Device for supporting a fluid-circulation duct, and assembly comprising such a device and such a duct

Abstract

A device (20) for supporting a fluid duct (C), comprising: - a link (22) for supporting the duct via two end parts (22a) of the link that are spaced apart from one another in a longitudinal direction and adopting, transversely, a curved shape for supporting a portion (Ca) of the duct, the two end parts (22a) being connected to one another by two intermediate parts of the link that each connect one end (22a1, 22a2) of the two end parts (22a), - two links (24, 26) for fastening the device (20) to an external structure, - two connection elements (28b-d) connecting the supporting link (22) and the fastening links (24, 26) and each traversed by a fastening link and an intermediate part of the supporting link and allowing these links to slide through the connection element.

Description

Description Title of the invention: Support device for a fluid circulation conduit and assembly comprising such a device and such a conduit Technical Field

[0001] This presentation concerns a support device for a fluid circulation conduit. Previous technique

[0002] In aeronautics and the space sector, various fluids (oxygen, hydrogen, helium, etc.) are used which must be transported from one point to another, for example between an engine and a launcher, or between a launcher and its launch pad, by means of circulation conduits for the fluid(s) concerned.

[0003] Such fluid circulation conduits must meet particularly demanding specifications due to the severe operating conditions to which they are subjected. In particular, this type of conduit may have to meet the following requirements (cumulative or not): -the conduit can be relatively long (for example, on the order of 0.3 to 2 meters); -it can carry pressurized or unpressurized fluid depending on the operational phases; -it can carry liquid or gas; -it can have a large diameter and a high mass flow rate (for example, on the order of 250kg / s, or even more); -it can be subjected to severe dynamic stresses; -it may need to accept small displacements of thermomechanical origin, particularly at its two opposite ends which are fixed / attached to different components, themselves connected in a more or less hyperstatic manner, all these components and the elements which connect them having different temperatures as well as different coefficients of thermal expansion; -it may have to accept engine movements / displacements; -it may have to connect different engine parts together or an engine part to a starter part.

[0004] Generally speaking, given these conditions, standard commercial (conventional) products such as flexible hoses made of convoluted metal (corrugated) with metal braids covering their opposite ends are unsuitable for the intended applications. Indeed, when the hose must connect different engine parts or an engine part to a launcher part, its length (for example, approximately 1 meter for a diameter of 15 cm) is such that its first natural frequency (vibration) is too low to prevent high and unacceptable dynamic displacements during operation.

[0005] The use of standard commercial (conventional) flexible hoses is possible, however, when their length is sufficiently small or when they are sufficiently rigid so as not to give rise to excessively high and unacceptable dynamic displacements in operation.

[0006] When it is not possible to use such conventional flexible hoses, it is possible to use cardan lines (with metallic convolutions to contain the pressure and ensure sealing) or assemblies composed of several short flexible hoses connected by sections of rigid lines.

[0007] These solutions are not satisfactory, however, and there is clearly a need in this regard, particularly to allow the use of existing long (conventional) hoses to convey a fluid while reducing the disadvantages described above during dynamic movement or deflection of the hoses in operational conditions. Description of the invention

[0008] One embodiment relates to a support device for at least one fluid circulation conduit, characterized in that the support device comprises: -a so-called support link intended to provide support to said at least one conduit by means of two end parts of the link which are separated from each other along a longitudinal direction X, each end part being able to adopt, in a cross-sectional view relative to the longitudinal direction X, a generally curved shape intended to receive and support a portion of said at least one fluid circulation conduit, the two end portions of the link being connected to each other by two intermediate portions of the link, each intermediate portion connecting one of the two opposite ends of one end portion to one of the two opposite ends of the other end portion, -two so-called fixing links intended to secure the support device via two opposite ends of each fixing link, each of which is intended to be fixed to a structure external to the support device, -at least two so-called connecting elements which are separated from each other along the longitudinal direction X and which ensure the connection between the support link and the fixing links, each connecting element being, on the one hand, crossed by at least one fixing link and at least an intermediate part of the support link and, on the other hand, capable of allowing the sliding of these links through the connecting element.

[0009] The support device allows the said at least one fluid circulation conduit to be supported in two zones separated along its length by means of the two distant end parts of the support link, which allows the first natural frequency to be increased (this frequency is equal to 1 / 2n(k / m) 1 / 2 where k is the stiffness and m the mass of the conduit) of the support device for said at least one fluid circulation conduit, and thus to limit the amplitude of the dynamic response of said at least one conduit when it is subjected to strong dynamic excitations at its ends. In general, the dynamic response of said at least one conduit is reduced to an acceptable level that prevents its deterioration or even rupture. More specifically, the above support device reduces the amplitude of the transverse / lateral displacements of said at least one conduit relative to the aforementioned longitudinal direction to an acceptable level, while also allowing it to accommodate its movements, particularly during relative movements between the structures to which the fastening links are attached (e.g., engine and its starter – particularly in the event of engine steering, or parts of the engine and starter).It should be noted that this at least one conduit can be flexible or rigid. The support device can have a different shape. when it is not functionally connected to at least one conduit, and in particular, its two distant end portions do not necessarily adopt a generally curved (concave) shape in the absence of a conduit. The support device can be used to support one or more separate conduits or conduits physically joined by a casing or fastening system.

