Aircraft propulsion system with integrated fuel cell cooling

Patent metadata

Field	Value
Publication number	US-2026077871-A1
Application number	US-202519397136-A
Country	US
Kind code	A1
Filing date	Nov 21, 2025
Priority date	Dec 28, 2022
Publication date	Mar 19, 2026
Grant date	—

Abstract

An aircraft includes a fuel cell system including a fuel cell powered by hydrogen received from a supply of hydrogen, and a propulsion unit including a conduit through which a flow of air is propelled. A first heat exchanger transfers heat from the fuel cell to a coolant fluid located in a coolant loop, and a second heat exchanger is located in the conduit for heating the air passing through the conduit by transferring heat to the air from the coolant fluid via the second heat exchanger. This configuration serves to cool the fuel cell while increasing the efficiency of the propulsion unit.

First claim

1 . An aircraft, comprising:
a fuel cell system including a fuel cell powered by hydrogen received from a supply of hydrogen; a first heat exchanger to cool the fuel cell by transferring heat generated by the fuel cell to a coolant fluid located in a coolant loop; an electrical propulsion unit including an electric motor driving a propulsor fan to provide thrust for the aircraft, the electrical propulsion unit being powered solely by electricity, the electricity at least in part being generated by the fuel cell system, the electrical propulsion unit including a conduit through which a flow of air is propelled by operation of the propulsor fan of the electrical propulsion unit; and a second heat exchanger located in the conduit and coupled to the coolant loop, for heating the flow of air passing through the conduit by transferring heat to the air from the coolant fluid, wherein the second heat exchanger comprises a turbine for decelerating at least part of the flow of air passing through the conduit.

2 . The aircraft of claim 1 , wherein the turbine is a multistage turbine.

3 . The aircraft of claim 1 , wherein the second heat exchanger further comprises a corresponding radiator.

4 . The aircraft of claim 3 , wherein the turbine decelerates at least part of the flow air before it passes through the corresponding radiator.

5 . The aircraft of claim 1 , further comprising at least one additional heat exchanger in the conduit and coupled to the coolant loop.

6 . The aircraft of claim 5 , wherein the at least one additional heat exchanger is located downstream of the second heat exchanger in the conduit.

7 . The aircraft of claim 6 , wherein the at least one additional heat exchanger comprises a turbine and a corresponding radiator.

8 . The aircraft of claim 1 , further comprising shroud, wherein at least part of the flow of air leaving the second heat exchanger is directed to the shroud.

9 . The aircraft of claim 8 , further comprising one or more secondary conduits configured to generate a secondary flow of air directed to the shroud.

10 . The aircraft of claim 1 , wherein a shape of the conduit defines a nozzle downstream of the second heat exchanger.

11 . The aircraft of claim 1 , wherein the nozzle is a variable area nozzle downstream of the second heat exchanger.

12 . The aircraft of claim 1 , wherein flow of coolant within the coolant loop is driven with aid of a pump.

13 . The aircraft of claim 1 , wherein the conduit is formed as a podded propulsor unit.

14 . The aircraft of claim 1 , wherein the conduit is embedded in a wing or other lifting surface of the aircraft.

15 . A propulsion unit for an aircraft, comprising:
a conduit through which a flow of air is propelled in use; a propulsor fan located in the conduit through which the flow of air is propelled; an electric motor, powered at least in part in use by a separate fuel cell, for driving the propulsor fan; and a heat exchanger located in the conduit and coupled to a coolant loop, for heating the flow of air passing through the conduit by transferring heat to the air from a coolant fluid, wherein, in use, the propulsion unit is powered solely by electricity, the electricity being generated at least in part by the separate fuel cell coupled to the coolant loop and, wherein, in use, the separate fuel cell is cooled by the coolant fluid in the coolant loop, wherein the heat exchanger comprises a turbine for decelerating at least part of the flow of air passing through the conduit.

16 . The propulsion unit of claim 15 , wherein the second heat exchanger further comprises a corresponding radiator.

17 . The propulsion unit of claim 16 , wherein the turbine decelerates at least part of the flow air before it passes through the corresponding radiator.

18 . The propulsion unit of claim 15 , further comprising at least one additional heat exchanger located downstream of the heat exchanger in the conduit.

19 . The propulsion unit of claim 18 , wherein the at least one additional heat exchanger comprises a turbine and a corresponding radiator.

20 . The propulsion unit of claim 18 , wherein the at least one additional heat exchanger is coupled to the coolant loop, for heating the flow of air passing through the conduit by transferring heat to the air from a coolant fluid.

Assignees

• Joby Aero Inc

Inventors

• Brelje Benjamin
• Lynn Robert Gulliver
• Lotterman Jeffrey Allen
• Mikic Gregor Veble

Classifications

• F02C7/141

  of working fluid · CPC title

• F02C7/12

  Cooling of plants (of component parts, see the relevant subclasses, e.g. F01D; cooling of engines in general F01P) · CPC title

• B64D33/10

  Radiator arrangement · CPC title

• Y02T90/40

  Application of hydrogen technology to transportation, e.g. using fuel cells · CPC title

• B64D27/355 Primary

  using fuel cells · CPC title