WO2022049335A1 - Cryogenic fuel circuit with recondensation - Google Patents

Cryogenic fuel circuit with recondensation Download PDF

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Publication number
WO2022049335A1
WO2022049335A1 PCT/FR2021/051484 FR2021051484W WO2022049335A1 WO 2022049335 A1 WO2022049335 A1 WO 2022049335A1 FR 2021051484 W FR2021051484 W FR 2021051484W WO 2022049335 A1 WO2022049335 A1 WO 2022049335A1
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WO
WIPO (PCT)
Prior art keywords
fuel
gaseous
liquid
gaseous fuel
circuit
Prior art date
Application number
PCT/FR2021/051484
Other languages
French (fr)
Inventor
Hugo Pierre Mohamed JOUAN
Samer MAALOUF
Original Assignee
Safran
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Publication date
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Publication of WO2022049335A1 publication Critical patent/WO2022049335A1/en

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
    • F02C3/22—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F02C9/40—Control of fuel supply specially adapted to the use of a special fuel or a plurality of fuels
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/213—Heat transfer, e.g. cooling by the provision of a heat exchanger within the cooling circuit
    • 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
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to a cryogenic fuel storage assembly comprising a fuel tank and means for managing the fuel in the gaseous phase in the tank, which results from the evaporation of the liquid fuel.
  • Some aircraft use fuel brought to a very low temperature for their operation, in particular because of a reduced environmental impact compared to fuel at ambient temperature.
  • This cryogenized fuel is stored in a thermally insulated tank to keep the fuel temperature as low as possible.
  • Part of the fuel then evaporates, which means that the fuel is present in the tank in liquid form and in gaseous form.
  • the fuel gradually evaporates, which increases the pressure of gaseous fuel inside the tank.
  • a system for regulating the quantity of gaseous fuel is then provided, in order to limit the pressure in the tank.
  • Such regulation systems comprise for example a heat exchanger through which the gaseous fuel circulates in order to be cooled and thus to condense.
  • the cold source of the heat exchanger is a source external to the device, which complicates the system and weighs down the device on which the system is intended to be mounted.
  • the object of the invention is to propose a storage assembly comprising means for regulating the quantity of gaseous fuel present inside the tank which does not comprise an external cold source.
  • the invention proposes a cryogenic fuel storage assembly for an aircraft turbomachine comprising
  • liquid fuel circuit connecting the tank to components intended to be supplied with fuel in liquid form, the liquid fuel circuit comprising a liquid fuel pressurization pump,
  • a gaseous fuel circuit taking fuel in gaseous form from the tank characterized in that it comprises a heat exchange member supplied by the liquid fuel circuit and by the gaseous fuel circuit, in which the fuel under liquid form coming from the liquid fuel circuit and the fuel in gaseous form coming from the gaseous fuel circuit are capable of exchanging heat to cause at least partial condensation of the gaseous fuel coming from the gaseous fuel circuit.
  • the flow of gaseous fuel is cooled by the liquid fuel.
  • the heat exchange takes place internally, which makes the assembly simpler to integrate into a structure such as that of an aircraft.
  • the heat exchange member comprises a mixing chamber in which the flow of gaseous fuel is injected into the flow of liquid fuel.
  • the gaseous fuel circuit comprises a compressor at the outlet of which the pressure of the gaseous fuel is equal to a predetermined pressure.
  • the pressure of the gaseous fuel at the outlet of the compressor is equal to the pressure of the liquid fuel at the outlet of the liquid fuel pressurization pump.
  • the heat exchange member further comprises a heat exchanger arranged upstream of the mixing chamber and in which the flow of liquid fuel takes heat from the gaseous fuel.
  • the heat exchanger comprises a heat exchanger in which the flow of liquid fuel takes heat from the gaseous fuel.
  • the gaseous fuel circuit comprises a compressor at the outlet of which the pressure of the gaseous fuel is equal to a predetermined pressure greater than the pressure of liquid fuel at the outlet of the pressurization pump.
  • the gaseous fuel circuit comprises an expansion valve arranged downstream of the heat exchanger, at the outlet of which the gaseous fuel pressure is substantially equal to the gaseous fuel pressure in the tank.
  • the invention also proposes an aircraft comprising at least one turbomachine and a storage assembly according to the invention, supplying said at least one turbomachine with liquid fuel.
  • the invention also proposes a method for regulating the quantity of fuel in gaseous form present inside the tank of a storage assembly according to the invention, characterized in that it comprises:
  • the method comprises a stage of compression of the gaseous fuel which is implemented before the stage of condensation.
  • the condensation step consists of a step of mixing the gaseous fuel into the flow of liquid fuel.
  • the condensation step consists of a heat exchange step between the gaseous fuel and the liquid fuel.
  • the method includes a step for expanding the at least partially condensed fuel, which is implemented after the condensation step.
  • FIG. 1 is a schematic representation of a storage unit for cryogenic fuel carrying out the regulation of the quantity of gaseous fuel according to the invention.
  • FIG. 2 is a schematic representation of a storage unit for cryogenic fuel performing the regulation of the quantity of gaseous fuel according to a second embodiment of the invention.
  • FIG. 3 is a schematic representation of an example of a mixing chamber implemented in the second embodiment of the invention.
  • FIG. 4 is a schematic representation of another example of a mixing chamber implemented in the second embodiment of the invention.
  • FIG. 5 is a schematic representation of a storage assembly for cryogenic fuel performing the regulation of the quantity of gaseous fuel according to a variant of the embodiment of the invention represented in FIG. 2.
  • FIG. 1 There is shown in Figure 1 a storage assembly 10 of cryogenized fuel, intended for example to supply the turbine engines of an aircraft.
  • the fuel is brought to a very low temperature, for example close to zero degrees Celsius or much lower in the case of liquid hydrogen, and it is stored in a thermally insulating tank 12 to maintain it at this low temperature.
  • the fuel is present in liquid form and in gaseous form.
  • the liquid fuel supplies the turbomachine(s) of the aircraft via a liquid fuel circuit 14.
  • the liquid fuel circuit 14 comprises a pump 16 for pressurizing the liquid fuel, itself being supplied by pumps feeding 18 arranged inside the reservoir 12.
