WO2022136183A1 - Système de réservoir pour le stockage de fluides réfrigérés - Google Patents

Système de réservoir pour le stockage de fluides réfrigérés Download PDF

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Publication number
WO2022136183A1
WO2022136183A1 PCT/EP2021/086618 EP2021086618W WO2022136183A1 WO 2022136183 A1 WO2022136183 A1 WO 2022136183A1 EP 2021086618 W EP2021086618 W EP 2021086618W WO 2022136183 A1 WO2022136183 A1 WO 2022136183A1
Authority
WO
WIPO (PCT)
Prior art keywords
tank system
shell
outer shell
spacers
layer
Prior art date
Application number
PCT/EP2021/086618
Other languages
German (de)
English (en)
Inventor
Albrecht Kluge
Markus Müller
Original Assignee
Airbus Operations Gmbh
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 Airbus Operations Gmbh filed Critical Airbus Operations Gmbh
Priority to EP21836197.0A priority Critical patent/EP4267388A1/fr
Publication of WO2022136183A1 publication Critical patent/WO2022136183A1/fr

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
    • B32B3/02—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions
    • B32B3/06—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions for securing layers together; for attaching the product to another member, e.g. to a support, or to another product, e.g. groove/tongue, interlocking
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B1/00—Layered products having a non-planar shape
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B27/00—Layered products comprising a layer of synthetic resin
    • B32B27/06—Layered products comprising a layer of synthetic resin as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • B32B27/065—Layered products comprising a layer of synthetic resin as the main or only constituent of a layer, which is next to another layer of the same or of a different material of foam
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B27/00—Layered products comprising a layer of synthetic resin
    • B32B27/06—Layered products comprising a layer of synthetic resin as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • B32B27/08—Layered products comprising a layer of synthetic resin as the main or only constituent of a layer, which is next to another layer of the same or of a different material of synthetic resin
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
    • B32B3/26—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer
    • B32B3/263—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer characterised by a layer having non-uniform thickness
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/18—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by features of a layer of foamed material
    • 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
    • B64D37/00—Arrangements in connection with fuel supply for power plant
    • B64D37/02—Tanks
    • 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
    • B64D37/00—Arrangements in connection with fuel supply for power plant
    • B64D37/30—Fuel systems for specific fuels
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/10—Inorganic fibres
    • B32B2262/106—Carbon fibres, e.g. graphite fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/30—Properties of the layers or laminate having particular thermal properties
    • B32B2307/304—Insulating
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2439/00—Containers; Receptacles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2605/00—Vehicles
    • B32B2605/18—Aircraft

