• passing the hot fluid from the thermal management system of the gas turbine engine through the at least one first channel defined within the at least one fan exit guide vane located aft of a rotor fan of the gas turbine engine;
• receiving bleed air from a low-pressure compressor of the gas turbine engine through at least one second channel defined within the at least one fan exit guide vane;
• cooling the hot fluid passing through the at least one first channel within the at least one fan exit guide vane by air from the rotor fan passing over the at least one fan exit guide vane in a ground idle mode of operation to provide a cooled fluid;
• cooling the hot fluid passing through the at least one first channel by the bleed air passing through the at least one second channel defined by the at least one fan exit guide vane in the first ground idle mode of operation to provide the cooled fluid;
• cooling the hot fluid passing through the at least one first channel within the at least one fan exit guide vane only by the air from the rotor fan passing over the at least one fan exit guide vane to provide the cooled fluid wherein the bleed air is not provided to the at least one second channel in a maximum takeoff mode of operation;
• and
• providing the cooled fluid to the thermal management system of the gas turbine engine via at least one outlet connected to a second end of the at least one first channel.

A system for cooling a hot fluid from a thermal management system of a gas turbine engine, comprising:

• at least one fan exit guide vane located aft of a rotor fan of the gas turbine engine, wherein the at least one fan exit guide vane defines at least one first channel therein for the hot fluid from the thermal management system of the gas turbine engine and at least one second channel therein for receiving bleed air from a low-pressure compressor of the gas turbine engine;
• at least one inlet connected to a first end of the at least one first channel for receiving the hot fluid from the thermal management system of the gas turbine engine;
• at least one outlet connected to a second end of the at least one first channel for providing a cooled fluid to the thermal management system of the gas turbine engine;
• wherein in a ground idle mode of operation of the gas turbine engine the hot fluid passing through the at least one first channel within the at least one fan exit guide vane is cooled by air from the rotor fan passing over the at least one fan exit guide vane and is further cooled by the bleed air passing through the at least one second channel defined by the at least one fan exit guide vane to provide the cooled fluid;
• and
• wherein in at least one of a maximum takeoff mode or cruising mode of operation of the gas turbine engine the hot fluid passing through the at least one first channel within the at least one fan exit guide vane is cooled only by the air from the rotor fan passing over the at least one fan exit guide vane to provide the cooled fluid and the bleed air is not provided to the at least one second channel.