Cryogenic turbopump supply line

Abstract

A cryogenic turbopump supply line (20) comprising a main flow path (21) capable of transporting a cryogenic fluid, and a plurality of secondary flow paths (22) arranged parallel to and around the main flow path (21), the plurality of secondary flow paths (22) being arranged around the periphery of the main flow path.

Description

[Technical Field]

[0001] The present invention relates to a cryogenic turbopump supply line. [Background technology]

[0002] In the field of liquid propellant rockets, thrust is obtained by the combustion of liquid propellants. Therefore, the different engine components operate at temperatures close to the propellant temperature (20 K for LH2, 110 K for CH4, 90 K for LOx). 0K The cooling phase consists of bringing the main components of the engine from ambient temperature to their nominal operating temperature.

[0003] More specifically, in a cryogenic propulsion system, cooling may have the purpose of avoiding at least the following phenomena: cavitation in at least one cryogenic propellant supply pump, which results in pump overspeed and reduced performance; embrittlement of materials due to thermal shock; loss of hardening as a result of uncontrolled thermal gradients; overheating and emanation of bearings; and static and / or dynamic imbalance of rotating parts due to bearing clearances.

[0004] Thus, cooling can be finalized if the functional criteria are met, for example, criteria regarding clearance between certain mechanical parts, criteria regarding wall temperature, criteria regarding the mechanical strength of turbopump parts, or criteria regarding fluid uniformity.

[0005] Fluids used during cooling are limited to this use. In particular, if propellant is used for cooling, it cannot be used to generate thrust, reducing the payload capacity of the rocket. Furthermore, since some engines are reusable or have rapid changes in operating temperature, the duration of the thermal transition phase is an important issue for improving engine and rocket performance.

[0006] In particular, in the early stages of cooling, when the temperature difference between the ambient temperature wall and the propellant reaches a maximum, a gas film is formed that insulates the liquid core wall, vaporizing the propellant (film boiling), which causes undesirable heat transfer.

[0007] In some supply lines, coatings and many additional components are used to reduce the duration of thermal conditioning of the components, these solutions complicate the manufacture and assembly of lines exposed to a wide temperature range, and the coatings also pose a risk of spalling leading to contamination of the secondary circuit. Summary of the Invention [Problem to be solved by the invention]

[0008] Therefore, there is a need for a cryogenic turbopump supply line that reduces the duration of cool-down and reduces the consumption of propellant during cool-down, and that at least partially lacks the drawbacks of known configurations discussed above. [Means for solving the problem]

[0009] The present disclosure relates to a cryogenic turbopump supply line comprising a main flow path capable of transporting a cryogenic fluid and a plurality of secondary flow paths parallel to and arranged around the periphery of the main flow path.

[0010] Such a supply line has the advantage of reducing the volume present around the main flow path, so that due to the large number and volume of flow paths, less mass is exposed to the temperature during cooling, while heat transfer between the main flow path and the surroundings outside the secondary flow paths is reduced. This reduces the amount of propellant used, allowing a reduced volume of material to be heated, limited to the immediate vicinity of the main flow path. Furthermore, the secondary flow paths allow film boiling to be concentrated at the start of cooling using the main flow path, which can then be cooled by better exchange.

[0011] In some embodiments, the secondary flow paths are arranged around the periphery of the primary flow path, in other words, the secondary flow paths are arranged around the entire periphery of the primary flow path.

[0012] In some embodiments, the plurality of secondary flow paths are partially disposed around the primary flow path.

[0013] The phrase "partially around the main channel" should be understood as meaning that the secondary flow paths are arranged on one or more portions of the contour around the main channel, in other words, on one or more non-adjacent segments of the contour of the main channel.

[0014] In other words, the secondary flow paths are arranged on one or more partial contours around the main flow path. The secondary flow paths can then be arranged on one or more portions around the periphery of the main flow path. In the remainder of the description of this invention, the terms "partial contour" and "portion of a contour" have the same meaning.

[0015] In some embodiments, the plurality of secondary flow paths are arranged on a plurality of non-adjacent secondary flow paths.

[0016] In some embodiments, when viewed from a cross-section of the line, at least one portion of the contour passing through the center of the plurality of secondary flow paths may have a ratio R of the length of the contour that does not intersect the secondary flow path to the total length L of the contour that is less than 40%, preferably less than 25%.

