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WO2015104487A1 - Emergency electrical generator of an aircraft, with a quick-starting fuel cell - Google Patents

Emergency electrical generator of an aircraft, with a quick-starting fuel cell Download PDF

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Publication number
WO2015104487A1
WO2015104487A1 PCT/FR2015/050006 FR2015050006W WO2015104487A1 WO 2015104487 A1 WO2015104487 A1 WO 2015104487A1 FR 2015050006 W FR2015050006 W FR 2015050006W WO 2015104487 A1 WO2015104487 A1 WO 2015104487A1
Authority
WO
WIPO (PCT)
Prior art keywords
emergency
battery
auxiliary
heat
auxiliary battery
Prior art date
Application number
PCT/FR2015/050006
Other languages
French (fr)
Inventor
Fabien Boudjemaa
François MOSER
Matthieu BARON
Original Assignee
Snecma
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Snecma filed Critical Snecma
Publication of WO2015104487A1 publication Critical patent/WO2015104487A1/en

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D41/00—Power installations for auxiliary purposes
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M8/00—Fuel cells; Manufacture thereof
    • H01M8/04—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
    • H01M8/04007—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids related to heat exchange
    • H01M8/04029—Heat exchange using liquids
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M8/00—Fuel cells; Manufacture thereof
    • H01M8/04—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
    • H01M8/04298—Processes for controlling fuel cells or fuel cell systems
    • H01M8/04313—Processes for controlling fuel cells or fuel cell systems characterised by the detection or assessment of variables; characterised by the detection or assessment of failure or abnormal function
    • H01M8/04664—Failure or abnormal function
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M8/00—Fuel cells; Manufacture thereof
    • H01M8/04—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
    • H01M8/04298—Processes for controlling fuel cells or fuel cell systems
    • H01M8/04313—Processes for controlling fuel cells or fuel cell systems characterised by the detection or assessment of variables; characterised by the detection or assessment of failure or abnormal function
    • H01M8/04664—Failure or abnormal function
    • H01M8/04679—Failure or abnormal function of fuel cell stacks
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M8/00—Fuel cells; Manufacture thereof
    • H01M8/04—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
    • H01M8/04298—Processes for controlling fuel cells or fuel cell systems
    • H01M8/04694—Processes for controlling fuel cells or fuel cell systems characterised by variables to be controlled
    • H01M8/04701—Temperature
    • H01M8/04731—Temperature of other components of a fuel cell or fuel cell stacks
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M8/00—Fuel cells; Manufacture thereof
    • H01M8/24—Grouping of fuel cells, e.g. stacking of fuel cells
    • H01M8/249—Grouping of fuel cells, e.g. stacking of fuel cells comprising two or more groupings of fuel cells, e.g. modular assemblies
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D41/00—Power installations for auxiliary purposes
    • B64D2041/005—Fuel cells
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M2250/00—Fuel cells for particular applications; Specific features of fuel cell system
    • H01M2250/20—Fuel cells in motive systems, e.g. vehicle, ship, plane
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M8/00—Fuel cells; Manufacture thereof
    • H01M8/04—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
    • H01M8/04007—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids related to heat exchange
    • H01M8/04067—Heat exchange or temperature measuring elements, thermal insulation, e.g. heat pipes, heat pumps, fins
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M8/00—Fuel cells; Manufacture thereof
    • H01M8/06—Combination of fuel cells with means for production of reactants or for treatment of residues
    • H01M8/0606—Combination of fuel cells with means for production of reactants or for treatment of residues with means for production of gaseous reactants
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M8/00—Fuel cells; Manufacture thereof
    • H01M8/06—Combination of fuel cells with means for production of reactants or for treatment of residues
    • H01M8/0606—Combination of fuel cells with means for production of reactants or for treatment of residues with means for production of gaseous reactants
    • H01M8/065—Combination of fuel cells with means for production of reactants or for treatment of residues with means for production of gaseous reactants by dissolution of metals or alloys; by dehydriding metallic substances
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02B—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO BUILDINGS, e.g. HOUSING, HOUSE APPLIANCES OR RELATED END-USER APPLICATIONS
    • Y02B90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
    • Y02B90/10—Applications of fuel cells in buildings
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
    • Y02E60/30—Hydrogen technology
    • Y02E60/50—Fuel cells
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
    • Y02T90/40—Application of hydrogen technology to transportation, e.g. using fuel cells

