IP Library › Granted Patent US 12,304,646
Granted Patent B2
US 12,304,646 · App. 18/778,405 · Granted May 20, 2025

Fuel cell turboelectric fan for an aircraft

Inventor: Rory Roberts (Cookeville, TN)
Assignee: TENNESSEE TECHNOLOGICAL UNIVERSITY
B64D27/33B64D27/10B64D27/355F01D15/10F02C7/22F05D2220/76
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Quick Facts
Patent No.
US 12,304,646
App. No.
18/778,405
Granted
May 20, 2025
Kind
B2
Abstract

A propulsion system for an aircraft as disclosed herein may include a nacelle, a shaft positioned centrally within a cylindrical passageway of the nacelle, a fan coupled to one end of the shaft, a turbine coupled to an opposite end of the shaft, an electric motor coupled to the shaft, a compressor positioned within the cylindrical passageway, and a solid oxide fuel cell positioned with a hollow ring-shaped interior of the nacelle. The hollow ring-shaped interior may surround and be isolated from the cylindrical passageway. The turbine may be configured to provide primary torque to the shaft while the electric motor may be configured to provide additional torque to the shaft. The electric motor may be powered an electric output of the solid oxide fuel cell while the turbine may be powered at least in part by output gases from the solid oxide fuel cell.

Claims (52)

1. A propulsion system for an aircraft, the aircraft propulsion system comprising:

a nacelle having a hollow ring-shaped interior surrounding a cylindrical passageway therethrough, the cylindrical passageway having a forward opening and a rearward opening, the hollow ring-shaped interior separated from the cylindrical passageway by the nacelle;

a shaft positioned centrally within the cylindrical passageway;

a fan coupled to the shaft and positioned within the cylindrical passageway closer to the forward opening than to the rearward opening;

a turbine coupled to the shaft and positioned within the cylindrical passageway closer to the rearward opening than to the forward opening, the turbine configured to provide primary torque to the shaft;

an electric motor coupled to the shaft and positioned within the cylindrical passageway of the nacelle, the electric motor configured to provide additional torque to the shaft;

a compressor coupled to the shaft and positioned within the cylindrical passageway; and

a solid oxide fuel cell positioned within the hollow ring-shaped interior of the nacelle or radially around the turbine, the solid oxide fuel cell configured to receive compressed air from the compressor, provide power to at least the electric motor, and provide output gases to at least the turbine.

2. The propulsion system of claim 1 , further comprising:

a fuel source coupled to the solid oxide fuel cell.

3. The propulsion system of claim 2 , wherein:

fuel from the fuel source is configured to be combusted within a combustion chamber of the solid oxide fuel cell after interacting with an anode of one or more solid oxide fuel cell tubes of the solid oxide fuel cell to define combustion products; and

the combustion products interact with a cathode of the one or more solid oxide fuel cell tubes of the solid oxide fuel cell prior to exiting the solid oxide fuel cell as the output gases.

4. The propulsion system of claim 1 , wherein:

the solid oxide fuel cell includes a combustion chamber positioned between an anode and a cathode of one or more solid oxide fuel cell tubes.

5. The propulsion system of claim 4 , wherein:

the solid oxide fuel cell includes an exhaust manifold configured to direct combustion products of the combustion chamber away from the solid oxide fuel cell.

6. The propulsion system of claim 5 , wherein:

each of the exhaust manifold and the combustion chamber are positioned at opposite ends of the solid oxide fuel cell.

7. The propulsion system of claim 1 , further comprising:

a combustor positioned within the cylindrical passageway of the nacelle, the combustor configured to receive one or more of the output gases from the solid oxide fuel cell or fuel from a fuel source, to produce combustor products, and to direct said combustor products to the turbine.

8. The propulsion system of claim 1 , further comprising:

a nozzle coupled to the rearward opening of the cylindrical passageway of the nacelle, wherein exhaust from the turbine and air from the fan mix prior to exiting the nozzle to produce thrust or may exit through multiple nozzles.

9. The propulsion system of claim 1 , wherein:

the hollow ring-shaped interior is isolated from the cylindrical passageway.

10. The propulsion system of claim 1 , wherein:

the solid oxide fuel cell is configured to provide additional power to electric payloads and electrical storage of the aircraft.

11. The propulsion system of claim 1 , wherein:

the solid oxide fuel cell is radially disposed within the hollow ring-shaped interior of the nacelle fully surrounding the cylindrical passageway.

12. The propulsion system of claim 1 , wherein:

the solid oxide fuel cell includes a plurality of fuel cell units radially disposed within the hollow ring-shaped interior of the nacelle fully surrounding the cylindrical passageway.

13. The propulsion system of claim 1 , further comprising:

nacelle support struts positioned within the cylindrical passageway of the nacelle and configured to support one or more of the shafts, the fan, the turbine, the electric motor, or the compressor.

14. The propulsion system of claim 13 , wherein:

the nacelle support struts include one or more passageways for routing the compressed air from the compressor to the solid oxide fuel cell and/or routing output gases from the solid oxide fuel cell to the turbine.

15. A propulsion system comprising:

a shaft;

a fan coupled to a first end of the shaft;

a turbine coupled to a second end of the shaft, the turbine configured to provide primary torque to the shaft;

an electric motor coupled to the shaft, the electric motor configured to provide additional torque to the shaft; and

a solid oxide fuel cell configured to provide power to at least the electric motor, and to provide output gases to the turbine, the solid oxide fuel cell includes a combustion chamber configured to receive fuel through an anode of one or more solid oxide fuel cell tubes or stacks of the solid oxide fuel cell and combust the fuel with compressed air to define combustion products, wherein the combustion products interact with a cathode of the one or more solid oxide fuel cell tubes or stacks of the solid oxide fuel cell prior to exiting the solid oxide fuel cell as the output gases.

16. The propulsion system of claim 15 , further comprising:

a compressor configured to provide the compressed air to the solid oxide fuel cell; and

a fuel source configured to provide the fuel to the solid oxide fuel cell.

17. The propulsion system of claim 15 , wherein:

the electric motor when operated in reverse is configured to operate as a power generator.

18. The propulsion system of claim 15 , wherein:

the electric motor is coupled to the fan.

19. The propulsion system of claim 15 , further comprising:

a nacelle having a hollow ring-shaped interior surrounding a cylindrical passageway, wherein the solid oxide fuel cell is configured to be positioned within the hollow ring-shaped interior.

20. The propulsion system of claim 15 , wherein:

the solid oxide fuel cell surrounds at least the turbine.

Assignments (1)
ASSIGNMENT OF ASSIGNOR'S INTEREST Recorded Aug 8, 2024
From: ROBERTS, RORY
To: TENNESSEE TECHNOLOGICAL UNIVERSITY
Reel/Frame 068222/0095 →
Continuity (2)
Provisional Application 63531512 · Aug 8, 2023
Related Publication 20250051018A1 · Feb 13, 2025
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