  • the gaseous fuel pressure in tank 12 is therefore caused to gradually increase.
  • the storage assembly 10 also comprises a gaseous fuel circuit 20 making it possible to regulate the quantity of fuel in gaseous form present inside the tank 12.
  • the gaseous fuel circuit 20 comprises a compressor 22 making it possible to increase the pressure and the temperature of the gaseous fuel in the gaseous fuel circuit 20 and a heat exchange member 24 making it possible to cool this gaseous fuel, to cause its condensation.
  • the heat exchanger 24 is designed so that the gaseous fuel compressed by the compressor 22 exchanges heat with the liquid fuel flowing in the liquid fuel circuit 14.
  • the liquid fuel then takes heat from the gaseous fuel, which causes both a condensation of the gaseous fuel and an increase in the heat of the liquid fuel before this liquid fuel supplies the turbomachine(s).
  • the heat exchange member 24 consists of a heat exchanger with separate flows.
  • the flow of gaseous fuel circulates in the hot part 26 of the heat exchanger 50, the flow of liquid fuel circulates in the cold part 28 of the heat exchanger 50, without mixing with each other.
  • the gaseous fuel having lost heat was cooled and condensed.
  • the gaseous fuel after having condensed, has a higher temperature of approximately 5 K (Kelvin) with respect to the temperature of the liquid fuel present in the tank.
  • the expansion causes the evaporation of part of the liquid fuel which had condensed in the heat exchanger 50, but the temperature of the mixture at two phases is lowered.
  • the temperature and the pressure of the fluid leaving the expansion valve 30 are substantially identical to the temperature and the pressure of the liquid present in the tank.
  • This fluid leaving the expansion valve 30 also contains a small proportion of gas, in particular less than 10%, whereas this fluid was 100% gaseous when it was extracted from the tank. This fluid also being potentially hotter than the temperature of the liquid present in the reservoir.
  • the gaseous fuel and liquid fuel pressures circulating respectively in the gaseous fuel circuit flow 20 and in the liquid fuel circuit 14 are regulated to promote heat exchange, in particular to increase the sub-cooling of the liquid.
  • the pressure of liquid fuel at the outlet of pump 16 is at least equal to 10 bars and the pressure of gaseous fuel at the outlet of compressor 22 is between 4 and 8 bars.
  • FIG. 2 Another embodiment of the invention in which the heat exchange member 24 consists of a mixing chamber 52.
  • the gaseous fuel introduced into the mixing chamber 52 is at a temperature higher than the temperature of the liquid fuel introduced into the mixing chamber 52.
  • the gaseous fuel exchanges heat directly with the liquid fuel with which it is mixed.
  • the pump 16 and the compressor 22 are configured so that the flow rates and pressures of the gaseous fuel and of the liquid fuel allow the condensation of all of the gaseous fuel injected, while avoiding the vaporization of the liquid fuel.
  • the pressure of the gaseous fuel injected into the mixing chamber 52 is preferably identical to the pressure of the liquid fuel.
  • the pressure of the gaseous fuel and the pressure of the liquid fuel injected into the mixing chamber 52 are approximately 10 bars.
  • This pressure value in the case of hydrogen as fuel, makes it possible to incorporate a quantity of gaseous fuel close to 20% of the flow rate of liquid fuel.
  • the temperature of the gaseous fuel increases and becomes higher than the temperature of the liquid fuel at the outlet of the pump 16.
  • the gaseous fuel is then cooled and condensed.
  • all of the fuel is in liquid form, its temperature being higher than the temperature of the liquid fuel at the outlet of the pump 16 and lower than the temperature of the gaseous fuel at the outlet of the compressor 22 .
  • the mixing chamber 52 comprises a tubular conduit 34 through which the liquid fuel circulates and a gas inlet tube 36 which extends partly in the tubular conduit 34.
  • the end 38 of the gas inlet tube 36 which extends into the tubular conduit 34 is through and has a plurality of orifices 40 which allow the gaseous fuel to be mixed as efficiently as possible with the liquid fuel in the form of fines. bubbles 42, thereby promoting heat transfer.
  • Such a mixing chamber 52 is known under the name "gas sparger".
  • the mixing chamber 52 has two coaxial inlets 44, 46, each associated with liquid fuel or gaseous fuel.
  • a section reduction 48 is located downstream of the inlets 44, 46, to cause an acceleration of the liquid fuel and promote the suction of gaseous fuel.
  • Such a mixing chamber 52 is known under the name "jet ejector”.
  • the compressor 22 is designed so as to maintain the pressure of gaseous fuel in the tank at a predefined so-called set point pressure.
  • FIG. 5 a variant embodiment of the heat exchange member 24 comprising a mixing chamber 52 combined with a heat exchanger 50.
  • the gaseous fuel and the liquid fuel are first carried at the same pressure via the compressor 22 and the pump 16, they are then brought to a heat exchanger 50 to be brought to the same temperature.
  • the two fuel streams exiting the heat exchanger are then mixed in the mixing chamber 52.
  • the gaseous fuel By circulating in the heat exchanger 50, the gaseous fuel is cooled, it then condenses. At the outlet of the heat exchanger 50, the two fuel streams are in liquid form and at similar temperatures.
  • the mixing of the two streams of liquid fuel is then simplified compared to a mixture of a stream of gaseous fuel with a stream of liquid fuel.
  • the regulation of the quantity of fuel in gaseous form present inside the tank 12 is thus carried out according to a method comprising:
  • the condensation step consists of a step of mixing the gaseous fuel into the flow of liquid fuel, via the mixing chamber 52 More generally, the condensation step consists of a heat exchange step between the gaseous fuel and the liquid fuel.
  • the method also includes a step of expanding the at least partially condensed fuel, which is implemented after the condensation step, at the outlet of the heat exchanger 50, via the expansion valve 30.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)

Abstract

The invention relates to an assembly (10) for storing cryogenized fuel, comprising - a reservoir (12) in which fuel is present in liquid form and in gaseous form, the gaseous form resulting from the evaporation of the fuel in liquid form, - a liquid fuel circuit (14) connecting the reservoir (12) to components intended to be supplied with fuel in liquid form, which comprises a pump (16) for pressurizing the liquid fuel, - a gaseous fuel circuit (20) drawing fuel in gaseous form from the reservoir (12), characterized in that it comprises a heat-exchange member (24) supplied by the liquid fuel circuit (14) and by the gaseous fuel circuit (20), in which the fuel in liquid form and the fuel in gaseous form are able to exchange heat in order to cause at least partial condensation of the drawn gaseous fuel.