Definitions

  • the present invention relates to the field of electric power sources of an aircraft.
  • the aircraft embark several power generation systems to ensure their power supply, namely batteries, generators, an auxiliary unit commonly referred to as the “Auxiliary Power Unit” or “APU”, and a power unit. emergency commonly referred to as “Emergency Power Unit” or “UPR”.
  • the batteries, generators and the auxiliary unit provide the power supply under the usual flight conditions, while the emergency unit realizes the power supply in case of failure of one or more of the other generation systems energy, or when an electrical requirement temporarily increases, for example during take-off or landing. It is understandable that the various energy generation systems are essential elements of an aircraft, and that their reactivity is essential.
  • the document WO 2006/094743 proposes to maintain the fuel cell in a given temperature range, for example greater than 5 ° C., in order to ensure its rapid availability, either by placing it in a medium having a sufficiently high temperature, for example the cabin of an aircraft, or by means of a heating system dedicated to the fuel cell, for example also able to achieve cooling when operating.
  • the document EP 2658022 proposes to keep the fuel cell in a given temperature range by controlling its operation intermittently so that the exothermic reaction it produces releases the heat necessary to maintain it at a predetermined temperature, or by using a heating resistor challenged to maintain the temperature of the fuel cell.
  • Such solutions are suitable only for fuel cells having low operating temperatures, and requires a dedicated heating system which is problematic in particular in terms of weight and bulk.
  • the present invention aims to respond at least in part to the aforementioned problems.
  • the present invention proposes a system for generating electrical energy from an aircraft, comprising
  • auxiliary power source and emergency power source each comprise a fuel cell, respectively an auxiliary battery and an emergency battery
  • said system comprises means for collecting heat released by the auxiliary battery during its operation so as to heat the emergency battery.
  • said means for taking the heat released by the auxiliary battery during its operation so as to heat the emergency battery comprises a common cooling circuit connecting said auxiliary and emergency batteries, configured in a manner maintaining the emergency battery at a temperature substantially equal to its operating temperature by heat dissipation of the heat generated by the auxiliary battery during operation of the auxiliary battery.
  • the system further comprises a controller adapted to detect a malfunction of a source of primary electrical energy and / or the source of auxiliary electrical energy, and to control the operation of the source emergency power supply in the event of failure of a primary power source and / or auxiliary power source.
  • system further comprises a controller configured to perform a test of the emergency battery to control its temperature.
  • the system further typically comprises a controller configured to drive the auxiliary battery and the cooling circuit so as to maintain the emergency battery at a temperature between 110 ° C and 180 ° C during operation of the auxiliary battery, said auxiliary battery and the emergency battery each having an operating temperature of between 110 ° C and 220 ° C.
  • the auxiliary battery and the emergency battery are, for example, high temperature proton exchange membrane fuel cells.
  • the cooling circuit is, for example, configured so that, when the emergency battery is not in operation, the fluid circulating in the cooling circuit is successively passed through a heat sink of the auxiliary battery, in a heat sink of the emergency battery, then in a radiator.
  • the cooling circuit can then also be configured so that, when the emergency battery is in operation, isolating the heat exchangers relative to each other in emergency operation so as to have two sub-circuits of separate cooling each performing the cooling of one of the auxiliary and emergency batteries.
  • the emergency stack is typically associated with a hydride-based solid hydrogen generator, coupled to a well for packaging and dispensing hydrogen from the hydrogen generator to the emergency stack, and a solid oxygen generator coupled to a chamber for conditioning and dispensing oxygen from the solid oxygen generator to the emergency stack.
  • the invention also relates to an aircraft equipped with an electric generating system as presented.
  • the invention further relates to a method of generating electrical energy in an aircraft by means of a primary energy source, an auxiliary power source and an emergency power source, wherein said auxiliary and emergency power sources each comprise a fuel cell, respectively an auxiliary battery and an emergency battery, said method being characterized in that the operation of the auxiliary battery releases heat which is removed and used to heat the emergency battery.
  • the emergency battery is advantageously maintained at a temperature substantially equal to its operating temperature by means of a common cooling circuit with the auxiliary battery.
  • the emergency battery is advantageously actuated in the event of failure of a source of primary electrical energy and / or of the source of auxiliary electrical energy.
  • a controller performs a test of the emergency battery to control its temperature and availability.
  • the emergency battery is maintained at a temperature of between 110 ° C. and 180 ° C., said auxiliary battery and the emergency battery each having an operating temperature. between 110 ° C and 220 ° C.
  • the auxiliary battery and the emergency battery are, for example, high temperature proton exchange membrane fuel cells.
  • FIG. 1 schematically represents an electrical energy generation system. according to one aspect of the invention.
  • FIG. 1 schematically represents a system 1 for generating electrical energy according to one aspect of the invention, comprising:
  • the source of primary electrical energy P can be of various types; it typically includes batteries and generators.
  • the APU auxiliary power source comprises a fuel cell which is designated by auxiliary battery 20, associated with a hydrogen reservoir 22 containing hydrogen in solid, liquid or gaseous form, and a compressor 24 provided with of an engine 26.
  • the hydrogen reservoir 22 is equipped with a valve 23 so as to selectively supply the hydrogen supply of the fuel cell 20.
  • the compressor 24 and the motor 26 are adapted to selectively provide oxygen supply to the fuel cell 20.
  • the emergency power source EPU comprises a fuel cell that is designated emergency stack 30, associated with a solid hydrogen generator 32 and a solid oxygen generator 34.
  • the solid hydrogen generator 32 and the solid oxygen generator 34 are connected to the emergency stack 30 via valves 33 and 35, respectively.
  • the emergency power source EPU further comprises an emergency battery 36, particularly adapted to supply the valves 33 and 35.
  • the auxiliary battery 20 and the emergency battery 30 each have a heat exchanger, respectively 42 and 43, connected to a cooling circuit 40 provided with a radiator 44.
  • the heat exchanger 42 of the auxiliary battery 20 is configured to perform a heat exchange between a fluid flowing in the cooling circuit 40 and the auxiliary battery 20.
  • the heat exchanger 40 of the emergency stack 30 is configured to perform a heat exchange between the fluid flowing in the cooling circuit 40 and the emergency stack 30.
  • the radiator 44 is configured to in order to achieve a heat exchange between the fluid flowing in the cooling circuit 40 and an external medium, in order to dissipate the heat accumulated by the fluid of the cooling circuit 40.
  • the fluid flows in the cooling circuit 40 in the direction indicated by the arrows in FIG.
  • the system 1 as presented further comprises an optional controller 50, configured to control the temperature and / or condition of the emergency stack 30, and also to detect the state of the power source.
  • the controller 50 is advantageously powered by an independent power source, for example the emergency battery 36. It can be connected to several power sources, so as not to reduce the load of the emergency battery 36 by normal running.
  • the source of primary electrical energy P provides electricity, including the compressor 24, the motor 26 as well as the hydrogen reservoir 22 and the associated valve 23.
  • the auxiliary battery 20 is thus supplied with hydrogen and oxygen; it is powered, and delivers electricity.
  • the system 1 thus delivers electrical energy, and can thus achieve for example the power supply of an aircraft.
  • the emergency stack 30 is not in operation; the valves 32 and 33 for its supply of hydrogen and oxygen are closed.
  • the auxiliary battery 20 During the operation of the auxiliary battery 20, the latter releases heat, which is transferred to the fluid flowing in the cooling circuit 40 through the heat exchanger 42.
  • the heated fluid flows in the cooling circuit 40 in the direction indicated. by the arrows in Figure 1; once out of the heat exchanger 42 of the auxiliary battery 20, it passes through the heat exchanger 43 of the emergency stack 30.
  • the emergency battery 30 is not in operation, it is at room temperature.
  • the heat exchanger 43 thus transfers heat from the fluid of the cooling circuit 40 to the emergency stack 30, the temperature of which increases until a predetermined value is reached, depending in particular on the operating temperature of the auxiliary battery 20 .
  • the fluid of the cooling circuit 40 then passes through the radiator 44, which transfers the remainder of the heat transmitted by the auxiliary battery 20 to the ambient medium before the fluid passes again through the heat exchanger 42 of the auxiliary battery 20.
  • the emergency battery 30 is not put into operation, but is maintained at a predetermined temperature, which is advantageously chosen to be substantially equal to, or at least close to its operating temperature.
  • the emergency battery 30 is a high-temperature proton exchange membrane fuel cell having an operating temperature of between 110 ° C. and 220 ° C.
  • the emergency stack 30 is then typically maintained at a temperature between 110 ° C and 180 ° C.
  • the auxiliary battery 20 may also be a high temperature proton exchange membrane fuel cell.
  • the controller 50 then directs the auxiliary battery 20 and the cooling circuit 40 to maintain in this temperature range.
  • the controller 50 detects a malfunction of the primary power source P and / or the auxiliary power source APU and controls the start-up of the emergency battery 30.
  • the battery 36 then feeds the valves 33 and 35, so as to supply the emergency battery 30 with hydrogen and oxygen, which triggers its operation so that it generates electricity to compensate for all or part of the lack of electricity resulting from the failure of the primary power source P and / or the auxiliary power source APU.
  • the emergency battery 30 has been brought and maintained at a predetermined temperature, advantageously chosen so as to be substantially equal to, or at least close to, its operating temperature; it can be put into operation immediately without requiring a preheating step.
  • the auxiliary battery stops operating in a nominal way, and therefore stops generating heat, or at least generates less heat than in normal operation.
  • the heat released by the auxiliary battery 20 picked up by the fluid of the cooling circuit 40 and which passes through the heat exchanger 43 of the emergency stack 30 is therefore reduced compared to the normal operation described above, and does not harm the operation. emergency stack 30.
  • controller 50 may be configured to isolate the heat exchangers 42 and 43 from one another in emergency operation so as to have two sub-circuits of the same. separate cooling each cooling one of the fuel cells 20 and 30.
  • the flow rate of fluid flowing in the cooling circuit 40 can also be modified depending on the operating mode in order to avoid any risk of overheating of the fuel cells 20 and 30.
  • the solid hydrogen generator 32 is typically a hydride-based generator, coupled to a box for packaging and dispensing hydrogen from the hydrogen generator 32.
  • the solid oxygen generator 34 is also typically coupled to a box for conditioning and dispensing oxygen from the oxygen generator 34.
  • valves 33 and 35 are controlled so as to deliver the appropriate amounts of oxygen and hydrogen; advantageously the stoichiometric amounts to ensure the proper functioning of the emergency stack 30.
  • Such hydrogen 32 and oxygen 34 generators make it possible to minimize the size and the weight of the storage of hydrogen and oxygen necessary for the operation of the emergency stack 30.
  • the system 1 as presented can for example be used to provide power to an aircraft.
  • the controller 50 may, for example, carry out availability tests of the emergency electrical power source EPU before take-off of the aircraft, or at intervals for example, when the primary power source P and / or the auxiliary power source APU are in operation.
  • the proposed system thus provides an emergency power supply that can be put into operation very quickly, for example within 3 to 8 seconds, while minimizing the weight and bulk of the system.
  • the proposed system optimizes the management of the heat released by the APU auxiliary power source, and makes it possible to dispense with an additional heating device dedicated to the emergency battery 30, by taking the heat released by the battery. auxiliary for heating the emergency battery.
  • the proposed power system is further independent of the flight conditions, including the altitude or inclination of the aircraft.

