ELECTRICITY GENERATION SYSTEM COMPRISING A FUEL CELL

Abstract

ELECTRICITY GENERATION SYSTEM COMPRISING A FUEL CELL The invention relates to an electricity generation system (200) comprising a fuel cell (206), a supply line (208a) for supplying oxygen to the cathode (206b), a supply line (210) between a source of hydrogen (202) and a heat exchanger (220), a transport line (214) between the heat exchanger (220) and a mixer (212), a supply line (216) between the anode (206a) and the mixer (212), a first recirculation line (217a) between the anode (206a) and the heat exchanger (220), a second recirculation line (217b) between the heat exchanger (220) and a gas / liquid separator (218), and a third recirculation line (217b) between the heat exchanger (220) and a gas / liquid separator (218). recirculation (217c) between the gas / liquid separator (218) and the mixer (212). Such an electrical production system thus makes it possible to recover unconsumed dihydrogen to return it to the fuel cell Fig. 2

Description

Title of the invention: ELECTRICITY PRODUCTION SYSTEM COMPRISING A FUEL CELL Technical field

[0001] The present invention relates to an electrical production system which comprises a fuel cell and which is intended to be implemented in an aircraft, as well as an aircraft comprising such an electrical production system. STATE OF THE PRIOR ART

[0002] In order to provide an electric current, in particular in an aircraft, it is known to use a fuel cell in which the generation of an electric voltage is achieved by the oxidation on one electrode of a reducing fuel, for example dihydrogen, coupled with the reduction on the other electrode of an oxidant, for example dioxygen from the air.

[0003] In certain fuel cells, in particular a solid oxide fuel cell (SOFC), it is necessary to supply excess hydrogen to the anode in order to guarantee a minimum concentration of hydrogen even in the presence of water resulting from the oxidation.

[0004] It is known to use the excess dihydrogen at the anode outlet to feed a combustion chamber whose exhaust gases can be used to turn a turbine. But depending on the fuel used, such an installation can release products such as nitrogen oxides or carbon dioxide. It is desirable to find an arrangement for which such products are not released. Statement of the invention

[0005] An object of the present invention is to propose an electrical production system which comprises a fuel cell and which makes it possible to limit the emissions of harmful products.

[0006] For this purpose, an electrical production system is proposed comprising:

[0007] - a fuel cell with an anode and a cathode,

[0008] - a first supply pipe intended to be fluidically connected between the cathode and a source of oxygen,

[0009] - a heat exchanger comprising a first inlet and a first outlet fluidly connected to each other, and a second inlet and a second outlet fluidly connected to each other,

[0010] - a supply pipe intended to be fluidically connected between a source of dihydrogen and the first inlet of the heat exchanger,

[0011] - a mixer comprising a first input, a second input and an output,

[0012] - a fluidically connected transport pipeline between the first outlet of the heat exchanger and the first mixer inlet,

[0013] - a second supply line fluidically connected between the anode and the mixer output,

[0014] - a first recirculation pipe fluidically connected between the anode and the second inlet of the heat exchanger,

[0015] - a gas / liquid separator with an inlet, a first outlet and a second exit,

[0016] - a second recirculation pipeline fluidically connected between the second outlet of the heat exchanger and the inlet of the gas / liquid separator,

[0017] - a third recirculation pipe fluidically connected between the first outlet of the gas / liquid separator and the second inlet of the mixer,

[0018] - a discharge pipe intended to be fluidically connected between the second outlet of the gas / liquid separator and a recovery system, and

[0019] - means for setting dihydrogen and dioxygen in motion in the electrical production system.

[0020] Such an electrical production system thus makes it possible to recover the unconsumed dihydrogen to return it to the fuel cell and thus only the excess dioxygen and water are recovered at the outlet of the fuel cell.

[0021] Advantageously, the movement means comprise a pump mounted on the first recirculation pipe.

[0022] The invention also proposes an aircraft comprising a source of dihydrogen, a source of dioxygen and an electrical production system according to one of the preceding variants where one end of the supply pipe is fluidically connected to the source of dihydrogen and where one end of the first supply pipe is fluidically connected to the source of dioxygen. Brief description of the drawings

[0023] The above-mentioned features of the invention, as well as others, will appear more clearly on reading the following description of an exemplary embodiment, said description being made in relation to the attached drawings, among which:

[0024] [Fig-1] is a side view of an aircraft having a production system electrical according to the invention, and

[0025] [Fig.2] is a schematic representation of an electrical production system according to the invention.