Description

Description Description
Titre : CIRCUIT DE CARBURANT CRYOGENIQUE A RECONDENSATION Title: CRYOGENIC FUEL CIRCUIT WITH RECONDENSATION
DOMAINE TECHNIQUE TECHNICAL AREA
L'invention concerne un ensemble de stockage de carburant cryogénique comportant un réservoir de carburant et des moyens de gestion du carburant sous phase gazeuse dans le réservoir, qui résulte de l'évaporation du carburant liquide. The invention relates to a cryogenic fuel storage assembly comprising a fuel tank and means for managing the fuel in the gaseous phase in the tank, which results from the evaporation of the liquid fuel.
ÉTAT DE LA TECHNIQUE ANTÉRIEURE PRIOR ART
Certains aéronefs utilisent un carburant porté à très basse température pour leur fonctionnement, notamment en raison d'un impact environnemental réduit par rapport à un carburant à température ambiante. Some aircraft use fuel brought to a very low temperature for their operation, in particular because of a reduced environmental impact compared to fuel at ambient temperature.
Ce carburant cryogénisé est stocké dans un réservoir isolé thermiquement permettant de maintenir la température du carburant la plus basse possible. This cryogenized fuel is stored in a thermally insulated tank to keep the fuel temperature as low as possible.
Cependant, du fait de la différence de température avec l'extérieur du réservoir, de la chaleur pénètre le réservoir et réchauffe alors de carburant. However, due to the temperature difference with the outside of the tank, heat enters the tank and then heats the fuel.
Une partie du carburant s'évapore alors, ce qui fait que le carburant est présent dans le réservoir sous forme liquide et sous forme gazeuse. Part of the fuel then evaporates, which means that the fuel is present in the tank in liquid form and in gaseous form.
Au fur et à mesure que la chaleur pénètre dans le réservoir, le carburant s'évapore progressivement, ce qui augmente la pression de carburant gazeux à l'intérieur du réservoir. As the heat enters the tank, the fuel gradually evaporates, which increases the pressure of gaseous fuel inside the tank.
Il est alors prévu un système de régulation de la quantité de carburant gazeux, afin de limiter la pression dans le réservoir. A system for regulating the quantity of gaseous fuel is then provided, in order to limit the pressure in the tank.
De tels systèmes de régulation comportent par exemple un échangeur thermique au travers duquel le carburant gazeux circule pour être refroidi et ainsi se condenser. Such regulation systems comprise for example a heat exchanger through which the gaseous fuel circulates in order to be cooled and thus to condense.
La source froide de l'échangeur thermique est une source externe au dispositif, ce qui ce qui complexifie le système et alourdit le dispositif sur lequel le système est destiné à être monté. L'invention a pour but de proposer un ensemble de stockage comportant des moyens de régulation de la quantité de carburant gazeux présent à l'intérieur du réservoir qui ne comporte pas de source froide externe. The cold source of the heat exchanger is a source external to the device, which complicates the system and weighs down the device on which the system is intended to be mounted. The object of the invention is to propose a storage assembly comprising means for regulating the quantity of gaseous fuel present inside the tank which does not comprise an external cold source.
EXPOSÉ DE L'INVENTION DISCLOSURE OF THE INVENTION
L'invention propose un ensemble de stockage de carburant cryogénisé pour une turbomachine d'aéronef comportant The invention proposes a cryogenic fuel storage assembly for an aircraft turbomachine comprising
- un réservoir dans lequel du carburant est présent sous forme liquide et sous forme gazeuse, la forme gazeuse résultant de l'évaporation du carburant sous forme liquide,- a tank in which fuel is present in liquid form and in gaseous form, the gaseous form resulting from the evaporation of the fuel in liquid form,
- un circuit de carburant liquide reliant le réservoir à des composants destinés à être alimentés en carburant sous forme liquide, le circuit de carburant liquide comportant une pompe de pressurisation du carburant liquide, - a liquid fuel circuit connecting the tank to components intended to be supplied with fuel in liquid form, the liquid fuel circuit comprising a liquid fuel pressurization pump,
- un circuit de carburant gazeux prélevant du carburant sous forme gazeux depuis le réservoir, caractérisé en ce qu'il comporte un organe d'échange de chaleur alimenté par le circuit de carburant liquide et par le circuit de carburant gazeux, dans lequel le carburant sous forme liquide provenant du circuit de carburant liquide et le carburant sous forme gazeuse provenant du circuit de carburant gazeux sont aptes à échanger de la chaleur pour provoquer une condensation au moins partielle du carburant gazeux provenant du circuit de carburant gazeux. - a gaseous fuel circuit taking fuel in gaseous form from the tank, characterized in that it comprises a heat exchange member supplied by the liquid fuel circuit and by the gaseous fuel circuit, in which the fuel under liquid form coming from the liquid fuel circuit and the fuel in gaseous form coming from the gaseous fuel circuit are capable of exchanging heat to cause at least partial condensation of the gaseous fuel coming from the gaseous fuel circuit.
Selon un tel ensemble, le flux de carburant gazeux est refroidi par le carburant liquide. L'échange de chaleur se fait en interne, ce qui rend l'ensemble plus simple à intégrer dans une structure telle que celle d'un aéronef. According to such an assembly, the flow of gaseous fuel is cooled by the liquid fuel. The heat exchange takes place internally, which makes the assembly simpler to integrate into a structure such as that of an aircraft.
De préférence, l'organe d'échange de chaleur comporte une chambre de mélange dans laquelle le flux de carburant gazeux est injecté dans le flux de carburant liquide. Preferably, the heat exchange member comprises a mixing chamber in which the flow of gaseous fuel is injected into the flow of liquid fuel.
