초록 ▼

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 compr

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.

대표청구항 ▼

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

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; anda 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; andproviding 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.