Definitions

  • Tank system for storing cool media
  • the invention relates to a tank system for storing cool media and an aircraft with such a tank system.
  • cryogenic tank systems for supplying hydrogen to fuel cells or internal combustion engines in means of transport, for example in aircraft. These have a tank volume in which liquid hydrogen is stored at a temperature of -253 °C. Hydrogen is removed from the tank volume in that part of the liquid hydrogen, for example, evaporates and is guided out of the tank volume in a targeted manner.
  • a particular challenge when designing such a tank system is to keep the temperature at the desired, low level even over longer flight durations. This is achieved in particular by thermal insulation.
  • a low overall weight is also important for the economy of the aircraft.
  • DE 102014 107 316 A1 shows a tank system for the cryogenic storage of hydrogen, the tank system having a tank structure with at least one Having a hollow body for receiving liquid hydrogen and at least one insulation means surrounding the tank structure for insulating the at least one hollow body.
  • a tank system for storing cool media having an inner shell made of a first fiber-reinforced material, which defines a receiving space for receiving a cool medium to be stored, an outer shell made of a second fiber-reinforced material, which surrounds the inner shell, and a plurality of spacers made of a third fibre-reinforced material arranged in a rod-like manner between and integrally connected to the inner shell and the outer shell and adapted to space the inner shell and the outer shell apart so that at least one thermally insulating gap is formed between the inner shell and the outer shell, wherein at least the inner shell prevents the medium to be stored from escaping.
  • the tank system is based on an arrangement of at least two shells, one shell being an inner shell and one shell representing an outer shell.
  • the inner shell defines the tank volume, which is filled with the cool medium, such as liquid hydrogen. Due to the distance between the outer shell and a thermal insulation realized because the heat conduction between the tank volume and the environment of the outer shell is significantly reduced.
  • the thermal insulation is dependent on a number of variables, which include, among other things, the type or the presence of a substance provided in the intermediate space, the size of the spacing and the material of the spacers.
  • the first fiber reinforced material may correspond to the second fiber reinforced material. However, they could also differ from each other to take advantage of different properties. Materials are particularly suitable which comprise a matrix with reinforcing fibers embedded therein.
  • the matrix acts as an embedding material for the reinforcing fibers and could comprise thermoplastic and thermoset polymers such as epoxies, ceramics or other suitable materials.
  • the reinforcing fibers could be carbon allotropes, for example carbon fibers, carbon nanotubes, graphene or the like.
  • glass fibers, aramid fibers, ceramic fibers and polymer fibers could also be suitable.
  • the third fiber reinforced material of the spacers could be the same as the first or the second fiber reinforced material or different. It may be advisable to produce the spacers with a fiber bundle, with the individual fibers of the fiber bundle extending in a main direction of extension of the spacers and being impregnated with a matrix material. For reasons of compatibility, it makes sense to select the first, the second and the third fiber-reinforced material to be identical. It also makes sense to equip the spacers with a closed cross section. However, the spacers could also be hollow, in particular tubular, in which case an interior space of the tubular spacers should not have any fluid connection with the receiving space.
  • At least the inner shell preferably also the outer shell, is provided with a coating that prevents the medium from escaping, in order to prevent the medium from escaping.
  • the medium can also be another cryogenic or liquid or gaseous cool or cooled medium, for example methane.
  • the coating can be realized in the form of a metallic layer. Alternatively, a suitable polymer, graphene or multi-layer insulation can also be used. The coating can therefore be implemented as a film, a spray layer, or a vapor-deposited coating. The coating can also be implemented using a special layer structure of the fiber-reinforced material.
  • the spacers are rod-shaped so that their lengths significantly exceed their widths or diameters.
  • the spacers preferably extend in a straight line from the inner shell to the outer shell. This enables them to absorb high tensile and compressive forces.
  • the combination of the highest possible strength, the smallest possible cross-sectional area resulting therefrom and/or the smallest possible number can lead to the lowest possible heat transport between the inner shell and the outer shell.
  • the spacers can form a framework structure and consequently extend in different directions.
  • the framework is a spatial framework that extends between the inner shell and the outer shell and a curved layer with a desired thickness.
  • the spacers are preferably embedded directly in the inner shell and/or the outer shell, so that they at least partially penetrate at least one of the two shells. As a result, they are firmly connected to the case in question.
  • the minimized heat transport counteracts the heating of the hydrogen or other cool media contained therein.
  • a significant weight saving is achieved in comparison to known metallic tanks for storing cool media and in particular cryogenic hydrogen.
  • a structurally integrated tank is made possible, which is able to at least partially absorb loads of the fuselage.
  • the volume taken up by the tank system is also reduced since a comparatively small distance is required between the inner shell and the outer shell. Manufacturing can be simplified by the possibility of automated manufacturing processes.
  • the tank system has good damage tolerance behavior and also allows for complex tank geometries.
  • the tank system can also be fully or partially integrated into the fuselage structure.
  • the spacers penetrate the inner shell and the outer shell at least partially and are bent or folded over at their ends.
  • the folding can occur before the third fiber reinforced material is cured.
  • the semi-finished fiber product is driven through the inner shell and the outer shell, for example with a needle, and then folded over so that the ends are flat on the inner shell and outer shell lay up. Infiltration with the matrix material and/or curing can then take place.
  • the at least one intermediate space has a layer of foam.
  • the foam forms a foam core between the inner shell and the outer shell. This can lead to further stiffening and/or insulation.
  • the spacers can extend completely through the foam.
  • the foam is preferably a rigid foam. It can be closed-pore or open-pore. According to the invention, an open-pored variant could be particularly useful for improving the vacuum properties.
  • the at least one intermediate space has a closed volume that can be evacuated.
  • the vacuum can extend completely between the inner shell and the outer shell.
  • the term "closed” does not have to mean that the volume is completely closed. Rather, at least local access to the desired evacuation is necessary.