De préférence, le circuit de carburant gazeux comporte un compresseur en sortie duquel la pression du carburant gazeux est égale à une pression prédéterminée. Preferably, the gaseous fuel circuit comprises a compressor at the outlet of which the pressure of the gaseous fuel is equal to a predetermined pressure.
De préférence, la pression du carburant gazeux en sortie du compresseur est égale à la pression du carburant liquide en sortie de la pompe de pressurisation du carburant liquide. De préférence, l'organe d'échange de chaleur comporte en outre un échangeur de chaleur agencé en amont de la chambre de mélange et dans lequel le flux de carburant liquide prélève de la chaleur à partir du carburant gazeux. Preferably, the pressure of the gaseous fuel at the outlet of the compressor is equal to the pressure of the liquid fuel at the outlet of the liquid fuel pressurization pump. Preferably, the heat exchange member further comprises a heat exchanger arranged upstream of the mixing chamber and in which the flow of liquid fuel takes heat from the gaseous fuel.
De préférence, l'organe d'échange de chaleur comporte un échangeur de chaleur dans lequel le flux de carburant liquide prélève de la chaleur à partir du carburant gazeux.Preferably, the heat exchanger comprises a heat exchanger in which the flow of liquid fuel takes heat from the gaseous fuel.
De préférence, le circuit de carburant gazeux comporte un compresseur en sortie duquel la pression du carburant gazeux est égale à une pression prédéterminée supérieure à la pression de carburant liquide en sortie de la pompe de pressurisation. Preferably, the gaseous fuel circuit comprises a compressor at the outlet of which the pressure of the gaseous fuel is equal to a predetermined pressure greater than the pressure of liquid fuel at the outlet of the pressurization pump.
De préférence, le circuit de carburant gazeux comporte une vanne de détente agencée en aval de l'échangeur de chaleur, en sortie de laquelle la pression de carburant gazeux est sensiblement égale à la pression de carburant gazeux dans le réservoir. Preferably, the gaseous fuel circuit comprises an expansion valve arranged downstream of the heat exchanger, at the outlet of which the gaseous fuel pressure is substantially equal to the gaseous fuel pressure in the tank.
L'invention propose aussi un aéronef comportant au moins une turbomachine et un ensemble de stockage selon l'invention, alimentant ladite au moins une turbomachine en carburant liquide. The invention also proposes an aircraft comprising at least one turbomachine and a storage assembly according to the invention, supplying said at least one turbomachine with liquid fuel.
L'invention propose aussi un procédé de régulation de la quantité de carburant sous forme gazeuse présente à l'intérieur du réservoir d'un ensemble de stockage selon l'invention, caractérisé en ce qu'il comporte : The invention also proposes a method for regulating the quantity of fuel in gaseous form present inside the tank of a storage assembly according to the invention, characterized in that it comprises:
- une étape de prélèvement de carburant sous forme gazeux depuis le réservoir, pour le faire circuler dans un circuit de carburant liquide, - a step for withdrawing fuel in gaseous form from the tank, to circulate it in a liquid fuel circuit,
- une étape de condensation d'au moins une partie du carburant sous forme gazeux prélevé. - a step of condensing at least part of the fuel in gaseous form withdrawn.
De préférence, le procédé comporte une étape de compression du carburant gazeux qui est mise en œuvre avant l'étape de condensation. Preferably, the method comprises a stage of compression of the gaseous fuel which is implemented before the stage of condensation.
De préférence, l'étape de condensation consiste en une étape de mélange du carburant gazeux dans le flux de carburant liquide. Preferably, the condensation step consists of a step of mixing the gaseous fuel into the flow of liquid fuel.
De préférence, l'étape de condensation consiste en une étape d'échange de chaleur entre le carburant gazeux et le carburant liquide. Preferably, the condensation step consists of a heat exchange step between the gaseous fuel and the liquid fuel.
De préférence, le procédé comporte une étape de détente du carburant condensé au moins partiellement, qui est mise en œuvre après l'étape de condensation. BRÈVE DESCRIPTION DES DESSINS Preferably, the method includes a step for expanding the at least partially condensed fuel, which is implemented after the condensation step. BRIEF DESCRIPTION OF DRAWINGS
[Fig. 1] est une représentation schématique d'un ensemble de stockage d'un carburant cryogénisé réalisant la régulation de la quantité de carburant gazeux selon l'invention. [Fig. 2] est une représentation schématique d'un ensemble de stockage d'un carburant cryogénisé réalisant la régulation de la quantité de carburant gazeux selon un deuxième mode de réalisation de l'invention. [Fig. 1] is a schematic representation of a storage unit for cryogenic fuel carrying out the regulation of the quantity of gaseous fuel according to the invention. [Fig. 2] is a schematic representation of a storage unit for cryogenic fuel performing the regulation of the quantity of gaseous fuel according to a second embodiment of the invention.
[Fig. 3] est une représentation schématique d'un exemple de chambre de mélange mise en œuvre dans le deuxième mode de réalisation de l'invention. [Fig. 3] is a schematic representation of an example of a mixing chamber implemented in the second embodiment of the invention.
[Fig. 4] est une représentation schématique d'un autre exemple de chambre de mélange mise en œuvre dans le deuxième mode de réalisation de l'invention. [Fig. 4] is a schematic representation of another example of a mixing chamber implemented in the second embodiment of the invention.
[Fig. 5] est une représentation schématique d'un ensemble de stockage d'un carburant cryogénisé réalisant la régulation de la quantité de carburant gazeux selon une variante du mode de réalisation de l'invention représenté à la figure 2. [Fig. 5] is a schematic representation of a storage assembly for cryogenic fuel performing the regulation of the quantity of gaseous fuel according to a variant of the embodiment of the invention represented in FIG. 2.
DESCRIPTION DES MODES DE REALISATION DESCRIPTION OF EMBODIMENTS
On a représenté à la figure 1 un ensemble de stockage 10 de carburant cryogénisé, destiné par exemple à alimenter les turbomachines d'un aéronef. There is shown in Figure 1 a storage assembly 10 of cryogenized fuel, intended for example to supply the turbine engines of an aircraft.
