Integration of fuel cell with cryogenic source for cooling and reactant

Patent metadata

Field	Value
Publication number	US-11459130-B2
Application number	US-201916703747-A
Country	US
Kind code	B2
Filing date	Dec 4, 2019
Priority date	Feb 12, 2016
Publication date	Oct 4, 2022
Grant date	Oct 4, 2022

Abstract

A fuel cell-based power system comprises a fuel cell configured for continuously receiving a first reactant and a second reactant to produce chemical reactions that generate electrical power, water, and heat, a coolant subsystem configured for circulating a primary coolant in association with the fuel cell, thereby absorbing the generated heat, a tank configured for storing a reactant, and a reactant distribution subsystem configured for conveying the reactant from the tank to an independent system, the fuel cell as the first reactant, and the coolant subsystem as a secondary coolant to remove the absorbed heat from the primary coolant and/or a water accumulator. The secondary coolant may be conveyed to a gas thruster as a gas after the absorbed heat has been removed from the secondary coolant. The reactant may boil off of a cryogenic liquid or vapor or gas transformed from a cryogenic liquid via a heater.

First claim

We claim:

1. A fuel cell-based power system, comprising:
a fuel cell configured for continuously receiving a first reactant and a second reactant to produce chemical reactions that generate electrical power, water, and heat;
a tank configured for storing a reactant;
a coolant subsystem configured for circulating a primary coolant in association with the fuel cell, thereby absorbing at least a portion of the heat from the fuel cell;
wherein the coolant subsystem comprises a first heat exchanger configured for injecting absorbed heat from the primary coolant into a secondary coolant, and a second heat exchanger configured for injecting absorbed heat from the primary coolant into the reactant;
a water accumulator for storing the water generated by the fuel cell;
a third heat exchanger configured for injecting absorbed heat from the water accumulator into the secondary coolant; and
a reactant distribution subsystem configured for conveying the reactant from the tank to the fuel cell as the first reactant, and further for conveying the reactant from the tank to the coolant subsystem as the secondary coolant to remove at least a portion of absorbed heat from the primary coolant.

2. The fuel cell-based power system of claim 1 , wherein the coolant subsystem comprises a coolant loop configured for circulating the primary coolant through the fuel cell.

3. The fuel cell-based power system of claim 1 , wherein the first reactant is gaseous hydrogen and the second reactant is gaseous oxygen.

4. The fuel cell-based power system of claim 1 , wherein the first reactant stored in the tank is a cryogenic liquid.

5. The fuel cell-based power system of claim 4 , wherein the reactant distribution subsystem is configured for receiving boil off of the cryogenic liquid directly from the tank.

6. The fuel cell-based power system of claim 4 , wherein the cryogenic liquid is liquid hydrogen.

7. A spacecraft or aircraft, comprising:
a structural bus;
the fuel cell-based power system of claim 1 contained within the structural bus; and
electronics that are supplied with the electrical power generated by the fuel cell-based power system.

8. The spacecraft or aircraft of claim 7 , wherein the reactant distribution subsystem is configured for conveying the secondary coolant to the coolant subsystem to remove the at least portion of the absorbed heat from the primary coolant, and further comprising a pair of gas thrusters and a bi-propellant thruster, wherein the reactant distribution subsystem conveys the secondary coolant to the pair of gas thrusters and the bi-propellant thruster after the at least portion of the absorbed heat has been removed from the primary coolant, and wherein the reactant distribution subsystem conveys the second reactant to the bi-propellant thruster.