[0017] By "contour" is understood the complete contour, i.e. the section that defines the inner and outer parts of the contour. In the case of a supply line, the inner part comprises the main flow path. A part of the contour corresponds to a segment of the contour, i.e. an element of the contour that has at least two distinct and unjoined ends.

[0018] The heat exchange between the secondary channels through the secondary channels is smaller in magnitude than the radial exchange through the spaces between the secondary channels and is comparable to the ratio of the exchange surface when the secondary channels are present to the exchange surface when the secondary channels are absent, which is approximately the ratio of the heat transfer between the radially inner periphery and the radially outer periphery when the secondary channels are present for the same heat transfer when the secondary channels are absent.

[0019] In some embodiments, the multiple secondary flow paths may be discontinuous.

[0020] In this way, the secondary flow paths can act as "backwaters" through which the cryogenic fluid can permeate and build up.

[0021] In some embodiments, the supply line can have a radial orifice for connection between the primary flow path and the secondary flow path.

[0022] These orifices facilitate supplying fluid from the primary flow path to the secondary flow path while restricting circulation of fluid through the secondary flow path, facilitating cleaning or maintenance operations on the line, such as removing residual material after manufacturing or removing residual propellant after use.

[0023] In some embodiments, multiple secondary flow paths may lead to at least one of the upstream and downstream ends of the line.

[0024] This configuration allows for fluid supply to multiple secondary flow paths, facilitating cleaning of the secondary flow paths.

[0025] In some embodiments, the primary flow path and the secondary flow paths may be separated by a strip that is less than 3 mm thick, preferably less than 2 mm thick.

[0026] Such sizing allows the structural integrity of the line to be maintained while limiting the amount of material in the immediate vicinity of the line.

[0027] In some embodiments, the secondary flow path may have a substantially circular cross section.

[0028] A circular shape is preferred to minimize the perimeter of the main flow path, and therefore the exchange surface, for a given cross-sectional area of ​​the main flow path.

[0029] In some embodiments, the cross section of the main flow channel is 50 mm 2 ~700mm 2 Between the 2 ~450mm 2 The surface may have a surface between

[0030] In some embodiments, the gap between two consecutive secondary channels near the peripheral elements of the main channel without ridges may be less than 3 mm, preferably 2 mm.

[0031] Such sizing allows the structural integrity of the line to be maintained while reducing heat transfer.

[0032] In some embodiments, the primary flow path can have a substantially circular cross section.

[0033] In a second embodiment, the main flow channel may have a cross section in the shape of a drop of water, with the base having substantially the shape of an arc of a circle with two extremities from which two connecting segments extend.

[0034] This droplet shape facilitates additive manufacturing processes by reducing the angle of overhanging material, thus limiting the risk of collapse during manufacturing.

[0035] In some embodiments, the secondary flow path may be provided with insulating material.

[0036] The insulating material makes it possible to limit the risk of contamination through the line, for example by preventing the passage of removable particles through the secondary flow path.

[0037] In some embodiments, the insulating material is a specialty epoxy resin for cryogenic applications.

[0038] The present disclosure also relates to a method for manufacturing a supply line, and to a method having at least one manufacturing step by an additive manufacturing method.

[0039] The accompanying drawings are schematic diagrams and are intended primarily to illustrate the principles of the present disclosure.

[0040] In these drawings, identical elements (or portions of elements) are identified by the same reference numerals throughout all figures. Furthermore, elements (or portions of elements) that belong to different exemplary embodiments but have similar functionality are identified in the figures by reference numerals that are incremented by 100, 200, 300, 400, 500, etc. [Brief explanation of the drawings]