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  • Engineering & Computer Science (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Manufacturing & Machinery (AREA)
  • Sustainable Development (AREA)
  • Sustainable Energy (AREA)
  • Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Electrochemistry (AREA)
  • General Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Fuel Cell (AREA)

Abstract

The invention relates to a system (1) for generating electrical energy, pertaining to an aircraft, comprising: a primary energy source (P), an auxiliary electrical energy source (APU), and an emergency electrical energy source (EPU), characterised in that said auxiliary electrical energy source (APU) and said emergency electrical energy source (EPU) each comprise a fuel cell, respectively an auxiliary cell (20) and an emergency cell (30), and in that said system (1) comprises means (40) for recovering the heat released by the auxiliary cell (20) during the operation thereof so as to heat the emergency cell (30).

Description

Générateur électrique de secours d'un aéronef avec pile à combustible à démarrage rapide  Emergency electrical generator of an aircraft with a quick start fuel cell

DOMAINE TECHNIQUE GENERAL GENERAL TECHNICAL FIELD

La présente invention concerne le domaine des sources d'énergie électrique d'un aéronef. The present invention relates to the field of electric power sources of an aircraft.

ETAT DE L'ART STATE OF THE ART

Les aéronefs embarquent plusieurs systèmes de génération d'énergie électrique afin d'assurer leur alimentation, à savoir des batteries, des génératrices, une unité auxiliaire communément désignée sous l'appellation anglaise « Auxiliary Power Unit » ou « APU », et une unité d'urgence communément désignée sous l'appellation anglaise « Emergency Power Unit » ou « EPU ». The aircraft embark several power generation systems to ensure their power supply, namely batteries, generators, an auxiliary unit commonly referred to as the "Auxiliary Power Unit" or "APU", and a power unit. emergency commonly referred to as "Emergency Power Unit" or "UPR".

Les batteries, génératrices et l'unité auxiliaire réalisent l'alimentation électrique dans les conditions usuelles de vol, tandis que l'unité d'urgence réalise l'alimentation électrique en cas de défaillance de l'un ou de plusieurs des autres systèmes de génération d'énergie, ou lorsqu'un besoin électrique augmente temporairement, par exemple lors du décollage ou de l'atterrissage. On comprend bien que les différents systèmes de génération d'énergie sont des éléments essentiels d'un aéronef, et que leur réactivité est essentielle. The batteries, generators and the auxiliary unit provide the power supply under the usual flight conditions, while the emergency unit realizes the power supply in case of failure of one or more of the other generation systems energy, or when an electrical requirement temporarily increases, for example during take-off or landing. It is understandable that the various energy generation systems are essential elements of an aircraft, and that their reactivity is essential.

Différentes structures d'unité d'urgence ont été proposées. Different emergency unit structures have been proposed.

Il a ainsi déjà été proposé d'intégrer un système d'éoliennes dans une structure d'aéronef, par exemple dans ses ailes, ces éoliennes pouvant être déployées en vol et ainsi générer de l'électricité. Toutefois, on comprend bien qu'un tel système est non seulement très complexe à intégrer dans une structure d'aéronef en raison de son poids et des contraintes auxquelles il soumet les parties de l'aéronef sur lesquelles les éoliennes sont fixées, mais également du fait que la génération d'électricité dépend alors directement de la vitesse de déplacement de l'aéronef et de son inclinaison par rapport au sol, ce qui ne permet pas de garantir une source d'énergie électrique fiable en toutes circonstances. II a également été proposé, notamment d'utiliser une pile à combustible comme unité d'urgence. Toutefois, les piles à combustible ont un temps de démarrage important, en ce qu'elles doivent atteindre leur température de fonctionnement pour délivrer leur quantité nominale d'électricité. Les piles à combustible nécessitent ainsi conventionneilement un préchauffage afin de les amener à leur température de fonctionnement. It has already been proposed to integrate a wind turbine system in an aircraft structure, for example in its wings, these wind turbines can be deployed in flight and thus generate electricity. However, it is understood that such a system is not only very complex to integrate into an aircraft structure because of its weight and the constraints to which it submits the parts of the aircraft on which the wind turbines are fixed, but also the As a result, the generation of electricity then depends directly on the speed of movement of the aircraft and its inclination with respect to the ground, which does not guarantee a source of reliable electrical power in all circumstances. It has also been proposed, in particular to use a fuel cell as an emergency unit. However, fuel cells have a significant start-up time, in that they must reach their operating temperature to deliver their nominal amount of electricity. Fuel cells thus conventionally require preheating to bring them to their operating temperature.

Afin d'éviter un tel préchauffage, le document WO 2006/094743 propose de maintenir la pile à combustible dans une plage de température donnée, par exemple supérieure à 5°C, afin d'assurer sa disponibilité rapide, soit en la plaçant dans un milieu ayant une température suffisamment élevée, par exemple la cabine d'un aéronef, soit au moyen d'un système de chauffage dédié à la pile à combustible, pouvant par exemple également réaliser son refroidissement lorsqu'elle fonctionne. In order to avoid such preheating, the document WO 2006/094743 proposes to maintain the fuel cell in a given temperature range, for example greater than 5 ° C., in order to ensure its rapid availability, either by placing it in a medium having a sufficiently high temperature, for example the cabin of an aircraft, or by means of a heating system dedicated to the fuel cell, for example also able to achieve cooling when operating.

Le document EP 2658022 propose de maintenir la pile à combustible dans une plage de température donnée soit en pilotant sa mise en fonctionnement par intermittence de manière à ce que la réaction exothermique qu'elle produit dégage la chaleur nécessaire à son maintien à une température prédéfinie, ou bien en utilisant une résistance chauffante défiée à ce maintien en température de la pile à combustible. De telles solutions sont cependant adaptées uniquement à des piles à combustible ayant des basses températures de fonctionnement, et nécessite un système de chauffage dédié ce qui est problématique notamment en termes de poids et d'encombrement. The document EP 2658022 proposes to keep the fuel cell in a given temperature range by controlling its operation intermittently so that the exothermic reaction it produces releases the heat necessary to maintain it at a predetermined temperature, or by using a heating resistor challenged to maintain the temperature of the fuel cell. Such solutions, however, are suitable only for fuel cells having low operating temperatures, and requires a dedicated heating system which is problematic in particular in terms of weight and bulk.

