Fluid passage system for a partition of a turbine engine and turbine engine comprising such a system

Abstract

The invention relates to a fluid passage system (100) for a partition of a turbine engine of an aircraft, comprising a plate (110) configured to be attached to the partition, characterized in that: - the plate (110) comprises a plurality of fluid passage channels, the channels being joined together at least two by two; - the peripheral wall of each channel extends on both sides of the plate to form a first duct (130) and a second duct (140); and - the plate (110) forms a single integral part with the first and second ducts (130, 140).

Description

Technical Field

[0001] This invention relates to a fluid channel system for a separator in a turbine engine of an aircraft. The invention also relates to a turbine engine equipped with such a fluid channel system, and a method for manufacturing such a fluid channel system.

[0002] This invention has applications in the aviation field. Background Technology

[0003] An aircraft turbine engine typically comprises, from upstream to downstream, a fan, one or more compressor stages (e.g., a low-pressure compressor and a high-pressure compressor), a combustion chamber, one or more turbine stages (e.g., a high-pressure turbine and a low-pressure turbine), and exhaust nozzles in the direction of gas flow. These different components are usually housed within a casing.

[0004] Many components of a turbine engine generate, consume, transport, or contain fluids, such as hydraulic fluids (water, oil) or fuel. Turbine engines also include conduits through which these fluids flow. For example, such conduits supply hydraulic circuits to control landing gear, flaps on aircraft wings (in the case of an aircraft), or any other aircraft accessory.

[0005] Such turbine engines are typically equipped with at least one fluid passage device for engine fluids, in particular via at least one pipe (also known as an auxiliary device) to transport fluids from one component of the turbine engine to another, and / or to prevent the accumulation of these fluids in the event of a leak and engine shutdown.

[0006] In modern technology, each individual duct or conduit is typically guided from a separate component of the turbine engine to other components, or even to the outside of the turbine engine, through partitions that separate their different spaces. These partitioned spaces are typically fire-resistant zones isolated from each other, with conduits from one zone to another secured, for example, within the arms of the housing, and sealed at the arms by baffles or seals. Each duct is typically secured to a support structure located inside the turbine engine and to the partitions to prevent unintended movement.

[0007] To ensure passage through the separator, many parts are required, resulting in a large number of part numbers to manage in the parts catalog. Additionally, a sealing area must be provided at the passageway of the separator.

[0008] The object of this invention is to alleviate at least some of the problems mentioned above. In particular, this invention proposes an improvement to the technology that is simple, effective, and economical, especially by achieving gains in the parts, compactness, and mass of the passageway of the turbine engine's partition. Summary of the Invention

[0009] Therefore, the present invention relates to a fluid channel system for a separator of a turbine engine, particularly an aircraft turbine engine, the fluid channel system comprising a plate configured to be fixed to the separator of the turbine engine.

[0010] According to the invention, the plate includes a plurality of fluid passages extending between a first surface and a second surface of the plate, each passage being defined by a peripheral wall and adjacent to at least one other passage.

[0011] Furthermore, according to the invention, for each channel, a peripheral wall extends from a first surface of the plate to a first free end to form a first conduit, and extends from a second surface to a second free end opposite to the first free end to form a second conduit.

[0012] Additionally, according to the present invention, a first conduit forms a first assembly, the first assembly including a first cylindrical portion extending from a first surface of a plate, wherein each first conduit is parallel to and adjacent to at least one other first conduit, and a second conduit forms a second assembly, the second assembly including a second cylindrical portion extending from a second surface of a plate, wherein each second conduit is parallel to and adjacent to at least one other second conduit.

[0013] Furthermore, according to the present invention, the plate, the first pipe, and the second pipe form a single integral part.

[0014] Therefore, this invention proposes an integral fluid channel system, which is formed primarily by a single component made of a continuous material. In fact, this single component combines the functions of supporting the pipes on the partition, sealing the pipes, and the pipes themselves. Thus, this invention reduces the number of components required to pass auxiliary devices through the partition, and consequently reduces the number of part numbers in the managed parts catalog.

[0015] The present invention also simplifies a system for sealing auxiliary devices as they pass through one or more separators.