  • the space between the inner shell and the outer shell it is also conceivable for the space between the inner shell and the outer shell to have a plurality of volumes which are separate from one another and are designed differently. The use of a vacuum is particularly useful, as this significantly reduces the heat transport over the corresponding volume.
  • the spacers are suitable for keeping the inner shell and the outer shell at a distance from one another with sufficient strength to compensate for the force exerted by the vacuum on the facing surfaces of the inner shell and the outer shell. Due to the vacuum, a smaller distance between the inner shell and the outer shell could be realized than with other embodiments described here.
  • the outer shell preferably has an outer shape that can be integrated into a load-bearing primary structure of an aircraft.
  • the outer shell be designed so that the tank system can be integrated into a tail section of a commercial aircraft.
  • the tank system can also be stiffened to such an extent that it is load-bearing and set up to at least partially absorb a load introduced into the primary structure.
  • the outer shell preferably has at least one external, in particular radially external, transition section, which is adjoined by a monolithic structure.
  • the transition section can, for example, form a kind of extension of a central part of the outer shell.
  • the outer shell can have two opposing, for example axial end sections which close off the middle part, for example as a kind of cap.
  • the transition section is provided in a preferably curved area of the outer shell, in which the caps are formed.
  • the outer shell could then have axial flanges, for example, which each enclose or enclose the associated cap and can be connected to a primary structure of an aircraft.
  • the inner shell and/or the outer shell has at least one thickened section, in which a wall thickness is greater than that in adjacent sections.
  • the double-walled structure also allows the realization of quite complex shapes, which can include indentations, bulges, uniform or varying curvatures, different curvatures adjoining one another, or the like.
  • arranging a thickening at the relevant points makes sense.
  • the arrangement of thickened sections can be implemented selectively and as required, so that a thickened section is only present where it is needed in order to achieve sufficient stability of the tank system and at the same time limit its weight.
  • spacers of at least one group of spacers intersect in pairs and are connected to one another at their crossing points.
  • connection can be made, for example, by gluing.
  • the group is to be understood as meaning that a subset, which can also be contiguous, of the spacers can intersect in pairs.
  • a single-layer or multi-layer thermal insulation layer can also be arranged on the inside of the outer shell.
  • this could have a foam that does not necessarily have to be provided with load-bearing properties.
  • the single-layer or multi-layer thermal insulation layer could be penetrated individually or it can be pre-drilled at the appropriate positions of the spacers.
  • the tank system according to the invention also has at least one intermediate shell, with at least one separate volume being formed between the inner shell and the at least one intermediate shell and between the outer shell and the at least one intermediate shell.
  • the spacers could then only extend in the individual, separate volumes. It is conceivable that the tank system has an intermediate shell, two or more intermediate shells. The spacers could then extend between the outer shell and the intermediate shell and from the intermediate shell and the inner shell. If there are several intermediate shells, spacers could also extend between two directly consecutive intermediate shells.
  • the arrangement of separate volumes makes it possible to realize, for example, several evacuated spaces that are separate from one another and that connect to one another from the inside to the outside of the tank system and result in an improved lead to thermal insulation. Furthermore, this could also increase security against leaks, failure of the tank system or misuse.
  • two intermediate shells could be provided, which form an outer layer, an inner layer and a core layer, with intersecting spacers being arranged in the outer layer and the inner layer and a reduced number of spacers being provided in the core layer compared to the inner layer and the outer layer.
  • the spacers could not cross, but only extend radially outwards between the intermediate shells.
  • the spacers in the core layer do not necessarily serve to reinforce the tank system, but largely only absorb weight and mass forces. As a result, the heat transport between the inner layer and the outer layer via the core layer can be significantly reduced.
  • the inner layer and the outer layer could also be provided with a hard foam, so that spacers are only provided in the core layer.
  • the inner shell and the outer shell have an integrated line holder in a connection section, which is designed to lead one or more lines into the tank volume in an insulated manner from the outside.
  • the line holder is particularly preferably integrated in one piece, so that the overall shape of the combination of outer sleeve and inner sleeve results in the realization of the line holder.
  • the line holder can have an inwardly extending section which has a peripheral surface which, for example, merges into the inner sleeve and represents an indentation. Spacers that stiffen the line holder can also extend between diametrically opposite sides of the line holder.
  • Several lines can be used to remove the cool medium and/or to Introducing air or another gas can be used.
  • electrical cables or sensors can also be fed through, or accessibility required for maintenance purposes can be provided.
  • the invention also relates to an aircraft, having a fuselage and at least one tank system arranged therein according to the preceding description.
  • the aircraft could also have a hydrogen consuming device that can be coupled to the tank system.
  • the hydrogen consuming device could include, for example, a fuel cell system and/or a hydrogen-operated engine.
  • the tank system could be integrated into the fuselage to support the load.
  • the weight of the aircraft can be optimized as a result, because the fuselage and the tank system are provided together to absorb the loads that arise during operation of the aircraft.
  • a recess for the passage of lines could be arranged between the outer shell of the tank system and a boundary of the fuselage facing the outer shell. This is particularly advantageous in the case of larger tank systems, as this could largely fill out a fuselage cross-section.
  • the recess can be implemented as a gap between the outer shell and the fuselage.
  • the recess could also be provided only locally and extend, for example, along a longitudinal axis of the fuselage in the tank system.
  • FIG. 1 shows a tank system in a cross-sectional view and a detailed section.
  • Figure 2 shows foam between the inner shell and the outer shell which can be detached.
  • FIG 3 shows another tank system in a cross-sectional view and a detailed section.
  • FIG. 4 shows an aircraft with a tank system integrated therein.
  • FIG. 5 shows an aircraft with a modified tank system.
  • Figures 6a and 6b show unit cells of a wall structure.
  • FIG. 7 shows a tank system with a modified wall structure.
