FLUID PASSAGE SYSTEM FOR A BULKHEAD OF A TURBOMACHINE AND TURBOMACHINE COMPRISING SUCH A SYSTEM

Abstract

The invention relates to a fluid passage system (100) for a partition of an aircraft turbomachine, comprising a plate (110) configured to be fixed to said partition and characterized in that: - the plate (110) comprises several fluid passage channels, the channels being joined at least two by two; - the peripheral wall of each channel extends on either side of the plate and to form a first pipe (130) and a second pipe (140); and - the plate (110), the first and second pipes (130, 140) form a single piece. Figure for the abstract: Figure 4

Description

Title of the invention: FLUID PASSAGE SYSTEM FOR A BULKHEAD OF A TURBOMACHINE AND TURBOMACHINE COMPRISING SUCH A SYSTEM Technical field

[0001] The invention relates to a fluid passage system for a partition of a turbomachine for an aircraft. The invention also relates to a turbomachine, equipped with such a fluid passage system as well as a method of manufacturing such a fluid passage system.

[0002] The invention finds applications in the field of aeronautics. Prior art

[0003] Aeronautical turbomachines are conventionally constituted, from upstream to downstream in the direction of gas flow, of a fan, one or more compressor stages, for example a low pressure compressor and a high pressure compressor, a combustion chamber, one or more turbine stages, for example a high pressure turbine and a low pressure turbine, and a gas exhaust nozzle. These various elements are generally contained in casings.

[0004] Many constituent elements of the turbomachine generate, consume, transport or contain fluids such as hydraulic fluids (water, oil) or fuel. The turbomachine also includes pipes in which these fluids circulate. Such pipes are used, for example, to supply hydraulic circuits for controlling landing gear, flaps on the wings of the aircraft (in the case of an airplane) or any other accessory of the aircraft...

[0005] Such a turbomachine is generally equipped with at least one means for passing fluids from the engine fluids in order to transfer fluids from one constituent element of the turbomachine to another, in particular via at least one pipe, also called a service line, and / or in order to avoid an accumulation of these fluids in the event of a leak and a disruption of the operation of the engine.

[0006] In the current technique, each individual pipe or conduit is generally routed from individual constituent elements of the turbomachine to other constituent elements, or even to the outside of the turbomachine, by crossing partitions of the turbomachine separating distinct spaces thereof. These distinct spaces are generally fire zones which are segregated from each other and the pipes passing from one zone to another are fixed in the arms of the casings for example and the sealing at the arms is ensured either by baffles or by joints. Each of the pipes is generally attached to a support structure positioned inside the turbomachine and fixed to a bulkhead to prevent unwanted movement.

[0007] To ensure the passage of the partition, many parts are thus necessary, consequently many references are to be managed in nomenclature. In addition, a sealing zone must be provided at the level of the passage of the partition.

[0008] The objective of the present invention is to overcome at least some of the problems mentioned in the above. In particular, the present invention proposes an improvement to this technology which is at the same time simple, effective and economical, in particular allowing a saving in parts, compactness and mass for the passage of the partitions of a turbomachine. Summary of the invention

[0009] For this purpose, the invention relates to a fluid passage system for a partition of a turbomachine, in particular an aircraft partition, comprising a plate configured to be fixed to said partition of the turbomachine. According to the invention, the plate comprises several fluid passage channels extending between a first face and a second face of the plate, each passage channel being delimited by a peripheral wall and being attached to at least one other passage channel. Furthermore, according to the invention, for each channel, the peripheral wall extends from the first face of the plate to form a first pipe to a first free end and extends from the second face to form a second pipe to a second free end opposite the first free end. Furthermore, according to the invention, the first pipes form a first assembly comprising a first cylindrical portion extending from the first face of the plate in which each first pipe is parallel and attached to at least one other first pipe and the second pipes form a second assembly comprising a second cylindrical portion extending from the second face of the plate in which each second pipe is parallel and attached to at least one other second pipe. And, according to the invention, the plate, the first and second pipes form a single, single-piece part.

[0010] Thus, the invention proposes a single-piece fluid passage system, i.e. formed mainly from a single part made with continuity of material. Indeed, a single part combines the functions of supporting the pipes to the partition, sealing and the pipes themselves. The invention thus makes it possible to reduce the number of parts required to cross the partition via the easements and consequently the number of references in the nomenclature to be managed.

