Systems and method of operating a fuel cell assembly

Patent metadata

Field	Value
Publication number	US-12351329-B2
Application number	US-202217581135-A
Country	US
Kind code	B2
Filing date	Jan 21, 2022
Priority date	Jan 21, 2022
Publication date	Jul 8, 2025
Grant date	Jul 8, 2025

Abstract

A method for operating a propulsion system for an aircraft, the propulsion system including a gas turbine engine and a fuel cell assembly, the fuel cell assembly including a fuel cell stack having a fuel cell defining an outlet positioned to remove output products from the fuel cell during operation, the method including: executing a startup sequence for the fuel cell assembly, wherein executing the startup sequence for the fuel cell assembly includes initiating the startup sequence for the fuel cell assembly; executing a startup sequence for the gas turbine engine, wherein executing the startup sequence for the gas turbine engine comprises initiating the startup sequence for the gas turbine engine subsequent to initiating the startup sequence for the fuel cell assembly; and operating the fuel cell assembly to provide output products to a combustion section of the gas turbine engine.

First claim

We claim:

1. A method for operating a propulsion system for an aircraft, the propulsion system comprising a gas turbine engine and a fuel cell assembly, the fuel cell assembly comprising a fuel cell stack having a fuel cell defining an outlet positioned to remove output products from the fuel cell during operation, the method comprising:
executing a startup sequence for the fuel cell assembly, wherein executing the startup sequence for the fuel cell assembly comprises initiating the startup sequence for the fuel cell assembly;
executing a startup sequence for the gas turbine engine, wherein executing the startup sequence for the gas turbine engine comprises initiating the startup sequence for the gas turbine engine subsequent to initiating the startup sequence for the fuel cell assembly; and
operating the fuel cell assembly to provide output products to a combustion section of the gas turbine engine.

2. The method of claim 1 , wherein executing the startup sequence for the fuel cell assembly comprises:
operating in a purge state after initiating the startup sequence for the fuel cell assembly;
operating in a first heat-up state prior to a temperature of the fuel cell stack reaching a first fuel cell temperature threshold;
operating in a second heat-up state subsequent to the temperature of the fuel cell stack reaching the first fuel cell temperature threshold and prior to the temperature of the fuel cell stack reaching a second fuel cell temperature threshold; and
operating in a power generation state subsequent to the temperature of the fuel cell stack reaching the second fuel cell temperature threshold.

3. The method of claim 1 , wherein initiating the startup sequence for the gas turbine engine subsequent to initiating the startup sequence for the fuel cell assembly comprises initiating the startup sequence for the gas turbine engine prior to a temperature of the fuel cell stack reaching a first fuel cell temperature threshold.

4. The method of claim 3 , wherein the first fuel cell temperature threshold is at least about 230 degrees C.

5. The method of claim 1 , wherein initiating the startup sequence for the gas turbine engine subsequent to initiating the startup sequence for the fuel cell assembly comprises initiating the startup sequence for the gas turbine engine after a temperature of the fuel cell stack has reached a first fuel cell temperature threshold and prior to the temperature of the fuel cell stack reaching a second fuel cell temperature threshold.

6. The method of claim 5 , wherein the first fuel cell temperature threshold is between about 230 degrees C. and about 400 degrees C., wherein the second fuel cell temperature threshold is between about 400 degrees C. and about 750 degrees C., and wherein the second fuel cell temperature threshold is greater than the first fuel cell temperature threshold.

7. The method of claim 1 , wherein initiating the startup sequence for the gas turbine engine subsequent to initiating the startup sequence for the fuel cell assembly comprises initiating the startup sequence for the gas turbine engine after a temperature of the fuel cell stack has reached a second fuel cell temperature threshold.

8. The method of claim 7 , wherein the second fuel cell temperature threshold is between about 400 degrees C. and about 750 degrees C.

9. The method of claim 1 , wherein the fuel cell assembly comprises an air processing unit, and wherein executing the startup sequence for the fuel cell assembly further comprises:
completing the startup sequence for the fuel cell assembly, and
routing one or more streams of the output products from the fuel cell to the air processing unit prior to completing the startup sequence for the fuel cell assembly.

10. The method of claim 9 , wherein the one or more streams of the output products from the fuel cell comprise an anode stream, a cathode stream, or both.

11. The method of claim 1 , wherein the fuel cell assembly comprises a fuel processing unit, and wherein executing the startup sequence for the fuel cell assembly further comprises:
completing the startup sequence for the fuel cell assembly, and
routing one or more streams of the output products from the fuel cell to the fuel processing unit prior to completing the startup sequence for the fuel cell assembly.

12. The method of claim 11 , wherein the one or more streams of the output products from the fuel cell comprise an anode stream, a cathode stream, or both.

13. The method of claim 1 , wherein executing the startup sequence for the fuel cell assembly comprises:
operating the fuel cell assembly in a warm standby state;
operating the fuel cell assembly in a ground idle power generation mode; and operating the fuel cell assembly in a normal power generation mode.

14. The method of claim 13 , wherein operating the fuel cell assembly in the ground idle power generation mode comprises operating the fuel cell assembly at fuel utilization within about 10% of a maximum fuel utilization.

15. The method of claim 1 , wherein executing the startup sequence for the fuel cell assembly comprises initiating operation of a fuel processing unit and providing an offgas of the fuel processing unit around an anode of the fuel cell to a combustor of the combustion section of the gas turbine engine, to an air processing unit of the fuel cell assembly, or both.

16. The method of claim 1 , wherein the fuel cell assembly comprises an air processing unit and a fuel processing unit, wherein executing the startup sequence for the fuel cell assembly comprises providing an offgas from the air processing unit to a cathode of the fuel cell and providing an offgas from the fuel processing unit to an anode of the fuel cell.

17. The method of claim 1 , wherein executing the startup sequence for the fuel cell assembly comprises providing a flow to an anode of the fuel cell having an oxygen content prior to a temperature of the fuel cell stack being greater than or equal to a first fuel cell temperature threshold.

18. The method of claim 1 , wherein executing the startup sequence for the fuel cell assembly comprises providing a flow to an anode of the fuel cell having an oxygen content prior to a temperature of the fuel cell stack being greater than or equal to a second fuel cell temperature threshold.

19. The method of claim 1 , wherein executing the startup sequence for the fuel cell assembly comprises performing a fuel reforming action at an anode of the fuel cell assembly.

20. A propulsion system for an aircraft having a gas turbine engine, the aircraft comprising an aircraft fuel supply, the propulsion system comprising:
a fuel cell assembly comprising a fuel cell stack having a fuel cell, the fuel cell defining an outlet positioned to remove output products from the fuel cell;
a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the combustion section configured to receive a flow of aviation fuel from the aircraft fuel supply and further configured to receive the output products from the fuel cell; and
a controller comprising memory and one or more processors, the memory storing instructions that when executed by the one or more processors cause the propulsion system to perform operations including:
executing a startup sequence for the fuel cell assembly, wherein executing the startup sequence for the fuel cell assembly comprises initiating the startup sequence for the fuel cell assembly;
executing a startup sequence for the gas turbine engi

Assignees

• Gen Electric

Inventors

• Wang Honggang
• Benjamin Michael Anthony
• Hong Seung-Hyuck
• Hart Richard L

Classifications

• B64D31/00 Primary

  Power plant control systems; Arrangement of power plant control systems in aircraft · CPC title

• B64D27/24

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

• B64D27/355

  using fuel cells · CPC title

• B64D31/18

  for hybrid-electric power plants · CPC title

• B64D27/33

  Hybrid electric aircraft · CPC title