FLUID TRANSFER SYSTEM FOR A BULK OF A TURBOMACHINE AND TURBOMACHINE FEATURING SUCH A SYSTEM

Abstract

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

Description

Title of the invention: FLUID TRANSFER SYSTEM FOR A BLOCK OF A TURBOMACHINE AND TURBOMACHINE COMPRISING SUCH A SYSTEM technical field

[0001] The invention relates to a fluid passage system for a bulkhead of a turbomachine for an aircraft. The invention also relates to a turbomachine equipped with such a fluid passage system and to a method for manufacturing such a fluid passage system.

[0002] The invention finds applications in the field of aeronautics. Previous technique

[0003] Aeronautical turbomachinery is conventionally composed, 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 within housings.

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

[0005] Such a turbomachine is generally equipped with at least one means of passing fluids from the engine in order to transfer fluids from one constituent element of the turbomachine to another, in particular by 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 current technology, each individual pipe or conduit is generally routed from individual components of the turbomachine to other components, or even outside the turbomachine, by passing through bulkheads of the turbomachine that separate distinct spaces within it. These distinct spaces are generally fire zones that are segregated from one another, and the pipes passing from one zone to another are fixed in the arms of the casings, for example, and sealing at the arms is ensured either by baffles or by joints. Each of the pipes is usually fixed to a support structure positioned inside the turbomachine and attached to a bulkhead to prevent unwanted movement.

[0007] To ensure the passage through the partition, numerous parts are required, therefore many references must be managed in the bill of materials. Furthermore, a sealed zone must be provided at the point where the partition passes through.

[0008] The objective of the present invention is to overcome at least some of the problems mentioned above. In particular, the present invention proposes an improvement to this technology that is simple, efficient, and economical, notably by allowing for savings in parts, compactness, and mass for passing through the bulkheads 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 of an aircraft, 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 channel to a first free end and extends from the second face to form a second channel 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 channels form a single monobloc piece.

[0010] Thus, the invention proposes a monobloc fluid passage system, that is to say, one formed primarily of a single piece made with continuous material. Indeed, a single piece 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 for the passage through the partition by the servitudes and consequently the number of references in nomenclature to manage.

[0011] In addition, it simplifies the sealing system for the passage of easements through the partition(s).

[0012] The invention also makes it possible to obtain a system with the smallest possible dimensions and the most compact set of pipes possible when passing through the partition(s) than with current solutions and therefore makes it possible to optimize pressure losses in the aerodynamic channel.

[0013] Thus, thanks to the invention, a reduction in the cross-sectional area of ​​the fluid passage system is ensured, allowing for this more compact integration. The invention makes it possible to reduce the axial length of the structure supporting the fluid passage system's pipes, but especially the thickness of this structure. The term "cross-sectional area" refers to the cross-section perpendicular to the flow of the fluids. In other words, the cross-sectional area is a dimension that corresponds to the length of the pipe / support assembly enclosed by the flow of the engine's fluids. Indeed, the first pipes, the second pipes, and the channels of the mounting plate are separated by a single wall, unlike the prior art where two walls are spaced apart with minimal clearance. In other words, the walls are shared between the different pipes / channels.This wall is relatively thin compared to prior art designs, making it possible to reduce the system's frontal area so that it closely matches the space occupied by the channel in the plate. With a reduced frontal area, the fluid passage system through a partition also offers a gain in compactness and mass, thus contributing to a lighter 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 features, taken individually or in combination with each other 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 assembly 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 assembly and for each second pipe, at least a part of the peripheral wall of said second pipe is tangent to a part of the peripheral wall of another second pipe; - the first free end of each first pipe is configured to be fluidly connected with a component of the turbomachine and the second free end of each second pipe is configured to be fluidly connected with another component of the turbomachine; - each first free end and each second free end are equipped with a fluidic connector, preferably made 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 turntable has lateral edges, the channels being arranged between the lateral 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 above.

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

[0017] The present invention will be better understood and other details, features and advantages of the present invention will become more apparent upon reading the following description of a non-limiting example, with reference to the accompanying drawings in which: - Fig. 1 represents a schematic axial (or longitudinal) cross-sectional view of an aircraft propulsion system, 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 cross-sectional view of the fluid passage system along plane AA of [Fig.5]; - [Fig. 7] is a cross-sectional view of the fluid passage system along plane BB of [Fig. 6]; and - [Fig.8] is a cross-sectional view in the plane of the plate of the fluid passage system of [Fig.4].

[0019] An example of an embodiment of a fluid passage system for a bulkhead of a turbomachine is described in detail below, with reference to the accompanying drawings. This example illustrates the features and advantages of the invention. It should be noted, however, that the invention is not limited to this example.