[0011] In addition, it makes it possible to simplify the sealing system for the passage of the services through the partition(s).

[0012] The invention also makes it possible to obtain a system having the smallest possible dimensions and a set of pipes that is as compact as possible when crossing the partition(s) than with current solutions and therefore makes it possible to optimize the pressure losses in the aerodynamic vein.

[0013] Thus, thanks to the invention, a reduction in the master torque of the fluid passage system is ensured, allowing this more compact integration. The invention makes it possible to reduce the axial length of the structure carrying the pipes of the fluid passage system but above all the thickness of this structure. The term "master torque" means the section perpendicular to the flow of the flows. In other words, the master torque is a dimension which corresponds to the length of the pipe / support assembly framed by the flow of the flows of the engine. Indeed, the first pipes, the second pipes and the channels of the plate are separated by a single wall unlike the state of the art where two walls are spaced from each other with a minimum of play. In other words, there is a pooling of walls between the different pipes / channels.This wall is not very thick compared to that of the state of the art, it is then possible to reduce the master torque of the system so as to make it substantially correspond to the space occupied by the channels of the plate. With a reduced master torque, the system for passing fluids through a partition also presents a gain in compactness and a gain in mass thus contributing to lightening the turbomachine intended to be equipped with such a system according to the invention.

[0014] The fluid passage system according to the invention may comprise one or more of the following characteristics, taken in isolation from one another or in combination with one another in all technically possible combinations: - the fluid passage channels of the plate are parallel to each other between the first face and the second face of the plate; - for each fluid passage channel of the plate, at least a part of the peripheral wall of said channel is tangent to a part of the peripheral wall of another fluid passage channel; - in the first portion of the first set and for each first pipe, at least a part of the peripheral wall of said first pipe is tangent to a part of the peripheral wall of another first pipe; and in the second portion of the second set and for each second pipe, at least a part of the peripheral wall of said second pipe is tangent to a portion of the peripheral wall of another second pipeline; - the first free end of each first pipe is configured to be fluidically connected with a component of the turbomachine and the second free end of each second pipe is configured to be fluidically connected with another component of the turbomachine; - each first free end and each second free end are equipped with a fluid connector, preferably produced during the manufacture of the assembly or added by welding; - the first cylindrical portion of the first assembly extends in a direction substantially perpendicular to the first face of the plate and / or the second cylindrical portion of the second assembly extends in a direction substantially perpendicular to the second face of the plate; - the fluid is water, oil or fuel; - the plate has side edges, with the channels arranged between the side edges.

[0015] The invention also relates to an aircraft turbomachine, comprising a partition equipped with a fluid passage system according to the invention and as described previously.

[0016] The invention also relates to a method for producing a fluid passage system according to the invention and as described previously, the fluid passage system being produced by additive manufacturing. Brief description of the drawings

[0017] The present invention will be better understood and other details, characteristics and advantages of the present invention will appear more clearly on reading the description of a non-limiting example which follows, with reference to the appended drawings in which: - [Fig.l] represents a schematic view in axial (or longitudinal) section of an aircraft propulsion unit, in particular a turbomachine, to which the invention applies; - [Fig.2] is an exploded schematic view of a fluid passage system for partition passage according to the state of the art; - [Fig.3] is a schematic perspective and assembled view of the fluid passage system of [Fig.2]; - [Fig.4] is a schematic perspective view of a fluid passage system for a partition of a turbomachine according to the invention;

[0018] - [Fig.5] is a schematic top view of the fluid passage system of the [Fig.4] ; - [Fig.6] is a sectional view of the fluid passage system along plane AA of [Fig.5]; - [Fig.7] is a sectional view of the fluid passage system along plane BB of [Fig.6]; and - [Fig.8] is a sectional view in the plane of the plate of the fluid passage system of [Fig.4].

[0019] An exemplary embodiment of a fluid passage system for a partition of a turbomachine is described in detail below, with reference to the attached drawings. This example illustrates the characteristics and advantages of the invention. It is however recalled that the invention is not limited to this example.