[0026] DETAILED DESCRIPTION OF EMBODIMENTS

[0027] [Fig.l] shows an aircraft 100 which has a fuselage 102 on either side of which a wing 104 is fixed. Under each wing 104 is fixed at least one propulsion system 106 by means of a support mast 108.

[0028] The aircraft 100 comprises a source of dihydrogen 202, a source of dioxygen 204 and an electrical production system 200 according to the invention, one embodiment of which is shown in [Fig.2].

[0029] The invention is more particularly described in the context of an aircraft 100, but it can be applied in other fields, whether in transport or others.

[0030] In the context of the implementation in the aircraft 100, the source of dihydrogen 202 is for example a tank filled with preferably liquid dihydrogen and the source of dioxygen 204 is for example constituted by a scoop arranged at the skin of the aircraft 100 to take outside air.

[0031] In the embodiment of the invention shown in [Fig.l], the hydrogen source 202, the oxygen source 204 and the electrical production system 200 are arranged in the fuselage 102, but a different distribution is possible. For example, the electrical production system 200 and the oxygen source 204 can be located at each propulsion system 106 and the hydrogen source 202 remaining in the fuselage 102.

[0032] In the same way, the electricity produced by the electrical production system 200 can be used either to run the propulsion system 106, for example when it is an electric motor, or to power the various electrical devices of the aircraft 100.

[0033] [Fig. 2] shows the electrical production system 200 which comprises a fuel cell 206 with an anode 206a and a cathode 206b, to which one or more electrical systems 50 are connected. As specified above, an electrical system 50 can be an electric motor such as a propeller motor, or any other electrical device.

[0034] The fuel cell 206 also comprises between the anode 206a and the cathode 206b, an electrolyte 206c. The oxygen which arrives at the cathode 206b combines with the electrons coming from the electrical system 50 to form oxygen ions which pass through the electrolyte 206c. The hydrogen which arrives at the anode 206a loses its electrons which go towards the electrical system 50 and form hydrogen ions which combine with the oxygen ions coming from the electrolyte 206c to form water at the anode 206a.

[0035] The electrical production system 200 comprises a first supply pipe 208a which is fluidically connected by one of its ends to the cathode 206b and by another of its ends to the oxygen source 204.

[0036] The electrical production system 200 comprises a heat exchanger 220 inside which two pipes 221a-b wind, which are arranged to allow a transfer of calories from the fluid flowing in one of the pipes 221b to the fluid flowing in the other of the pipes 221a.

[0037] The heat exchanger 220 comprises a first inlet 220a and a first outlet 220b which correspond to one of the pipes 221a and a second inlet 220c and a second outlet 220d which correspond to the other of the pipes 221b. Thus, the first inlet 220a and the first outlet 220b are fluidically connected to each other, and the second inlet 220c and the second outlet 220d are fluidically connected to each other.

[0038] The electrical production system 200 comprises a supply pipe 210 which is fluidically connected by one of its ends to the source of dihydrogen 202 and by another of its ends to the heat exchanger 220. The supply pipe 210 thus supplies the heat exchanger 220 with the dihydrogen which will be reheated.

[0039] The electrical production system 200 comprises a mixer 212 comprising a first inlet 212a, a second inlet 212b and an outlet 212c. As explained below, the mixer makes it possible to combine the two flows of dihydrogen which come from the dioxygen source 204 and the heat exchanger 220 into a single flow which feeds the anode 206a. The mixer 212 may take the form of an enclosure into which the pipes connected to the inlets / outlets 202a-c of the mixer 212 open, or it may optionally take the form of a three-way valve or a T-tube.

[0040] The electrical production system 200 comprises a transport pipe 214 which is fluidically connected by one of its ends to the first outlet 220b of the heat exchanger 220 and by another of its ends to the first inlet 212a of the mixer 212.

[0041] The electrical production system 200 comprises a second supply pipe 216 which is fluidically connected by one of its ends to the anode 206a and by another of its ends to the outlet 212c of the mixer 212.

[0042] The electrical production system 200 comprises a first recirculation pipe 217a which is fluidically connected by one of its ends to the anode 206a and by another of its ends to the second inlet 220c of the heat exchanger 220.

[0043] The power generation system 200 includes a gas / liquid separator 218 with an inlet 218a, a first outlet 218b, and a second outlet 218c. Conventionally, the gas / liquid separator 218 operates by gravity to separate toward the top (here the first outlet 218b), the gases, and downwards (here the second outlet 218c), the liquid.

[0044] The inlet 218a is intended to receive a gas / liquid mixture, here a dihydrogen / water mixture, the first outlet 218b allows the dihydrogen to be evacuated and the second outlet 218c allows the water to be evacuated.