[0016] Compared to current solutions, the present invention also enables the production of a system with the smallest possible size and a set of pipes that are as compact as possible when passing through one or more separators, and thus optimizes pressure loss in pneumatic pipes.

[0017] In this way, the present invention reduces the main torque of the fluid channel system, thereby achieving this more compact integration. The present invention is able to reduce the axial length of the structure carrying the fluid channel system's pipes, and most importantly, reduce the thickness of this structure. The term "main torque" refers to the cross-section perpendicular to the flow. In other words, the main torque is the dimension corresponding to the length of the pipe / support assembly formed by the flow from the motor. In fact, the first pipe, the second pipe, and the channel on the plate are separated by a single wall, unlike the prior art, where two walls are separated by a minimal gap. In other words, the wall between the different pipes / supports is shared. This wall is not very thick compared to the walls in the prior art, thus reducing the main torque of the system so that it essentially corresponds to the space occupied by the channel on the plate. With the reduced main torque, the fluid channel system through the separator is also more compact and lighter, contributing to the weight reduction of turbine engines designed to be equipped with such a system according to the present invention.

[0018] The fluid channel system according to the invention may include one or more of the following features, which may be used independently or in any technically possible combination: The fluid in the plate passes through channels parallel to each other between the first and second surfaces of the plate. - For each fluid passage of the plate, at least one section of the peripheral wall of the passage is tangent to a section of the peripheral wall of another fluid passage; - In the first part of the first component and for each first pipe, at least one segment of the peripheral wall of the first pipe is tangent to a segment of the peripheral wall of another first pipe; and in the second part of the second component and for each second pipe, at least one segment of the peripheral wall of the second pipe is tangent to a segment of the peripheral wall of another second pipe. - The first free end of each first pipe is configured to be fluidly connected to a component of the turbine engine, and the second free end of each second pipe is configured to be fluidly connected to another component of the turbine engine; - Each first free end and each second free end are equipped with a fluid connector, which is preferably made during the manufacture of the component or added by welding; - The first cylindrical portion of the first component extends in a direction substantially perpendicular to the first surface of the plate, and / or the second cylindrical portion of the second component extends in a direction substantially perpendicular to the second surface of the plate; - The fluid is water, oil, or fuel; - The plate includes lateral edges, and channels are arranged between the lateral edges.

[0019] The present invention also relates to an aircraft turbine engine, including a separator equipped with a fluid channel system according to the present invention and as described above.

[0020] The present invention also relates to a method for manufacturing a fluid channel system according to the invention and as described above, the fluid channel system being manufactured by additive manufacturing. Attached Figure Description

[0021] The invention will be better understood from the following description, given by way of non-limiting example and with reference to the accompanying drawings, and other details, features and advantages of the invention will become more apparent, in which: - Figure 1 A schematic axial (or longitudinal) cross-sectional view of the aircraft propulsion unit, particularly a turbine engine, to which this invention is applied is shown. - Figure 2 This is a schematic exploded view of a fluid channel system for separating components, based on existing technology; - Figure 3 yes Figure 2 A schematic perspective view of the fluid channel system shown. - Figure 4 This is a schematic perspective view of a fluid passage system for a separator in a turbine engine according to the present invention; - Figure 5 yes Figure 4 A schematic top view of the fluid channel system shown; - Figure 6 It is along Figure 5 A cross-sectional view of the fluid channel system in plane AA; - Figure 7 It is along Figure 6 Cross-sectional view of the fluid channel system in plane BB; and - Figure 8 yes Figure 4 A cross-sectional view of the plate in the fluid channel system.

[0022] An example of a fluid passage system for a turbine engine separator is described in detail below with reference to the accompanying drawings. This example illustrates the features and advantages of the invention. However, the invention is not limited to this example.

[0023] In the accompanying drawings, the same elements are labeled with the same reference numerals. These drawings are presented in an illustrative manner and in no way limit the scope of the invention. To facilitate readability, the dimensions of the elements shown are not taken into account. Detailed Implementation

[0024] This invention applies to turbine engines intended for installation on aircraft such as airplanes or helicopters. The turbine engine can be a turboshaft engine, a turbojet engine, such as a turbine engine equipped with a ducted fan (turbofan), or a turboprop, such as a propulsion unit equipped with an unducted propeller (“open rotor”, “USF” stands for “Unducted Single Fan” or “UDF” stands for “Unducted Fan”).