[0020] In the figures, presented for information purposes and in no way limiting the invention, identical elements are identified by identical references. For reasons of readability of the figures, the size scales between elements represented are not respected. Description of the embodiments

[0021] The invention applies to a turbomachine intended to be mounted on an aircraft, such as an airplane or a helicopter. The turbomachine may be a turboshaft engine, a turbojet, for example a turbomachine equipped with a ducted fan (turbofan) or a turboprop, for example a propulsion unit equipped with an unducted propeller ("open rotor", "USF" for "Unducted Single Fan" or "UDF" for "Unducted Fan").

[0022] [Fig. 1] represents an example of such an aircraft turbomachine 10. In the illustrated example, the turbomachine is a double-flow, double-spool turbomachine which has a longitudinal axis C parallel to the axis X.

[0023] In all of the figures, the X direction designates the direction of the C axis of the turbomachine, and the Y and Z directions are two directions orthogonal to each other. Upstream and downstream refer to the main flow direction of the flow in the turbomachine.

[0024] In a known manner, the turbomachine 10 comprises from upstream to downstream, with reference to the direction of flow of the gases (see arrows), an air inlet 20, a low-pressure compressor 22, a high-pressure compressor 24, an annular combustion chamber 26, a high-pressure turbine 28 and a low-pressure turbine 30.

[0025] The high-pressure turbine 28 is connected to the high-pressure compressor 24 by a high-pressure shaft so as to form a high-pressure body, while the low-pressure turbine 30 is connected to the low-pressure compressor 22 by a low-pressure shaft so as to form a low-pressure body, so that each turbine drives the associated compressor in rotation around the axis of the turbomachine X under the effect of the thrust of gases from the combustion chamber 26.

[0026] The turbomachine 10 further comprises, upstream of the low-pressure compressor 22, a fan 32 which is here arranged directly downstream of an air inlet cone. The fan 32 comprises a ring of fan blades 34 rotating around the axis C of the turbomachine. The fan 32 is here shrouded by a nacelle 36.

[0027] Furthermore, in the illustrated example, the turbomachine 10 defines a primary vein VI intended to be crossed by a primary flow F1, as well as a secondary vein V2 intended to be crossed by a secondary flow F2 located radially outwards relative to the primary flow. The flow F of the fan is divided at the level of a flow separation nozzle 40 of an intermediate casing 42. The intermediate casing 42 is usually interposed between the low pressure 22 and high pressure 24 compressors.

[0028] In operation, air flows through the fan 32 and a first part of the air flow, the primary flow F1, is routed through the low pressure compressor 22, where the primary air flow F1 is compressed, then the high pressure compressor 24 where the primary air flow F1 is compressed to a higher pressure level and sent to the combustion chamber 26. The hot combustion products from the combustion chamber 26 are used to drive the high pressure 28 and low pressure 30 turbines and thus produce part of the thrust of the turbomachine 10 (about 20%). The other part of the thrust comes from the secondary flow (about 80%).

[0029] Several types of fluids circulate in the turbomachine 10, in particular oil for lubricating the bearings of the rotating parts, water which can be sucked in by the ventilation scoops or formed by condensation on the engine, fuel, aircraft hydraulic fluid such as Skydrol, hydrogen, nitrogen, etc.

[0030] In operation, these fluids are conveyed to the various associated elements of the turbomachine by pipes, also called services. These fluids are either brought from outside the turbomachine in order to supply the various elements which constitute it, or from one constituent element of the turbomachine to another, or from one constituent element to the outside of the turbomachine by a fluid passage mast in order to evacuate them.

[0031] For this purpose, certain pipes must pass through one or more partitions from their starting point to their arrival point. These partitions make it possible to separate two distinct spaces of the turbomachine. For example, a nacelle separates the interior of the turbomachine from the exterior thereof, an intermediate casing makes it possible to separate a first space housing first components of the turbomachine using fluids from a second space housing other components of the turbomachine using the same fluids or the fluids generated / supplied by the first components.

[0032] We now refer to Figures 2 and 3 which illustrate the state of the art. [Fig.3] is a view of a fluid passage system 100A through a partition while [Fig.2] is an exploded view of it in order to better visualize the different parts that constitute it. The partition separates a first space and a second space of the turbomachine.

[0033] The fluid passage system 100A comprises an elongated support 110A. The support 110A comprises a first longitudinal end 112A and a second longitudinal end 113A, each intended to be fixed to the partition to be crossed.