  • FIG. 8 shows a wall structure with a core layer.
  • FIG. 9 shows a wall structure that is modified compared to FIG.
  • 10a and 10b show a tank system with a line holder.
  • DETAILED PRESENTATION OF EXEMPLARY EMBODIMENTS 1 shows an exemplary embodiment of a tank system 2 for storing a cool medium.
  • the tank system 2 has an inner shell 4 made of a first fiber-reinforced material, for example a fiber-reinforced plastic, which defines a receiving space 6 for receiving the medium.
  • An outer shell 8 is provided which consists of a second fiber reinforced material and which surrounds the inner shell 4 .
  • the tank system 2 has a cylindrical central part 10, which is supplemented by two approximately hemispherical end caps 12 and 14.
  • spacers 18 are provided which extend between the inner shell 4 and the outer shell 8 and keep them at a predetermined distance.
  • the arrangement of the shells 4 and 8 and the spacers 18 leads to thermal insulation, which limits the heat transport from the receiving space 6 to the outside.
  • the spacers each have a base section 20 at both ends, for example, which is angled to form a main section 22 and runs in the plane of the inner shell 4 or the outer shell 8 .
  • the spacers 18 may consist of a third fiber reinforced material having impregnated fibers which can be pierced through the inner shell 4 and the outer shell 8 and then harden. The fibers can also run in the inner shell 4 and the outer shell 8 and could be folded over several times to pass through the intermediate space there.
  • the materials, i.e. the first fiber-reinforced material, the second fiber-reinforced material and the third fiber-reinforced material can be the same or similar and in particular have the same thermal expansion behavior.
  • a particularly light tank system 2 can be realized with such an arrangement.
  • the foam core 16 can be used in the manufacture of the Support tank system 2.
  • the inner shell 4 and the outer shell 8 are positioned relative to one another by the foam core 16 so that the spacers 18 are driven through the arrangement of inner shell 4, foam core 16 and outer shell 8 and bent over, for example using a suitable tool.
  • a suitable tool For example, this could be realized by a needle device.
  • the foam core 16 is dissolved by heat or suitable chemical compounds (see the right-hand side of FIG. 2), so that at least one coherent volume 24 that can be evacuated can arise.
  • a particularly low level of heat transfer is achieved by extracting air.
  • FIG. 3 shows a tank system 26 which largely corresponds to the tank system 2 and has two transition sections 30 lying radially on the outside, each of which is adjoined by a monolithic structure 28 . These are shown in an enlarged detailed view for better visibility and each surround the end caps 12 and 14 in a ring shape. It can further be seen that the transition section 30 has a particular layer structure in which layers extend between the end caps 12, 14 and the respective monolithic structure 28, and lie on layers extending from the middle part 10 to the respective end cap 12, 14, with further layers extending from the central part 10 to the monolithic structure. All layers are connected to each other and form a kind of flange in the area from the transition section 30 to the monolithic structure 28 . There, the monolithic structure supplements the central part 10 in a largely cylindrical manner.
  • the tank system 26 can thus be easily integrated into a cylindrical or approximately cylindrical fuselage structure.
  • Fig. 4 shows an aircraft 32 with a fuselage 34 and a hydrogen-consuming device 36, indicated here by a box.
  • a tank system 38 is arranged in the fuselage 34 and is flush with an inside of the fuselage 34 tied together.
  • the tank system 38 can be load bearing. In principle, it could be identical to the tank system 2 or 26.
  • the tank system 38 is intended to store cryogenic hydrogen. It would be conceivable to equip a fuselage section of the fuselage 34 with the tank system 38 before the aircraft 32 is finally assembled, so that the fuselage section can provide the largest possible cross section for accommodating the tank system 38 .
  • the hull 34 could also be made of a material that is compatible with the fiber-reinforced materials of the tank system 38, in particular in order to have the same thermal expansion behavior.
  • FIG. 5 also shows an aircraft 32, in which, however, the tank system 38 leaves a recess 40 between the outer shell 8 and a boundary of the fuselage 34 facing the outer shell 8, which is suitable for the passage of lines (not shown).
  • FIG. 6a schematically shows a type of unit cell 42 as the smallest imaginary unit for constructing a tank system according to the preceding figures.
  • the unit cell 42 is to be regarded here as a recurring pattern of an arrangement of spacers 18, the unit cell 42 being connected to a shell or layer of the tank system at opposite ends.
  • the spacers 18 in a unit cell 42 are arranged separately from each other and do not touch.
  • the spacers 18 intersect in pairs and are connected to one another at crossing points 44 .
  • Such a unit cell 46 could have greater strength.
  • the tank system 2 is shown in FIG. 7 , which is modified by arranging a multi-layer insulation 48 on an inside of the outer shell 8 .
  • the multilayer insulation 48 can be designed as at least one additional insulating layer with a plastic film. It is conceivable that it is embodied in a mirroring or reflective manner in order to also additionally reduce heat radiation effects.
  • the at least one further insulating layer can also have a plurality of insulating layers.
  • FIG. 8 shows a section of a tank system 49 in which intermediate sleeves 50 and 52 are arranged between the outer sleeve 8 and the inner sleeve 42 .
  • the spacers 18 are arranged with a crossed framework structure.
  • spacers 60 are arranged in the core layer 58 and only extend in the radial direction between the two between the intermediate shells 50 and 52 .
  • their number is less than the number of spacers 18 in the other two layers, so that a particularly low heat transport can be implemented here.
  • the reduction in the number of spacers is between 10% to 80%, preferably about 50% based on a unit area.
  • a modified tank system 63 can be realized in which no spacers 18 are provided in the outer layer 54 and 56, but only a foam 62, in particular made of a rigid foam.
  • FIG. 10a shows a tank system 70 in which the inner shell 4 and the outer shell 8 have an integrated line holder 66 in a connection section 64, which is designed to lead a number of lines into the tank volume 6 in an insulated manner from the outside. For this purpose, several elongated openings 68 are provided.
  • the line holder 66 is realized by an indentation and constructed completely integrally with the rest of the structure of the tank system 70 . Spacers 18 can also be provided here.
  • the 10b additionally shows a capsule 72 for covering the line holder 66 on an outside of the tank system 70.
  • the capsule 72 can serve as a housing for accommodating pumps, valves, heat exchangers, sensors or other devices.
  • the capsule and line holder are in this example centered to the tank structure.
  • the embodiment according to the invention also enables tank structures and line holder configurations with complex shapes, which can be adapted to the local geometric conditions of the predetermined volume for the integration of the tank structure.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)