[0010] Depending on other possible characteristics: -the support device comprises two pairs of connecting elements, each formed of two connecting elements spaced apart along the longitudinal direction, the two pairs of connecting elements being spaced apart transversely and parallel to each other and to the longitudinal direction, each of the two connecting elements of each pair of connecting elements being crossed, on the one hand, by one of the two fixing links and, on the other hand, by one of the two parallel intermediate parts of the support link; - each connecting element is a ring or a bushing; the shape of each connecting element may be circular or elliptical, or, more generally, of a shape suitable to ensure the sliding of the fixing links in the longitudinal direction and of the support link in the transverse and longitudinal directions; -the support device includes a spacing element arranged between said at least two connecting elements in the longitudinal direction; -the spacing element is chosen from the following elements: a rigid rod longitudinally connecting said at least two connecting elements to each other, and a rigid tube which is crossed, on one side, by one of the two fixing links and, on the other side, by one of the two parallel parts of the support link, the tube having an internal diameter smaller than the diameter of the connecting elements; -a pre-drawn tight tension is applied (before use) in both fixing links (during the assembly / installation of the conduit(s)-device assembly, the fixing links are subjected to tension / tension according to their length before they are each fixed to an external structure); -The support link and fixing links are made of materials such as Kevlar (registered trademark), stainless steel, Inconel (registered trademark).

[0011] Another embodiment relates to an assembly comprising at least one fluid circulation conduit and at least one support device for said at least one fluid circulation conduit, as briefly described above. By way of example, several support devices may be used to support different portions of one or more conduits.

[0012] Depending on other possible characteristics: -the assembly includes a means of protection against deformation of said at least one fluid circulation conduit which is positioned between, on the one hand, each of the two distant end parts of generally curved shape of the support link, according to a cross-sectional view and, on the other hand, each portion of said at least one fluid circulation conduit which is received and supported by the end part concerned; -the means of protection is chosen from the following: a protective strip disposed between each of the two distant end parts of generally curved shape of the support link and each relevant portion of said at least one fluid circulation conduit; a positioning guide having a U cross-section and which is disposed between each of the two distant end parts of generally curved shape of the support link and each relevant portion of said at least one fluid circulation conduit in order to receive the relevant end part of the support link; each of the two sides or branches of the U prevents the conduit(s) from moving laterally and exiting the part forming the bottom of the U and which locally protects the conduit; a sheath of circular cross-section disposed around each of the two distant end parts of generally curved shape of the support link.

[0013] Another embodiment relates to a space vehicle such as a launcher, comprising internal components and at least one assembly of conduit-support devices as briefly described above, said at least one fluid circulation conduit of said at least one assembly connecting two internal components of said space vehicle in a fluidic manner.

[0014] Another embodiment relates to a fluid supply system for an aeronautical or space vehicle, comprising at least one set of conduit(s)-support device(s) as briefly described above. Brief description of the drawings

[0015] The purpose and advantages of this presentation will be better understood upon reading the detailed description below of various embodiments given as non-limiting examples. This description refers to the attached figure pages, on which:

[0016] [Fig. 1 A] Figure 1A represents a possible example of the application of a fluid conduit support device connecting a launcher to its engine, following a side view;

[0017] [Fig. 1 B] Figure 1 B represents a front view of the device in Figure 1;

[0018] [Fig. 1 C] Figure 1 C represents the device of Figure 1 A with an angulation of the motor;

[0019] [Fig. 1 D] Figure 1 D represents the device of Figure 1 B with an angulation of the motor;

[0020] [Fig. 2A] Figure 2A represents a possible embodiment of the support device for figures 1 AD, as seen from the front;

[0021] [Fig. 2B] Figure 2B represents a side view of the support device of Figure 2A;

[0022] [Fig. 2C] Figure 2C represents a cross-sectional view of the support device of figures 2A-B;

[0023] [Fig. 2D] Figure 2D is a partial enlarged view of one of the connecting elements of figures 2A-C linking links of the support device;

[0024] [Fig. 3A] Figure 3A represents a possible embodiment of the support device of figures 2A-D from a front view;

[0025] [Fig. 3B] Figure 3B represents a side view of the support device of Figure 3A;

[0026] [Fig. 3C] Figure 3C represents another possible embodiment of the support device of figures 2A-D from a side view;

[0027] [Fig. 3D] Figure 3D represents yet another possible embodiment of the support device of figures 2A-D from a side view;

[0028] Fig. 4A] Figure 4A represents another possible embodiment of the support device for figures 1 AD, following a cross-sectional view;

[0029] [Fig. 4B] Figure 4B represents a top view of the support device of Figure 4A.