PRESENTATION DE L'INVENTION PRESENTATION OF THE INVENTION

La présente invention vise à répondre au moins en partie aux problématiques précitées. The present invention aims to respond at least in part to the aforementioned problems.

A cet effet, la présente invention propose un système de génération d'énergie électrique d'un aéronef, comprenant For this purpose, the present invention proposes a system for generating electrical energy from an aircraft, comprising

- une source d'énergie primaire,  - a source of primary energy,

- une source d'énergie électrique auxiliaire,  - a source of auxiliary electrical energy,

- une source d'énergie électrique d'urgence, - a source of emergency electrical energy,

caractérisé en ce que lesdites source d'énergie électrique auxiliaire et source d'énergie électrique d'urgence comprennent chacune une pile à combustible, respectivement pile auxiliaire et pile d'urgence, et en ce que ledit système comprend des moyens pour prélever de la chaleur dégagée par la pile auxiliaire lors de son fonctionnement de manière à chauffer la pile d'urgence. characterized in that said auxiliary power source and emergency power source each comprise a fuel cell, respectively an auxiliary battery and an emergency battery, and that said system comprises means for collecting heat released by the auxiliary battery during its operation so as to heat the emergency battery.

Selon un mode de réalisation particulier, lesdits moyens pour prélever de la chaleur dégagée par la pile auxiliaire lors de son fonctionnement de manière à chauffer la pile d'urgence comprennent un circuit de refroidissement commun reliant lesdites piles auxiliaire et d'urgence, configuré de manière à maintenir la pile d'urgence à une température sensiblement égale à sa température de fonctionnement par dissipation thermique de la chaleur générée par la pile auxiliaire lors du fonctionnement de la pile auxiliaire. Selon un mode de réalisation particulier, le système comprend en outre un contrôleur adapté pour détecter un dysfonctionnement d'une source d'énergie électrique primaire et/ou de la source d'énergie électrique auxiliaire, et pour commander la mise en fonctionnement de la source d'énergie électrique d'urgence en cas de défaillance d'une source d'énergie électrique primaire et/ou de la source d'énergie électrique auxiliaire. According to a particular embodiment, said means for taking the heat released by the auxiliary battery during its operation so as to heat the emergency battery comprises a common cooling circuit connecting said auxiliary and emergency batteries, configured in a manner maintaining the emergency battery at a temperature substantially equal to its operating temperature by heat dissipation of the heat generated by the auxiliary battery during operation of the auxiliary battery. According to a particular embodiment, the system further comprises a controller adapted to detect a malfunction of a source of primary electrical energy and / or the source of auxiliary electrical energy, and to control the operation of the source emergency power supply in the event of failure of a primary power source and / or auxiliary power source.

Selon un mode de réalisation particulier, le système comprend en outre un contrôleur configuré de manière à réaliser un test de la pile d'urgence afin de contrôler sa température. In a particular embodiment, the system further comprises a controller configured to perform a test of the emergency battery to control its temperature.

Le système comprend en outre typiquement un contrôleur configuré de manière à piloter la pile auxiliaire et le circuit de refroidissement de manière à maintenir la pile d'urgence à une température comprise entre 110°C et 180°C lors du fonctionnement de la pile auxiliaire, ladite pile auxiliaire et la pile d'urgence ayant chacune une température de fonctionnement comprise entre 110°C et 220°C. The system further typically comprises a controller configured to drive the auxiliary battery and the cooling circuit so as to maintain the emergency battery at a temperature between 110 ° C and 180 ° C during operation of the auxiliary battery, said auxiliary battery and the emergency battery each having an operating temperature of between 110 ° C and 220 ° C.

La pile auxiliaire et la pile d'urgence sont par exemple des piles à combustible à membrane d'échange de protons à haute température.  The auxiliary battery and the emergency battery are, for example, high temperature proton exchange membrane fuel cells.

Le circuit de refroidissement est par exemple configuré de manière à, lorsque la pile d'urgence n'est pas en fonctionnement, faire passer le fluide circulant dans le circuit de refroidissement successivement dans un dissipateur thermique de la pile auxiliaire, dans un dissipateur thermique de la pile d'urgence, puis dans un radiateur. The cooling circuit is, for example, configured so that, when the emergency battery is not in operation, the fluid circulating in the cooling circuit is successively passed through a heat sink of the auxiliary battery, in a heat sink of the emergency battery, then in a radiator.

Le circuit de refroidissement peut alors également être configuré de manière à, lorsque la pile d'urgence est en fonctionnement, isoler les échangeurs thermiques l'un par rapport à l'autre en fonctionnement d'urgence de manière à avoir deux sous-circuits de refroidissement distincts réalisant chacun le refroidissement de l'une des piles auxiliaire et d'urgence. La pile d'urgence est typiquement associée à un générateur d'hydrogène solide à base d'hydrure, couplé à un caisson permettant le conditionnement et la distribution de l'hydrogène issu du générateur d'hydrogène à la pile d'urgence, et à un générateur d'oxygène solide couplé à un caisson permettant le conditionnement et la distribution de l'oxygène issu du générateur d'oxygène solide à la pile d'urgence. The cooling circuit can then also be configured so that, when the emergency battery is in operation, isolating the heat exchangers relative to each other in emergency operation so as to have two sub-circuits of separate cooling each performing the cooling of one of the auxiliary and emergency batteries. The emergency stack is typically associated with a hydride-based solid hydrogen generator, coupled to a well for packaging and dispensing hydrogen from the hydrogen generator to the emergency stack, and a solid oxygen generator coupled to a chamber for conditioning and dispensing oxygen from the solid oxygen generator to the emergency stack.

L'invention concerne également un aéronef muni d'un système de génération électrique tel que présenté. The invention also relates to an aircraft equipped with an electric generating system as presented.

L'invention concerne en outre un procédé de génération d'énergie électrique dans un aéronef au moyen d'une source d'énergie primaire, d'une source d'énergie électrique auxiliaire et d'une source d'énergie électrique d'urgence, dans lequel lesdites sources d'énergie électrique auxiliaire et d'urgence comprennent chacune une pile à combustible, respectivement pile auxiliaire et pile d'urgence, ledit procédé étant caractérisé en ce que le fonctionnement de la pile auxiliaire dégage de la chaleur qui est prélevée et utilisée de manière à chauffer la pile d'urgence. The invention further relates to a method of generating electrical energy in an aircraft by means of a primary energy source, an auxiliary power source and an emergency power source, wherein said auxiliary and emergency power sources each comprise a fuel cell, respectively an auxiliary battery and an emergency battery, said method being characterized in that the operation of the auxiliary battery releases heat which is removed and used to heat the emergency battery.

