Cooling architecture for liquid hydrogen superconducting system
An aircraft propulsion system a cryogenic fuel system, a superconducting electrical device that is operable at a cryogenic temperature, a cooling system where a cooling fuel flow is utilized for maintaining the superconducting electrical device at the cryogenic temperature, an ejector where the primary fuel flow from the fuel system drives the cooling fuel flow through the cooling system to form a combined fuel flow, and a separator where a first portion of the combined fuel flow from the ejector is routed to the core engine and a second portion of the combined fuel flow is routed back to the cooling system.
1. A method of managing thermal conditions of a superconducting electrical device of an aircraft propulsion system comprising:
driving a cooling fuel flow with a primary fuel flow through an ejector to output a combined fuel flow;
separating the combined fuel flow including the primary fuel flow and the cooling fuel flow in a separator into a first portion routed to a core engine and a second portion for cooling the superconducting electrical device;
cooling the second portion of the combined fuel flow to generate the cooling fuel flow in a preliminary heat exchanger with a portion of the primary fuel flow upstream of the ejector; and
transferring thermal energy from the superconducting electrical device into the cooling flow to maintain the superconducting electrical device within a temperature range.
2. The method as recited in claim 1 , further comprising further cooling the cooling fuel flow from the preliminary heat exchanger by expansion through an expansion valve.
3. The method as recited in claim 1 , further comprising generating a motive energy within the primary flow by accepting thermal energy from at least one heat load prior to flowing into the ejector.
4. The method as recited in claim 1 , further comprising transferring thermal energy from the superconducting electrical device into a coolant within a coolant loop and transferring thermal energy from the coolant into the cooling fuel flow.
5. An aircraft propulsion system comprising:
a core engine configured to generate an exhaust gas flow;
a cryogenic fuel system including a fuel pump configured to communicate a primary fuel flow to the core engine;
a superconducting electrical device operable at a cryogenic temperature;
a cooling system where a cooling fuel flow is utilized for maintaining the superconducting electrical device at the cryogenic temperature;
an ejector where the primary fuel flow from the fuel system drives the cooling fuel flow through the cooling system to form a combined fuel flow; and
a separator where a first portion of the combined fuel flow from the ejector is routed to the core engine and a second portion of the combined fuel flow is routed back to the cooling system.
6. The aircraft propulsion system as recited in claim 5 , including a preliminary heat exchanger where the second portion of the combined fuel flow is cooled by a portion of the primary fuel flow upstream of the ejector.
7. The aircraft propulsion system as recited in claim 6 , including at least one heat load in thermal communication with the primary fuel flow, wherein the primary fuel flow is heated by the at least one heat load upstream of the ejector.
8. The aircraft propulsion system as recited in claim 6 , including a superconducting device heat exchanger where thermal energy from the superconducting electrical device is transferred into the cooling fuel flow of the cooling system.
9. The aircraft propulsion system as recited in claim 6 , including an expansion device disposed between the preliminary heat exchanger and the superconducting electrical device where the cooling fuel flow is cooled through expansion to generate a supercooling flow.
10. The aircraft propulsion system as recited in claim 5 , wherein the cooling system includes a coolant loop with a secondary coolant, and the secondary coolant is cooled by the cooling fuel flow in a coolant loop heat exchanger.
11. The aircraft propulsion system as recited in claim 10 , wherein the secondary coolant is of a compound different than the cooling fuel flow.
12. The aircraft propulsion system as recited in claim 5 , wherein the fuel system includes a cryogenic fuel tank that is maintained at temperatures sufficient to maintain a cryogenic fuel in a liquid state.
13. The aircraft propulsion system as recited in claim 5 , wherein the superconducting electrical device comprises one of an electric motor or a generator.
14. The aircraft propulsion system as recited in claim 13 , wherein the electric motor is coupled to a portion of the core engine to provide a portion of power to drive a propulsor.
15. The aircraft propulsion system as recited in claim 5 , wherein the separator comprises a controllable valve assembly.
16. A superconducting thermal management system for an aircraft propulsion system comprising:
a superconducting electrical device;
a heat exchanger in thermal communication with the superconducting electrical device, the heat exchanger configured to transfer thermal energy from the superconducting electrical device into a cooling fuel flow;
an ejector configured to receive a primary fuel flow and the cooling fuel flow, the ejector configured to drive the cooling fuel flow using the primary fuel flow and form a combined fuel flow with the primary fuel flow and the cooling fuel flow;
a separator in fluid communication with the ejector and the heat exchanger and configured to separate the combined fuel flow into a first portion routed to a core engine and a second portion routed to the heat exchanger for cooling the superconducting electrical device.
17. The superconducting thermal management system as recited in claim 16 , including a preliminary heat exchanger where the second portion of the combined fuel flow is cooled by a portion of the primary fuel flow to generate the cooling fuel flow.
18. The superconducting thermal management system as recited in claim 17 , including an expansion device for further cooling the cooling fuel flow.
19. The superconducting thermal management system as recited in claim 17 , including a secondary coolant loop with a secondary coolant, the secondary coolant transferring thermal energy generated by the superconducting device into the cooling fuel flow in a coolant loop heat exchanger.
20. The superconducting thermal management system as recited in claim 16 , wherein the primary fuel flow and the cooling fuel flow comprise liquid hydrogen.