[0034] The fluid passage system 100A comprises a central portion 114A arranged between the first longitudinal end 112A and the second longitudinal end 113A. The central portion 114A has a first face 115A facing the first space of the turbomachine and a second face 116A facing the second space of the turbomachine. A through orifice 111A is provided in the central portion 114A for the passage of pipes. In the illustrated example, three pipes 120A are shown. Of course, there may be fewer pipes or more pipes.

[0035] The pipes 120A extend between a first end 122A arranged in the first space and a second end 123A arranged in the second space of the turbomachine. The ends 122A, 123A of the pipes 120A are therefore arranged on either side of the support 110A.

[0036] Furthermore, the fluid passage system 100A comprises a part 130A common to all the pipes 120A passing through the partition. This part 130A forms a sheath for the pipes. In the illustrated example, the sheath 130A comprises a first part 132A and a second part 133A. The two parts 132A, 133A are shaped to cooperate with each other, so that when they are assembled they form passages 134A, each adapted and shaped to receive and hold in position a pipe 120A. Each of the passages 134A is separated from another passage 134A by a wall 135A having a thickness E1A.

[0037] The two parts 132A, 133A of the sheath 130A are then assembled together around the pipes and fixed to each other by fixing means such as screws and sealing means at the level of the tubes are put in place and fixed when these two parts are tightened.

[0038] In addition, the sheath 130A is then fixed to the support 110A, and in particular to the central portion 114A, by fixing means, for example screws 136A, as illustrated in FIGS. 2 and 3.

[0039] Furthermore, in order to ensure a seal between the first and second spaces of the turbomachine, the fluid passage system 100A comprises a seal 140A arranged between the central portion 114A of the support 110A and the sheath 130A.

[0040] The central portion 114A further comprises a first lateral edge 117A and a second lateral edge 118A opposite the first lateral edge 117A. The first lateral edge 117A and the second lateral edge 118A are substantially parallel to each other and each perpendicular to the central portion 114A.

[0041] The pipes 120A are also separated and spaced from the lateral edges 117A, 118A by walls 119A whose smallest thickness is denoted E2A. The arrangement of the pipes 120A gives a minimum possible distance denoted DA separating the first lateral edge 117A and the second lateral edge 118A.

[0042] The current configuration of the fluid passage system described above does not offer full satisfaction, particularly concerning its compactness, which could be improved. Indeed, the spacing between each passage 135A gives a maximum axial length MA with a given dimension corresponding to the maximum distance between two pipes 120A, pipes included. Another arrangement of the pipes can then modify this length and improve the compactness.

[0043] Reference is now made to [Fig. 4] to 8 which illustrate an embodiment of the invention aimed at increasing the compactness of the fluid passage system 100.

[0044] [Fig.4] represents a perspective view of the fluid passage system according to this embodiment of the invention. [Fig. 5] is a top view of the system. Figures 6, 7 and 8 are sectional views in perpendicular planes of the fluid passage system.

[0045] In this embodiment, the fluid passage system 100 according to the invention is configured to pass fluids through a partition of a turbomachine, in particular an aircraft partition, the partition separating a first space and a second space of the turbomachine.

[0046] The fluid passage system 100 comprises a plate 110 of elongated shape. The plate 110 comprises a first longitudinal end 112 and a second longitudinal end 113 opposite the first longitudinal end 112. Each of the longitudinal ends 112, 113 is intended to be fixed to the partition to be crossed, by fixing means, for example screws. The plate comprises a central portion 114 arranged between the first longitudinal end 112 and the second longitudinal end 113.

[0047] The plate 110 has a first face 115 facing the first space of the turbomachine and a second face 116 facing the second space of the turbomachine.

[0048] The central portion 114 of the plate further comprises a first stiffening lateral edge 117 and a second stiffening lateral edge 118 opposite the first stiffening lateral edge 117. The first stiffening lateral edge 117 and the second stiffening lateral edge 118 are substantially parallel to each other and each perpendicular to the central portion 114.

