Power generation system for an aircraft using a fuel cell
View Patent ↗A fuel cell ( 10 ) has a compressed air inlet fed by a compressor ( 20 ) and a fuel inlet, and it produces direct current electricity. A turbine ( 30 ) receives a flow of gas under pressure from the fuel cell and is mechanically coupled to the first compressor in order to drive it. A second compressor ( 46 ) of a circuit for use in flight to feed pressurized air to the aircraft cabin ( 40 ) is mechanically coupled to a shaft of the turbine. An electric machine ( 50 ) may be coupled to the same turbine shaft as drives the compressor ( 46 ), the electric machine being capable of operating as a generator or as an electric motor.
1. A power generator system for an aircraft, the system comprising:
a first compressor having an air inlet and a compressed air outlet;
an electricity generating device including a fuel cell having a compressed air inlet connected to the outlet of the first compressor and a fuel inlet, and producing direct current electricity on a power line connected to the fuel cell through reaction of the oxygen from the compressed air with the fuel;
a turbine receiving a flow of gas under pressure from the fuel cell and mechanically coupled to the first compressor; and
a second compressor of a circuit for use in flight to feed the aircraft cabin with pressurized air;
the second compressor for feeding the cabin being mechanically coupled to a shaft of the turbine.
2. A system according to claim 1 , wherein the first compressor and the second compressor are mounted on a common turbine shaft.
3. A power generator system for an aircraft, the system comprising:
a first compressor;
a fuel cell having a compressed air inlet connected to the outlet of the first compressor and a fuel inlet, and producing direct current electricity;
a turbine receiving a flow of gas under pressure from the fuel cell and mechanically coupled to the first compressor; and
a second compressor of a circuit for use in flight to feed the aircraft cabin with pressurized air;
the second compressor for feeding the cabin being mechanically coupled to a shaft of the turbine,
wherein the turbine comprises a first turbine stage receiving the flow of gas under pressure from the fuel cell and driving a first turbine shaft, and a second turbine stage receiving a flow of gas from the first turbine stage and driving a second turbine shaft, the first compressor being driven by the first turbine shaft, while the second compressor is driven by the second shaft.
4. A system according to claim 1 , further comprising an electric machine mechanically coupled to a shaft of the turbine.
5. A system according to claim 4 , wherein the electric machine and the second compressor are mounted in common on the same turbine shaft.
6. A system according to claim 4 , wherein the electric machine has a first mode of operation as an electricity generator and a second mode of operation as an electric motor, and a regulator circuit is provided for switching the operation of the electric machine between the first and second modes in order to maintain the mechanical torque available on the turbine shaft on which the electric machine is mounted to a value that is not less than a determined minimum value.
7. A system according to claim 4 , wherein a regulator system is provided for servo-controlling the speed of rotation of the electric machine to a predetermined setpoint value.
8. A system according to claim 1 , further including a heat exchanger separately passing the compressed air feeding the fuel cell and a gas flow leaving the turbine so as to heat the compressed air produced by the compressor prior to admitting said compressed air into the fuel cell.
9. A power generator system for an aircraft, the system comprising:
a first compressor having an air inlet and a compressed air outlet;
a fuel cell having a compressed air inlet connected to the outlet of the first compressor, a fuel inlet and a gas outlet and producing direct current electricity;
a turbine receiving a flow of gas under pressure from the fuel cell and mechanically coupled to the first compressor in order to drive it;
a second compressor of a circuit for use in flight to feed the aircraft cabin with pressurized air, the second compressor for feeding the cabin being mechanically coupled to a shaft of the turbine;
an electric machine mechanically coupled to a shaft of the turbine and having a first mode of operation as an electricity generator and a second mode of operation as an electric motor; and
a regulator circuit for switching the operation of the electric machine between the first and second modes in order to maintain the mechanical torque available on the turbine shaft on which the electric machine is mounted to a value that is not less than a determined minimum value.
10. A system according to claim 9 , wherein the first compressor, the second compressor and the electric machine are mounted on a common turbine shaft.
11. A system according to claim 9 , wherein the turbine comprises a first turbine stage receiving the flow of gas under pressure from the fuel cell and driving a first turbine shaft, and a second turbine stage receiving a flow of gas from the first turbine stage and driving a second turbine shaft, the first compressor being driven by the first turbine shaft, while the second compressor and the electric machine are driven by the second turbine shaft.
12. A system according to claim 9 , wherein a regulator system is provided for servo-controlling the speed of rotation of the electric machine to a predetermined set point value.