[0041] [Figure 1] FIG. 1 is a schematic diagram of a space launcher. [Figure 2] FIG. 2 is a schematic perspective view of the space launcher line of FIG. [Figure 3] FIG. 3 is a cross-sectional view of the line of FIG. [Figure 4A] FIG. 4A is an axial cross-section of a first example of a line. [Figure 4B] FIG. 4B is an axial cross-section of a second example of a line. [Figure 5A] FIG. 5A is a cross-sectional view of a line along axis BB of FIG. 3 during cooling. [Figure 5B] FIG. 5B corresponds to FIG. 5A at a subsequent moment of cooling. [Figure 5C] FIG. 5C corresponds to FIGS. 5A and 5B at a later moment of cooling. [Figure 5D] FIG. 5D corresponds to the end of cooling for the first example line. [Figure 6] FIG. 6 is an isometric perspective view of a line according to a second embodiment. [Figure 7] FIG. 7 is a schematic cross-sectional view of the line of FIG. [Figure 8] FIG. 8A is a cross-sectional view of a line according to a third embodiment. [Figure 8B] FIG. 8B is a cross-sectional view of a line according to one alternative of the third embodiment. [Figure 9] FIG. 9 is a cross-sectional view of a line according to the fourth embodiment. [Figure 10] FIG. 10 is a cross-sectional view of a line according to the fifth embodiment. [Figure 11] FIG. 11 is a cross-sectional view of a line according to the sixth embodiment. DETAILED DESCRIPTION OF THE INVENTION

[0042] In this disclosure, the terms "axial", "radial", "internal", "external" and their derivatives are defined relative to the main axis of the line, the term "axial plane" means the plane passing through the main axis of the line, the term "radial plane" means the plane perpendicular to this main axis, and finally, the terms "upstream" and "downstream" are defined relative to the direction of fluid circulation in the line.

[0043] 1 shows a schematic representation of a rocket 1 comprising at least one tank 10, at least one turbopump 30, and at least one rocket engine 40, which are in communication with each other via a number of lines 20. The tank 10 contains propellant which is supplied to the rocket engine 40 by the turbopump 30 and the lines 20.

[0044] The operating temperature of the turbopump 30 is close to the temperature of the propellant, for example, about 20 K (Kelvin) for liquid dihydrogen (LH2), 110 K for methane (CH4), and 90 K for oxygen.

[0045] A perspective schematic diagram of line 20 is shown in FIG.

[0046] The line 20 may be made of an alloy suitable for cryogenic use, such as, for example, Inconel 718. The material of the line 20 is hereinafter referred to as "the material of the line" or "the interstitial material."

[0047] The line 20 has a major axis AA extending in the main direction of the line 20 .

[0048] The line 20 comprises a main flow path 21 through which the propellant can circulate.

[0049] A plurality of secondary flow passages 22 are arranged around and parallel to the main flow passage 21 .

[0050] For example, the number of secondary flow paths is 10 to 30.

[0051] It is advantageous for the cross section of the line 20 to be uniform along the main axis AA, for example, to limit losses and / or heat conduction to the outside of the line 20. However, the invention is not limited to this embodiment, and the shape and dimensions may vary, for example, when bends are present.

[0052] FIG. 3 shows an example of a cross section of a line 20 along a radial plane.

[0053] The primary flow path 21 and the secondary flow paths 22 have substantially circular cross sections. The secondary flow paths 22 are arranged around the periphery of the primary flow path 21.

[0054] In particular, in cross section, the centres of the secondary channels are located on a circle concentric with the circular outer contour of the main channel 21, this circle being represented by a dashed line.

[0055] The main flow passage 21 has a diameter D, and the secondary flow passage has a diameter d which is smaller than the diameter D.

[0056] The arrangement of the secondary channels 22 around the periphery of the main channel 21 is such that the secondary channels 22 do not intersect with the main channel 21. A distance can therefore be defined between a point on the periphery of the secondary channels 22 and a point on the periphery of the main channel 21. In particular, this distance reaches a minimum value between the point of the secondary channel 22 closest to the center of the main channel 21 and the point of the diametrically opposite secondary channel 22 located on the same radial plane, which corresponds to the distance a represented in Figure 3.

[0057] In other words, in the case of these circular flow paths 21, 22, when viewed in cross section, a ring is defined between the outer contour of the main flow path 21 and the smallest circle concentric and tangent to the secondary flow path 22, this ring having a thickness a.

[0058] Therefore, a circle passing through the center of the secondary flow passage has a perimeter L such that:

[0059]

number

[0060] The secondary channels 22 are separate from one another, and a circle passing through the center of the secondary channels 22 continuously crosses the secondary channels 22 and the interstitial material of the line 20. A ratio R is defined that corresponds to the ratio of the perimeters of the circles that intersect with the interstitial material of the line 20. In other words, the ratio R is the sum of the distances b between the contours of the secondary channels 22 while following the circle, divided by the perimeter L of the circle. This gap b between two consecutive secondary channels 22 is less than 3 mm, and preferably less than 2 mm.