[0030] [Fig. 5] Figure 5 illustrates a possible configuration that involves a damping cushion between load-bearing structures;

[0031] [Fig. 6A] Figure 6A illustrates a first possible configuration of a plurality of conduits supported by a support device such as that of figures 2A-D;

[0032] [Fig. 6B] Figure 6B illustrates a second possible configuration of a plurality of conduits supported by a support device such as that in Figures 2A-D;

[0033] [Fig. 6C] Figure 6C illustrates a third possible configuration of a plurality of conduits supported by a support device such as that in Figures 2A-D;

[0034] [Fig. 6D] Figure 6D illustrates a fourth possible configuration of a plurality of conduits supported by a support device such as that in Figures 2A-D;

[0035] [Fig. 7A] Figure 7A represents another possible example of the application of a fluid conduit support device within a launcher propulsion system;

[0036] [Fig. 7B] Figure 7B represents other possible examples of application of a fluid conduit support device linking a launcher to a ground facility and connecting two internal components of a launcher;

[0037] [Fig. 7C] Figure 7C represents another possible example of the application of a fluid conduit support device linking a ground installation to an aircraft. Description of the implementation methods

[0038] Figures 1A and 1B schematically represent, respectively in side view and front view, an example of an embodiment where a support device A fluid conduit 20 is used to support a fluid conduit C that carries a fluid, such as hydrogen, methane, oxygen, nitrogen, or helium, between a launcher 10 and an engine 12 attached to the latter by a articulated mechanism capable of transmitting a torsional movement of the cardan type 14. The fluid conduit C is a conventional flexible hose of relatively significant length (e.g., one meter), allowing it to connect a part 10a of the launcher 10 to a part 12a of the engine 12. Schematic figures 1C and 1D show, under operational conditions of the launcher-engine assembly, the angular movements that the engine can adopt and that the conduit C must therefore follow while remaining functional and without deteriorating. The dashed lines in figures 1C and 1D illustrate the rest position (without engine angulation) of the conduit C.

[0039] The support device 20, which will be described in more detail in Figures 2A and following, can accommodate these motor angulation movements, as well as limit lateral displacements in dynamic response of the conduit C, particularly in the case of significant dynamic stresses (it should be noted that the device can also limit vertical displacements when the conduit is positioned horizontally). The device 20 provides relatively flexible support for the movements of the flexible conduit C relative to the surrounding supporting structures 10 and 12.

[0040] Figures 2A-2C illustrate a possible embodiment of the support device 20 for conduit C, respectively from the front (conduit C is in the background), side, and transverse views. Although conduit C extends here in a curved manner at rest (when installed and fixed to parts 10a and 12; it should be noted that in other configurations the conduit may extend straight at rest), as illustrated in Figures 1AB, it is possible to consider that locally the conduit extends substantially along a longitudinal direction marked X in Figures 2A-2C (straight conduit).

[0041] The support mechanism 20 mainly comprises: - a support link 22 for the fluid circulation conduit C, - two fastening links 24, 26 that allow the device 20 to be fixed or attached to the surrounding structures (here the launcher 10 and the engine 12), - at least two rings 28a-d or connecting elements (alternatively these The elements can take other forms (rings, etc.) which are spaced apart along the longitudinal direction X and which connect the support link 22 and the fastening links 24, 26. The support link 22 passes through all the rings regardless of their number, while when there are only two rings, the fastening links pass through all of them. When there are four rings, each fastening link passes through only two of the four rings, as will be seen below. The support device 20 and the conduit C together form a functional unit when the device is fixed to the surrounding load-bearing structures and is connected to the conduit by the connecting structure described briefly above and in more detail below. The connecting elements are closed to prevent the links or cables passing through them from coming loose. The links 24 and 26 are simply threaded through the connecting elements 28a-d.

[0042] In the described embodiment, the support device 20 comprises two pairs of rings, each formed by two rings 28a, 28b and 28c, 28d, which are spaced apart (within each pair) along the longitudinal direction X. The two pairs of rings 28a, 28b and 28c, 28d are spaced transversely apart (in the plane of Figure 2C), arranged along the conduit C, and parallel to each other (or globally parallel, i.e., they can accommodate angles on the order of a few degrees between their global alignment directions) and to the longitudinal direction X. The four-ring connecting structure makes it possible to form a support structure for the conduit in the general shape of a cradle with two support zones, as shown in the cross-sectional view of Figure 2C with the support zone 22a.