La pile d'urgence est avantageusement maintenue à une température sensiblement égale à sa température de fonctionnement au moyen d'un circuit de refroidissement commun avec la pile auxiliaire. La pile d'urgence est avantageusement actionnée en cas de défaillance d'une source d'énergie électrique primaire et/ou de la source d'énergie électrique auxiliaire. The emergency battery is advantageously maintained at a temperature substantially equal to its operating temperature by means of a common cooling circuit with the auxiliary battery. The emergency battery is advantageously actuated in the event of failure of a source of primary electrical energy and / or of the source of auxiliary electrical energy.

Selon un mode de réalisation particulier, lors de l'application d'une commande, un contrôleur réalise un test de la pile d'urgence afin de contrôler sa température et sa disponibilité. Selon un mode de réalisation particulier, lors du fonctionnement de la pile auxiliaire, la pile d'urgence est maintenue à une température comprise entre 110°C et 180°C, ladite pile auxiliaire et la pile d'urgence ayant chacune une température de fonctionnement comprise entre 110°C et 220°C. La pile auxiliaire et la pile d'urgence sont par exemple des piles à combustible à membrane d'échange de protons à haute température. According to a particular embodiment, during the application of a command, a controller performs a test of the emergency battery to control its temperature and availability. According to a particular embodiment, during operation of the auxiliary battery, the emergency battery is maintained at a temperature of between 110 ° C. and 180 ° C., said auxiliary battery and the emergency battery each having an operating temperature. between 110 ° C and 220 ° C. The auxiliary battery and the emergency battery are, for example, high temperature proton exchange membrane fuel cells.

PRESENTATION DES FIGURES PRESENTATION OF FIGURES

D'autres caractéristiques, buts et avantages de l'invention ressortiront de la description qui suit, qui est purement illustrative et non limitative, et qui doit être lue en regard de la figure 1 annexée qui représente schématiquement un système de génération d'énergie électrique selon un aspect de l'invention. Other features, objects and advantages of the invention will emerge from the description which follows, which is purely illustrative and nonlimiting, and which should be read with reference to the appended FIG. 1 which schematically represents an electrical energy generation system. according to one aspect of the invention.

DESCRIPTION DETAILLEE DETAILED DESCRIPTION

La figure 1 représente schématiquement un système 1 de génération d'énergie électrique selon un aspect de l'invention, comprenant : FIG. 1 schematically represents a system 1 for generating electrical energy according to one aspect of the invention, comprising:

- une source d'énergie électrique primaire P,  a source of primary electrical energy P,

- une source d'énergie électrique auxiliaire APU,  an auxiliary power source APU,

- une source d'énergie électrique d'urgence EPU. La source d'énergie électrique primaire P peut être de divers types ; elle comprend typiquement des batteries et des génératrices.  - an emergency power source EPU. The source of primary electrical energy P can be of various types; it typically includes batteries and generators.

La source d'énergie électrique auxiliaire APU comprend une pile à combustible que l'on désigne par pile auxiliaire 20, associée à un réservoir d'hydrogène 22 contenant de l'hydrogène sous forme solide, liquide ou gazeux, et à un compresseur 24 muni d'un moteur 26. Le réservoir d'hydrogène 22 est équipé d'une vanne 23 de manière à réaliser sélectivement l'alimentation en hydrogène de la pile à combustible 20. The APU auxiliary power source comprises a fuel cell which is designated by auxiliary battery 20, associated with a hydrogen reservoir 22 containing hydrogen in solid, liquid or gaseous form, and a compressor 24 provided with of an engine 26. The hydrogen reservoir 22 is equipped with a valve 23 so as to selectively supply the hydrogen supply of the fuel cell 20.

Le compresseur 24 et le moteur 26 sont adaptés pour réaliser sélectivement une alimentation en oxygène de la pile à combustible 20.  The compressor 24 and the motor 26 are adapted to selectively provide oxygen supply to the fuel cell 20.

La source d'énergie électrique d'urgence EPU comprend une pile à combustible que l'on désigne par pile d'urgence 30, associée à un générateur d'hydrogène solide 32 et à un générateur d'oxygène solide 34. The emergency power source EPU comprises a fuel cell that is designated emergency stack 30, associated with a solid hydrogen generator 32 and a solid oxygen generator 34.

Le générateur d'hydrogène solide 32 et le générateur d'oxygène solide 34 sont reliés à la pile d'urgence 30 par l'intermédiaire de vannes, respectivement 33 et 35.  The solid hydrogen generator 32 and the solid oxygen generator 34 are connected to the emergency stack 30 via valves 33 and 35, respectively.

La source d'énergie électrique d'urgence EPU comprend en outre une batterie d'urgence 36, adaptée notamment pour alimenter les vannes 33 et 35.  The emergency power source EPU further comprises an emergency battery 36, particularly adapted to supply the valves 33 and 35.

La pile auxiliaire 20 et la pile d'urgence 30 présentent chacune un échangeur thermique, respectivement 42 et 43, reliés à un circuit de refroidissement 40 muni d'un radiateur 44. The auxiliary battery 20 and the emergency battery 30 each have a heat exchanger, respectively 42 and 43, connected to a cooling circuit 40 provided with a radiator 44.

L'échangeur thermique 42 de la pile auxiliaire 20 est configuré de manière à réaliser un échange thermique entre un fluide circulant dans le circuit de refroidissement 40 et la pile auxiliaire 20. The heat exchanger 42 of the auxiliary battery 20 is configured to perform a heat exchange between a fluid flowing in the cooling circuit 40 and the auxiliary battery 20.

De la même manière, l'échangeur thermique 40 de la pile d'urgence 30 est configuré de manière à réaliser un échange thermique entre le fluide circulant dans le circuit de refroidissement 40 et la pile d'urgence 30. Le radiateur 44 est configuré de manière à réaliser un échange thermique entre le fluide circulant dans le circuit de refroidissement 40 et un milieu externe, afin de dissiper la chaleur accumulée par le fluide du circuit de refroidissement 40. In the same way, the heat exchanger 40 of the emergency stack 30 is configured to perform a heat exchange between the fluid flowing in the cooling circuit 40 and the emergency stack 30. The radiator 44 is configured to in order to achieve a heat exchange between the fluid flowing in the cooling circuit 40 and an external medium, in order to dissipate the heat accumulated by the fluid of the cooling circuit 40.

Le fluide circule dans le circuit de refroidissement 40 dans le sens indiqué par les flèches sur la figure 1. Le système 1 tel que présenté comprend en outre un contrôleur 50 optionnel, configuré de manière à contrôler la température et/ou l'état de la pile d'urgence 30, et également de manière à détecter l'état de la source d'énergie électrique primaire P et de la source d'énergie auxiliaire APU. Le contrôleur 50 est avantageusement alimenté par une source d'énergie indépendante, par exemple la batterie d'urgence 36. Il peut être relié à plusieurs sources d'alimentation, de manière à ne pas réduire la charge de la batterie d'urgence 36 en fonctionnement normal. The fluid flows in the cooling circuit 40 in the direction indicated by the arrows in FIG. The system 1 as presented further comprises an optional controller 50, configured to control the temperature and / or condition of the emergency stack 30, and also to detect the state of the power source. primary electric P and APU auxiliary power source. The controller 50 is advantageously powered by an independent power source, for example the emergency battery 36. It can be connected to several power sources, so as not to reduce the load of the emergency battery 36 by normal running.