[0061] If the number of secondary channels is more than 10, the distance b between two secondary channels 22 while following the circle is equal to the distance b between the perimeters of the secondary channels 22.

[0062] The line dimensions are such that the ratio R is less than 40%, preferably less than 25%.

[0063] Because heat conduction through the gap material of line 20 is approximately two orders of magnitude greater than conduction through the secondary flow passage containing the gas mixture, reducing this ratio R can reduce heat conduction between the main flow passage 21 and the exterior of line 20. In particular, because of the order of magnitude of conduction, heat conduction between the main flow passage 21 and the exterior of line 20 is comparable to heat conduction through the gap material of line 20. Therefore, because heat conduction is proportional to the ratio R, a ratio R of 25% divides the thermal resistance of line 20 by four, thereby reducing the mass to be cooled and the duration of cooling as well as the amount of propellant consumed for cooling.

[0064] The cross section of the main flow path 21 is 50 mm 2 ~700mm 2 Between the 2 ~450mm 2 In particular, in the case of a circular cross section, this corresponds to a diameter of the main channel 21 which is preferably comprised between 10 mm and 24 mm, and between approximately 8 mm and 30 mm.

[0065] The thickness a of the ring is less than 3 mm, preferably less than 2 mm.

[0066] Three examples of secondary flow paths are described in relation to FIGS. 4A and 4B, which represent cross sections along an axial plane whose intersection with the radial plane of FIG. 3 is represented by axis BB.

[0067] 4A is a schematic diagram of a line 20 in which the secondary flow paths 22 are discontinuous, with an interstitial space 23 between two consecutive flow paths located on the same axis, which prevents communication between two secondary flow paths 22 on the same axis.

[0068] As shown in FIG. 4A, multiple secondary flow paths 22 may also communicate with at least one of the upstream and downstream ends of line 20, thereby allowing propellant to enter some of the secondary flow paths 22.

[0069] FIG. 4B is a schematic diagram of line 20, in which multiple radial orifices 24 are provided between main flow path 21 and secondary flow path 22 to allow circulation of fluid between main flow path 21 and secondary flow path 22.

[0070] These three exemplary embodiments are compatible and can be implemented independently of each other.

[0071] In particular, when at least one of the three exemplary embodiments is used, the propellant can fill the secondary flow passage 22. Examples of axial cross sections of such a line 20 are described in relation to Figures 5A, 5B, and 5C, which present three successive cooling stages in this order, and Figure 5D, which shows the end of cooling for a line having a secondary flow passage 22 with a gap space 23. The liquid propellant is represented by a dotted filling pattern, and the gap material of the line 20 is represented by a continuous diagonal pattern. The gas phase is represented by a flat surface. The arrows indicate the direction of circulation towards the downstream portion of the propellant.

[0072] 5A shows the first cooling stage when the liquid has just penetrated the main and secondary flow channels 21 and 22. The temperature gradient is high and the surfaces of the flow channels are still hot compared to the cryogenic temperature of the propellant. A vapor layer that is unfavorable for heat exchange then forms between the flow channels and the propellant, while the downstream portion of the propellant breaks down into droplets.

[0073] Subsequently, as shown in Figures 5B and 5C, the presence of propellant in the secondary flow path 22 can accelerate the heating of the ring located between the main flow path 21 and the secondary flow path 22, thereby reducing the temperature difference between the flow path and the fluid, and therefore enabling the propagation of the liquid throughout the entire length of the line 20.

[0074] 5D, the secondary flow channels 22 can be filled with propellant, while the interstitial spaces 23 prevent the circulation of the propellant over the entire length of the secondary flow channels 22, acting as a "backwater" where the propellant stagnates and gradually vaporizes. This allows for easy cooling around the secondary flow channels 22, but also ensures thermal insulation of the main flow channels 21 in the event that the propellant contained in the secondary flow channels 22 vaporizes. The propellant can then circulate in the main flow channels 21 while remaining mainly in the liquid phase, which corresponds to the end of cooling.