[0045] The electrical production system 200 comprises a second recirculation pipe 217b which is fluidically connected by one of its ends to the second outlet 220d of the heat exchanger 220 and by another of its ends to the inlet 218a of the gas / liquid separator 218.

[0046] The electrical production system 200 comprises a third recirculation pipe 217c which is fluidically connected by one of its ends to the first outlet 218b of the gas / liquid separator 218 and by another of its ends to the second inlet 212b of the mixer 212.

[0047] The electrical production system 200 comprises an evacuation pipe 219 which is fluidically connected by one of its ends to the second outlet 218c of the gas / liquid separator 218 and by another of its ends to a recovery system 222. The recovery system 222 recovers and treats the water that it receives to possibly use it on board the aircraft 100 or to discharge it outside.

[0048] The electrical production system 200 comprises movement means 230, such as pumps, which ensure the movement of dihydrogen and dioxygen in the electrical production system 200.

[0049] The oxygen is brought to the cathode 206b by the first supply pipe 208a.

[0050] The dihydrogen is brought to the anode 206a by the second supply pipe 216.

[0051] The excess hydrogen and water in vapor form are evacuated from the anode 206a by the first recirculation pipe 217a to the heat exchanger 220 where they heat the hydrogen leaving the hydrogen source 202 which also passes through the heat exchanger 220.

[0052] Arriving in the second recirculation pipe 217b, the dihydrogen is thus cooled and the water is condensed in liquid form. The dihydrogen / liquid water mixture is then introduced into the gas / liquid separator 218. The dihydrogen exits through the first outlet 218b to join the mixer 212 and supply the anode 206a. The liquid water exits through the second outlet 218c to be treated and / or evacuated.

[0053] The dihydrogen thus recirculates to be completely consumed.

[0054] With such an arrangement, all the hydrogen is consumed and the only products that can possibly be released are water. Furthermore, using a fuel cell to completely consume the hydrogen has a higher efficiency than using a combustion chamber.

[0055] As presented above, the heat exchanger 220 performs the function of a condenser which makes it possible to heat the dihydrogen leaving the dihydrogen source 202 and to liquefy the water.

[0056] In the embodiment of the invention presented in [Fig. 2], the movement means 230 comprise a pump mounted on the first recirculation pipe 217a. Of course, it is possible to provide other pumps at other locations in the circuit constituting the electrical production system 200 depending on requirements.

[0057] To evacuate the excess oxygen at the cathode 206b, the electrical production system 200 here comprises a discharge pipe 208b which discharges said oxygen outside the aircraft 100.

Claims

Claims

1. An electrical production system (200) comprising: - a fuel cell (206) with an anode (206a) and a cathode (206b), - a first supply line (208a) intended to be fluidically connected between the cathode (206b) and a source of oxygen (204), - a heat exchanger (220) comprising a first inlet (220a) and a first outlet (220b) fluidly connected to each other, and a second inlet (220c) and a second outlet (220d) fluidly connected to each other, - a supply line (210) intended to be fluidically connected between a source of hydrogen (202) and the first inlet (220a) of the heat exchanger (220), - a mixer (212) comprising a first inlet (212a), a second inlet (212b) and an outlet (212c), - a transport pipe (214) fluidically connected between the first outlet (220b) of the heat exchanger (220) and the first inlet (212a) of the mixer (212),- a second supply line (216) fluidly connected between the anode (206a) and the outlet (212c) of the mixer (212), - a first recirculation line (217a) fluidly connected between the anode (206a) and the second inlet (220c) of the heat exchanger (220), - a gas / liquid separator (218) with an inlet (218a), a first outlet (218b) and a second outlet (218c), - a second recirculation line (217b) fluidly connected between the second outlet (220d) of the heat exchanger (220) and the inlet (218a) of the gas / liquid separator (218), - a third recirculation line (217c) fluidly connected between the first outlet (218b) of the gas / liquid separator (218) and the second inlet (212b) of the mixer (212), - an evacuation pipe (219) intended to be fluidically connected between the second outlet (218c) of the gas / liquid separator (218) and a recovery system (222),and - means for moving (230) the dihydrogen and dioxygen in the electrical production system (200).,

2. Electrical production system (200) according to claim 1, characterized in that the movement means (230) comprise a pump mounted on the first recirculation pipe (217a).

3. An aircraft (100) comprising a hydrogen source (202), an oxygen source (204) and an electrical production system (200) according to one of the preceding claims, wherein one end of the supply line (210) is fluidically connected to the hydrogen source (202) and wherein one end of the first supply line (208a) is fluidically connected to the oxygen source (204).

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