Dans cet ensemble de stockage, le carburant est porté à une très basse température, par exemple proche de zéro degrés Celsius ou très inférieure dans le cas de l'hydrogène liquide, et il est conservé dans un réservoir 12 isolant thermiquement pour le maintenir à cette basse température. In this storage assembly, the fuel is brought to a very low temperature, for example close to zero degrees Celsius or much lower in the case of liquid hydrogen, and it is stored in a thermally insulating tank 12 to maintain it at this low temperature.
A l'intérieur du réservoir 12, le carburant est présent sous forme liquide et sous forme gazeuse. Inside the tank 12, the fuel is present in liquid form and in gaseous form.
Le carburant liquide alimente la ou les turbomachines de l'aéronef par l'intermédiaire d'un circuit de carburant liquide 14. Le circuit de carburant liquide 14 comporte une pompe 16 de pressurisation du carburant liquide, elle-même étant alimentée par des pompes de gavage 18 disposées à l'intérieur du réservoir 12. The liquid fuel supplies the turbomachine(s) of the aircraft via a liquid fuel circuit 14. The liquid fuel circuit 14 comprises a pump 16 for pressurizing the liquid fuel, itself being supplied by pumps feeding 18 arranged inside the reservoir 12.
Le réchauffement du carburant dans le réservoir 12, provoqué par la différence entre la température de l'air ambiant et la température du carburant dans le réservoir 12, se traduit par une évaporation d'une partie du carburant. La pression de carburant gazeux dans le réservoir 12 est donc amenée à augmenter progressivement. The heating of the fuel in the tank 12, caused by the difference between the temperature of the ambient air and the temperature of the fuel in the tank 12, results in an evaporation of part of the fuel. The gaseous fuel pressure in tank 12 is therefore caused to gradually increase.
L'ensemble de stockage 10 comporte aussi un circuit de carburant gazeux 20 permettant de réguler la quantité de carburant sous forme gazeuse présente à l'intérieur du réservoir 12. The storage assembly 10 also comprises a gaseous fuel circuit 20 making it possible to regulate the quantity of fuel in gaseous form present inside the tank 12.
Le circuit de carburant gazeux 20 comporte un compresseur 22 permettant d'augmenter la pression et la température du carburant gazeux dans le circuit de carburant gazeux 20 et un organe d'échange de chaleur 24 permettant de refroidir ce carburant gazeux, pour provoquer sa condensation. The gaseous fuel circuit 20 comprises a compressor 22 making it possible to increase the pressure and the temperature of the gaseous fuel in the gaseous fuel circuit 20 and a heat exchange member 24 making it possible to cool this gaseous fuel, to cause its condensation.
Selon l'invention, l'organe d'échange de chaleur 24 est conçu pour que le carburant gazeux comprimé par le compresseur 22 échange de la chaleur avec le carburant liquide s'écoulant dans le circuit de carburant liquide 14. According to the invention, the heat exchanger 24 is designed so that the gaseous fuel compressed by the compressor 22 exchanges heat with the liquid fuel flowing in the liquid fuel circuit 14.
Le carburant liquide prélève alors de la chaleur depuis le carburant gazeux, ce qui provoque à la fois une condensation du carburant gazeux et une augmentation de la chaleur du carburant liquide avant que ce carburant liquide alimente la ou les turbomachines. The liquid fuel then takes heat from the gaseous fuel, which causes both a condensation of the gaseous fuel and an increase in the heat of the liquid fuel before this liquid fuel supplies the turbomachine(s).
Selon un premier mode de réalisation représenté à la figure 1, l'organe d'échange de chaleur 24 consiste en un échangeur de chaleur à flux séparés. According to a first embodiment represented in FIG. 1, the heat exchange member 24 consists of a heat exchanger with separate flows.
Le flux de carburant gazeux circule dans la partie chaude 26 de l'échangeur de chaleur 50, le flux de carburant liquide circule dans la partie froide 28 de l'échangeur de chaleur 50, sans se mélanger l'un à l'autre. The flow of gaseous fuel circulates in the hot part 26 of the heat exchanger 50, the flow of liquid fuel circulates in the cold part 28 of the heat exchanger 50, without mixing with each other.
En sortie de l'échangeur de chaleur 50, le carburant gazeux ayant perdu de la chaleur a été refroidit et s'est condensé. At the outlet of the heat exchanger 50, the gaseous fuel having lost heat was cooled and condensed.
La compression du liquide par le compresseur 22 combinée au fait que la température du carburant gazeux sortant de l'échangeur de chaleur 50 n'est pas parfaitement égale à la température du carburant liquide sortant de l'échangeur de chaleur 50, induit que la température du carburant gazeux sortant de l'échangeur de chaleur 50 peut avoir une température supérieure à la température du carburant liquide présent dans le réservoir. A titre d'exemple non limitatif, le carburant gazeux, après s'être condensé présente une température supérieure d'environ 5K (Kelvin) par rapport à la température du carburant liquide présent dans le réservoir. The compression of the liquid by the compressor 22 combined with the fact that the temperature of the gaseous fuel leaving the heat exchanger 50 is not perfectly equal to the temperature of the liquid fuel leaving the heat exchanger 50, induces that the temperature gaseous fuel leaving the heat exchanger 50 can have a temperature higher than the temperature of the liquid fuel present in the tank. By way of non-limiting example, the gaseous fuel, after having condensed, has a higher temperature of approximately 5 K (Kelvin) with respect to the temperature of the liquid fuel present in the tank.
Le flux de carburant gazeux qui sort de l'échangeur de chaleur, qui a été refroidi et condensé, circule alors au travers d'une vanne de détente 30 par laquelle sa pression et sa température sont abaissées pour que la pression du carburant en sortie de la vanne de détente 30 soit égale à la pression du carburant gazeux dans le réservoir 12. La détente provoque l'évaporation d'une partie du carburant liquide qui s'était condensé dans l'échangeur de chaleur 50, mais la température du mélange à deux phases est abaissée. La température et la pression du fluide qui sort de la vanne de détente 30 sont sensiblement identiques à la température et la pression du liquide présent dans le réservoir. Ce fluide sortant de la vanne de détente 30 contient en outre une faible proportion de gaz, notamment inférieure à 10%, alors que ce fluide était 100% gazeux lors qu'il a été extrait du réservoir. Ce fluide étant en outre potentiellement plus chaud que la température du liquide présent dans le réservoir. The flow of gaseous fuel which leaves the heat exchanger, which has been cooled and condensed, then circulates through an expansion valve 30 by which its pressure and its temperature are lowered so that the pressure of the fuel at the outlet of the expansion valve 30 is equal to the pressure of the gaseous fuel in the tank 12. The expansion causes the evaporation of part of the liquid fuel which had condensed in the heat exchanger 50, but the temperature of the mixture at two phases is lowered. The temperature and the pressure of the fluid leaving the expansion valve 30 are substantially identical to the temperature and the pressure of the liquid present in the tank. This fluid leaving the expansion valve 30 also contains a small proportion of gas, in particular less than 10%, whereas this fluid was 100% gaseous when it was extracted from the tank. This fluid also being potentially hotter than the temperature of the liquid present in the reservoir.