[0043] The support link 22 is generally rigid overall but can nevertheless exhibit some elasticity without excessive elongation when a preload or prestress is applied to the links 24 and 26. For example, it may be made of Kevlar (registered trademark), stainless steel, or Inconel (registered trademark). The support link 22 (e.g., cable) is closed upon itself and inserted through the four rings 28a-d to form: -two distant end parts 22a, 22b separated from each other along the longitudinal direction X and arranged opposite each other (figs. 2A-B), each of these parts being able to adopt, according to a cross-sectional view (fig. 2C), a general curved shape (general U shape more or less open at its upper part) whose concavity allows to receive and support (in directions perpendicular to the longitudinal direction of the conduit, in particular in the direction of movement F1 on fig. 2C) a portion Ca, Cb of the fluid circulation conduit C; it should be noted that no support is provided to the conduit C in the direction of movement F2 opposite to F1; -two intermediate parts 22c, 22d globally parallel to each other, to the conduit C and to the longitudinal direction X (figs. 2A-B) (a difference of several degrees is conceivable between the two intermediate parts, the conduit and / or the longitudinal direction) and which each connect one of the two opposite ends 22a1, 22a2 of the general curved shape of one 22a of the two end parts 22a, 22b to one of the two opposite ends 22b1, 22b2 of the general curved shape of the other distant end part 22b, respectively at the level of the rings 28a, 28b, for the end part 22c, and at the level of the rings 28c, 28d for the end part 22d (see for example the partial enlarged view of the ring 28a on figure 2D).

[0044] Note that a system for joining the two ends of the support link 22 (by crimping or welding) can be considered. Alternatively, hooks can be fitted to both ends of the support link 22 and hooked together once the link 22 is threaded through the rings. Alternatively, a knot can be tied in the link 22.

[0045] Supporting the conduit in two distinct zones, namely supporting two conduit sections Ca and Cb respectively by the two distant end sections 22a and 22b, allows the support force to be distributed and thus prevents a local concentration of stress on the conduit. Generally, the two end sections 22a and 22b are axially separated from each other by a minimum distance of between two and five times the diameter of the conduit C. The two end sections 22a and 22b are positioned at a distance from the two opposite ends of the conduit(s) that the device supports, and the maximum distance between these two sections depends on the stiffness of the conduit(s) being supported. The greater the stiffness, the closer the two end sections can be placed to each other. These general remarks apply regardless of the embodiment of the invention and its variations.

[0046] Each end part, such as part 22a in figure 2C, extends from one of the rings, here 28b, to the other ring of the other pair which is transversely opposite, here 28d, forming downwards a curvature or concavity (here U-shaped) at the bottom of which is housed a portion (here Ca) of the conduit. The two rings, here 28b, 28d (fig. 2C), are thus arranged vertically at a position (or height) higher than the position (or height) of the bottom of the end part, here referenced 22a (fig. 2C), and of the conduit C. The two rings 28b, 28d are spaced transversely so as not to be directly positioned above (in line with) the conduit C (fig. 2C) and are arranged at the two opposite ends of the end part 22a so as to adopt with the latter an overall U shape whose two branches extend along an angular sector of approximately 60° at most.The transverse spacing between the two rings 28b and 28d is equal to k * diameter of the conduit C (with k between 2 and 4 in the case where the angle is 60°). The same description applies to the other distant end portion 22b with rings 28a and 28c. Furthermore, the minimum spacing between the median plane passing through the two rings 28b, 28d and the median plane passing through the conduit C can be between two and four times the diameter of the conduit in this embodiment.

[0047] Each of the two fastening links 24, 26 has two opposite ends 24a-b, 26a-b illustrated for example in Figure 1B and which are each intended to be fixed (for example by means of rings) to a structure such as the launcher 10 and the motor 12. Each fastening link 24, 26 extends from one end to the opposite end by passing through the two successive rings 28a, 28b of the device 20 by an intermediate part 24c of the link 24 and the two successive rings 28c, 28d by an intermediate part 26c of the link 26. The intermediate part 24c, 26c of each link 24, 26 which passes through the two rings of the same pair extends parallel to the intermediate part 22c, 22d (support link 22) which passes through the same two rings.The links are cables with slight elasticity: excessive elasticity does not provide sufficient stiffness to the assembly of "flexible links + fastening links," and insufficient elasticity reduces the "smoothness" of the support provided by the device according to the embodiment of the invention, in the event of engine steering. Examples of fastening link materials include steel, Inconel, and Kevlar.

[0048] In the described embodiment, the fastening links 24 and 26 can be pre-tensioned (applied and adjusted in a known manner on links or cables, for example, based on prior tests) when they are installed on the supporting structures and connected to the conduit C. Thus, they apply a pre-tension to the conduit C from the moment of installation. When the conduit is pressurized, it tends to deform naturally outwards (and not towards the supporting structures), i.e., in the direction indicated by arrow F1 in Figure 2C, which increases the initial tension in the links 24 and 26. The fastening links are, for example, made of materials such as Kevlar (registered trademark), stainless steel, or Inconel (registered trademark).