[0049] Furthermore, the plate 110, and more precisely the central portion 114 of the plate, comprises several fluid passage channels 120 extending between the first face and the second face of the plate. In the illustrated example, three channels 120-1, 120-2, 120-3 are shown. Of course, there may be more channels and at least one passage channel. The fluid passage channels 120 are arranged between the first lateral edge 117 and the second lateral edge 118 and at a minimum distance from the lateral edges 117, 118 denoted E2. This distance E2 is of the order of a few millimeters. The lateral edges 117, 118 make it possible to stiffen the part. They also form joint bearing edges with a bifurcation cowling, i.e. cowls of the arm which crosses the aerodynamic vein, generally extending radially between two shells of the turbomachine and houses the fluid passage system.

[0050] Each channel 120 comprises an inlet orifice 121 opening onto the first face 115 and an outlet orifice 122 opening onto the second face 116 of the central portion 114 of the plate. Preferably, the channels are cylindrical.

[0051] Preferably, the fluid passage channels 120 of the plate are parallel to each other between the first face 115 and the second face 116 of the plate 110.

[0052] In the example illustrated, the inlet 121 and outlet 122 orifices are all circular. However, they can be of any shape and different from each other.

[0053] Preferably, the channels are straight cylinders of circular cross-section, that is to say they extend longitudinally in a direction perpendicular to the first face 115 of the plate. It is understood that the outlet orifices 122 are therefore aligned with the inlet orifices 121. However, they can extend longitudinally in a direction inclined relative to the first face 115 of the plate 110.

[0054] Each passage channel 120 is delimited by a peripheral wall 125 and is attached to at least one other passage channel 120. In the example illustrated, channel 120-1 is attached to channel 120-2, as is channel 120-3. As a result, only channel 120-2 is attached to the two other passage channels 120-1 and 120-3.

[0055] Preferably, the peripheral wall 125 has a constant thickness E around the entire perimeter of the passage channel 120. This thickness is for example of the order of a millimeter.

[0056] It is thus understood that two adjacent passage channels 120 are separated by at least a distance 2E to ensure that the channels are held under pressure. Preferably, two adjacent passage channels 120 are separated by a distance equal to 2E in order to compact the fluid passage system and reduce the mass of the fluid passage system.

[0057] It nevertheless remains possible that two adjacent passage channels 120 are separated by a distance of less than 2E, or even that two channels 120 locally share a common wall whose thickness may be between E and 2E. Such arrangements may prove advantageous in terms of size and mass, provided that it is established that the pressure resistance of the channels remains assured.

[0058] In addition, for each channel, the peripheral wall 125 extends on the one hand from the first face 115 of the plate 110 to form a first pipe 130 to at least one first free end 132 and extends on the other hand from the second face 116 to form a second pipe 140 to at least one second free end 142 opposite the first free end 132.

[0059] It is thus understood that the first pipes 130 and the second pipes 140 extend on either side of the plate 110. In other words, the first pipes 130 extend in the first space of the turbomachine while the second pipes 140 extend in the second space of the turbomachine.

[0060] The first free end 132 of each first pipe 130 is configured to be fluidically connected with a component of the turbomachine housed in the first space of the turbomachine. For this purpose, each first free end 132 can advantageously be equipped with a fluid connector 150, preferably produced during the manufacture of the assembly or added by welding. Similarly, the second free end 142 of each second pipe 140 is configured to be fluidically connected with another component of the turbomachine housed in the second space of the turbomachine. Each first free end and each second free end are equipped with a fluid connector, preferably by welding. For this purpose, each second free end 142 can advantageously be equipped with a fluid connector 150, preferably produced during the manufacture of the assembly or added by welding.

[0061] In addition, the set of first pipes 130 form a first set E130. The first set E130 of pipes comprises a first cylindrical portion 135 extending from the first face 115 of the plate 110. In this cylindrical portion 135, the first pipes 130 are parallel to each other and each first pipe 130 is attached to at least one other first pipe 130 in a manner similar to the passage channels 120 of the plate 110.

[0062] Preferably, the first adjacent pipes 130 are joined at least two by two. Preferably, the peripheral wall 125 has a constant thickness around the entire periphery of the first pipes 130. This thickness is preferably equal to the thickness E of the peripheral wall of the passage channels 120. It is thus understood that two first adjacent pipes 130 are separated by at least a distance equal to twice the thickness of the peripheral wall to ensure that the pipes are held under pressure.

