Electrical Equipment Support Assembly for an Aircraft Propulsion System

Abstract

The invention relates to an assembly of support (114) for electrical equipment for an aircraft propulsion assembly (100), the assembly comprising: a structural support (200); electrical equipment (204a, 204b, 204c) carried by the structural support (200); at least one electrical linking element (206) of the equipment (204a, 204b, 204c) between them, and dampers (208) interposed between the electrical equipment (204a, 204b, 204c) and the structural support (200); characterized in that it further comprises a single mounting plate (202) for at least two of the electrical components (204a, 204b, 204c), said at least two electrical components (204a, 204b, 204c) being rigidly fixed to the mounting plate which is fixed by the shock absorbers (208) to the structural support (200), and in that said at least one electrical connecting element (206) is at least partially rigid. Figure for the abbreviation: Figure 2

Description

Title of the invention: ELECTRICAL EQUIPMENT SUPPORT ASSEMBLY FOR AN AIRCRAFT PROPULSION ASSEMBLY Technical field of the invention

[0001] The present invention relates to an electrical equipment support assembly for an aircraft propulsion assembly and a propulsion assembly comprising this support assembly. Technological background

[0002] An aircraft propulsion system may include at least one turbomachine and a nacelle surrounding the turbomachine. The nacelle may contain various electrical components that must be mounted on a structural support. Generally, this structural support is the turbomachine housing.

[0003] A prior art support assembly for electrical equipment for an aircraft propulsion system is thus known, the assembly comprising: - structural support; - electrical equipment supported by the structural support; - at least one electrical connection element between the equipment, and - shock absorbers interposed between the electrical equipment and the structural support.

[0004] The shock absorbers are configured to absorb the vibrations generated by the operation of the turbomachine engine and transmitted to the structural support, in particular the casing on which the electrical equipment is fixed.

[0005] As for the electrical connections linking the various electrical components, they do not include shock absorbers and can be subjected to vibrations from the support. When these electrical connections are rigid, this can lead to their damage. When an electrical connection is damaged, it can also cause damage to the electrical components or even degradation or a decrease in the performance of the propulsion system.

[0006] One solution to reduce the risk of damage to electrical equipment, and in particular to electrical connections, is to install each piece of electrical equipment independently of the other equipment and to interconnect these pieces of equipment via flexible electrical connections such as harnesses, power feeders, or flexible busbars. However, this solution is costly (especially with the use of flexible busbars) and often involves complex assembly (the harness solution), increasing the There is a risk of poor equipment connections and making maintenance operations difficult. Indeed, the structural support, such as the casing or a pylon for attaching the turbomachine to the aircraft, is an environment that can be subject to strong stresses (vibrations, temperatures, etc.) and the use of harnesses in such an environment can prove complex (need to respect different professional rules such as the radius of curvature, the accessibility of connectors, the retention of harnesses, etc.).

[0007] In addition, such a solution can very quickly limit the number of equipment to be installed on the structural support when the space provided for the arrangement of the equipment is restricted.

[0008] It may therefore be desirable to provide a set of support which makes it possible to overcome at least some of the aforementioned problems and constraints. Summary of the invention

[0009] A support assembly for electrical equipment for an aircraft propulsion system is therefore proposed, the assembly comprising: - structural support; - electrical equipment supported by the structural support; - at least one electrical connection element between the equipment, and - shock absorbers inserted between the electrical equipment and the structural support; characterized in that it further comprises a single support plate for at least two of the electrical equipment, said at least two electrical equipment being rigidly fixed to the plate which is fixed by the shock absorbers to the structural support, and in that said at least one electrical linking element is at least partly rigid.

[0010] Thus, thanks to the invention, it is possible to reduce the risk of damage to electrical connections and equipment and to simplify the installation and arrangement of this equipment.

[0011] The invention makes it possible to facilitate the routing between different electrical equipment installed in the same area by freeing oneself from the constraints related to harness routing (need to respect different business rules such as the radius of curvature, the accessibility of connectors, the maintenance of harnesses...).

[0012] The invention also makes it possible to have a more compact installation of this equipment and to free up space for other equipment and / or to facilitate the installation of this electrical equipment in constrained environments.

