Aircraft fuel system with electrochemical hydrogen compressor

Patent metadata

Field	Value
Publication number	US-11745891-B2
Application number	US-202117227602-A
Country	US
Kind code	B2
Filing date	Apr 12, 2021
Priority date	Apr 14, 2020
Publication date	Sep 5, 2023
Grant date	Sep 5, 2023

Abstract

A propulsion system according to an exemplary embodiment of this disclosure, among other possible things includes a fuel storage tank that is configured to store a fuel in a compressed state, a power generation device that is configured to consume the fuel and generate an output, a fuel system that is configured to provide the fuel from the fuel storage tank to the power generation device, and an electrochemical compressor that is in communication with the fuel system. The electrochemical compressor is configured to gather residual fuel from the fuel system and communicate the gathered residual fuel to at least one of the power generation device and the fuel storage tank.

First claim

What is claimed is:

1. A propulsion system, comprising:
a fuel storage tank configured to store a fuel in a compressed state;
a fan;
a compressor section configured to compress an inlet airflow;
a combustor configured to mix the compressed inlet airflow with the fuel to generate a high energy exhaust gas flow;
a turbine section where the high energy exhaust gas flow from the combustor is expanded to provide a power output that drives the compressor section and the fan;
a fuel system configured to provide the fuel from the fuel storage tank to the combustor; and
an electrochemical compressor in communication with the fuel system, the electrochemical compressor configured to gather residual fuel from the fuel system and communicate the gathered residual fuel to at least one of the combustor and the fuel storage tank.

2. The propulsion system as recited in claim 1 , further comprising a thermal management system disposed between the fuel system and the electrochemical compressor, the thermal management system being configured to transfer thermal energy into the gathered residual fuel.

3. The propulsion system as recited in claim 1 , wherein
the propulsion system includes a check valve disposed between the fuel system and the combustor to provide flow from the fuel system to the combustor and to limit flow from the combustor to the fuel system.

4. The propulsion system as recited in claim 1 , wherein
the electrochemical compressor is configured to remove fuel from the fuel system when the combustor is off.

5. The propulsion system as recited in claim 1 , further comprising a pressure sensor configured to measure a fuel pressure, wherein
the electrochemical compressor is configured to remove fuel from the fuel system when a measured fuel pressure is within a range.

6. The propulsion system as recited in claim 1 , wherein the electrochemical compressor includes at least one membrane-electrode-assembly.

7. The propulsion system as recited in claim 1 , including a second fuel storage tank configured to receive residual fuel from the electrochemical compressor and communicate fuel to the combustor.

8. The propulsion system as recited in claim 1 , wherein the fuel includes compressed and/or liquid hydrogen.

9. A power generation system, comprising:
a fuel cell configured to generate an electric power output;
a fuel system configured to communicate fuel to the fuel cell;
a fuel storage tank configured to communicate fuel to the fuel system, wherein the fuel storage tank is configured to store fuel at a pressure greater than an ambient pressure; and
an electrochemical compressor in communication with the fuel system, the electrochemical compressor configured to gather residual fuel from the fuel system, wherein the fuel cell and the electrochemical compressor comprise a stack configured to operate in a first mode to remove residual fuel from the fuel system, pressurize the removed fuel and communicate that pressurized fuel back to the fuel storage tank and in a second mode to produce the electric power output.

10. The power generation system as recited in claim 9 , including a three way control valve between the stack and the fuel storage tank, wherein the three way control valve is configured to direct fuel back to the fuel storage tank from the stack when operating in the first mode and to exhaust depleted air and prevent airflow to the fuel storage tank when the stack is operating in the second mode.

11. The power generation system as recited in claim 9 , wherein the electrochemical compressor includes at least one membrane-electrode-assembly.

12. The power generation system as recited in claim 10 , further comprising a thermal management system disposed between the fuel system and the electrochemical compressor, the thermal management system being configured to transfer thermal energy into the gathered residual fuel.

13. The power generation system as recited in claim 9 , including a combustor configured to ignite a mixture of air and fuel from the fuel system to generate a high energy exhaust gas flow output.

14. The power generation system as recited in claim 9 , wherein the compressed fuel comprises hydrogen.

15. A method of operating propulsion system comprising:
storing a compressed fuel in a fuel storage tank;
communicating fuel from the fuel storage tank through a fuel system to a power generation device configured to consume fuel and generate an output;
recovering residual fuel from the fuel system with an electrochemical compressor; and
communicating the recovered residual fuel to the fuel storage tank.

16. The method as recited in claim 15 , including transferring thermal energy into the recovered residual fuel in a thermal management system disposed between the fuel system and the electrochemical compressor.

17. The method as recited in claim 15 , including removing the residual fuel from the fuel system in response to the power generation device being turned off.

18. The method as recited in claim 15 , including measuring a fuel pressure within the fuel system and operating the electrochemical compressor to remove excess fuel from the fuel system when a measured fuel pressure is within a predefined range.

19. The method as recited in claim 15 , wherein the fuel comprises hydrogen.

Assignees

• Raytheon Tech Corp

Inventors

• Rheaume Jonathan
• Darling Robert Mason

Classifications

• B64D27/026

  comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine (Hybrid electric aircraft B64D27/33) · CPC title

• B64D37/30 Primary

  Fuel systems for specific fuels · CPC title

• B64D27/10

  of gas-turbine type  (jet aircraft B64D27/16) · CPC title

• B64D27/24

  using steam or spring force (jet aircraft B64D27/16) · CPC title

• H01M8/0258

  characterised by the configuration of channels, e.g. by the flow field of the reactant or coolant · CPC title