Turbine engine having fuel-cooled air intercooling
A turbine engine is disclosed. The turbine engine may have a first compressor configured to pressurize inlet air, and a second compressor configured to further pressurize the inlet air. The turbine engine may also have a cooling circuit fluidly located to cool the inlet air after the inlet air is pressurized by the first compressor and before the inlet air is further pressurized by the second compressor. The cooling circuit may have a first heat exchanger configured to transfer heat from the inlet air to a fuel of the engine, and a second heat exchanger configured to transfer heat from exhaust of the engine to the fuel of the engine.
1. A turbine engine, comprising:
a first compressor configured to pressurize inlet air;
a second compressor configured to further pressurize the inlet air;
a cooling circuit located to cool the inlet air after the inlet air is pressurized by the first compressor and before the inlet air is further pressurized by the second compressor, the cooling circuit including:
a first heat exchanger configured to transfer heat from the inlet air to a fuel of the engine; and
a second gas-to-gas heat exchanger configured to transfer heat from the inlet air to the fuel;
a third heat exchanger configured to transfer heat from exhaust of the engine to the fuel of the engine.
2. The turbine engine of claim 1 , wherein the first heat exchanger is a liquid-to-gas type heat exchanger.
3. The turbine engine of claim 1 , further including a fourth heat exchanger located upstream of the first heat exchanger and configured to transfer heat from the inlet air to a coolant different from the fuel.
4. The turbine engine of claim 1 , further including a catalytic cracker configured to receive fuel from the third heat exchanger and condition the fuel for combustion.
5. The turbine engine of claim 1 , further including a combustor configured to receive the cooled and compressed inlet air, wherein all of the fuel passing through the first, second, and third heat exchangers is directed to mix and combust with the cooled and compressed air in the combustor.
6. The turbine engine of claim 1 , wherein the cooling circuit is an open loop.
7. The turbine engine of claim 1 , further including a recuperator configured to transfer heat from the exhaust to the inlet air after the inlet air has been further pressurized by the second compressor.
8. The turbine engine of claim 1 , wherein the fuel is anhydrous ammonia.
9. A method of generating power, comprising:
pressurizing air during a first compression stage;
further pressurizing the air during a second compression stage;
transferring heat with a first heat exchanger from the pressurized air to a fuel between the first and second compression stages when the fuel is in a liquid state;
transferring heat with a second heat exchanger from the air to the fuel between the first and second compression stages when the fuel is in gaseous state;
transferring heat with a third heat exchanger from an exhaust flow to the fuel; and combusting a mixture of the further pressurized air and the heated fuel.
10. The method of claim 9 , further including transferring heat with a fourth heat exchanger from the air to a coolant different from the fuel.
11. The method of claim 9 , further including cracking the fuel prior to combusting the mixture.
12. The method of claim 9 , wherein all of the fuel receiving heat from the air is directed to mix with the further pressurized air.
13. The method of claim 9 , further including transferring heat with a recuperator from the exhaust flow to the air exiting said second compression stage.
14. The method of claim 9 , wherein the fuel is anhydrous ammonia.
15. An engine, comprising:
a first compressor configured to pressurize inlet air;
a second compressor configured to further pressurize the inlet air;
a combustor configured to receive and combust a mixture of the further pressurized air and an ammonia fuel; and
an open loop cooling circuit located to cool the inlet air after the inlet air is pressurized by the first compressor and before the inlet air is further pressurized by the second compressor, the open loop cooling circuit including:
a first liquid-to-gas heat exchanger configured to transfer heat from the pressurized inlet air to the ammonia fuel,
a second gas-to-gas heat exchanger located downstream of the first liquid-to-gas heat exchanger configured to transfer heat from the pressurized inlet air to the ammonia fuel, wherein all of the ammonia fuel passing through the heat exchanger is directed to mix and combust with the cooled and compressed air in the combustor.
16. The engine of claim 15 , further including a catalytic cracker configured to receive the ammonia fuel from the heat exchanger and condition the ammonia fuel for combustion.
17. The engine of claim 15 , further including a recuperator configured to transfer heat from an exhaust flow to the inlet air after the inlet air has been further pressurized by the second compressor.