On décrit ensuite un exemple de fonctionnement que l'on qualifie de fonctionnement « normal » du système, c'est-à-dire sans défaillance électrique. La source d'énergie électrique primaire P fournit de l'électricité, alimentant notamment le compresseur 24, le moteur 26 ainsi que le réservoir d'hydrogène 22 et la vanne 23 associée. An example of operation described as "normal" operation of the system, that is to say without electrical failure, is described below. The source of primary electrical energy P provides electricity, including the compressor 24, the motor 26 as well as the hydrogen reservoir 22 and the associated valve 23.

La pile auxiliaire 20 est ainsi alimentée en hydrogène et en oxygène ; elle est actionnée, et délivre de l'électricité.  The auxiliary battery 20 is thus supplied with hydrogen and oxygen; it is powered, and delivers electricity.

Le système 1 délivre ainsi de l'énergie électrique, et peut ainsi réaliser par exemple l'alimentation électrique d'un aéronef. The system 1 thus delivers electrical energy, and can thus achieve for example the power supply of an aircraft.

La pile d'urgence 30 n'est quant à elle pas en fonctionnement ; les vannes 32 et 33 permettant son alimentation en hydrogène et en oxygène sont fermées. The emergency stack 30 is not in operation; the valves 32 and 33 for its supply of hydrogen and oxygen are closed.

Lors du fonctionnement de la pile auxiliaire 20, cette dernière dégage de la chaleur, qui est transférée au fluide circulant dans le circuit de refroidissement 40 grâce à l'échangeur thermique 42. Le fluide chauffé circule dans le circuit de refroidissement 40 dans le sens repéré par les flèches sur la figure 1 ; une fois sorti de l'échangeur thermique 42 de la pile auxiliaire 20, il passe par l'échangeur thermique 43 de la pile d'urgence 30. La pile d'urgence 30 n'étant pas en fonctionnement, elle est à température ambiante. L'échangeur thermique 43 transfère ainsi de la chaleur du fluide du circuit de refroidissement 40 vers la pile d'urgence 30, dont la température augmente jusqu'à atteindre une valeur prédéfinie, en fonction notamment de la température de fonctionnement de la pile auxiliaire 20. During the operation of the auxiliary battery 20, the latter releases heat, which is transferred to the fluid flowing in the cooling circuit 40 through the heat exchanger 42. The heated fluid flows in the cooling circuit 40 in the direction indicated. by the arrows in Figure 1; once out of the heat exchanger 42 of the auxiliary battery 20, it passes through the heat exchanger 43 of the emergency stack 30. The emergency battery 30 is not in operation, it is at room temperature. The heat exchanger 43 thus transfers heat from the fluid of the cooling circuit 40 to the emergency stack 30, the temperature of which increases until a predetermined value is reached, depending in particular on the operating temperature of the auxiliary battery 20 .

Le fluide du circuit de refroidissement 40, passe ensuite par le radiateur 44, qui transfère le reliquat de la chaleur transmise par la pile auxiliaire 20 vers le milieu ambiant avant que le fluide ne passe à nouveau par l'échangeur thermique 42 de la pile auxiliaire 20.  The fluid of the cooling circuit 40, then passes through the radiator 44, which transfers the remainder of the heat transmitted by the auxiliary battery 20 to the ambient medium before the fluid passes again through the heat exchanger 42 of the auxiliary battery 20.

En fonctionnement normal, la pile d'urgence 30 n'est donc pas mise en fonctionnement, mais est maintenue à une température prédéfinie, qui est avantageusement choisie de manière à être sensiblement égale, ou à tout le moins proche de sa température de fonctionnement. In normal operation, the emergency battery 30 is not put into operation, but is maintained at a predetermined temperature, which is advantageously chosen to be substantially equal to, or at least close to its operating temperature.

A titre d'exemple en considérant que la pile d'urgence 30 soit une pile à combustible à membrane d'échange de protons à haute température, ayant une température de fonctionnement comprise entre 110°C et 220°C, lors du fonctionnement normal du système, la pile d'urgence 30 est alors typiquement maintenue à une température comprise entre 110°C et 180°C. La pile auxiliaire 20 peut également être une pile à combustible à membrane d'échange de protons à haute température. Le contrôleur 50 réalise alors le pilotage de la pile auxiliaire 20 et du circuit de refroidissement 40 pour assurer le maintien dans cette plage de températures. By way of example, considering that the emergency battery 30 is a high-temperature proton exchange membrane fuel cell having an operating temperature of between 110 ° C. and 220 ° C., during normal operation of the system, the emergency stack 30 is then typically maintained at a temperature between 110 ° C and 180 ° C. The auxiliary battery 20 may also be a high temperature proton exchange membrane fuel cell. The controller 50 then directs the auxiliary battery 20 and the cooling circuit 40 to maintain in this temperature range.

On décrit ci-après le fonctionnement en cas de défaillance électrique, que l'on qualifie de fonctionnement « d'urgence », intervenant lors du fonctionnement normal. En fonctionnement d'urgence, la source d'énergie électrique primaire P et/ou la source d'énergie électrique auxiliaire APU cessent de fonctionner et cessent donc de produire de l'électricité. The following describes the operation in case of electrical failure, which is called "emergency" operation, involved during normal operation. In emergency operation, the primary power source P and / or the auxiliary power source APU stop working and therefore stop producing electricity.

Au cours d'un fonctionnement normal du système 1 tel que décrit précédemment, le contrôleur 50 détecte un dysfonctionnement de la source d'énergie électrique primaire P et/ou de la source d'énergie électrique auxiliaire APU et commande la mise en fonctionnement de la pile d'urgence 30. La batterie 36 alimente alors les vannes 33 et 35, de manière à alimenter la pile d'urgence 30 en hydrogène et en oxygène, ce qui déclenche sa mise en fonctionnement de sorte qu'elle génère de l'électricité afin de compenser tout ou partie du manque d'électricité résultant de la défaillance de la source d'énergie électrique primaire P et/ou de la source d'énergie électrique auxiliaire APU.  During normal operation of the system 1 as described above, the controller 50 detects a malfunction of the primary power source P and / or the auxiliary power source APU and controls the start-up of the emergency battery 30. The battery 36 then feeds the valves 33 and 35, so as to supply the emergency battery 30 with hydrogen and oxygen, which triggers its operation so that it generates electricity to compensate for all or part of the lack of electricity resulting from the failure of the primary power source P and / or the auxiliary power source APU.

La pile d'urgence 30 a été amenée et maintenue à une température prédéfinie, avantageusement choisie de manière à être sensiblement égale, ou à tout le moins proche de sa température de fonctionnement ; sa mise en fonctionnement peut ainsi être réalisée immédiatement, sans nécessiter une étape préalable de préchauffage. The emergency battery 30 has been brought and maintained at a predetermined temperature, advantageously chosen so as to be substantially equal to, or at least close to, its operating temperature; it can be put into operation immediately without requiring a preheating step.

En fonctionnement d'urgence, la pile auxiliaire cesse de fonctionner de manière nominale, et cesse donc de générer de la chaleur, ou à tout le moins en génère moins de chaleur qu'en fonctionnement normal. In emergency operation, the auxiliary battery stops operating in a nominal way, and therefore stops generating heat, or at least generates less heat than in normal operation.