Les pressions de carburant gazeux et de carburant liquide circulant respectivement dans le flux circuit de carburant gazeux 20 et dans le circuit de carburant liquide 14, sont régulées pour favoriser l'échange de chaleur, notamment pour augmenter le sous refroidissement du liquide. The gaseous fuel and liquid fuel pressures circulating respectively in the gaseous fuel circuit flow 20 and in the liquid fuel circuit 14 are regulated to promote heat exchange, in particular to increase the sub-cooling of the liquid.
A titre d'exemple non limitatif, la pression de carburant liquide en sortie de la pompe 16 est au moins égale à 10 bars et la pression de carburant gazeux en sortie du compresseur 22 est comprise entre 4 et 8 bars. By way of non-limiting example, the pressure of liquid fuel at the outlet of pump 16 is at least equal to 10 bars and the pressure of gaseous fuel at the outlet of compressor 22 is between 4 and 8 bars.
On a représenté à la figure 2 un autre mode de réalisation de l'invention selon lequel l'organe d'échange de chaleur 24 consiste en une chambre de mélange 52. There is shown in Figure 2 another embodiment of the invention in which the heat exchange member 24 consists of a mixing chamber 52.
Le carburant gazeux introduit dans la chambre de mélange 52 est à une température supérieure à la température du carburant liquide introduit dans la chambre de mélange 52. The gaseous fuel introduced into the mixing chamber 52 is at a temperature higher than the temperature of the liquid fuel introduced into the mixing chamber 52.
En se mélangeant au carburant liquide dans la chambre de mélange 52, le carburant gazeux échange de la chaleur directement avec le carburant liquide auquel il est mélangé. La pompe 16 et le compresseur 22 sont configurés pour que les débits et pressions du carburant gazeux et du carburant liquide permettent la condensation de la totalité du carburant gazeux injecté, tout en évitant la vaporisation du carburant liquide. By mixing with the liquid fuel in the mixing chamber 52, the gaseous fuel exchanges heat directly with the liquid fuel with which it is mixed. The pump 16 and the compressor 22 are configured so that the flow rates and pressures of the gaseous fuel and of the liquid fuel allow the condensation of all of the gaseous fuel injected, while avoiding the vaporization of the liquid fuel.
De plus, la pression du carburant gazeux injecté dans la chambre de mélange 52 est de préférence identique à la pression du carburant liquide. Moreover, the pressure of the gaseous fuel injected into the mixing chamber 52 is preferably identical to the pressure of the liquid fuel.
Selon un exemple de réalisation préféré, mais non limitatif, la pression du carburant gazeux et la pression du carburant liquide injectés dans la chambre de mélange 52 sont d'environ 10 bars. According to a preferred, but non-limiting, embodiment, the pressure of the gaseous fuel and the pressure of the liquid fuel injected into the mixing chamber 52 are approximately 10 bars.
Cette valeur de pressions, dans le cas de l'hydrogène en tant que carburant, permet d'incorporer une quantité de carburant gazeux proche de 20% du débit de carburant liquide. This pressure value, in the case of hydrogen as fuel, makes it possible to incorporate a quantity of gaseous fuel close to 20% of the flow rate of liquid fuel.
Ici encore, en passant au travers du compresseur 22 pour atteindre la pression prédéfinie, la température du carburant gazeux augmente et devient supérieure à la température du carburant liquide en sortie de la pompe 16. En se mélangeant au carburant liquide, le carburant gazeux est alors refroidi et se condense. Here again, passing through the compressor 22 to reach the predefined pressure, the temperature of the gaseous fuel increases and becomes higher than the temperature of the liquid fuel at the outlet of the pump 16. By mixing with the liquid fuel, the gaseous fuel is then cooled and condensed.
Ainsi, en sortie de la chambre de mélange 52, la totalité du carburant se présente sous forme liquide, sa température étant supérieure à la température du carburant liquide en sortie de la pompe 16 et inférieure à la température du carburant gazeux en sortie du compresseur 22. Thus, at the outlet of the mixing chamber 52, all of the fuel is in liquid form, its temperature being higher than the temperature of the liquid fuel at the outlet of the pump 16 and lower than the temperature of the gaseous fuel at the outlet of the compressor 22 .
On a représenté aux figures 3 et 4 deux exemples non limitatifs de modes de réalisation de la chambre de mélange 52. There is shown in Figures 3 and 4 two non-limiting examples of embodiments of the mixing chamber 52.
Selon le mode représenté à la figure 3, la chambre de mélange 52 comporte une conduite tubulaire 34 au travers de laquelle le carburant liquide circule et un tube d'entrée de gaz 36 qui s'étend en partie dans la conduite tubulaire 34. According to the mode shown in Figure 3, the mixing chamber 52 comprises a tubular conduit 34 through which the liquid fuel circulates and a gas inlet tube 36 which extends partly in the tubular conduit 34.
L'extrémité 38 du tube d'entrée de gaz 36 qui s'étend dans la conduite tubulaire 34 est débouchante et comporte une pluralité d'orifices 40 qui permettent de mélanger le plus efficacement possible le carburant gazeux au carburant liquide sous la forme de fines bulles 42, favorisant ainsi le transfert de chaleur. The end 38 of the gas inlet tube 36 which extends into the tubular conduit 34 is through and has a plurality of orifices 40 which allow the gaseous fuel to be mixed as efficiently as possible with the liquid fuel in the form of fines. bubbles 42, thereby promoting heat transfer.
