Dual cycle intercooled hydrogen engine architecture
In one aspect of the present disclosure, there is provided a gas turbine engine. The gas turbine engine includes a primary gas path having, in fluid series communication: an air inlet, a compressor fluidly connected to the air inlet, a combustor fluidly connected to an outlet of the compressor, and a turbine section fluidly connected to an outlet of the combustor section. In embodiments, a hydrogen expansion turbine is in fluid communication to receive hydrogen from the gaseous hydrogen outlet of the heat exchanger. In certain embodiments, the gas turbine engine includes a heat exchanger having a gas conduit fluidly connected to the primary gas path, and a fluid conduit in fluid isolation from the gas conduit and in thermal communication with the gas conduit.
1. An aircraft engine, comprising:
a compressor, a combustor downstream of the compressor, and a turbine downstream of the combustor, the turbine drivingly engageable to a rotatable load;
an evaporator having a gas conduit fluidly connected to the compressor and a fuel conduit in heat exchange relationship with the gas conduit, the fuel conduit fluidly connected to a source of a cryogenic fuel;
an expansion turbine fluidly connected to the fuel conduit of the evaporator and located downstream of the evaporator, the expansion turbine having an outlet fluidly connected to the combustor;
a flow meter fluidly connected to the outlet of the expansion turbine and to the combustor, the flow meter located upstream of the combustor; and
a controller operatively connected to the flow meter, the controller having a processing unit and a computer-readable medium operatively connected to the processing unit and comprising instructions stored thereon executable by the processing unit to:
receiving a command power indicative of a desired power at the rotatable load; and
adjust a flow rate of the cryogenic fuel with the flow meter to achieve the desired power.
2. The aircraft engine of claim 1 , wherein a pump is fluidly connected to the source of the cryogenic fuel and operable to drive a flow of the cryogenic fuel from the source to the evaporator.
3. The aircraft engine of claim 2 , wherein the controller is operatively connected to the pump, the controller configured for controlling the pump to adjust the flow rate of the cryogenic fuel.
4. The aircraft engine of claim 1 , comprising a gaseous accumulator downstream of the expansion turbine and upstream of the flow meter.
5. The aircraft engine of claim 1 , wherein the expansion turbine is drivingly engaged to the rotatable load such that the turbine and the expansion turbine are conjointly driving the rotatable load.
6. The aircraft engine of claim 1 , wherein a gear box is drivingly engaged to a main shaft driven by the turbine, the gear box having an output shaft driven by combined power from the turbine and the expansion turbine.
7. The aircraft engine of claim 6 , wherein the expansion turbine is drivingly engaged to one or more of:
an electrical power generator, and an auxiliary air compressor.
8. The aircraft engine of claim 1 , wherein the cryogenic fuel is hydrogen.
9. A cryogenic fuel delivery system for an aircraft engine having a compressor, comprising:
an evaporator having a gas conduit fluidly connectable to the compressor and a fuel conduit in heat exchange relationship with the gas conduit, the fuel conduit fluidly connected to a source of a cryogenic fuel;
an expansion turbine fluidly connected to the fuel conduit of the evaporator and located downstream of the evaporator, the expansion turbine having an outlet;
a flow meter fluidly connected to the outlet of the expansion turbine, the flow meter having an outlet fluidly connectable to a combustor for delivering the cryogenic fuel to the combustor; and
a controller operatively connected to the flow meter, the controller having a processing unit and a computer-readable medium operatively connected to the processing unit and comprising instructions stored thereon executable by the processing unit to:
receiving a command power indicative of a desired power of the aircraft engine; and
adjust a flow rate of the cryogenic fuel with the flow meter to achieve the desired power.
10. The cryogenic fuel delivery system of claim 9 , wherein a pump is fluidly connected to the source of the cryogenic fuel and operable to drive a flow of the cryogenic fuel from the source to the evaporator.
11. The cryogenic fuel delivery system of claim 10 , wherein the controller is operatively connected to the pump, the controller configured for controlling the pump to adjust the flow rate of the cryogenic fuel.
12. The cryogenic fuel delivery system of claim 9 , comprising a gaseous accumulator downstream of the expansion turbine and upstream of the flow meter.
13. The cryogenic fuel delivery system of claim 9 , wherein the expansion turbine is drivingly engaged to the turbine such that the turbine and the expansion turbine are conjointly driving a rotatable load.
14. The cryogenic fuel delivery system of claim 9 , wherein a gear box is drivingly engaged to a main shaft driven by the turbine, the gear box having an output shaft driven by combined power from the turbine and the expansion turbine.
15. The cryogenic fuel delivery system of claim 14 , wherein the expansion turbine is drivingly engaged to one or more of: an electrical power generator, and an auxiliary air compressor.
16. The cryogenic fuel delivery system of claim 9 , wherein the cryogenic fuel is hydrogen.