[0020] In the figures, which are shown by way of illustration and in no way limit the invention, identical elements are identified by identical reference numerals. For the sake of legibility, the size scales between the represented elements are not to scale. Description of the implementation methods

[0021] The invention relates to a turbomachine intended to be mounted on an aircraft, such as an airplane or a helicopter. The turbomachine may be a turboengine, a turbojet, for example a turbomachine equipped with a shrouded fan (turbofan) or a turboprop, for example a propulsion unit equipped with an unshrouded 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 twin-spool, twin-body turbomachine which has a longitudinal axis C parallel to the X axis.

[0023] In all the figures, the X direction denotes 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 gas flow (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 unit, 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 unit, so that each turbine drives the associated compressor in rotation about the axis of the turbomachine X under the effect of the pressure of gases coming from the combustion chamber 26.

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

[0027] Furthermore, in the illustrated example, the turbomachine 10 defines a primary flow VI intended to be traversed by a primary flow Fl, and a secondary flow V2 intended to be traversed by a secondary flow F2 located radially outwards with respect to the primary flow. The flow F from the fan is split at a flow separation nozzle 40 of an intermediate casing 42. The intermediate casing 42 is usually interposed between the low pressure compressor 22 and the high pressure compressor 24.

[0028] In operation, air flows through the blower 32 and a first part of the airflow, the primary flow Fl, is routed through the low-pressure compressor 22, where the primary airflow Fl is compressed, then through the high-pressure compressor 24 where the primary airflow Fl 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 turbines 28 and low-pressure turbines 30 and thus produce part of the thrust of the turbomachine 10 (approximately 20%). The other part of the thrust comes from the secondary flow (approximately 80%).

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

[0030] During operation, these fluids are conveyed to the various associated components of the turbomachine by means of pipes, also called service lines. These fluids are either brought from outside the turbomachine to supply its various components, or from one component of the turbomachine to another, or from one component to the outside of the turbomachine via a fluid passage mast for discharge.

[0031] To this end, certain pipes must pass through one or more partitions from their starting point to their ending point. These partitions allow two distinct spaces within the turbomachine to be separated. For example, a nacelle separates the interior of the turbomachine from its exterior, and an intermediate casing separates a first space housing the initial 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 initial components.

[0032] Reference is now made to Figures 2 and 3, which illustrate the prior art. The [Fig. 3] is a view of a 100A fluid passage system through a partition, while [Fig. 2] is an exploded view of the same system to better visualize its various components. The partition separates a first and a second space within the turbomachine.

[0033] The fluid passage system 100A includes 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 passed through.

[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-port 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 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 and 123A of the pipes 120A are therefore arranged on either side of the support 110A.

[0036] Furthermore, the fluid passage system 100A includes a component 130A common to all the pipes 120A passing through the partition. This component 130A forms a sleeve for the pipes. In the illustrated example, the sleeve 130A comprises a first part 132A and a second part 133A. The two parts 132A and 133A are shaped to cooperate with each other, so that when 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 sleeve 130A are then assembled together around the pipes and fixed to each other by means of fixings 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] Furthermore, the sleeve 130A is then fixed to the support 110A, and in particular to the central portion 114A, by means of fixing, for example screws 136A, as illustrated in figures 2 and 3.

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

[0040] The central portion 114A further comprises a first lateral edge 117A and a second lateral edge 118A opposite to 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, the smallest thickness of which 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 is not entirely satisfactory, particularly with regard to its compactness, which could be improved. Indeed, the spacing between each passage 135A results in a maximum axial length MA with a given dimension corresponding to the maximum distance between two pipes 120A, including the pipes themselves. A different pipe arrangement could then modify this length and improve 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] Figure 4 shows a perspective view of the fluid passage system according to This embodiment of the invention. Figure 5 is a top view of the system. Figures 6, 7, and 8 are cross-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 of an aircraft, the partition separating a first space and a second space of the turbomachine.

[0046] The fluid passage system 100 comprises an elongated plate 110. The plate 110 has 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 traversed by means of fasteners, for example, screws. The plate has 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 opposite the first space of the turbomachine and a second face 116 opposite the second space of the turbomachine.

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

[0049] Furthermore, the plate 110, and more specifically the central portion 114 of the plate, includes several fluid passage channels 120 extending between the first and second faces of the plate. In the illustrated example, three channels 120-1, 120-2, and 120-3 are shown. Of course, there may be more channels, but 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 and 118, denoted E2. This distance E2 is on the order of a few millimeters. The lateral edges 17 and 118 provide rigidity to the part. They also form joint support edges with bifurcation hooding, i.e. hoods of the arm which crosses the aerodynamic duct, generally extending radially between two turbomachine ferrules and houses the fluid passage system.

[0050] Each channel 120 has 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 illustrated example, the inlet orifice 121 and outlet orifice 122 are all circular. However, they can be of any shape and different from each other.