[0025] Figure 1 An example of such an aircraft turbine engine 10 is shown. In the example shown, the turbine engine is a twin-flow, twin-shaft turbine engine with a longitudinal axis C parallel to the axis X.

[0026] In all the accompanying figures, the X direction refers to the direction of the turbine engine's axis C, while the Y and Z directions are two orthogonal directions. Upstream and downstream refer to the main flow directions within the turbine engine.

[0027] In a known manner, the turbine engine 10 includes 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 from upstream to downstream, with reference to the gas flow direction (see arrow).

[0028] The high-pressure turbine 28 is connected to the high-pressure compressor 24 via a high-pressure shaft to form a high-pressure body, while the low-pressure turbine 30 is connected to the low-pressure compressor 22 via a low-pressure shaft to form a low-pressure body, such that each turbine drives the associated compressor to rotate around the axis X of the turbine engine under the thrust of the gas from the combustion chamber 26.

[0029] The turbine engine 10 also includes a fan 32 located upstream of the low-pressure compressor 22, which is positioned directly downstream of the intake cone. The fan 32 includes a ring of fan blades 34 that rotate about the axis C of the turbine engine. The fan 32 is housed in a nacelle 36.

[0030] Additionally, in the example shown, the turbine engine 10 defines a main duct V1 and a secondary duct V2, through which the main flow F1 is intended to pass, and through which the secondary flow F2, positioned radially outward relative to the main flow, is intended to pass. The fan flow F is separated at the flow separation nozzle 40 of the intermediate housing 42.

[0031] The intermediate housing 42 is typically positioned between the low-pressure compressor 22 and the high-pressure compressor 24.

[0032] During operation, air flows through fan 32, and a first portion of this airflow (mainstream F1) is directed through low-pressure compressor 22, where the main airflow F1 is compressed. It is then directed through high-pressure compressor 24, where the main airflow F1 is compressed to a higher pressure level and delivered to combustion chamber 26. The hot combustion products from combustion chamber 26 drive high-pressure turbine 28 and low-pressure turbine 30, thereby generating a portion (approximately 20%) of the thrust of the turbine engine 10. Another portion of the thrust comes from the secondary flow (approximately 80%).

[0033] Various types of fluids circulate in the turbine engine 10, particularly oil used to lubricate the bearings of rotating parts, water that can be drawn in through the ventilation scoop or formed by condensation on the engine, fuel, and hydraulic fluids for the aircraft (such as Skydrol (special hydraulic working oil), hydrogen, nitrogen, etc.).

[0034] During operation, these fluids are directed via pipes (also known as auxiliary devices) to the various components associated with the turbine engine. These fluids are supplied from outside the turbine engine to supply the various components that make up the turbine engine, or from one component of the turbine engine to another, or from one component to the outside of the turbine engine via a fluid channel mast to vent them.

[0035] Therefore, some pipes must pass through one or more partitions from their starting point to their destination. These partitions separate two different spaces of the turbine engine. For example, the nacelle separates the interior of the turbine engine from the exterior, and the intermediate casing separates the first space, which houses the first components of the turbine engine that use fluid, from the second space, which houses other components of the turbine engine that use the same fluid or fluid generated / supplied by the first component.

[0036] Now for reference Figure 2 and Figure 3 It demonstrates existing technology. Figure 3 This is a view of the fluid channel system 100A passing through the separator, and Figure 2 This is an exploded view to better observe the individual components that make up the fluid channel system. The separator separates the first space from the second space in the turbine engine.

[0037] The fluid channel system 100A includes an elongated support member 110A. The support member 110A includes a first longitudinal end 112A and a second longitudinal end 113A, each of which is intended to be secured to a separator to be passed through.