[0049] It should be noted that the fastening links 24, 26 and the support link 22, which pass through the rings, are capable of sliding / gliding within them (in other words, a relative sliding movement can occur between the rings and the various links). This allows the support device 20 to adapt, to a certain extent, to the movements of the conduit C and the surrounding movable supporting structures 10 and 12, particularly in the event of engine angulation (in other words, it allows the movement / displacement of the conduit C to be accompanied as smoothly as possible, especially in the event of engine steering). The device 20 can indeed follow certain movements of the conduit C and limit the amplitude of certain movements (e.g., lateral displacements in a direction perpendicular to the directions of movement F1 and F2 in Figure 2C) that could damage the conduit.

[0050] The support device 20 can achieve a minimum ratio of two between the excitation frequency of the launcher assembly 10 and motor 12 and the first natural frequency of the conduit C (once supported by the device of the invention), thereby preventing excessive vibration (unacceptable amplitude of lateral dynamic displacements of the conduit that could damage it). In other words, the device modifies (increases) the first frequency of the conduit C, thereby shifting this first frequency away from the frequency range in which the dynamic excitation levels from the launcher are at their maximum. This results in a reduction of the dynamic amplification factor of the response of the conduit C.

[0051] Figures 3A and 3B are respectively front and side views illustrating an alternative embodiment of the support device of Figures 2A-D in which a spacer element (an element that ensures a minimum distance) is provided between the two rings of the same pair of rings 28a-b and 28c-d along the longitudinal direction X (or along a generally longitudinal direction that is therefore capable of accommodating relative transverse angular deviations) for both pairs of rings. The support device 20' more specifically comprises two spacer elements 30a and 30b parallel to each other and to the conduit C, which thus maintain a minimum distance between the two rings 28a, 28b and 28c, 28d respectively, preventing the two rings of the same pair from moving axially closer to each other.Thanks to maintaining a minimum spacing between the rings, the support forces of the conduit are better distributed and therefore more effective than if the rings were likely to move closer longitudinally to each other.

[0052] As an example (Figs. 3A-B), each spacer element can be a rigid rod 30a, 30b which connects the two rings of the same pair to each other at its two opposite ends, being, for example, fixed (e.g., by welding) to these rings, or even not fixed to the rings. Each rod is, for example, positioned between the two parallel intermediate parts 22c, 24c and 22d, 26c of the links passing through the rings in question.

[0053] Alternatively (Fig. 3C), each spacer element of the support device 20” can be a rigid tube, such as tube 32 in the side view of Figure 3C, which is traversed, on one side, by an intermediate portion of each of the two fastening links, here portion 24c of link 24, and, on the other side, by each of the two parallel intermediate portions of the support link 22, here portion 22c. Tube 32 has an internal diameter that is smaller than the diameter of rings 28a-b so that they cannot penetrate it. An identical tube, not shown, is provided to surround portions 26c and 22d, between rings 28c-d.

[0054] In one embodiment of each of the support devices in Figures 2A-D and 3A-C, the support device 20" may include a means for protecting against deformation of the fluid circulation conduit C. Such a means serves to distribute the contact pressure between, on the one hand, each end part 22a, 22b in general U shape which partially surrounds a portion of conduit Ca, Cb (fig. 2C) and, on the other hand, each corresponding portion of conduit Ca, Cb in contact with an end part in order to avoid, in particular, pinching or puncturing of the conduit C (here a flexible one) by the support link 22 in operational condition of the conduit C. The protection means is more particularly positioned between each end part 22a, 22b of the support link and each portion Ca, Cb of the conduit received in the concavity of the general U shape of the end part concerned and supported by the latter.

[0055] As shown in Figure 3D, the protection means comprises two positioning guides 34, each with a U-shaped cross-section, arranged between each of the two end portions 22a, 22b located away from the support link 22 and each relevant portion Ca, Cb of the fluid circulation conduit C, in order to receive, within the guide, the relevant end portion 22a, 22b. The lateral edges of each guide prevent the relevant portion of the conduit from moving laterally out of the protection zone.

[0056] As alternative solutions (not shown), the means of protection may take the form of: - a protective strip (or reinforcement) placed between each of the two end parts 22a, 22b distant from the support link 22 and each relevant portion Ca, Cb of the conduit C; it should be noted that the strip may suffice in place of the U-shaped positioning guide in the case where a spacer element is placed between the two rings of each pair (figs. 3A-C) and the width of the strip must be sufficient for the link to remain on it under operational conditions of the conduit, in particular in the case of longitudinal or axial displacements of the conduit; - a sheath with a circular cross-section around each of the two end parts 22a, 22b distant from the support link, each sheath thus being in contact with each relevant portion Ca, Cb of the conduit C.

[0057] It should be noted that each of the elements described above can be integrated into the support link 22 or into conduit C, or even be independent of each of them and simply interposed between them at the time of their functional connection.

[0058] As an alternative (not shown), additional links or cables can be attached to the mounting links 24 and 26, along their length, to limit their lateral movement during flight phases when the conduit C is not pressurized and therefore not stiffened or rigidified. These additional links or cables can be attached to the engine or the launcher, or both. It is also possible to connect the two parts of link 24 together, as well as the two parts of link 26, i.e., the parts located above and below the "cradle" formed by the support link 22. It is also possible to connect links 24 and 26 directly to each other.

