Return fluid air cooler system for turbine cooling with optional power extraction
In an aircraft including a gas turbine engine, a system for cooling the gas turbine engine includes a tank provided in a wing of the aircraft, the tank being configured to store a cooling fluid supply; and a heat exchanger provided in the gas turbine engine configured to exchange heat from the compressor discharge air to the cooling fluid.
1. In an aircraft including a gas turbine engine having a compressor and a turbine, a system for cooling compressor discharge air provided to the turbine to cool the turbine, the system comprising:
a tank provided in a wing of the aircraft, the tank being configured to store a cooling fluid supply;
a heat exchanger provided in the gas turbine engine configured to exchange heat from the compressor discharge air to the cooling fluid;
an anti-icing system provided in the wing of the aircraft, wherein the cooling fluid heated by the heat exchanger is provided to the anti-icing system;
a second turbine; and
a generator connected to the second turbine configured to generate electrical power, wherein at least a portion of the cooling fluid heated by the heat exchanger is provided to rotate the second turbine.
2. A system according to claim 1 , further comprising:
a second heat exchanger configured to exchange heat from the cooling fluid to fuel provided from the wing of the aircraft.
3. A system according to claim 1 , further comprising:
a pump configured to pump the cooling fluid in a loop through the heat exchangers.
4. A system according to claim 2 , further comprising:
a pump configured to pump the fuel heated by the second heat exchanger to the wing of the aircraft.
5. A system according to claim 3 , wherein the pump is configured to pump the cooling fluid during at least one of take-off and climb of the aircraft and to not pump the cooling fluid during cruise of the aircraft.
6. A system according to claim wherein the cooling fluid is fuel.
7. A system according to claim 1 , wherein the cooling fluid undergoes a phase change when heated by the heat exchanger.
8. A system according to claim 1 , wherein the cooling fluid is water.
9. A method of cooling compressor discharge air provided to a turbine of a gas turbine engine of an aircraft to cool the turbine, the method comprising:
providing cooling fluid from a tank provided in a wing of the aircraft;
exchanging heat from the compressor discharge air to the cooling fluid with a heat exchanger provided in the gas turbine engine;
providing the cooling fluid heated by the heat exchanger to an anti-icing system provided in the wing and/or a tail of the aircraft; and
providing at least a portion of the cooling fluid heated by the heat exchanger to a second turbine to rotate an electrical generator.
10. A method according to claim 9 , further comprising:
exchanging heat from the cooling fluid to fuel provided from the wing of the aircraft with a second heat exchanger provided in the gas turbine engine.
11. A method according to claim 10 , further comprising:
pumping the cooling fluid in a loop through the heat exchangers.
12. A method according to claim 10 , further comprising:
pumping the fuel heated by the second heat exchanger to the wing of the aircraft.
13. A method according to claim 10 , wherein the cooling fluid is pumped in a loop through the heat exchangers during at least one of take-off and climb of the aircraft and not during cruise of the aircraft.
14. A method according to claim 9 , wherein the cooling fluid is fuel.
15. A method according to claim 9 , wherein the cooling fluid undergoes a phase change when heated by the heat exchanger.
16. A method according to claim 9 , wherein the cooling fluid is water.