Cooled cooling air system for a gas turbine
In an aircraft including a gas turbine engine having a compressor including a compressor booster, a turbine, and a nacelle, a system for cooling compressor discharge air provided to the turbine to cool the turbine includes a heat exchanger provided in a nacelle compartment of the gas turbine engine configured to cool the compressor discharge air by exchanging heat from the compressor discharge air to a cooling fluid; and a cooling fluid circuit configured to circulate cooling fluid through the heat exchanger and a heat sink, wherein the heat sink is at least one of an inlet of the nacelle compartment, an inlet of the compressor booster, or outlet guide vanes of the gas turbine engine.
1. In an aircraft including a gas turbine engine having a compressor including a compressor booster, a turbine, and a nacelle, a system for cooling compressor discharge air provided to the turbine to cool the turbine, the system comprising:
a heat exchanger provided in a nacelle compartment of the gas turbine engine configured to cool the compressor discharge air by exchanging heat from the compressor discharge air to a cooling fluid; and
a cooling fluid circuit configured to circulate cooling fluid through the heat exchanger and a heat sink, wherein the heat sink includes one or more outlet guide vanes of the gas turbine engine and also includes at least one of a nacelle aft core cowl, a nacelle external cowl, a thrust reverser outer fixed structure, or one or more other surfaces exposed to a bypass duct.
2. A system according to claim 1 , wherein at least a portion of the cooled compressor discharge air is provided to a high pressure compressor of the compressor.
3. A system according to claim 1 , wherein at least a portion of the cooled compressor discharge air is provided to at least one of a disk of the high pressure turbine or blades of the high pressure turbine.
4. A system according to claim 2 , wherein another portion of the cooled compressor discharge air is provided to a rear cone of the high pressure compressor.
5. A system according to claim 1 , further comprising:
a pump configured to pump the cooling fluid, wherein the pump is configured to pump the cooling fluid during at least one of take-off of the aircraft, climb of the aircraft, or icing of the nacelle compartment inlet or compressor booster inlet, and to not pump the cooling fluid during cruise of the aircraft.
6. A system according to claim 1 , wherein the cooling fluid is polyalphaolefin or water with glycol or ammonia.
7. A system according to claim 1 , further comprising:
a second turbine provided in the nacelle compartment; 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.
8. A system according to claim 7 , wherein the cooling fluid undergoes a phase change when heated by the heat exchanger.
9. A system according to claim 1 , wherein the cooling fluid does not undergo a phase change when heated by the heat exchanger.
10. A method of cooling compressor discharge air provided to a turbine of a gas turbine engine of an aircraft having a compressor including a compressor booster, a turbine, and a nacelle, to cool the turbine, the method of cooling the compressor discharge air comprising:
circulating a cooling fluid through a heat exchanger and a heat sink, wherein the heat sink includes at least one of a nacelle aft core cowl or a thrust reverser outer fixed structure; and
exchanging heat in the heat exchanger from the compressor discharge air to the cooling fluid to cool the compressor discharge air.
11. A method according to claim 10 , further comprising:
providing at least a portion of the cooled compressor discharge air to a high pressure compressor of the compressor.
12. A method according to claim 10 , wherein another portion of the cooled compressor discharge air is provided to at least one of a disk of the high pressure turbine or blades of the high pressure turbine.
13. A method according to claim 11 , wherein another portion of the cooled compressor discharge air is provided to a rear cone of the high pressure compressor.
14. A method according to claim 10 , further comprising:
pumping the cooling fluid during at least one of take-off of the aircraft, climb of the aircraft, or icing of the nacelle compartment inlet or compressor booster inlet.
15. A method according to claim 10 , further comprising:
providing at least a portion of the cooling fluid heated by the heat exchanger to rotate a second turbine connected to an electrical generator.
16. A method according to claim 15 , wherein the cooling fluid undergoes a phase change when heated by the heat exchanger.
17. A method according to claim 10 , wherein the cooling fluid does not undergo a phase change when heated by the heat exchanger.
18. A system according to claim 1 , wherein the heat exchanger is located radially outward of the combustor.
19. In an aircraft including a gas turbine engine having a compressor including a compressor booster, a turbine, a nacelle, and a bypass duet, a system for cooling compressor discharge air provided to the turbine to cool the turbine, the system comprising: a heat exchanger provided in a nacelle compartment of the gas turbine engine configured to cool the compressor discharge air by exchanging heat from the compressor discharge air to a cooling fluid; and a cooling fluid circuit configured to circulate cooling fluid through the heat exchanger and a heat sink, wherein the heat sink includes at least one of a nacelle aft core cowl or a thrust reverser outer fixed structure.