[0013] The invention also makes it easier to access the assembly, disassembly and maintenance operations, but also reduces the risks of reversing the connections.

[0014] The invention may further include one or more of the following optional features, in any technically feasible combination: - the turntable is adjustable in width and / or length; - at least three of the electrical equipment, or even all of the electrical equipment, are mounted on the circuit board; - said at least one connecting element is integral with the plate, and in particular fixed directly to the plate; - the plate has a lattice shape; - the shock absorbers are elastically deformable pads; - said at least one connecting element includes at least one rigid bus bar; - the electrical equipment is chosen from a power distribution management unit, a high-pressure converter and a low-pressure converter; - the structural support is chosen from a pylon and a casing.

[0015] The invention also relates to a propulsion system for an aircraft comprising: - a turbomachine; and - a support assembly as described above.

[0016] The propulsion assembly may further include the following optional feature, according to any technically possible combination: the structural support is a pylon or an external or internal casing of the turbomachine. Brief description of the figures

[0017] The invention will be better understood with the aid of the following description, given solely by way of example and made with reference to the accompanying drawings in which: - [Fig.1] is a schematic representation of a propulsion assembly according to the invention; - [Fig. 2] is a perspective view representation of an example of a support assembly according to the invention; and - [Fig.3] a perspective view of part of the support assembly of [Fig.2]. Detailed description of the invention

[0018] With reference to [Fig.1], an example of an aircraft propulsion assembly 100 in which the invention is implemented will now be described.

[0019] The propulsion assembly 100 includes at least one turbomachine 102 and an electrical equipment support assembly 114.

[0020] In general, the turbomachine 100, in particular of aircraft, as illustrated in [Fig.1], comprises from upstream to downstream (i.e. in the direction of flow of the gas flows F), a blower 112, one or more compressors 104a, 104b, a combustion chamber 106, one or more turbines 108a, 108b and an ejection nozzle 110 of the combustion gases exiting the turbine(s).

[0021] With reference to [Fig.2], the support assembly 114 includes a structural support 200. By structural support is meant a rigid support capable of transmitting a force.

[0022] The structural support 200 can be, for example, an internal casing of the turbomachine 102 or a mounting pylon of the turbomachine 102 to a wing of the aircraft 100. Preferably, the structural support 200 is selected from a mounting pylon of the turbomachine 102 as illustrated in [Fig.2] or, an external or internal casing of the turbomachine 102. The casing can be made of metallic or composite material.

[0023] Still with reference to [Fig.2], the support assembly 114 further includes electrical equipment 204a, 204b, 204c, which can be independent of each other and carried by the structural support 200. In the example of [Fig.2], the support assembly includes three electrical equipment.

[0024] Electrical equipment may be, for example, a power distribution management unit (or PDMU for Power Distribution Management Unit) or generators or converters.

[0025] The support assembly 114 further includes at least one electrical connection element 206 for the equipment 204a, 204b, 204c. At least one electrical connection element 206 is at least partially rigid.

[0026] The electrical connection includes at least one rigid bus bar. Preferably, the electrical connections 206 are rigid bus bars.

[0027] Advantageously, the use of rigid electrical connections makes it possible to make the arrangement of electrical equipment 204a, 204b, 204c more compact and to overcome the constraints related to the use of harnesses and their routing.

[0028] The support assembly 114 further includes shock absorbers 208 interposed between the electrical equipment 204a, 204b, 204c and the structural support 200. Preferably, the shock absorbers 208 are elastically deformable pads.

[0029] With reference to [Fig.3], the support assembly 114 of the present invention further comprises a single support plate 202 for at least two of the electrical equipment 204a, 204b, 204c.

[0030] The electrical equipment 204a, 204b, 204c is rigidly fixed to the support plate 202 which, in turn, is fixed by the shock absorbers 208 to the structural support 200. The shock absorbers are therefore mainly located between the support plate 202 and the structural support 200.

[0031] At least one electrical connection element 206 is preferably integral with the mounting plate, and in particular fixed directly to the mounting plate 202. If the electrical connection 206 is directly fixed (or integrated) into the mounting plate 202, the various electrical components 204a, 204b, 204c can be directly fixed to the mounting plate 202 and to the electrical connection, one after the other. This simplifies the assembly of the system.