[0059] According to yet another variant, one or more intermediate damping cushions can be arranged between the duct C and one or more rigid components of the motor. Figure 5 illustrates an example of a possible configuration where such a cushion 50 is positioned between two structures or components 52 and 54, between which a support device 56, similar to any of the devices described above, is placed.

[0060] Each of the support devices described above is particularly simple to set up to support a fluid conduit and also simple to remove (e.g., in case of maintenance).

[0061] It should be noted that several support devices conforming to the above can be used on the same fluid conduit (pipe) carrying fluid between two points. Alternatively, it is also possible to place several devices conforming to the invention on the same pipe C at different locations along the pipe, for example, simply to sufficiently dampen the dynamic movements of the pipe in all directions if it is long.

[0062] Under the operating conditions, each of the support devices described above can behave as described below.

[0063] During cooling phases and under thermomechanical stresses, the length of conduit C can decrease, which has the effect of slightly relaxing the tension in the fixing links 24 and 26, while conduit C remains supported by these links.

[0064] During pressure loading: -the length of conduit C increases, which has the effect of increasing the tension in the fixing links 24 and 26; -duct C moves slightly; -rings 28a, 28b slide slightly along link 24 and rings 28c, 28d slide slightly along link 26; -the general U shape of each end part 22a, 22b becomes slightly more pronounced (the opening of the U closes); -the distance between rings 28a to 28d varies; -the dynamic response of conduit C is limited thanks to the stiffening provided by the device according to the invention.

[0065] During a motor angulation: -conduit C moves; -rings 28a, 28b slide significantly along link 24 and rings 28c, 28d slide along link 26 (the amplitude of the slip depends on the side towards which the motor turns; here we consider that the motor turns on the side which causes the greatest slip at the level of rings 28a-b); -the general U-shape of each end part 22a, 22b changes; -the distance between rings 28a to 28d varies; -the dynamic response of conduit C is limited thanks to the stiffening provided by the device according to the invention.

[0066] According to another embodiment illustrated in Figures 4A and 4B, the support device 40 comprises only two distant rings 42a, 42b (connecting elements), spaced apart along the longitudinal direction X and positioned at the level of the fluid circulation conduit C'. Unlike the other support devices, here the support link 44 has two opposing end portions 44a, 44b, each with a generally curved shape that more completely surrounds the conduit C' than in the previous figures (an open U-shape at an angle of approximately 60°), forming a loop or collar around it (Fig. 4A), and whose two opposite ends join one of the two rings (here 42b for the end portion 44b). As with the previous figures, the support link 44 It also includes two parallel or generally parallel intermediate portions 44c, 44d, each extending from one ring to the other and passing through it to join one of the two opposite ends of the relevant end portion 44a, 44b. As in the previous figures, the support device 40 includes two fastening links 24' and 26', which in this case extend through the same two rings by means of each of their intermediate portions 24'c and 26'c. Thus, the two rings 42a and 42b are each traversed in a sliding manner by the two intermediate portions 24'c and 26'c of the two fastening links and by the two parallel intermediate portions 44c, 44d of the support link 44.

[0067] This configuration offers the same stiffening efficiency as the four-ring configuration when the duct is moved in the direction indicated by arrow F' in Figure 4A (see arrow F1 in Figure 2C). During lateral movement of the duct C' (horizontal displacement), this configuration limits lateral dynamic displacements, but is nevertheless less effective than the four-ring configuration.

[0068] Figures 6A to 6D illustrate different possible configurations of assemblies or systems in which a support device provides support for several fluid conduits (here represented for example by three conduits C1, C2, C3 although this number may differ).

[0069] In Figure 6A, the conduits C1-C3, freely arranged in the cradle formed by the two end sections, including part 22a, are physically separated or free from each other, meaning they can be moved freely relative to one another. In Figure 6B, the conduits C1-C3 are physically joined / grouped together by a link or connecting element 60 (e.g., a Serflex-type link (registered trademark)). In Figure 6C, the conduits C1-C3 are physically connected by a comb-type device 62, which ensures a defined lateral spacing between the conduits. In Figure 6D, the conduits C1-C3 are joined inside an external casing, here a tube that can extend over almost the entire length of the conduits or only along the portion of their length supported by the support device.

[0070] Everything described above, including the various features, functions, and advantages of the previous mode and its variants, applies also to the method of implementation of figures 4A-B, except for technical incompatibility between the methods such as for example the number of rings.

