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EP-4737326-A2 - SYSTEM FOR SUPERCONDUCTING ELECTRONICS IN AEROSPACE APPLICATIONS

EP4737326A2EP 4737326 A2EP4737326 A2EP 4737326A2EP-4737326-A2

Abstract

A powertrain system (10) of an aircraft includes one or more electrical components (16, 24, 28, 32) to provide electrical power to one or more electrical loads (20) of the aircraft. The system (10) further includes a rechargeable cryogenic heat sink (42) containing a volume of cryogenic cooling material. The cryogenic heat sink (42) is configured to cool the one or more electrical components (16...32). A method of operating a powertrain system (10) of an aircraft includes generating thermal energy at one or more electrical components (16...32) of the powertrain system (10), fluidly connecting a cryogenic heat sink (42) to the one or more electrical components (16...32), and cooling the one or more electrical components (16...32) via a volume of cryogenic cooling material of the cryogenic heat sink (42).

Inventors

  • TERWILLIGER, NEIL J.
  • LENTS, CHARLES E.
  • Baig, Zubair A.
  • CORDATOS, HARALAMBOS
  • STAUBACH, JOSEPH B.
  • MACDONALD, MALCOLM P.

Assignees

  • RTX Corporation

Dates

Publication Date
20260506
Application Date
20230210

Claims (15)

  1. A powertrain system (10) for an aircraft, comprising: one or more electrical components (16, 24, 28, 32) to provide electrical power to one or more electrical loads (20) of the aircraft; and a rechargeable cryogenic heat sink (42) containing a volume of cryogenic cooling material, the cryogenic heat sink (42) configured to cool the one or more electrical components (16...32).
  2. The powertrain system (10) of claim 1, wherein the volume of cryogenic cooling material is one or more of a hydrogen, helium, neon, nitrogen material.
  3. The powertrain system (10) of claim 1 or 2, wherein the volume of cryogenic material is at a heat sink temperature lower than a superconducting temperature of the one or more electrical components (16....32).
  4. The powertrain system (10) of claim 1, 2 or 3, wherein the cryogenic heat sink (42) is connected to the one or more electrical components (16...32) via an intermediate cooling loop (44) carrying an intermediate cooling fluid.
  5. The powertrain system (10) of any preceding claim, wherein the volume of cryogenic material exchanges thermal energy with an or the intermediate cooling fluid at an intermediate heat exchanger (46).
  6. The powertrain system (10) of any preceding claim, wherein the volume of cryogenic material is a primary propulsion fuel of the aircraft.
  7. The powertrain system (10) of any preceding claim, wherein the one or more electrical components (16...32) include one or more of an electrical generator (16), a rectifier (28), an inverter (32), and an electric motor (24).
  8. The powertrain system (10) of any preceding claim, wherein the cryogenic heat sink (42) undergoes a phase change while absorbing heat from the one or more electrical components (16...32).
  9. A propulsion system for an aircraft, comprising: one or more power units (12) to generate electrical energy utilizing a flow of fuel (14); one or more propulsion units (18) operably connected to and driven by the electrical energy; the powertrain system (10) of any preceding claim, the one or more electrical components (16...32) operably connected to the one or more power units (12) and/or the one or more propulsion units (18).
  10. The propulsion system of claim 9, wherein the volume of cryogenic material is a fuel source (36) of the flow of fuel (14).
  11. A method of operating a powertrain system (10) of an aircraft, comprising: generating thermal energy at one or more electrical components (16...32) of the powertrain system (10); fluidly connecting a cryogenic heat sink (42) to the one or more electrical components (16...32); and cooling the one or more electrical components (16...32) via a volume of cryogenic cooling material of the cryogenic heat sink (42).
  12. The method of claim 11, further comprising periodically recharging the cryogenic heat sink (42).
  13. The method of claim 12, wherein the recharging occurs when the aircraft is on the ground.
  14. The method of claim 11, 12 or 13, further comprising: exchanging thermal energy between the volume of cryogenic material and an intermediate cooling fluid circulated through an intermediate cooling loop (44); and exchanging thermal energy between the intermediate cooling fluid and the one or more electrical components (16...32) to cool the one or more electrical components (16...32).
  15. The method of any of claims 11 to 14, wherein the volume of cryogenic material is a primary propulsion fuel of the aircraft and/or the volume of cryogenic material is at a heat sink temperature lower than a superconducting temperature of the one or more electrical components (16...32).