La chaleur dégagée par la pile auxiliaire 20 captée par le fluide du circuit de refroidissement 40 et qui passe par l'échangeur thermique 43 de la pile d'urgence 30 est donc réduite par rapport au fonctionnement normal décrit précédemment, et ne nuit pas au fonctionnement de la pile d'urgence 30.  The heat released by the auxiliary battery 20 picked up by the fluid of the cooling circuit 40 and which passes through the heat exchanger 43 of the emergency stack 30 is therefore reduced compared to the normal operation described above, and does not harm the operation. emergency stack 30.

De manière optionnelle, le contrôleur 50 peut être configuré de manière à isoler les échangeurs thermiques 42 et 43 l'un par rapport à l'autre en fonctionnement d'urgence de manière à avoir deux sous-circuits de refroidissement distincts réalisant chacun le refroidissement de l'une des piles à combustible 20 et 30. Optionally, the controller 50 may be configured to isolate the heat exchangers 42 and 43 from one another in emergency operation so as to have two sub-circuits of the same. separate cooling each cooling one of the fuel cells 20 and 30.

Le débit de fluide circulant dans le circuit de refroidissement 40 peut également être modifié en fonction du mode de fonctionnement afin d'éviter tout risque de surchauffe des piles à combustible 20 et 30.  The flow rate of fluid flowing in the cooling circuit 40 can also be modified depending on the operating mode in order to avoid any risk of overheating of the fuel cells 20 and 30.

Le générateur d'hydrogène solide 32 est typiquement un générateur à base d'hydrure, couplé à un caisson permettant le conditionnement et la distribution de l'hydrogène issu du générateur d'hydrogène 32. The solid hydrogen generator 32 is typically a hydride-based generator, coupled to a box for packaging and dispensing hydrogen from the hydrogen generator 32.

Le générateur d'oxygène solide 34 est également typiquement couplé à un caisson permettant le conditionnement et la distribution de l'oxygène issu du générateur d'oxygène 34. The solid oxygen generator 34 is also typically coupled to a box for conditioning and dispensing oxygen from the oxygen generator 34.

Les vannes 33 et 35 sont pilotées de manière à délivrer les quantités adaptées d'oxygène et d'hydrogène ; avantageusement les quantités stœchiométriques pour assurer le bon fonctionnement de la pile d'urgence 30.  The valves 33 and 35 are controlled so as to deliver the appropriate amounts of oxygen and hydrogen; advantageously the stoichiometric amounts to ensure the proper functioning of the emergency stack 30.

De tels générateurs d'hydrogène 32 et d'oxygène 34 permettent de minimiser la taille et le poids du stockage d'hydrogène et d'oxygène nécessaire au fonctionnement de la pile d'urgence 30. Such hydrogen 32 and oxygen 34 generators make it possible to minimize the size and the weight of the storage of hydrogen and oxygen necessary for the operation of the emergency stack 30.

Le système 1 tel que présenté peut par exemple être utilisé pour assurer l'alimentation électrique d'un aéronef. The system 1 as presented can for example be used to provide power to an aircraft.

Afin de s'assurer de la disponibilité des sources d'alimentation en énergie électrique, le contrôleur 50 peut par exemple effectuer des tests de disponibilité de la source d'énergie électrique d'urgence EPU avant le décollage de l'aéronef, ou à intervalles réguliers, par exemple dès lors que la source d'énergie électrique primaire P et/ou la source d'énergie électrique auxiliaire APU sont en fonctionnement. Le système proposé permet ainsi d'assurer une alimentation électrique d'urgence pouvant être mise en fonctionnement de manière très rapide, par exemple dans un délai de 3 à 8 secondes, tout en minimisant le poids et l'encombrement du système. In order to ensure the availability of electric power supply sources, the controller 50 may, for example, carry out availability tests of the emergency electrical power source EPU before take-off of the aircraft, or at intervals for example, when the primary power source P and / or the auxiliary power source APU are in operation. The proposed system thus provides an emergency power supply that can be put into operation very quickly, for example within 3 to 8 seconds, while minimizing the weight and bulk of the system.

Le système proposé optimise la gestion de la chaleur dégagée par la source d'énergie électrique auxiliaire APU, et permet de s'affranchir d'un dispositif de chauffage additionnel dédié à la pile d'urgence 30, en prélevant la chaleur dégagée par la pile auxiliaire pour réaliser le chauffage de la pile d'urgence. The proposed system optimizes the management of the heat released by the APU auxiliary power source, and makes it possible to dispense with an additional heating device dedicated to the emergency battery 30, by taking the heat released by the battery. auxiliary for heating the emergency battery.

Dans le cas de l'utilisation d'un tel système sur un aéronef, le système d'alimentation proposé est en outre indépendant des conditions de vol, et notamment de l'altitude ou de l'inclinaison de l'aéronef. In the case of the use of such a system on an aircraft, the proposed power system is further independent of the flight conditions, including the altitude or inclination of the aircraft.