[0075] The secondary flow passage 22 may also be filled with an insulating material, such as a special epoxy resin for cryogenic applications.

[0076] A second embodiment line is presented in connection with FIGS.

[0077] FIG. 6 shows a perspective view of a line 120 in which the main channel 121 has a drop-shaped cross section, i.e. the base has a substantially arc-shaped end where the two joining segments are located.

[0078] The circular secondary channels 122 are arranged so that their centers lie on a contour having a shape similar to that of the main channel 121 .

[0079] The ratio R is then defined along a contour passing through the center of the secondary channel 122 while the cross section of the line 120 has a strip of thickness a between the main channel 121 and the secondary channel 122 .

[0080] The lines 20, 120 may be implemented by additive manufacturing methods.

[0081] In particular, the shape of the water droplets makes it easier to carry out the powder bed fusion method, while the communication between flow path 121 and flow path 122 and the communicating secondary flow path 122 make it easier to remove residual powder.

[0082] In the lines of the first and second embodiments, the secondary flow passages 22, 122 have been represented as a band around the outer periphery of the main flow passages 21, 121.

[0083] The third embodiment of the line will now be described with reference to Figures 8A-8B.

[0084] The third embodiment is a modification of the first embodiment, and common elements will not be described again.

[0085] The line 220 of the third embodiment differs from the line 20 of the first embodiment in that the secondary flow passages 222 are arranged around the periphery of the main flow passage on a partial contour around the main flow passage.

[0086] As shown in FIGS. 8A and 8B, the line 220 has the same arrangement of secondary flow paths 222 as the line 20 of FIGS. 2 and 3 in the lower half of the line 220, while the upper half does not have secondary flow paths 222.

[0087] On the partial contours presenting the secondary flow paths 222, the secondary flow paths 222 can then, as described above, act as thermal insulation for the main flow path 221. This thermal insulation function is maintained over the entire partial contour of the secondary flow paths 222.

[0088] Such an arrangement allows for local tuning of the thermomechanical performance of the line, as will be explained in more detail in connection with the embodiment of FIGS.

[0089] It will be appreciated that the definitions of the contour length L and the ratio R defined above for the entire contour can be generalized to the placement of secondary flow passages 222 on a partial contour.

[0090] The portion of the contour considered is then the portion of the contour located between the centers of the secondary flow paths 222 located at the tips of the partial contour, passing through the centers of the secondary flow paths 222 located between the centers of the secondary flow paths 222 at the tips of the partial contour.

[0091] The length L of the partial contour is represented in the cross-sectional views of Figures 8A and 8B.

[0092] FIG. 8B shows a cross-sectional view of one alternative to the line of FIG. 8A, in which the partial contour in which the secondary channels 222 are located is longer and has more secondary channels 222 .

[0093] Note that the alternatives of Figures 8A and 8B correspond to the lines of Figure 3, with some secondary flow paths 222 removed and others retained in the same position.

[0094] Thus, although the dimensions a, b, d and D are the same, the ratio R is the same for the alternatives of Figures 3, 8A and 8B because the variation in length L between these alternatives is compensated for by the variation in the number of secondary flow paths.

[0095] It is understood that a line can have secondary flow paths disposed across more than one portion of the contour. Two distinct, non-adjacent portions of a contour are characterized when two consecutive secondary flow paths have a gap b that is at least three times, and preferably twice, the gap b between two consecutive secondary flow paths in the same portion of the contour. If the gaps b are different, the criterion for distinguishing between two distinct, non-adjacent portions of a contour can be based on the minimum gap, maximum gap, median gap, or average gap between two consecutive secondary flow paths.

[0096] It will be appreciated that the definition of contour length L and associated ratio R can also be generalized to lines having secondary flow paths formed over several distinct and non-adjacent portions of the contour by defining a partial contour length and partial ratio for each of the partial contours of the line.

[0097] An example of a line having multiple sub-contours is described in connection with FIG.

[0098] It will be appreciated that the definition of contour length L and associated ratio R can also be generalized to lines having secondary flow paths formed on several distinct and non-adjacent portions of the contour by defining a partial contour length and partial ratio for each of the partial contours of the line.

[0099] 9 and 10 show lines of the fourth and fifth embodiments, respectively.