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

[0054] Each passage channel 120 is delimited by a peripheral wall 125 and is adjacent to at least one other passage channel 120. In the illustrated example, channel 120-1 is adjacent to channel 120-2, as is channel 120-3. Therefore, only channel 120-2 is adjacent to the other two 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, on the order of a millimeter.

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

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

[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 channel 130 up to at least a first free end 132 and extends on the other hand from the second face 116 to form a second channel 140 up to at least a 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 into the first space of the turbomachine while the second pipes 140 extend into the second space of the turbomachine.

[0060] The first free end 132 of each first pipe 130 is configured to be fluidically connected to a turbomachine component 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 fabricated during the assembly's manufacture or attached by welding. Similarly, the second free end 142 of each second pipe 140 is configured to be fluidically connected to another turbomachine component 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 fabricated during the assembly's manufacture or attached by welding.

[0061] Furthermore, 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 joined to at least one other first pipe 130 in a manner similar to the channels 120 through 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 circumference 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 the first two adjacent pipes 130 are separated by a distance at least equal to twice the thickness of the peripheral wall to ensure the pipes can withstand pressure.

[0063] Preferably, in the first portion 135 of the first assembly E130, the first two 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 forms 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 joined to at least one other second pipe 140 in a manner similar to the passage channels 120 of the plate 110.

[0065] Preferably, the adjacent second pipes 140 are joined together. Preferably, the peripheral wall 125 has a constant thickness around the entire circumference 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 adjacent second pipes 140 are separated by a distance at least equal to twice the thickness of the peripheral wall to ensure the pipes can withstand pressure.

[0066] Preferably, in the second cylindrical portion 145 of the second assembly El40, 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 channel 130 in the cylindrical portion 135, an associated channel 120 and a corresponding second channel 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 include an angled portion 137 between the first cylindrical portion 135 and the first free end 132. Similarly, at least one second pipe 140 may include an angled 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, monobloc piece in order to limit the number of parts and reduce the number of part numbers to be managed in the bill of materials. Reducing the number of parts also facilitates the installation of the fluid passage system 100. A single, monobloc piece is defined as the assembly formed by the plate 110, the first pipes 130, and the second pipes 140 being formed from a single, continuous piece of material.

[0072] The flow channels 120 can be arranged in a staggered pattern with respect to each other and / or distributed in two rows in order to minimize the footprint of the fluid flow system. In other words, the inlet ports 121 and the outlet channels 122 can be arranged in a staggered pattern with respect to each other and / or 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 ports 121 (and consequently of the channels 120 and the first and second pipes 130 and pipes 140) as described above allows the inlet ports 121 to be placed closer together than in the prior 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 for a reduction in the axial length of the pipes in the fluid passage system 100.

[0074] Reducing the axial length allows, among other things, for improved compactness of the fluid passage system 100. A reduced footprint 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 bifurcations at 12 o'clock and 6 o'clock, by analogy to a sundial, on propulsion assemblies 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 helps to reduce its mass, in other words contributes to its weight reduction.

[0077] The Applicant has also developed a method for implementing a system The fluid passage system 100 is as described above. System 100 is created by tilting it to ensure the pipes are as vertical as possible. In this process, System 100 is manufactured using additive manufacturing. Additive manufacturing refers to manufacturing by adding or agglomerating material, by stacking successive layers. This manufacturing technique has the advantage of allowing the easy production of three-dimensional parts. In this case, it allows the plate 110, the first pipes 130, and the second pipes 140 to be formed from a single piece, in other words, the production of a more compact assembly.

[0078] The fluid passage system 100 described above has at least the advantage of increased compactness, thanks to the reduction in the cross-sectional area of ​​the pipes, compared to existing techniques. Increased compactness allows, in particular, a reduction in mass, for example, to lighten a propulsion assembly. Furthermore, the fluid passage system 100 is advantageously made of a single part produced by additive manufacturing. This has the advantage of reducing the number of parts and thus facilitating system assembly.

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

Claims

Demands

1. Fluid passage system (100) for a bulkhead of a turbomachine, in particular of an aircraft, comprising a plate (110) configured to be fixed to said bulkhead 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 adjacent 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 channel (130) to a first free end (132) and extends from the second face (116) to form a second channel (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 monobloc piece.

2. 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. A 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 part of the peripheral wall (125) of said first pipe is tangent to a part of the peripheral wall (125) of another first pipe; and - in the second portion (145) of the second assembly and for each second pipe (140), at least a part of the peripheral wall (125) of said second pipe is tangent to a part of the peripheral wall of another second pipe.

5. 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 fluidly connected with another component of the turbomachine.

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

7. Fluid passage system according to any one of the preceding claims, 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. Fluid passage system according to any one of the preceding claims, wherein the plate (110) has lateral edges (117, 118), the channels (120) being arranged between the lateral 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 of making a fluid passage system according to any one of claims 1 to 8, characterized in that said fluid passage system is made by additive manufacturing.

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