Une telle chambre de mélange 52 est connue sous la dénomination "gas sparger". Selon le mode de réalisation représenté à la figure 4, la chambre de mélange 52 comporte deux entrées coaxiales 44, 46, chacune associée au carburant liquide ou au carburant gazeux. Une réduction de section 48 est située en aval des entrées 44, 46, pour provoquer une accélération du carburant liquide et favoriser l'aspiration de carburant gazeux. Such a mixing chamber 52 is known under the name "gas sparger". According to the embodiment shown in Figure 4, the mixing chamber 52 has two coaxial inlets 44, 46, each associated with liquid fuel or gaseous fuel. A section reduction 48 is located downstream of the inlets 44, 46, to cause an acceleration of the liquid fuel and promote the suction of gaseous fuel.
Une telle chambre de mélange 52 est connue sous la dénomination "jet ejector". Such a mixing chamber 52 is known under the name "jet ejector".
Quel que soit le mode de réalisation de l'organe d'échange de chaleur 24, le compresseur 22 est conçu de manière à maintenir la pression de carburant gazeux dans le réservoir à une pression prédéfinie dite de consigne. Whatever the embodiment of the heat exchange unit 24, the compressor 22 is designed so as to maintain the pressure of gaseous fuel in the tank at a predefined so-called set point pressure.
Par conséquent, il prélève en continuité du carburant gazeux depuis le réservoir. Therefore, it continuously draws gaseous fuel from the tank.
On a représenté à la figure 5 une variante de réalisation de l'organe d'échange de chaleur 24 comportant une chambre de mélange 52 combinée à un échangeur thermique 50. Selon cette variante, le carburant gazeux et le carburant liquide sont d'abord portés à une même pression par l'intermédiaire du compresseur 22 et de la pompe 16, ils sont alors amenés vers un échangeur thermique 50 pour être portés à une même température.There is shown in Figure 5 a variant embodiment of the heat exchange member 24 comprising a mixing chamber 52 combined with a heat exchanger 50. According to this variant, the gaseous fuel and the liquid fuel are first carried at the same pressure via the compressor 22 and the pump 16, they are then brought to a heat exchanger 50 to be brought to the same temperature.
Les deux flux de carburant sortant de l'échangeur thermique sont ensuite mélangés dans la chambre de mélange 52. The two fuel streams exiting the heat exchanger are then mixed in the mixing chamber 52.
En circulant dans l'échangeur thermique 50, le carburant gazeux est refroidi, il se condense alors. En sortie de l'échangeur thermique 50, les deux flux de carburant sont sous la forme liquide et à des températures proches. By circulating in the heat exchanger 50, the gaseous fuel is cooled, it then condenses. At the outlet of the heat exchanger 50, the two fuel streams are in liquid form and at similar temperatures.
Le mélange des deux flux de carburant liquide est alors simplifié par rapport à un mélange d'un flux de carburant gazeux avec un flux de carburant liquide. The mixing of the two streams of liquid fuel is then simplified compared to a mixture of a stream of gaseous fuel with a stream of liquid fuel.
La régulation de la quantité de carburant sous forme gazeuse présente à l'intérieur du réservoir 12 s'effectue ainsi selon un procédé comportant: The regulation of the quantity of fuel in gaseous form present inside the tank 12 is thus carried out according to a method comprising:
- une étape de prélèvement de carburant sous forme gazeux depuis le réservoir 12, pour le faire circuler dans le circuit de carburant gazeux 20 et - a step of withdrawing fuel in gaseous form from the tank 12, to cause it to circulate in the gaseous fuel circuit 20 and
- une étape de condensation d'au moins une partie du carburant sous forme gazeux prélevé. - a step of condensing at least part of the fuel in gaseous form withdrawn.
Ce procédé comporte notamment une étape de compression du carburant gazeux qui est mise en œuvre avant l'étape de condensation. Comme on l'a montré précédemment, selon les modes de réalisation représentés aux figures 2 et suivantes l'étape de condensation consiste en une étape de mélange du carburant gazeux dans le flux de carburant liquide, par l'intermédiaire de la chambre de mélange 52. Plus généralement, l'étape de condensation consiste en une étape d'échange de chaleur entre le carburant gazeux et le carburant liquide. This method comprises in particular a stage of compression of the gaseous fuel which is implemented before the stage of condensation. As shown previously, according to the embodiments represented in FIGS. 2 and following, the condensation step consists of a step of mixing the gaseous fuel into the flow of liquid fuel, via the mixing chamber 52 More generally, the condensation step consists of a heat exchange step between the gaseous fuel and the liquid fuel.
Le procédé comporte aussi une étape de détente du carburant condensé au moins partiellement, qui est mise en œuvre après l'étape de condensation, en sortie de l'échangeur de chaleur 50, par l'intermédiaire de la vanne de détente 30. The method also includes a step of expanding the at least partially condensed fuel, which is implemented after the condensation step, at the outlet of the heat exchanger 50, via the expansion valve 30.

