Integrated fuel cell and engine combustor assembly
An engine assembly includes a combustor, a fuel cell stack integrated with the combustor, and a pre-burner system fluidly connected to the fuel cell stack. The fuel cell stack is configured to direct fuel and air exhaust from the fuel cell stack into the combustor. The pre-burner system is configured to control a temperature of an air flow directed into the fuel cell stack. The combustor is configured to combust the fuel and air exhaust from the fuel cell stack into one or more gaseous combustion products that drive a downstream turbine. The engine assembly can further include a catalytic partial oxidation convertor that is fluidly connected to the fuel cell stack. The catalytic partial oxidation convertor is configured to develop a hydrogen rich fuel stream to be directed into the fuel cell stack.
1. An engine assembly comprising:
(a) a combustor;
(b) a fuel cell stack integrated with the combustor;
(c) a catalytic partial oxidation convertor that is fluidly connected to the fuel cell stack, wherein the catalytic partial oxidation convertor is configured to develop a stream of hydrogen rich fuel to be directed into the fuel cell stack; and
(d) a pre-burner system disposed upstream from and fluidly connected to the fuel cell stack separately from and in parallel with the catalytic partial oxidation convertor, the pre-burner system being configured to control a temperature of an air flow directed into the fuel cell stack, wherein the pre-burner system is fluidly connected directly to the fuel cell stack separately from the catalytic partial oxidation convertor, wherein the fuel cell stack is configured to direct the stream of hydrogen rich fuel and air exhaust from the fuel cell stack into the combustor, wherein the combustor is configured to combust the stream of hydrogen rich fuel and the air exhaust from the fuel cell stack into one or more gaseous combustion products that drive a downstream turbine.
2. The engine assembly of claim 1 , further comprising a compressor that is fluidly connected upstream of (i) the combustor and (ii) the pre-burner system, wherein the compressor is configured to direct a portion of air into the pre-burner system.
3. The engine assembly of claim 2 , further comprising a fuel source that provides fuel to and is fluidly connected to the pre-burner system and the catalytic partial oxidation convertor, wherein a portion of the fuel is directed from the fuel source to the pre-burner system to raise a temperature of the portion of the air flow directed into the pre-burner system from the compressor.
4. The engine assembly of claim 1 , wherein the catalytic partial oxidation convertor, the pre-burner system, and the fuel cell stack are manifolded together within the engine assembly.
5. The engine assembly of claim 4 , further comprising a fuel source that provides fuel and is fluidly connected to the pre-burner system and the catalytic partial oxidation convertor, wherein (i) a first portion of the fuel is directed from the fuel source to the pre-burner system to raise a temperature of a portion of the air directed into the pre-burner system from a compressor and (ii) a second portion of the fuel is directed from the fuel source to the catalytic partial oxidation convertor for developing the stream of hydrogen rich fuel.
6. The engine assembly of claim 1 , further comprising a hydrogen fuel source.
7. The engine assembly of claim 1 , wherein the temperature of the air flow being directed into the fuel cell stack from the pre-burner system is from 500° C. to 1000° C.
8. The engine assembly of claim 1 , wherein the combustor further comprises one or more pilot/main fuel nozzles being configured to combust the stream of hydrogen rich fuel and the air exhaust directed into the combustor from the fuel cell stack into the one or more gaseous combustion products.
9. The engine assembly of claim 1 , further comprising an engine case that encases the combustor, the fuel cell stack, and the pre-burner system.
10. The engine assembly of claim 1 , further comprising the downstream turbine connected downstream of the combustor.
11. The engine assembly of claim 1 , wherein the engine assembly is configured to control the temperature of the air flow directed into the fuel cell stack from the pre-burner system, by controlling a flow rate of a fuel and a flow rate of an air stream directed into the pre-burner system, to at least one of (i) an operating point of the fuel cell stack, (ii) up to 200° C. less than the operating point of the fuel cell stack, and (iii) up to 200° C. more than the operating point of the fuel cell stack.
12. The engine assembly of claim 1 , wherein the fuel cell stack is at least one of (i) circumferentially surrounding the combustor and (ii) axially coupled to the combustor.
13. The engine assembly of claim 1 , wherein the fuel cell stack is integrated within at least one of an inner liner and an outer liner of the combustor.
14. The engine assembly of claim 1 , wherein the fuel cell stack is a solid oxide fuel cell stack.
15. An engine assembly comprising:
(a) a combustor;
(b) a fuel cell stack integrated with the combustor, the fuel cell stack configured to direct a hydrogen rich fuel stream and air exhaust from the fuel cell stack into the combustor;
(c) a pre-burner system fluidly connected to and disposed upstream from the fuel cell stack, the pre-burner system being configured to control a temperature of an air flow directed into the fuel cell stack from the pre-burner system; and
(d) a catalytic partial oxidation convertor that is fluidly connected to the fuel cell stack separately from and in parallel with the pre-burner system, wherein the catalytic partial oxidation convertor is configured to develop the hydrogen rich fuel stream to be directed into the fuel cell stack, wherein the pre-burner system is fluidly connected directly to the fuel cell stack separately from the catalytic partial oxidation convertor,
wherein the combustor is configured to combust the hydrogen rich fuel stream and the air exhaust from the fuel cell stack into one or more gaseous combustion products that drive a downstream turbine.
16. The engine assembly of claim 15 , further comprising a compressor that is fluidly connected upstream of (i) the combustor and (ii) the pre-burner system, wherein the compressor is configured to direct a portion of the air flow into the pre-burner system.
17. The engine assembly of claim 15 , wherein the temperature of the air flow being directed into the fuel cell stack from the pre-burner system is from 500° C. to 1000° C.
18. The engine assembly of claim 15 , further comprising a fuel source that provides fuel and is fluidly connected to the pre-burner system and the catalytic partial oxidation convertor, wherein (i) a first portion of the fuel is directed from the fuel source to the pre-burner system to raise a temperature of a portion of the air flow directed into the pre-burner system from a compressor and (ii) a second portion of the fuel is directed from the fuel source to the catalytic partial oxidation convertor for developing the hydrogen rich fuel stream.
19. The engine assembly of claim 15 , wherein the engine assembly is configured to control the temperature of the air flow directed into the fuel cell stack from the pre-burner system, by controlling a flow rate of fuel and a flow rate of an air stream directed into the pre-burner system, to at least one of (i) an operating point of the fuel cell stack, (ii) up to 200° C. less than the operating point of the fuel cell stack, and (iii) up to 200° C. more than the operating point of the fuel cell stack.