[0032] Thus, unlike the prior art, the shock absorbers are not directly attached to the electrical equipment. In the event of vibration of the structural support 200, the forces are essentially transmitted to the support plate 202, which reduces the risk of damage to the electrical equipment 204a, 204b, 204c and primarily to the electrical connections 206.

[0033] Preferably, the support plate 202 has a lattice-shaped structure comprising horizontal bars 302, vertical bars 304 and diagonal bars 306. This structure further moderates the stresses experienced by the plate and thus further reduces the risk of damage to the connections 206 and the electrical equipment 204a, 204b, 204c.

[0034] The support assembly may further include a sliding member (not shown) on a portion of the plate, the member being configured to lengthen or shorten a dimension of the plate (the one on which the member is located). The dimension may be a length or a width of the plate.

[0035] A person skilled in the art will understand that it is possible to adapt the dimensions of the plate to different sizes of electrical equipment and / or to add new equipment. The sliding element is, for example, a slide.

[0036] In order to maintain overall damping and keep the assembly in balance in case of additional equipment, the support assembly may further include counterweights placed near each piece of equipment.

[0037] Advantageously, a person skilled in the art will understand that the invention as described above makes it possible to: - facilitate routing between different equipment installed in the same area by eliminating the constraints related to harness routing (need to respect different business rules such as bend radius, connector accessibility, harness retention...); - to create a more compact installation for this equipment and free up space for other equipment and / or facilitate the installation of this electrical equipment in constrained environments; and - to facilitate accessibility for assembly, disassembly and maintenance operations, but also to reduce the risks of reversing connections.

[0038] In the detailed presentation of the invention given above, the terms used shall not be interpreted as limiting the invention to the embodiments set forth in this description, but shall be interpreted as including all equivalents which can be foreseen by a person skilled in the art by applying their general knowledge to the implementation of the teaching which has just been disclosed to them.

Claims

Demands

1. Electrical equipment support assembly (114) for an aircraft propulsion assembly (100), the assembly comprising: - a structural support (200); - electrical equipment (204a, 204b, 204c) carried by the structural support (200); - at least one electrical linking element (206) for the equipment (204a, 204b, 204c) between them, and - shock absorbers (208) interposed between the electrical equipment (204a, 204b, 204c) and the structural support (200); characterized in that it further comprises a single support plate (202) for at least two of the electrical equipment (204a, 204b, 204c), said at least two electrical equipment (204a, 204b, 204c) being rigidly fixed to the plate which is fixed by the shock absorbers (208) to the structural support (200), and in that said at least one electrical connecting element (206) is at least partly rigid.

2. Support assembly (114) according to claim 1, wherein the plate (202) is adjustable in width and / or length.

3. Support assembly (114) according to claim 1 or 2, wherein at least three of the electrical equipment (204a, 204b, 204c), or even all of the electrical equipment (204a, 204b, 204c), are mounted on the plate (202).

4. Support assembly (114) according to any one of claims 1 to 3, wherein said at least one connecting element (206) is integral with the plate (202), and in particular fixed directly to the plate (202).

5. Support assembly (114) according to any one of claims 1 to 4, wherein the plate (202) has a lattice shape.

6. Support assembly (114) according to any one of claims 1 to 5, wherein the dampers (208) are elastically deformable pads.

7. Support assembly (114) according to any one of claims 1 to 6, wherein said at least one connecting element (206) comprises at least one rigid bus bar.

8. Support assembly (114) according to any one of claims 1 to 7, wherein the electrical equipment (204a, 204b, 204c) is selected from a power distribution management unit, a converter or a generator.

9. Support assembly (114) according to any one of claims 1 to 8, wherein the structural support (200) is selected from a pylon and a casing.

10. Propulsion assembly (100) for an aircraft comprising: - a turbomachine (102); and - a support assembly (114) according to any one of the preceding claims.

11. Propulsion assembly (100) according to the preceding claim, wherein the structural support (200) is a pylon or an external or internal casing of the turbomachine (102).

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