[0038] The fluid channel system 100A includes a central portion 114A disposed between a first longitudinal end 112A and a second longitudinal end 113A. The central portion 114A has a first surface 115A facing a first space of the turbine engine and a second surface 116A facing a second space of the turbine engine. A through-hole 111A is provided in the central portion 114A for a conduit to pass through. In the example shown, three conduits 120A are illustrated. Of course, fewer or more conduits may be present.

[0039] The pipe 120A extends between a first end 122A disposed in the first space and a second end 123A disposed in the second space of the turbine engine. Therefore, the ends 122A and 123A of the pipe 120A are disposed on both sides of the support 110A.

[0040] Additionally, the fluid channel system 100A includes a portion 130A shared by all pipes 120A passing through the separator. This portion 130A forms a sheath for the pipes. In the example shown, the sheath 130A includes a first section 132A and a second section 133A. The two sections 132A and 133A are shaped to mate with each other such that, during assembly, they form channels 134A, each channel 134A being adapted and shaped to receive and hold the pipes 120A in place. Each channel 134A is separated from the other channel 134A by a wall 135A having a thickness E1A.

[0041] Then, the two sections 132A and 133A of the sheath 130A are assembled together around the pipe and secured to each other by fastening devices (such as screws), and when the two sections are secured, the sealing device at the pipe is placed in place and secured.

[0042] Then, the sheath 130A is secured to the support 110A by means of a fastening device (e.g., screw 136A), particularly to the central portion 114A, as follows. Figure 2 and Figure 3 As shown.

[0043] In addition, to ensure the sealing between the first space and the second space of the turbine engine, the fluid passage system 100A includes a seal 140A disposed between the central portion 114A of the support 110A and the sheath 130A.

[0044] The central portion 114A also includes 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.

[0045] The conduit 120A is also separated and spaced from the lateral edges 117A and 118A by a wall 119A, the minimum thickness of which is denoted as E2A. The arrangement of the conduit 120A gives the minimum possible distance, denoted as DA, that separates the first lateral edge 117A from the second lateral edge 118A.

[0046] The current configuration of the fluid channel system described above is not entirely satisfactory, particularly in terms of its compactness, which can be improved. In fact, the spacing between each channel 135A gives a maximum axial length MA of a given dimension, which corresponds to the maximum distance between two pipes 120A (inclusive). Therefore, different pipe layouts can modify this length and improve compactness.

[0047] Now for reference Figures 4 to 8 This illustrates an embodiment of the invention designed to improve the compactness of the fluid channel system 100.

[0048] Figure 4 A perspective view of a fluid channel system according to an embodiment of the present invention is shown. Figure 5 This is a top view of the system. Figure 6 , Figure 7 and Figure 8 It is the cross-section of the fluid channel system in a vertical plane.

[0049] In this embodiment, the fluid channel system 100 according to the invention is configured to allow fluid to pass through a separator of a turbine engine (particularly an aircraft turbine engine) that separates a first space of the turbine engine from a second space.

[0050] The fluid channel system 100 includes an elongated plate 110. The plate 110 includes a first longitudinal end 112 and a second longitudinal end 113 opposite to the first longitudinal end 112. Each of the longitudinal ends 112 and 113 is designed to be secured to a partition to be passed through by a fastening device (e.g., screws). The plate includes a central portion 114 disposed between the first longitudinal end 112 and the second longitudinal end 113.

[0051] Plate 110 has a first surface 115 facing a first space of the turbine engine and a second surface 116 facing a second space of the turbine engine. The central portion 114 of the plate also includes a first lateral reinforcing edge 117 and a second lateral reinforcing edge 118 opposite to the first lateral edge 117. The first lateral edge 117 and the second lateral reinforcing edge 118 are substantially parallel to each other and each perpendicular to the central portion 114.

[0052] Additionally, plate 110, more specifically, the central portion 114 of the plate, includes a plurality of fluid passage channels 120 extending between the first and second surfaces of the plate. In the example shown, three channels 120-1, 120-2, and 120-3 are illustrated. Of course, more channels and at least one passage channel may exist. The fluid passage channels 120 are arranged between the first lateral edge 117 and the second lateral edge 118, and are at a minimum distance from the lateral edges 117 and 118, denoted as E2. This distance E2 is approximately several millimeters. The lateral edges 117 and 118 reinforce the components. The lateral edges 117 and 118 also form sealing support edges with the bifurcation fairing, which is a fairing for arms passing through pneumatic ducts, extending generally radially between the two housings of the turbine engine and housing the fluid passage system.