Abstract

L'invention concerne un système de réservoir destiné au stockage d'un fluide réfrigéré, présentant une enveloppe intérieure constituée d'un premier matériau renforcé par des fibres, qui définit un espace de réception destiné à recevoir le fluide, une enveloppe extérieure constituée d'un second matériau renforcé par des fibres, qui entoure l'enveloppe intérieure, ainsi que plusieurs entretoises en forme de barres qui sont disposées entre l'enveloppe intérieure et l'enveloppe extérieure et qui sont conçues pour maintenir l'enveloppe intérieure et l'enveloppe extérieure à une certaine distance l'une de l'autre de sorte qu'au moins un espace intermédiaire thermiquement isolant soit créé entre l'enveloppe intérieure et l'enveloppe extérieure, au moins l'enveloppe intérieure empêchant la fuite du fluide à stocker.
PCT/EP2021/086618 2020-12-22 2021-12-17 Système de réservoir pour le stockage de fluides réfrigérés WO2022136183A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP21836197.0A EP4267388A1 (fr) 2020-12-22 2021-12-17 Système de réservoir pour le stockage de fluides réfrigérés

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102020007826.5 2020-12-22
DE102020007826.5A DE102020007826A1 (de) 2020-12-22 2020-12-22 Tanksystem zur Lagerung kühler Medien

Publications (1)

Publication Number Publication Date
WO2022136183A1 true WO2022136183A1 (fr) 2022-06-30

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EP (1) EP4267388A1 (fr)
DE (1) DE102020007826A1 (fr)
WO (1) WO2022136183A1 (fr)

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20050089661A1 (en) * 2003-10-11 2005-04-28 The Boeing Company Cryogenic fuel tank insulation assembly
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