[0100] In the fourth embodiment of Figure 9, the line 320 is attached to a volume 330. This embodiment can be implemented according to other examples, for example, to limit the space occupied by the line, or to improve its stability, or both at the same time.

[0101] Due to the presence of volume 330, the thermal inertia increases locally in the vicinity of the main flow path 321 of line 320, thereby resulting in a greater consumption of propellant for cooling line 320. Furthermore, the presence of secondary flow paths 322 in the vicinity of the interface between the part of line 320 outside volume 330 and the part integrated in volume 330 may weaken line 320, which is subjected to high mechanical stresses during the cooling phase.

[0102] In response to this increase in thermal inertia, the secondary flow passage 322 can then be positioned on a partial contour corresponding to a position located near the volume 330 .

[0103] This placement of the secondary flow path 322 allows for improved thermal performance of the line 320 near the volume 330, while maintaining satisfactory mechanical performance by not having the secondary flow path 322 in a position on the line 320 away from the interface between the portion of the line 320 outside the volume 330 and the portion of the line 320 integrated into the volume 330.

[0104] Such an arrangement then makes it possible to improve the thermal behavior of the line 320 by locally adapting the cooling duration, which also allows for homogenization of the cooling of the line 320.

[0105] 10, an additional volume 430 is provided. This embodiment differs from the fourth embodiment in that the volume 430 forms part of the line 420.

[0106] Similar to the fourth embodiment of FIG. 9, the secondary flow path 422 is located adjacent to the volume 430 .

[0107] The volume 330, 430 is described as adding material external or internal to the line 320, 420, which results in increased thermal inertia in the vicinity of the main flow path 321, 421. It will be understood that the volume 330, 430 broadly refers to any element that causes degradation of the thermal performance of the line, including but not limited to localized changes in the material or the presence of a heat source such as an electronic cable.

[0108] The sixth embodiment of FIG. 11 corresponds to the embodiment of FIG. 10, with an additional partial contour located away from the volume 530.

[0109] The addition of an additional partial contour makes it possible to improve the thermal behavior of the line 520, especially at positions away from the volume 530.

[0110] In the embodiment of Figures 8 and 9, the line 520 does not have a secondary flow path 522 at the location of the contour of the line 520 that is located at the interface between the portion of the line 520 outside the volume 530 and the portion of the line that is integrated into the volume 530.

[0111] The absence of secondary flow paths 522 at these locations then allows for mechanical reinforcement of lines 520 there.

[0112] While the present invention has been described with reference to certain exemplary embodiments, it is obvious that modifications and variations can be made to these examples without departing from the general scope of the invention as defined by the scope of the claims. In particular, individual features of different illustrated or mentioned embodiments can be combined in additional embodiments. The specification and drawings are therefore to be considered in an illustrative rather than a restrictive sense.

[0113] In particular, the above features are not limited to circular lines, but are also applicable to any other line shape, for example, water drop shaped lines as mentioned above.