[0053] Each channel 120 includes an inlet hole 121 leading to a first surface 115 of the central portion 114 of the plate and an outlet hole 122 leading to a second surface 116. Preferably, the channel is cylindrical.

[0054] Preferably, the fluid through the plate passes through the channel 120 parallel to each other between the first surface 115 and the second surface 116 of the plate 110.

[0055] In the example shown, both the inlet hole 121 and the outlet hole 122 are circular. However, the inlet hole and the outlet hole can have any shape and be different from each other.

[0056] Preferably, the channel is a straight cylinder with a circular cross-section, that is, the channel extends longitudinally in a direction perpendicular to the first surface 115 of the plate. It should be understood that the outlet hole 122 is therefore aligned with the inlet hole 121. However, the inlet hole and the outlet hole may extend longitudinally at an angle to the first surface 115 of the plate 110.

[0057] Each passageway 120 is defined by a peripheral wall 125 and is adjacent to at least one other passageway 120. In the example shown, passageway 120-1 is adjacent to passageway 120-2, and so is passageway 120-3. As a result, only passageway 120-2 is adjacent to the other two passageways 120-1 and 120-3.

[0058] Preferably, the peripheral wall 125 has a constant thickness E around the entire perimeter of the passage 120. For example, this thickness is about one millimeter.

[0059] This means that two adjacent passageways 120 are separated by a distance of at least 2E to ensure that the passageways remain pressurized. Preferably, the distance between two adjacent passageways 120 is equal to 2E to make the fluid passage system compact and reduce the mass of the fluid passage system.

[0060] However, two adjacent passageways 120 can still be separated by a distance less than 2E, or even the two passageways 120 can partially share a common wall, the thickness of which can be between E and 2E. This arrangement can be advantageous in terms of size and weight, provided that the passageways remain stable under pressure.

[0061] In addition, for each channel, the peripheral wall 125 extends from the first surface 115 of the plate 110 to at least one first free end 132 to form a first conduit 130, and from the second surface 116 to at least one second free end 142 opposite to the first free end 132 to form a second conduit 140.

[0062] Therefore, it should be understood that the first conduit 130 and the second conduit 140 extend on both sides of the plate 110. In other words, the first conduit 130 extends into the first space of the turbine engine, while the second conduit 140 extends into the second space of the turbine engine.

[0063] A first free end 132 of each first conduit 130 is configured to be fluidly connected to a component of the turbine engine housed in a first space within the turbine engine. For this purpose, each first free end 132 may advantageously be fitted with a fluid connector 150, which is preferably fabricated during the manufacture of the assembly or added by welding. Similarly, a second free end 142 of each second conduit 140 is configured to be fluidly connected to another component of the turbine engine housed in a second space within the turbine engine, and each first and second free end is preferably equipped with a fluid connector by welding. For this purpose, each second free end 142 may advantageously be fitted with a fluid connector 150, which is preferably fabricated during the manufacture of the assembly or added by welding.

[0064] Additionally, all the first conduits 130 form a first assembly E130. The first conduit assembly E130 includes a first cylindrical portion 135 extending from a first surface 115 of the plate 110. In this cylindrical portion 135, the first conduits 130 are parallel to each other, and each first conduit 130 is adjacent to at least one other first conduit 130 in a manner similar to a channel 120 of the plate 110.

[0065] Preferably, adjacent first conduits 130 are at least pairwise adjacent. Preferably, the peripheral wall 125 has a constant thickness around the entire perimeter of the first conduit 130. Preferably, this thickness is equal to the thickness E of the peripheral wall through the channel 120. Therefore, it should be understood that the distance between two adjacent first conduits 130 is at least equal to twice the thickness of the peripheral wall to ensure that the conduits remain under pressure.

[0066] Preferably, in the first portion 135 of the first component E130, the distance between two adjacent first pipes 130 is equal to twice the thickness of the peripheral wall, so as to make the fluid channel system compact and reduce the mass of the fluid channel system.