9. A spacecraft or aircraft, comprising:
a fuel cell configured for continuously receiving a first reactant and a second reactant to produce chemical reactions that generate electrical power, water, and heat;
electronics that are supplied with the electrical power generated by the fuel cell;
a coolant subsystem configured for circulating a primary coolant in association with the fuel cell, thereby absorbing at least a portion of the heat from the fuel cell;
wherein the coolant subsystem comprises a primary heat exchanger configured for injecting absorbed heat from the primary coolant into a secondary coolant, and secondary heat exchangers configured for injecting absorbed heat from the primary coolant into the first reactant and the second reactant;
a water accumulator for storing the water generated by the fuel cell;
a tertiary heat exchanger configured for injecting absorbed heat from the water accumulator into the secondary coolant;
a tank configured for storing the secondary coolant;
a thruster; and
a distribution subsystem configured for conveying the secondary coolant from the tank to the coolant subsystem to remove at least a portion of absorbed heat from the primary coolant, and for conveying the secondary coolant to the thruster after the at least portion of the absorbed heat has been removed from the primary coolant.

10. The spacecraft or aircraft or claim 9 , wherein the thruster is gas thruster, and the secondary coolant is conveyed to the gas thruster as a gas.

11. The spacecraft or aircraft of claim 9 , further comprising a second thruster, wherein the second thruster is a bi-propellant thruster, the secondary coolant is hydrogen, and the distribution subsystem is configured for conveying oxygen to the bi-propellant thruster and for conveying the secondary coolant to the second thruster after that least portion of the absorbed heat has been removed from the primary coolant.

12. The spacecraft or aircraft of claim 9 , wherein the primary heat exchanger is configured for removing at least a portion of the absorbed heat from the primary coolant and injecting the at least a portion of the absorbed heat into the secondary coolant.

13. The spacecraft or aircraft of claim 9 , wherein the first reactant is gaseous hydrogen and the second reactant is gaseous oxygen.

14. The spacecraft or aircraft of claim 9 , wherein the secondary coolant stored in the tank is a cryogenic liquid.

15. The spacecraft or aircraft of claim 14 , wherein the distribution subsystem is configured for receiving boil off of the cryogenic liquid directly from the tank.

16. The spacecraft or aircraft of claim 15 , wherein the cryogenic liquid is liquid hydrogen.

17. A fuel cell-based power system, comprising:
a fuel cell configured for continuously receiving a first reactant and a second reactant to produce chemical reactions that generate electrical power, water, and heat;
a tank configured for storing a cryogenic liquid; and
a coolant subsystem configured for circulating a primary coolant in association with the fuel cell, thereby absorbing at least a portion of the heat from the fuel cell;
wherein the coolant subsystem comprises a primary heat exchanger configured for injecting absorbed heat from the primary coolant into a secondary coolant, and secondary heat exchangers configured for injecting absorbed heat from the primary coolant into the first reactant and the second reactant;
a water accumulator for storing the water generated by the fuel cell;
a tertiary heat exchanger configured for injecting absorbed heat from the water accumulator into the secondary coolant;
a quaternary heat exchanger configured for thermally transforming the cryogenic liquid from the tank into a vapor or gas; and
a reactant distribution subsystem configured for conveying the vapor or gas to the fuel cell as the second reactant, and for conveying the first reactant to the coolant subsystem as the secondary coolant to remove at least a portion of the heat absorbed by the primary coolant.

18. The fuel cell-based power system of claim 17 , wherein the cryogenic liquid is liquid hydrogen.

19. The fuel cell-based power system of claim 17 , wherein the cryogenic liquid is liquid oxygen.

20. A spacecraft or aircraft, comprising:
a structural bus;
the fuel cell-based power system of claim 17 contained within the structural bus; and
electronics that are supplied with the electrical power generated by the fuel cell-based power system,
wherein the water stored in the water accumulator is used as a heat sink for at least a portion of the electronics.

Assignees

• Boeing Co

Inventors

• Mata Marianne E
• Lozano Martin E
• Staudinger Tyler C
• Blumer John H
• Henley Mark W

Classifications

• H01M8/04701

  Temperature · CPC title

• Y02T50/40

  Weight reduction · CPC title

• H01M2250/20

  Fuel cells in motive systems, e.g. vehicle, ship, plane · CPC title

• Y02T90/40

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

• H01M8/04208

  Cartridges, cryogenic media or cryogenic reservoirs · CPC title