[0114] 11 presents two partial contours for which the parameters R, L, a, b, and d are identified and indexed as R1, L1, a1, b1, d1 and R2, L2, a2, b2, d2, it being understood that in practice each partial contour can be dimensioned independently. The present invention also includes the following inventions. A first aspect of the present invention is In the cryogenic turbopump supply line, The cryogenic turbo pump supply line a main flow path capable of transporting a cryogenic fluid; a plurality of secondary flow paths parallel to and disposed about a periphery of the periphery of the primary flow path, the plurality of secondary flow paths being discontinuous. A second aspect of the present invention is The plurality of secondary flow paths are arranged around the main flow path, and are a cryogenic turbopump supply line in a first embodiment. A third aspect of the present invention is The plurality of secondary flow paths are arranged partially around the main flow path, in a first embodiment, as a cryogenic turbopump supply line. A fourth aspect of the present invention is A supply line in any of the first to third aspects, wherein in cross section, at least one portion of the contour passing through the center of the plurality of secondary flow paths has a ratio of the length of at least one portion of the contour that does not cross the secondary flow path to the total length of at least one portion of the contour that is less than 40%, preferably less than 25%. A fifth aspect of the present invention is The supply line is the supply line according to any one of the first to fourth aspects, which has a connecting radial orifice between the main flow path and the secondary flow path. A sixth aspect of the present invention is The supply line according to any one of the first to fifth aspects, wherein the plurality of secondary flow paths communicate with at least one of an upstream end and a downstream end of the supply line. A seventh aspect of the present invention is The supply line according to any one of the first to sixth aspects, wherein the main flow path and the plurality of secondary flow paths are separated by a strip having a thickness of less than 3 mm, preferably less than 2 mm. An eighth aspect of the present invention is The secondary flow path is the supply line according to any one of the first to seventh embodiments, which has a substantially circular cross section. A ninth aspect of the present invention is a method for manufacturing a semiconductor device comprising: The cross section of the main flow path is 50 mm 2 ~700mm 2 , preferably 75 mm 2 ~450mm 2 The supply line according to any one of the first to eighth embodiments has a surface between: A tenth aspect of the present invention is a method for manufacturing a semiconductor device comprising: A supply line according to any one of the first to ninth aspects, wherein the gap between two consecutive secondary flow paths near a contour element of the main flow path without a ridge is less than 3 mm, preferably 2 mm. An eleventh aspect of the present invention is a method for manufacturing a semiconductor device comprising: The main flow path is the supply line according to any one of the first to tenth aspects, which has a substantially circular cross section. A twelfth aspect of the present invention is a method for manufacturing a semiconductor device comprising: The main flow path is a supply line in any one of the first to eleventh aspects, having a cross section in the shape of a water droplet, with the base substantially in the shape of an arc of a circle having two apexes from which two connecting segments extend. A thirteenth aspect of the present invention is a method for manufacturing a semiconductor device comprising: The supply line according to any one of the first to twelfth aspects, wherein the secondary flow path is provided with an insulating material. A fourteenth aspect of the present invention is a method for manufacturing a semiconductor device comprising: 13. The supply line according to claim 13, wherein the insulating material is a special epoxy resin for cryogenic applications. A fifteenth aspect of the present invention is a method for manufacturing a semiconductor device comprising: A method for manufacturing a supply line according to any one of the first to fourteenth aspects, comprising at least one manufacturing step by an additive manufacturing method.

Claims

1. In the cryogenic turbopump supply line, The cryogenic turbo pump supply line a main flow path capable of transporting a cryogenic fluid; a plurality of secondary flow paths parallel to and disposed about a periphery of an outer periphery of the primary flow path, each secondary flow path including an interstitial space providing axial discontinuities therebetween.

2. The cryogenic turbopump supply line of claim 1 , wherein the plurality of secondary flow paths are arranged around the main flow path.

3. The cryogenic turbopump supply line of claim 1 , wherein the plurality of secondary flow paths are partially disposed around the main flow path.

4. 4. The supply line according to claim 1, wherein in cross section, at least one portion of a contour passing through the centers of the plurality of secondary flow paths has a ratio of a length of the at least one portion of the contour that does not intersect the secondary flow path to a total length of the at least one portion of the contour that is less than 40%.

5. A supply line according to any one of claims 1 to 4, wherein the supply line has a connecting radial orifice between the main flow path and the secondary flow path.

6. The supply line according to any one of claims 1 to 5, wherein the plurality of secondary flow paths communicate with at least one of an upstream end and a downstream end of the supply line.

7. A supply line according to any one of claims 1 to 6, wherein the main flow path and the plurality of secondary flow paths are separated by a strip having a thickness of less than 3 mm.

8. A supply line according to any preceding claim, wherein the secondary flow path has a substantially circular cross section.

9. The cross section of the main flow path is 50 mm 2 ~700mm 2 9. The supply line according to claim 1, having a surface area of ​​between 0.1 and 0.5 mm.

10. A supply line according to any one of the preceding claims, wherein the gap between two successive secondary flow paths in the vicinity of an element of the profile of the main flow path is less than 3 mm.

11. A supply line according to any preceding claim, wherein the main flow path has a substantially circular cross section.

12. 2. The supply line of claim 1, wherein the main flow path has a cross section in the shape of a drop of water, the base of the main flow path having substantially the shape of an arc of a circle with two extremities from which two joining segments extend.

13. A method for manufacturing a supply line according to any one of claims 1 to 12, comprising at least one manufacturing step by an additive manufacturing method.

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