Gas turbine combustion section having an integrated fuel cell assembly

Patent metadata

Field	Value
Publication number	US-12567595-B2
Application number	US-202217984615-A
Country	US
Kind code	B2
Filing date	Nov 10, 2022
Priority date	Nov 10, 2022
Publication date	Mar 3, 2026
Grant date	Mar 3, 2026

Abstract

A combustion section includes a casing that defines a diffusion chamber. The combustion section further includes a combustion liner that is disposed within the diffusion chamber and that defines a combustion chamber. The combustion liner is spaced apart from the casing such that a passageway is defined between the combustion liner and the casing. The combustion section further includes a fuel cell assembly that is disposed in the passageway. The fuel cell assembly includes a fuel cell stack having a plurality of fuel cells. The plurality of fuel cells extend from an inlet end in fluid communication with the diffusion chamber to an outlet end extending through the combustion liner and in fluid communication with the combustion chamber.

First claim

We claim:

1 . A combustion section comprising:
a casing defining a diffusion chamber; a combustion liner disposed within the diffusion chamber and defining a combustion chamber, the combustion liner spaced apart from the casing such that a passageway is defined between the combustion liner and the casing; a fuel cell assembly disposed in the passageway, the fuel cell assembly comprising a fuel cell stack having a plurality of fuel cells, at least one structural member, and at least one electrically conducting member, the at least one electrically conducting member disposed between the fuel cell stack and the at least one structural member, the plurality of fuel cells extending from an inlet end in fluid communication with the diffusion chamber to an outlet end extending through the combustion liner and in fluid communication with the combustion chamber, wherein the inlet end of the plurality of fuel cells is spaced apart from the casing such that an airflow gap is defined between the inlet end and the casing; and an air manifold extending from an inlet in fluid communication with the diffusion chamber to an outlet fluidly coupled to the airflow gap, and wherein the air manifold extends radially outwardly of the casing and the passageway between the inlet and the outlet.

2 . The combustion section as in claim 1 , wherein the diffusion chamber is at a first pressure, and wherein the combustion chamber is at a second pressure lower than the first pressure such that air from the diffusion chamber flows through the fuel cell stack and into the combustion chamber.

3 . The combustion section as in claim 1 , wherein the at least one electrically conducting member is disposed at one of a forward end or an aft end of the fuel cell stack.

4 . The combustion section as in claim 1 , wherein the at least one structural member comprises a first structural member at a forward end of the fuel cell assembly and a second structural member at an aft end of the fuel cell assembly, wherein the first structural member and the second structural member each extend from the combustion liner to the casing.

5 . The combustion section as in claim 4 , wherein the at least one structural member defines an air channel that fluidly couples the diffusion chamber and the inlet end of the fuel cell stack.

6 . The combustion section as in claim 1 , wherein the fuel cell assembly defines a power density, wherein a radial gap is defined between the casing and the combustion liner, wherein the radial gap is sized based on the power density of the fuel cell assembly, and wherein the radial gap is between about 2 inches and about 8 inches.

7 . The combustion section as in claim 1 , wherein the fuel cell assembly is a first fuel cell assembly in a plurality of fuel cell assemblies disposed in the passageway, the plurality of fuel cell assemblies circumferentially spaced apart from one another such that a circumferential gap is defined between each fuel cell assembly of the plurality of fuel cell assemblies.

8 . The combustion section as in claim 1 , further comprising a swirler assembly disposed at a forward end of the combustion liner, the swirler assembly fluidly coupled to a fuel source, the diffusion chamber, and the combustion chamber, wherein the fuel cell assembly is disposed entirely aft of the swirler assembly.

9 . The combustion section as in claim 1 , wherein the air manifold extends through the casing at both the inlet and the outlet.

10 . A turbomachine comprising:
a compressor section, a combustion section, and a turbine section arranged in serial flow order, the combustion section comprising:
a casing defining a diffusion chamber that receives air from the compressor section;
a combustion liner disposed within the diffusion chamber and defining a combustion chamber, the combustion liner spaced apart from the casing such that a passageway is defined between the combustion liner and the casing; and
a fuel cell assembly disposed in the passageway, the fuel cell assembly comprising a fuel cell stack having a plurality of fuel cells, at least one structural member, and at least one electrically conducting member, the at least one electrically conducting member disposed between the fuel cell stack and the at least one structural member, the plurality of fuel cells extending from an inlet end in fluid communication with the diffusion chamber to an outlet end extending through the combustion liner and in fluid communication with the combustion chamber, wherein the inlet end of the plurality of fuel cells is spaced apart from the casing such that an airflow gap is defined between the inlet end and the casing; and
an air manifold extending from an inlet in fluid communication with the diffusion chamber to an outlet fluidly coupled to the airflow gap, and wherein the air manifold extends radially outwardly of the casing and the passageway between the inlet and the outlet.

11 . The turbomachine as in claim 10 , wherein the diffusion chamber is at a first pressure, and wherein the combustion chamber is at a second pressure lower than the first pressure such that air from the diffusion chamber flows through the fuel cell stack and into the combustion chamber.

12 . The turbomachine as in claim 10 , wherein the at least one electrically conducting member is disposed at one of a forward end or an aft end of the fuel cell stack.

13 . The turbomachine as in claim 10 , wherein the at least one structural member couples the fuel cell assembly to at least one of the casing or the combustion liner of the combustion section.

14 . The turbomachine as in claim 13 , wherein the at least one structural member defines an air channel that fluidly couples the diffusion chamber and the inlet end of the fuel cell stack.

15 . The turbomachine as in claim 10 , wherein the fuel cell assembly defines a power density, wherein a radial gap is defined between the casing and the combustion liner, wherein the radial gap is sized based on the power density of the fuel cell assembly, and wherein the radial gap is between about 2 inches and about 8 inches.

16 . The turbomachine as in claim 10 , wherein the fuel cell assembly is a first fuel cell assembly in a plurality of fuel cell assemblies disposed in the passageway, the plurality of fuel cell assemblies circumferentially spaced apart from one another such that a circumferential gap is defined between each fuel cell assembly of the plurality of fuel cell assemblies.

17 . The turbomachine as in claim 10 , further comprising a swirler assembly disposed at a forward end of the combustion liner, the swirler assembly fluidly coupled to a fuel source, the diffusion chamber, and the combustion chamber, wherein the fuel cell assembly is disposed aft of the swirler assembly.

Assignees

• Gen Electric

Inventors

• Hong Seung-Hyuck
• Hart Richard L
• Wang Honggang
• Duggal Anil Raj
• Benjamin Michael Anthony
• Rickey Owen James Sullivan
• Joshi Narendra Digamber
• De Bock Hendrik Pieter Jacobus

Classifications

• H01M2250/20

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

• F23R3/002

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title

• 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

• H01M8/04111 Primary

  using a compressor turbine assembly · CPC title

• H01M8/2425

  High-temperature cells with solid electrolytes · CPC title