[0067] Similarly, all the second conduits 140 form a second assembly E140. The second conduit assembly E140 includes a second cylindrical portion 145 extending from the second surface 116 of the plate 110. In this cylindrical portion 145, the second conduits 140 are parallel to each other, and each second conduit 140 is adjacent to at least one other second conduit 140 in a manner similar to the through channel 120 of the plate 110.

[0068] Preferably, adjacent second conduits 140 are abutted. Preferably, the peripheral wall 125 has a constant thickness around the entire perimeter of the second conduit 140. Preferably, this thickness is equal to the thickness E of the peripheral wall through the channel 120. Therefore, it should be understood that two adjacent second conduits 140 are at least twice the thickness of the peripheral wall to ensure that the conduits remain under pressure.

[0069] Preferably, in the second cylindrical portion 145 of the second component E140, the distance between two adjacent second pipes 140 is equal to twice the thickness of the peripheral wall, so as to make the fluid channel system compact and reduce the mass of the fluid channel system.

[0070] Preferably, the first cylindrical portion 135 of the first component E130 extends in a direction substantially perpendicular to the first surface 115 of the plate 110, and / or the second cylindrical portion 145 of the second component E140 extends in a direction substantially perpendicular to the second surface 116 of the plate 110.

[0071] Preferably, each peripheral wall 125 in the cylindrical portions 135 and 145 extends in the same direction as the longitudinal extension direction of the corresponding one or more channels. Therefore, it should be understood that, preferably, the assembly formed by the first conduit 130 in the cylindrical portion 135, the associated channel 120, and the corresponding second conduit 40 in the cylindrical portion 145 forms a straight fluid channel, i.e., a straight cylinder extending in a single longitudinal direction.

[0072] It should also be understood that, in cross-section, the first conduit 130 has the same shape as the inlet orifice 121 and the associated passage 120, i.e., preferably a circular shape. Similarly, the second conduit 140 has the same cross-sectional shape as the outlet orifice 122 and the associated passage 120, i.e., preferably a circular shape.

[0073] Of course, and as Figure 4As shown, at least one first conduit 130 may include a bend 137 located between a first cylindrical portion 135 and a first free end 132. Similarly, at least one second conduit 140 may include a bend 147 located between a second cylindrical portion 145 and a second free end 142.

[0074] It should be noted that, according to the present invention, plate 110, first conduit 130, and second conduit 140 are formed from a single integral part to limit the number of parts and reduce the number of numbers to be managed in the parts catalog. The reduction in the number of parts also makes the installation of the fluid channel system 100 easier. A single integral part means that the assembly formed by plate 110, first conduit 130, and second conduit 140 is integrally formed from a single piece of material.

[0075] The channels 120 can be staggered and / or arranged in two rows to minimize the overall size of the fluid channel system. In other words, the inlet holes 121 and the outlet channels 122 can be staggered relative to each other and / or distributed in two rows on the first surface 115 and the second surface 116 of the plate 110, respectively.

[0076] The arrangement of the inlet hole 121 (and therefore the channel 120 and the first conduit 130 and the second conduit 140) as described above allows the inlet hole 121 to be more... Figure 3 The prior art shown is closer together. In this way, the distance D separating the first lateral edge 117 and the second lateral edge 118 of the plate can be reduced, and a second axial length M can be obtained. The second axial length M is smaller than the first axial length MA. In other words, the present invention is able to reduce the axial length of the channel of the fluid channel system 100.

[0077] One benefit of reducing the axial length is that the fluid channel system 100 becomes more compact. Reducing the size of the fluid channel system 100 has the advantage of reducing its mass.

[0078] The applicant has also developed a turbine engine that includes a fluid channel system 100 as described above, for example for bifurcations located at 12 o'clock and 6 o'clock positions on a propulsion unit equipped with a "D-shaped pipe" type nacelle.

[0079] Such a turbine engine has the advantage of being equipped with a more compact fluid passage system, which improves the layout of the turbine engine's components and helps to reduce its weight.