[0071] The fluid circulation duct support devices described above apply to any duct subjected to high dynamic loads and thermomechanical stresses that are likely to induce bending moments, tensile or compressive forces, shear forces, or even torsional moments in the duct. These types of stresses can result from fluid pressures flowing through the duct causing bottom effects of several kilograms to several tons, from temperature variations ranging from the temperature of a cryogenic fluid (20 K) to the temperature of a hot gas (>800 K), and from dynamic excitations due to the engine, the stage (launcher), or wind on umbilicals connecting the stage to the ground facilities of the launch pad.More specifically, the values ​​of thermomechanical stresses depend on the material, the temperature, and the failure mode considered: for the resistance of ducts under direct (non-repeated) stresses, it is preferable to prevent plastic deformation. For the risk of fatigue crack initiation or the risk of crack propagation under dynamic loading (with low or high cycle counts), the level of alternating stress at each permissible cycle depends on the average stress, the material, and the temperature.The severity of the loads on the conduits supported by the device according to the invention results in torsors (tensile and shear forces; bending and torsional moments) whose magnitude depends on the material of the conduits, their support means (including the support devices according to the invention), their boundary conditions, their length, their nature (type of hoses, number of braids), the materials supporting them, their temperature, and the movements of their environment, i.e., the components to which they are attached (e.g., engine steering). They also depend on the magnitude of the dynamic response of the hoses to the stresses arising, on the one hand, from the flow of the fluids they carry and, on the other hand, from the excitation of the components to which they are connected.In general, hoses should not suffer unacceptable or irreversible damage under stress. thermomechanical; damage such as the initiation or propagation of cracks, and plastic deformation of hoses.

[0072] The conduit to be supported / supported can be flexible or rigid as already mentioned above.

[0073] An extended flexible hose and associated support device can replace a costly fluid (drain) line with one or more universal joints. In such a case, the extended flexible hose is attached to the exhaust lines with several Serflex (trademark) type fasteners (attached to the supporting structure, particularly the engine, by inserting one or more cushions as illustrated in Figure 5). Since the exhaust lines are hot during operation, the clamping force exerted by the Serflex (trademark) type fasteners increases.

[0074] In liquid propellant propulsion systems, rigid lines / pipes of small diameters (for example, line diameters of 6, 8, 12, 24...60, 90, and 110 mm) connect different parts of the engine and are sometimes insufficiently supported. This can lead to excessively low dynamic frequencies and therefore excessive lateral dynamic displacements during testing or flight. Using a support device such as one described above helps to limit the amplitude of lateral displacements in such rigid lines to an acceptable level.

[0075] Figure 7A illustrates a possible application of a fluid conduit support device according to the invention within a space launcher engine 70, for example, within a cryogenic propulsion system. Conduits 72, 74, through which one or more fluids flow, connect two internal engine components. Here, two conduits are shown, but a different number of conduits can of course be considered (e.g., one conduit or more than two). The conduits can fluidically connect internal components or constituent elements of the launcher, and in particular its propulsion system, namely, but not limited to, elements of the fuel conditioning system, and / or elements of the fluid pressurization system, and / or constituent elements of the combustion chamber. of the propulsion system's combustion, such as an injection system. In the example shown, fluid conduit 72 connects a fluid pressurization system 78 to an injection system 76, and fluid conduit 74 connects two internal components 80 and 82 of a fuel conditioning system. Each of these fluid conduits can be supported by one or more fluid conduit support devices according to the invention, 84, 86, as described above. The fluid conduit(s) and the support device(s) together form one or more conduit-device assemblies.

[0076] Figure 7B illustrates a possible application of a fluid conduit support device according to the invention between a space launcher 90 and a ground facility 92 (launch pad). More specifically, one or more fluid conduits 94 (filling umbilicals for fluid supply) fluidly connect a lower part 92a of the ground facility 92 to a first stage 90a of the launcher 90, and one or more fluid conduits 96 (filling umbilicals for fluid supply) fluidly connect an upper part 92b of the ground facility 92 to a second stage 90b of the launcher 90. Similarly, two internal components of the first stage 90a of the launcher, for example, an engine 90a1 and a fuel or oxidizer tank 90a2, can be fluidly connected to each other by one or more fluid conduits 98.Each of these fluid conduits 94, 96, 98 can be supported by one or more fluid conduit support devices according to the invention, 100, 102, 104, as described above. The fluid conduit(s) and the support device(s) together form one or more conduit-device assemblies. It should be noted that said at least one conduit-support device(s) assembly 94, 100 is part of a fluid supply system of the space vehicle 90 and that the same is true of said at least one conduit-support device(s) assembly 96, 102. Device 100 is for example fixed to the lower part 92a of the ground installation 92, device 102 is for example fixed to the upper part 92b of the ground installation 92 and device 104 is for example fixed to the first stage 90a of the launcher.

[0077] Figure 7C illustrates a possible application of a fluid conduit support device according to the invention in the aeronautical sector. More Specifically, one or more fluid conduits 110 fluidically connect a ground installation 112 to an aircraft vehicle such as an aircraft 114, including its fuel tank, to supply the aircraft with fluid. The fluid conduit(s) 110 may be supported by one or more fluid conduit support devices according to the invention, 116, as described above. The fluid conduit(s) and the support device(s) together form one or more conduit-device assemblies. It should be noted that said at least one conduit-support device assembly 110, 116 is part of a fluid supply system for the aircraft vehicle 114. The device 116 is, for example, attached to the ground installation 112.