Claims

Revendications Claims
1. Ensemble de stockage (10) de carburant cryogénisé pour une turbomachine d'aéronef comportant 1. Cryogenic fuel storage assembly (10) for an aircraft turbine engine comprising
- un réservoir (12) dans lequel du carburant est présent sous forme liquide et sous forme gazeuse, la forme gazeuse résultant de l'évaporation du carburant sous forme liquide,- a tank (12) in which fuel is present in liquid form and in gaseous form, the gaseous form resulting from the evaporation of the fuel in liquid form,
- un circuit de carburant liquide (14) reliant le réservoir (12) à des composants destinés à être alimentés en carburant sous forme liquide, le circuit de carburant liquide (14) comportant une pompe (16) de pressurisation du carburant liquide, - a liquid fuel circuit (14) connecting the tank (12) to components intended to be supplied with fuel in liquid form, the liquid fuel circuit (14) comprising a pump (16) for pressurizing the liquid fuel,
- un circuit de carburant gazeux (20) prélevant du carburant sous forme gazeux depuis le réservoir (12), l'ensemble de stockage (10) comportant un organe d'échange de chaleur (24) alimenté par le circuit de carburant liquide (14) et par le circuit de carburant gazeux (20), dans lequel le carburant sous forme liquide provenant du circuit de carburant liquide (14) et le carburant sous forme gazeuse provenant du circuit de carburant gazeux (20) sont aptes à échanger de la chaleur pour provoquer une condensation au moins partielle du carburant gazeux provenant du circuit de carburant gazeux (20), dans lequel le circuit de carburant gazeux (20) débouche dans le réservoir (12) et comporte un compresseur (22) en sortie duquel la pression du carburant gazeux est égale à une pression prédéterminée supérieure à la pression de carburant liquide en sortie de la pompe (16) de pressurisation et comporte une vanne de détente (30) agencée en aval de l'échangeur de chaleur (50), en sortie de laquelle la pression de carburant gazeux est sensiblement égale à la pression de carburant gazeux dans le réservoir (12). - a gaseous fuel circuit (20) taking fuel in gaseous form from the tank (12), the storage assembly (10) comprising a heat exchange member (24) supplied by the liquid fuel circuit (14 ) and by the gaseous fuel circuit (20), in which the fuel in liquid form coming from the liquid fuel circuit (14) and the fuel in gaseous form coming from the gaseous fuel circuit (20) are capable of exchanging heat to cause at least partial condensation of the gaseous fuel coming from the gaseous fuel circuit (20), in which the gaseous fuel circuit (20) opens into the tank (12) and comprises a compressor (22) at the outlet of which the pressure of the gaseous fuel is equal to a predetermined pressure greater than the liquid fuel pressure at the outlet of the pressurization pump (16) and comprises an expansion valve (30) arranged downstream of the heat exchanger (50), at the outlet of which one The gaseous fuel pressure is substantially equal to the gaseous fuel pressure in the tank (12).
2. Ensemble de stockage (10) selon la revendication 1, caractérisé en ce que l'organe d'échange de chaleur (24) comporte une chambre de mélange (52) dans laquelle le flux de carburant gazeux est injecté dans le flux de carburant liquide. 2. storage assembly (10) according to claim 1, characterized in that the heat exchange member (24) comprises a mixing chamber (52) in which the flow of gaseous fuel is injected into the flow of fuel liquid.
3. Ensemble de stockage (10) selon la revendication 1 ou 2, caractérisé en ce que le circuit de carburant gazeux (20) comporte un compresseur (22) en sortie duquel la pression du carburant gazeux est égale à une pression prédéterminée. 3. Storage assembly (10) according to claim 1 or 2, characterized in that the gaseous fuel circuit (20) comprises a compressor (22) at the outlet of which the pressure of the gaseous fuel is equal to a predetermined pressure.
4. Ensemble de stockage (10) selon la revendication 3, caractérisé en ce que la pression du carburant gazeux en sortie du compresseur (22) est égale à la pression du carburant liquide en sortie de la pompe (16) de pressurisation du carburant liquide. 4. Storage assembly (10) according to claim 3, characterized in that the pressure of the gaseous fuel at the outlet of the compressor (22) is equal to the pressure of the liquid fuel at the outlet of the pump (16) for pressurizing the liquid fuel .
5. Ensemble de stockage (10) selon la revendication 2, caractérisé en ce que l'organe d'échange de chaleur (24) comporte en outre un échangeur de chaleur (50) agencé en amont de la chambre de mélange (52) et dans lequel le flux de carburant liquide prélève de la chaleur à partir du carburant gazeux. 5. storage assembly (10) according to claim 2, characterized in that the heat exchange member (24) further comprises a heat exchanger (50) arranged upstream of the mixing chamber (52) and wherein the flow of liquid fuel draws heat from the gaseous fuel.
6. Ensemble de stockage (10) selon la revendication 1, caractérisé en ce que l'organe d'échange de chaleur (24) comporte un échangeur de chaleur (50) dans lequel le flux de carburant liquide prélève de la chaleur à partir du carburant gazeux. 6. storage assembly (10) according to claim 1, characterized in that the heat exchange member (24) comprises a heat exchanger (50) in which the flow of liquid fuel takes heat from the gaseous fuel.
7. Aéronef comportant au moins une turbomachine et un ensemble de stockage (10) selon l'une quelconque des revendications précédentes, alimentant ladite au moins une turbomachine en carburant liquide. 7. Aircraft comprising at least one turbomachine and a storage assembly (10) according to any one of the preceding claims, supplying said at least one turbomachine with liquid fuel.
8. Procédé de régulation de la quantité de carburant sous forme gazeuse présente à l'intérieur du réservoir (12) d'un ensemble de stockage (10) selon l'une quelconque des revendications précédentes, caractérisé en ce qu'il comporte : 8. Method for regulating the quantity of fuel in gaseous form present inside the tank (12) of a storage assembly (10) according to any one of the preceding claims, characterized in that it comprises:
- une étape de prélèvement de carburant sous forme gazeux depuis le réservoir (12), pour le faire circuler dans un circuit de carburant liquide (14), - a step for withdrawing fuel in gaseous form from the tank (12), to cause it to circulate in a liquid fuel circuit (14),
- une étape de condensation d'au moins une partie du carburant sous forme gazeux prélevé - a step of condensing at least part of the fuel in gaseous form withdrawn
- une étape de compression du carburant gazeux qui est mise en œuvre avant l'étape de condensation, dans lequel l'étape de condensation consiste en une étape d'échange de chaleur entre le carburant gazeux et le carburant liquide, caractérisé en ce qu'il comporte une étape de détente du carburant condensé au moins partiellement, qui est mise en œuvre après l'étape de condensation. - a stage of compression of the gaseous fuel which is implemented before the stage of condensation, wherein the condensation step consists of a heat exchange step between the gaseous fuel and the liquid fuel, characterized in that it includes a step of expanding the at least partially condensed fuel, which is implemented after the condensing step.
9. Procédé selon la revendication 8 en ce que l'étape de condensation consiste en une étape de mélange du carburant gazeux dans le flux de carburant liquide. 9. Method according to claim 8 in that the condensation step consists of a step of mixing the gaseous fuel in the flow of liquid fuel.
PCT/FR2021/051484 2020-09-02 2021-08-25 Cryogenic fuel circuit with recondensation WO2022049335A1 (en)

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