[0063] Preferably, in the first portion 135 of the first assembly E130, two first adjacent pipes 130 are separated by a distance equal to twice the thickness of the peripheral wall in order to compact the fluid passage system and reduce the mass of the fluid passage system.

[0064] Similarly, the set of second pipes 140 form a second set E140. The second set E140 of pipes comprises a second cylindrical portion 145 extending from the second face 116 of the plate 110. In this cylindrical portion 145, the second pipes 140 are parallel to each other and each second pipe 140 is attached to at least one other second pipe 140 in a manner similar to the passage channels 120 of the plate 110.

[0065] Preferably, the second adjacent pipes 140 are joined together. Preferably, the peripheral wall 125 has a constant thickness around the entire periphery of the second pipes 140. This thickness is preferably equal to the thickness E of the peripheral wall of the passage channels 120. It is thus understood that two second adjacent pipes 140 are separated by at least a distance equal to twice the thickness of the peripheral wall to ensure that the pipes are held under pressure.

[0066] Preferably, in the second cylindrical portion 145 of the second assembly E140, two second adjacent pipes 140 are separated by a distance equal to twice the thickness of the peripheral wall in order to compact the fluid passage system and reduce the mass of the fluid passage system.

[0067] Preferably, the first cylindrical portion 135 of the first assembly E130 extends in a direction substantially perpendicular to the first face 115 of the plate 110 and / or the second cylindrical portion 145 of the second assembly E140 extends in a direction substantially perpendicular to the second face 116 of the plate 110.

[0068] Preferably, each peripheral wall 125 in the cylindrical portions 135 and 145 extends in the same direction as the longitudinal direction of extension of the corresponding channel(s). It is thus understood that, preferably, the assembly formed by a first pipe 130 in the cylindrical portion 135, an associated channel 120 and a corresponding second pipe 40 in the cylindrical portion 145 form a straight fluid passage, that is to say a straight cylinder extending in a single longitudinal direction.

[0069] It is also understood that the first pipes 130 have in cross section the shape of the inlet orifice 121 and the associated passage channel 120, that is to say preferably a circular shape. Similarly, the second pipes 140 have in cross section the shape of the outlet orifice 122 and the associated passage channel 120, that is to say preferably a circular shape.

[0070] Of course, and as illustrated in [Fig.4], at least one first pipe 130 may comprise a bent portion 137 between the first cylindrical portion 135 and the first free end 132. Similarly, at least one second pipe 140 may comprise a bent portion 147 between the second cylindrical portion 145 and the second free end 142.

[0071] It should be noted that, according to the invention, the plate 110, the first pipes 130 and the second pipes 140 are formed from a single piece in order to limit the number of parts and reduce the number of references to be managed in the nomenclature. The reduction in the number of parts also makes it easier to install the fluid passage system 100. By a single piece, it is meant that the assembly formed by the plate 110, the first pipes 130 and the second pipes 140 is formed in integral continuity of material.

[0072] The passage channels 120 may be arranged in a staggered manner relative to one another and / or be distributed in two rows in order to minimize the size of the fluid passage system. In other words, the inlet orifices 121 and the outlet channels 122 may be arranged in a staggered manner relative to one another and / or be distributed in two rows respectively on the first face 115 and the second face 116 of the plate 110.

[0073] The arrangement of the inlet orifices 121 (and consequently of the channels 120 and of the first pipes 130 and second pipes 140) as described above allows the inlet orifices 121 to be brought closer to each other, compared to what is done in the state of the art shown in [Fig. 3]. In this way, the distance D separating the first lateral edge 117 from the second lateral edge 118 of the plate can be reduced, and a second axial length M is obtained. The second axial length M is less than the first axial length MA. In other words, the invention allows a reduction in the axial length of the passage of the pipes of the fluid passage system 100.

[0074] The reduction in the axial length makes it possible, among other things, to improve the compactness of the fluid passage system 100. A reduced size of the fluid passage system 100 has the advantage of reducing its mass.

[0075] The Applicant has also developed a turbomachine comprising a fluid passage system 100 as described above, for example for the bifurcations at 12 o'clock and 6 o'clock, by analogy with a sundial, on propulsion units equipped with a “D-Duct” type nacelle.