[0078] Although the present invention has been described with reference to specific embodiments, it is evident that modifications and changes can be made to these examples without departing from the general scope of the invention as defined by the claims. In particular, individual features of the various embodiments illustrated / mentioned can be combined in additional embodiments. Therefore, the description and drawings should be considered in an illustrative rather than restrictive sense.

[0079] It is also evident that all the characteristics described with reference to a process are transposable, alone or in combination, to a device, and conversely, all the characteristics described with reference to a device are transposable, alone or in combination, to a process.

Claims

Demands

1. A support device (20; 40) for at least one fluid circulation conduit (C), characterized in that the support device comprises: - a link (22) said to be a support link intended to provide support to said at least one conduit by means of two end portions (22a, 22b) of the link which are separated from each other along a longitudinal direction (X), each end portion being able to adopt, in a cross-sectional view relative to the longitudinal direction (X), a generally curved shape intended to receive and support a portion (Ca, Cb) of said at least one fluid circulation conduit, the two end portions (22a, 22b) of the link being connected to each other by two intermediate portions (22c, 22d) of the link, each intermediate portion connecting one of the two opposite ends (22a1, 22a2, 22b1, 22b2) of an end portion (22a, 22b) to one of the two opposite ends of the other end part (22a, 22b), -two links (24, 26) called fixing links intended to ensure the fixing of the support device (20; 40) by means of two opposite ends (24a, 24b, 26a, 26b) of each fixing link which are each intended to be fixed to a structure external to the support device, -at least two so-called connecting elements (28a-d) which are separated from each other along the longitudinal direction (X) and which ensure the connection between the support link (22) and the fixing links (24, 26), each connecting element being, on the one hand, crossed by at least one fixing link and at least an intermediate part of the support link and, on the other hand, capable of allowing the sliding of these links through the connecting element.

2. Support device according to claim 1, characterized in that the support device (20) comprises two pairs of connecting elements (28a-d), each formed of two connecting elements spaced apart along the longitudinal direction (X), the two pairs of connecting elements being spaced apart transversely and parallel to each other and to the longitudinal direction, each of the two connecting elements of each pair of connecting elements being traversed , on the one hand, by one of the two fixing links (24, 26) and, on the other hand, by one of the two parallel intermediate parts (22c, 22d) of the support link.

3. Support device according to claim 1 or 2, characterized in that each connecting element is a ring or a bushing.

4. Support device according to any one of claims 1 to 3, characterized in that it comprises a spacer element (30a-b; 32) disposed between said at least two connecting elements (28a-d) along the longitudinal direction (X).

5. Support device according to the preceding claim, characterized in that the spacer element is selected from the following elements: a rigid rod (30a-b) longitudinally connecting said at least two connecting elements (28a-d) to each other, and a rigid tube (32) which is traversed, on the one hand, by one of the two fixing links (24, 26) and, on the other hand, by one of the two parallel parts (22c, 22d) of the support link (22), the tube having an internal diameter smaller than the diameter of the connecting elements.

6. Support device according to any one of the preceding claims, characterized in that a tensile preload is applied in each of the two fixing links (24, 26).

7. Support device according to any one of the preceding claims, characterized in that the support link (22) and the fixing links (24, 26) are made of materials such as Kevlar (registered trademark), stainless steel, Inconel (registered trademark).

8. Assembly, characterized in that it comprises at least one fluid circulation conduit (C) and at least one support device (20; 40) for said at least one fluid circulation conduit (C) according to any one of claims 1 to 7.

9. Assembly according to the preceding claim, characterized in that it comprises a means of protection (34) against deformation of said at least one fluid circulation conduit (C) which is positioned between, on the one hand, each of the two distant end parts (22a, 22b) of the support link and, on the other hand, each portion (Ca, Cb) of said at least one fluid circulation conduit which is received and supported by the relevant end part.

10. Assembly according to the preceding claim, characterized in that the means of protection is chosen from among the following elements: - a protective strip placed between each of the two distant end parts of the support link and each relevant portion of said at least one fluid circulation conduit, - a positioning guide (34) having a U-shaped cross-section and which is disposed between each of the two distant end portions of the support link and each relevant portion of said at least one fluid circulation conduit, the positioning guide receiving and holding in position the relevant end portion of the support link, - a sheath with a circular cross-section arranged around each of the two distant end parts of the support link.

11. Space vehicle such as a launcher, comprising internal components and at least one assembly according to any one of claims 8 to 10, said at least one fluid circulation conduit (C) of said at least one assembly connecting two internal components of said space vehicle in a fluidic manner.

12. Fluid supply system for an aeronautical or space vehicle, comprising at least one assembly according to any one of claims 8 to 10.

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