Gas turbine engine and fuel cell assembly
A gas turbine engine is provided. The gas turbine engine includes a turbomachine having a compressor section, a combustor, and a turbine section arranged in serial flow order, the turbomachine further including an outer casing and, during operation of the gas turbine engine, an exhaust gas flow from the turbine section; and a fuel cell assembly positioned within the outer casing of the turbomachine, the fuel cell assembly having a fuel cell defining an inlet positioned to receive a portion of the exhaust gas flow, an outlet positioned to provide output products directly to the exhaust gas flow, or both.
1. A gas turbine engine comprising:
a turbomachine having a compressor section, a combustor, and a turbine section arranged in serial flow order, the turbomachine further comprising an outer casing and, during operation of the gas turbine engine, an exhaust gas flow from the turbine section; and
a fuel cell assembly positioned within the outer casing of the turbomachine, the fuel cell assembly comprising a fuel cell defining an inlet positioned to receive a portion of the exhaust gas flow, an outlet positioned to provide output products directly to the exhaust gas flow, or both, wherein the fuel cell defines the outlet positioned to provide output products directly to the exhaust gas flow, wherein the fuel cell is a first fuel cell of a plurality of fuel cells of the fuel cell assembly, wherein the plurality of fuel cells further comprises a second fuel cell in series flow communication with the first fuel cell at a location downstream of the first fuel cell and wherein the first fuel cell and the second fuel cell define varying geometries.
2. The gas turbine engine of claim 1 , wherein the fuel cell defines the inlet positioned to receive the portion of the exhaust gas flow.
3. The gas turbine engine of claim 2 , wherein the turbomachine further comprises an exhaust nozzle defining a primary exhaust gas flowpath, wherein the fuel cell is in fluid communication with the primary exhaust gas flowpath for receiving the portion of the exhaust gas flow through the primary exhaust gas flowpath.
4. The gas turbine engine of claim 3 , wherein the fuel cell is configured to receive up to 10% of the exhaust gas flow provided to the exhaust nozzle.
5. The gas turbine engine of claim 2 , wherein the fuel cell comprises a cathode, and wherein the cathode is positioned to receive the portion of the exhaust gas flow.
6. The gas turbine engine of claim 2 , wherein the turbomachine further comprises an exhaust nozzle defining a primary exhaust gas flowpath, wherein the turbomachine defines a fuel cell flowpath in parallel with the primary exhaust gas flowpath, wherein the fuel cell is in fluid communication with the fuel cell flowpath.
7. The gas turbine engine of claim 1 , wherein the turbomachine comprises an exhaust nozzle, wherein the fuel cell is in thermal communication with an exhaust gas flow through the exhaust nozzle during operation of the gas turbine engine, and wherein the fuel cell is pressurized relative to the exhaust gas flow through the exhaust nozzle during operation of the gas turbine engine.
8. The gas turbine engine of claim 1 , wherein the fuel cell comprises a redox-stable anode.
9. The gas turbine engine of claim 1 , wherein the fuel cell defines a maximum power output that is less than or equal to 3% of a maximum power output of the gas turbine engine.
10. The gas turbine engine of claim 1 , wherein the fuel cell is configured to provide substantially all of the output products directly to the exhaust gas flow during operation of the fuel cell.
11. The gas turbine engine of claim 1 , wherein the second fuel cell is smaller than the first fuel cell.
12. The gas turbine engine of claim 1 , wherein the first fuel cell comprises an electrolyte defining a first porosity, wherein the second fuel cell comprises an electrolyte defining a second porosity, and wherein the second porosity is greater than the first porosity.
13. The gas turbine engine of claim 1 , wherein the fuel cell assembly comprises a reformer downstream of the outlet and upstream of the exhaust gas flow.
14. The gas turbine engine of claim 13 , wherein the reformer is configured to reduce a fuel composition of a flow to less than a predetermined threshold.
15. The gas turbine engine of claim 13 , further comprising:
a heat source exchanger located downstream of the reformer.
16. A method of operating a gas turbine engine having a fuel cell assembly, the method comprising:
receiving with a cathode of a fuel cell of the fuel cell assembly a portion of an exhaust gas flow through an exhaust nozzle of a turbomachine of the gas turbine engine;
providing, from a fuel cell of the fuel cell assembly, output products directly to an exhaust gas flow through an exhaust nozzle of a turbomachine of the gas turbine engine, wherein the fuel cell assembly comprises a reformer downstream of the outlet and upstream of the exhaust gas flow; and
reducing a fuel composition of a flow to less than a predetermined threshold via the reformer.
17. A gas turbine engine comprising:
a turbomachine having a compressor section, a combustor, and a turbine section arranged in serial flow order, the turbomachine further comprising an outer casing and, during operation of the gas turbine engine, an exhaust gas flow from the turbine section; and
a fuel cell assembly positioned within the outer casing of the turbomachine, the fuel cell assembly comprising a fuel cell defining an inlet positioned to receive a portion of the exhaust gas flow, an outlet positioned to provide output products directly to the exhaust gas flow, or both, wherein the fuel cell defines the outlet positioned to provide output products directly to the exhaust gas flow, wherein the fuel cell is a first fuel cell of a plurality of fuel cells of the fuel cell assembly, wherein the fuel cell assembly comprises a reformer downstream of the outlet and upstream of the exhaust gas flow, and wherein the reformer is configured to reduce a fuel composition of a flow to less than a predetermined threshold.
18. The gas turbine engine of claim 17 , further comprising a heat source exchanger located downstream of the reformer.
19. The gas turbine engine of claim 17 , wherein the fuel cell defines the inlet positioned to receive the portion of the exhaust gas flow, wherein the turbomachine further comprises an exhaust nozzle defining a primary exhaust gas flowpath, wherein the fuel cell is in fluid communication with the primary exhaust gas flowpath for receiving the portion of the exhaust gas flow through the primary exhaust gas flowpath.
20. The gas turbine engine of claim 17 , wherein the turbomachine comprises an exhaust nozzle, wherein the fuel cell is in thermal communication with an exhaust gas flow through the exhaust nozzle during operation of the gas turbine engine, and wherein the fuel cell is pressurized relative to the exhaust gas flow through the exhaust nozzle during operation of the gas turbine engine.