Description

TECHNICAL FIELD The present disclosure pertains to the art of aircraft, and in particular to electronics and propulsion systems for aircraft. BACKGROUND Electric powertrains for aircraft offer the potential for the introduction of new power sources and propulsion configurations to the aircraft, such as fuel cell systems and distributed propulsion systems. There are, however, significant difficulties with large scale distribution of electric power onboard aircraft. Losses of 10% of the transmitted energy to heat and the increased drag associated with rejecting the heat eliminates most or all of the available system benefits. Increasing voltage improves transmission efficiency, but partial discharge mitigation requirements increase with the increase in voltage. Superconduction would enable lower distribution voltages and reduce the energy lost in transmission by an order of magnitude, and could allow architectures that rely heavily on electric power distribution and distributed propulsion. However, systems for creating superconducting temperatures, typically less than 70 K, are most often heavy and power intensive. BRIEF DESCRIPTION In one aspect of the present invention, a powertrain system of an aircraft includes one or more electrical components to provide electrical power to one or more electrical loads of the aircraft. The system further includes a rechargeable cryogenic heat sink containing a volume of cryogenic cooling material. The cryogenic heat sink is configured to cool the one or more electrical components. Additionally or alternatively, the volume of cryogenic cooling material is one or more of a hydrogen, helium, neon, nitrogen material. Additionally or alternatively, the volume of cryogenic material is at a heat sink temperature lower than a superconducting temperature of the one or more electrical components. Additionally or alternatively, the cryogenic heat sink is connected to the one or more electrical components via an intermediate cooling loop carrying an intermediate cooling fluid. Additionally or alternatively, the volume of cryogenic material exchanges thermal energy with an intermediate cooling fluid at an intermediate heat exchanger. Additionally or alternatively, the volume of cryogenic material is a primary propulsion fuel of the aircraft. Additionally or alternatively, the one or more electrical components include one or more of an electrical generator, a rectifier, an inverter, and an electric motor. Additionally or alternatively, the cryogenic heat sink undergoes a phase change while absorbing heat from the electrical components. In another aspect of the present invention, a propulsion system of an aircraft includes one or more power units to generate electrical energy utilizing a flow of fuel. one or more propulsion units are operably connected to and driven by the electrical energy. One or more electrical components are operably connected to the one or more power units and/or the one or more propulsion units. The propulsion system further includes a rechargeable cryogenic heat sink containing a volume of cryogenic cooling material. The cryogenic heat sink is configured to cool the one or more electrical components to cool the one or more electrical components. Additionally or alternatively, the volume of cryogenic material is one or more of a hydrogen, helium, neon, nitrogen material. Additionally or alternatively, the volume of cryogenic material is at a heat sink temperature lower than a superconducting temperature of the one or more electrical components. Additionally or alternatively, the cryogenic heat sink is connected to the one or more electrical components via an intermediate cooling loop carrying an intermediate cooling fluid. Additionally or alternatively, the volume of cryogenic material exchanges thermal energy with an intermediate cooling fluid at an intermediate heat exchanger. Additionally or alternatively, the volume of cryogenic material is a fuel source of the flow of fuel. In yet another aspect of the present invention, a method of operating a powertrain system of an aircraft includes generating thermal energy at one or more electrical components of the powertrain system, fluidly connecting a cryogenic heat sink to the one or more electrical components, and cooling the one or more electrical components via a volume of cryogenic cooling material of the cryogenic heat sink. Additionally or alternatively, the cryogenic heat sink is periodically recharged. Additionally or alternatively, the recharging occurs when the aircraft is on the ground. Additionally or alternatively, thermal energy is exchanged between the volume of cryogenic material and an intermediate cooling fluid circulated through an intermediate cooling loop. Thermal energy is exchanged between the intermediate cooling fluid and the one or more electrical components to cool the one or more electrical components. Additionally or alternatively, the volume of cryogenic material is a primary propulsio