[0076] Such a turbomachine has the advantage of being equipped with a more compact fluid passage system, which improves the arrangement of the parts of the turbomachine and contributes to reducing its mass, in other words contributes to making it lighter.

[0077] The Applicant has also developed a method for producing a system 100 of fluid passage as described in the above. The system 100 is produced by tilting it so as to have the pipes as vertical as possible. In this method, the system 100 is produced by additive manufacturing. Additive manufacturing means manufacturing by adding or agglomerating material, by stacking successive layers. This manufacturing technique has the advantage of allowing the easy production of parts in volume. In the present case, it allows the plate 110, the first pipes 130 and the second pipes 140 to be formed in a single piece, in other words the manufacture of a more compact assembly.

[0078] The fluid passage system 100 described in the above has at least the advantage of having increased compactness, thanks to the reduction in the master torque of the passage of the pipes, compared to the existing technique. An increase in compactness allows in particular a reduction in its mass, with a view to lightening a propulsion assembly for example. In addition, the fluid passage system 100 is advantageously made up of a single part produced by additive manufacturing. This has the advantage of reducing the number of parts and thus facilitating the assembly of the system.

[0079] Although described through a certain number of examples, variants and embodiments, the cooling device according to the invention includes various variants, modifications and improvements which will be obvious to those skilled in the art, it being understood that these variants, modifications and improvements are part of the scope of the invention.

Claims

Claims

1. Fluid passage system (100) for a partition of a turbomachine, in particular an aircraft, comprising a plate (110) configured to be fixed to said partition of the turbomachine and characterized in that: - the plate (110) comprises several fluid passage channels (120) extending between a first face (115) and a second face (116) of the plate, each passage channel being delimited by a peripheral wall (125) and being attached to at least one other passage channel; - for each channel, the peripheral wall (125) extends from the first face (115) of the plate to form a first pipe (130) to a first free end (132) and extends from the second face (116) to form a second pipe (140) to a second free end (142) opposite the first free end;- the first pipes (130) form a first assembly (E130) comprising a first cylindrical portion (135) extending from the first face (115) of the plate in which each first pipe (130) is parallel and attached to at least one other first pipe and the second pipes (140) form a second assembly (E140) comprising a second cylindrical portion (145) extending from the second face (116) of the plate in which each second pipe (140) is parallel and attached to at least one other second pipe; and - the plate (110), the first and second pipes (130, 140) form a single piece.;

2. A fluid passage system according to claim 1, wherein the fluid passage channels (120) of the plate (110) are parallel to each other between the first face (115) and the second face (116) of the plate.

3. Fluid passage system according to claim 1 or 2, wherein for each fluid passage channel (120) of the plate, at least a portion of the peripheral wall (125) of said channel is tangent to a portion of the peripheral wall of another fluid passage channel.

4. Fluid passage system according to any one of the preceding claims, wherein: - in the first portion (135) of the first assembly and for each first pipe (130), at least a portion of the peripheral wall (125) of said first pipe is tangent to a portion of the peripheral wall (125) of another first pipe; and - in the second portion (145) of the second set and for each second pipe (140), at least a portion of the peripheral wall (125) of said second pipe is tangent to a portion of the peripheral wall of another second pipe.

5. A fluid passage system according to any one of the preceding claims, wherein: the first free end (132) of each first pipe (130) is configured to be fluidically connected with a component of the turbomachine and the second free end (142) of each second pipe (140) is configured to be fluidically connected with another component of the turbomachine.

6. Fluid passage system according to the preceding claim, in which each first free end (132) and each second free end (142) are equipped with a fluid connector (150), preferably produced during the manufacture of the assembly or added by welding.

7. A fluid passage system according to any preceding claim, wherein the first cylindrical portion (135) of the first assembly extends in a direction substantially perpendicular to the first face (115) of the plate and / or the second cylindrical portion (145) of the second assembly extends in a direction substantially perpendicular to the second face (116) of the plate.

8. A fluid passage system according to any preceding claim, wherein the plate (110) has side edges (117, 118), the channels (120) being arranged between the side edges.

9. Aircraft turbomachine characterized in that it comprises a partition equipped with a fluid passage system according to any one of the preceding claims.

10. Method for producing a fluid passage system according to any one of claims 1 to 8, characterized in that said fluid passage system is produced by additive manufacturing.

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