[0080] The applicant has also developed a method for manufacturing the fluid channel system 100 as described above. System 100 is manufactured by tilting it so that the pipes are as vertical as possible. In this method, system 100 is manufactured using additive manufacturing. Additive manufacturing refers to manufacturing by adding or agglomerating materials, by stacking continuous layers. The advantage of this manufacturing technique is that it allows for the easy fabrication of bulk parts. In this case, this manufacturing technique enables plate 110, the first pipe 130, and the second pipe 140 to be formed from a single piece; in other words, to form a more compact assembly.

[0081] Because the main torque of the pipe channel is reduced compared to existing technologies, the aforementioned fluid channel system 100 has at least the advantage of being more compact. Increased compactness means reduced weight, for example, to reduce the weight of the propulsion unit. Furthermore, the fluid channel system 100 is advantageously composed of individual parts manufactured through additive manufacturing. This has the advantage of reducing the number of parts and making the system easier to assemble.

[0082] Although described in many examples, variations and embodiments, the cooling device according to the invention includes various variations, modifications and improvements that will be obvious to those skilled in the art, and it should be understood that such variations, modifications and improvements are within the scope of the invention.

Claims

1. A fluid passage system (100) for a partition of a turbine engine, particularly an aircraft turbine engine, the fluid passage system comprising a plate (110) configured to be fixed to the partition of the turbine engine, characterized in that: - The plate (110) includes a plurality of fluid passages (120) extending between a first surface (115) and a second surface (116) of the plate, each passage being defined by a peripheral wall (125) and adjacent to at least one other passage; - For each channel, the peripheral wall (125) extends from the first surface (115) of the plate to the first free end (132) to form a first conduit (130), and extends from the second surface (116) to the second free end (142) opposite to the first free end to form a second conduit (140). - The first conduit (130) forms a first assembly (E130) including a first cylindrical portion (135) extending from a first surface (115) of the plate, wherein each first conduit (130) is parallel to and adjacent to at least one other first conduit; the second conduit (140) forms a second assembly (E140) including a second cylindrical portion (145) extending from a second surface (116) of the plate, wherein each second conduit (140) is parallel to and adjacent to at least one other second conduit; and - The plate (110) forms a single integral part with the first pipe and the second pipe (130, 140).

2. The fluid channel system according to claim 1, wherein, The fluid of the plate (110) passes through the channel (120) parallel to each other between the first surface (115) and the second surface (116) of the plate.

3. The fluid channel system according to claim 1 or 2, wherein, For each fluid passage (120) of the plate, at least one section of the peripheral wall (125) of the passage is tangent to a section of the peripheral wall of another fluid passage.

4. The fluid channel system according to any one of the preceding claims, wherein, - In the first portion (135) of the first component and for each first conduit (130), at least one segment of the peripheral wall (125) of the first conduit is tangent to a segment of the peripheral wall (125) of another first conduit; and - In the second part (145) of the second component and for each second pipe (140), at least one segment of the peripheral wall (125) of the second pipe is tangent to a segment of the peripheral wall of another second pipe.

5. The fluid channel system according to any one of the preceding claims, wherein, The first free end (132) of each first pipe (130) is configured to be fluidly connected to a component of the turbine engine, and the second free end (142) of each second pipe (140) is configured to be fluidly connected to another component of the turbine engine.

6. The fluid channel system according to the preceding claim, wherein, Each first free end (132) and each second free end (142) is equipped with a fluid connector (150), which is preferably made during the manufacture of the component or added by welding.

7. The fluid channel system according to any one of the preceding claims, wherein, The first cylindrical portion (135) of the first component extends in a direction substantially perpendicular to the first surface (115) of the plate, and / or the second cylindrical portion (145) of the second component extends in a direction substantially perpendicular to the second surface (116) of the plate.

8. The fluid channel system according to any one of the preceding claims, wherein, The plate (110) includes lateral edges (117, 118), and the channel (120) is arranged between the lateral edges.

9. An aircraft turbine engine, characterized in that, The aircraft turbine engine includes a partition, the partition being equipped with a fluid channel system according to any one of the preceding claims.

10. A method for manufacturing a fluid channel system according to any one of claims 1 to 8, characterized in that, The fluid channel system is manufactured using additive manufacturing.

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