Claims

Revendications claims 1. Système (1) de génération d'énergie électrique d'un aéronef, comprenant 1. System (1) for generating electrical energy from an aircraft, comprising - une source d'énergie primaire (P), a primary energy source (P), - une source d'énergie électrique auxiliaire (APU),  - a source of auxiliary electrical energy (APU), - une source d'énergie électrique d'urgence (EPU),  - an emergency power source (EPU), caractérisé en ce que lesdites source d'énergie électrique auxiliaire (APU) et source d'énergie électrique d'urgence (EPU) comprennent chacune une pile à combustible, respectivement pile auxiliaire (20) et pile d'urgence (30), et en ce que ledit système (1) comprend des moyens (40) pour prélever de la chaleur dégagée par la pile auxiliaire (20) lors de son fonctionnement de manière à chauffer la pile d'urgence (30). characterized in that said auxiliary power source (APU) and emergency power source (EPU) each comprise a fuel cell, respectively an auxiliary battery (20) and an emergency battery (30), and said system (1) comprises means (40) for taking heat from the auxiliary battery (20) during operation to heat the emergency battery (30). 2. Système (1) selon la revendication 1, dans lequel lesdits moyens pour prélever de la chaleur dégagée par la pile auxiliaire (20) lors de son fonctionnement de manière à chauffer la pile d'urgence (30) comprennent un circuit de refroidissement (40) commun reliant lesdites piles auxiliaire (20) et d'urgence (30), configuré de manière à maintenir la pile d'urgence (30) à une température sensiblement égale à sa température de fonctionnement par dissipation thermique de la chaleur générée par la pile auxiliaire (20) lors du fonctionnement de la pile auxiliaire (20). The system (1) according to claim 1, wherein said means for drawing heat from the auxiliary battery (20) during operation to heat the emergency battery (30) comprises a cooling circuit ( 40) communicating said auxiliary (20) and emergency (30) cells, configured to maintain the emergency battery (30) at a temperature substantially equal to its operating temperature by heat dissipation of the heat generated by the auxiliary battery (20) during operation of the auxiliary battery (20). 3. Système (1) selon l'une des revendications 1 ou 2, comprenant en outre un contrôleur (50) adapté pour détecter un dysfonctionnement d'une source d'énergie électrique primaire (P) et/ou de la source d'énergie électrique auxiliaire (APU), et pour commander la mise en fonctionnement de la source d'énergie électrique d'urgence (EPU). 3. System (1) according to one of claims 1 or 2, further comprising a controller (50) adapted to detect a malfunction of a source of primary electrical energy (P) and / or the energy source auxiliary power supply (APU), and to control the operation of the Emergency Power Source (EPU). 4. Système (1) selon l'une des revendications 1 à 3, comprenant en outre un contrôleur (50) configuré de manière à réaliser un test de la pile d'urgence (30) afin de contrôler sa température. 4. System (1) according to one of claims 1 to 3, further comprising a controller (50) configured to perform a test of the emergency battery (30) to control its temperature. 5. Système (1) selon l'une des revendications 1 à 4, comprenant en outre un contrôleur (50) pilotant la pile auxiliaire (20) et le circuit de refroidissement (40) de manière à maintenir la pile d'urgence (30) à une température comprise entre 110°C et 180°C lors du fonctionnement de la pile auxiliaire (20), ladite pile auxiliaire (20) et la pile d'urgence (30) ayant chacune une température de fonctionnement comprise entre 110°C et 220°C. 5. System (1) according to one of claims 1 to 4, further comprising a controller (50) driving the auxiliary battery (20) and the cooling circuit (40) so as to maintain the emergency battery (30). ) at a temperature between 110 ° C and 180 ° C during operation of the auxiliary battery (20), said auxiliary battery (20) and the emergency battery (30) each having an operating temperature of between 110 ° C and 220 ° C. 6. Système (1) selon l'une des revendications 1 à 5, dans lequel ledit circuit de refroidissement (40) est configuré de manière à, lorsque la pile d'urgence (30) n'est pas en fonctionnement, faire passer le fluide circulant dans le circuit de refroidissement (40) successivement dans un dissipateur thermique (42) de la pile auxiliaire (20), dans un dissipateur thermique (43) de la pile d'urgence (30), puis dans un radiateur (44). 6. System (1) according to one of claims 1 to 5, wherein said cooling circuit (40) is configured so that, when the emergency stack (30) is not in operation, pass the fluid circulating in the cooling circuit (40) successively in a heat sink (42) of the auxiliary battery (20), in a heat sink (43) of the emergency battery (30), then in a radiator (44) . 7. Système (1) selon la revendication 6, dans lequel ledit circuit de refroidissement (40) est configuré de manière à, lorsque la pile d'urgence (30) est en fonctionnement, isoler les échangeurs thermiques (42) et (43) l'un par rapport à l'autre en fonctionnement d'urgence de manière à avoir deux sous-circuits de refroidissement distincts réalisant chacun le refroidissement de l'une des piles auxiliaire (20) et d'urgence (30). 7. System (1) according to claim 6, wherein said cooling circuit (40) is configured so that, when the emergency stack (30) is in operation, isolate the heat exchangers (42) and (43) relative to each other in emergency operation so as to have two separate cooling subcircuits each cooling one of the auxiliary battery (20) and emergency (30). 8. Système (1) selon l'une des revendications 1 à 7, dans lequel la pile d'urgence (30) est associée à un générateur d'hydrogène solide (32) à base d'hydrure, couplé à un caisson permettant le conditionnement et la distribution de l'hydrogène issu du générateur d'hydrogène (32) à la pile d'urgence (30), et à un générateur d'oxygène solide (34) couplé à un caisson permettant le conditionnement et la distribution de l'oxygène issu du générateur d'oxygène solide (34) à la pile d'urgence (30). 8. System (1) according to one of claims 1 to 7, wherein the emergency stack (30) is associated with a hydride-based solid hydrogen generator (32), coupled to a housing allowing the conditioning and dispensing hydrogen from the hydrogen generator (32) to the emergency stack (30), and a solid oxygen generator (34) coupled to a box for packaging and dispensing oxygen from the solid oxygen generator (34) to the emergency stack (30). 9. Procédé de génération d'énergie électrique dans un aéronef au moyen d'une source d'énergie primaire (P), d'une source d'énergie électrique auxiliaire (APU) et d'une source d'énergie électrique d'urgence (EPU), dans lequel lesdites sources d'énergie électrique auxiliaire (APU) et d'urgence (EPU) comprennent chacune une pile à combustible, respectivement pile auxiliaire (20) et pile d'urgence (30), ledit procédé étant caractérisé en ce que le fonctionnement de la pile auxiliaire (20) dégage de la chaleur qui est prélevée et utilisée de manière à chauffer la pile d'urgence (30). 9. A method of generating electrical energy in an aircraft using a primary energy source (P), an auxiliary electrical power source (APU) and an emergency power source (EPU), wherein said auxiliary power supply (APU) and emergency power sources (EPU) each comprise a fuel cell, respectively an auxiliary battery (20) and an emergency battery (30), said method being characterized by the operation of the auxiliary battery (20) releases heat which is drawn off and used to heat the emergency battery (30). 10. Procédé selon la revendication 9, dans lequel la pile d'urgence (30) est maintenue à une température sensiblement égale à sa température de fonctionnement au moyen d'un circuit de refroidissement (40) commun avec la pile auxiliaire (20). The method of claim 9, wherein the emergency stack (30) is maintained at a temperature substantially equal to its operating temperature by means of a cooling circuit (40) common with the auxiliary battery (20). 11. Procédé selon l'une des revendications 9 ou 10, dans lequel ladite pile d'urgence (30) est actionnée en cas de défaillance d'une source d'énergie électrique primaire (P) et/ou de la source d'énergie électrique auxiliaire (APU). The method according to one of claims 9 or 10, wherein said emergency stack (30) is actuated in the event of failure of a source of primary electrical energy (P) and / or of the energy source. auxiliary power supply (APU). 12. Procédé selon l'une des revendications 9 à 11, dans lequel lors de l'application d'une commande, un contrôleur (50) réalise un test de la pile d'urgence (30) afin de contrôler sa température et sa disponibilité 12. Method according to one of claims 9 to 11, wherein during the application of a command, a controller (50) performs a test of the emergency stack (30) to control its temperature and availability. 13. Procédé selon l'une des revendications 9 à 12, dans lequel lors du fonctionnement de la pile auxiliaire (20), la pile d'urgence (30) est maintenue à une température comprise entre 110°C et 180°C, ladite pile auxiliaire (20) et la pile d'urgence (30) ayant chacune une température de fonctionnement comprise entre 110°C et 220°C. 13. Method according to one of claims 9 to 12, wherein during operation of the auxiliary battery (20), the emergency battery (30) is maintained at a temperature between 110 ° C and 180 ° C, said auxiliary battery (20) and the emergency battery (30) each having an operating temperature of between 110 ° C and 220 ° C.
PCT/FR2015/050006 2014-01-10 2015-01-05 Emergency electrical generator of an aircraft, with a quick-starting fuel cell WO2015104487A1 (en)

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FR1450188A FR3016345B1 (en) 2014-01-10 2014-01-10 EMERGENCY POWER GENERATOR WITH FAST STARTER FUEL CELL
FR1450188 2014-01-10

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