Turbomachine incorporating improved harness support means

Abstract

The invention relates to an aircraft turbomachine (10) with main axis A comprising: - a radial arm (18) with respect to the main axis A extending through an airflow channel (14); - a support wall (22) belonging to the radial arm (18) and having two openings (24); - a plurality of electrical harnesses (16) extending partially through the radial arm (18) and of which a section (26) of each harness (16) is fixed to said support wall (22) of the arm (18); characterized in that it comprises two mounting blocks (20), each mounting block (20) being associated with a group of harness sections (26). Figure for the abstract: Figure 3

Description

Title of the invention: Turbomachine comprising improved harness support means technical field

[0001] The invention relates to a turbomachine comprising simplified means for assembling electrical harnesses to a radial support arm. PREVIOUS STATE OF THE ART

[0002] An aircraft turbomachine includes a plurality of electrical cables and pipes which are intended to connect components of the turbomachine located at a place, either to other components, or to sources of electrical power or sources of fluid flowing in the pipes.

[0003] To secure the routing of these electrical cables and pipes, it is known to use harnesses, in which the cables and pipes are grouped together.

[0004] These harnesses are in turn attached to a fixed structure of the turbomachine, by means of mounting blocks.

[0005] According to one embodiment of a mounting block, this is made in three parts which are clamped two by two on either side of aligned harness sections.

[0006] Assembling the parts of the mounting block with the harnesses is relatively complex because a first group of harness sections must be attached to the mounting block before attaching the rest of the harness sections.

[0007] The difficulty of assembly is all the greater because the mounting block must be assembled with the harnesses after the harnesses have passed through openings formed in the fixed structure.

[0008] The various assemblies are made by screwing, parts of the block to each other and to the fixed structure, respectively.

[0009] However, since the harnesses are already in place relative to the fixed structure, access to the fixing screws is difficult.

[0010] This results in a risk of poor assembly, leading to potential pinching of the harnesses, poor positioning of the block or insufficient tightening of the screws.

[0011] The invention aims to provide a solution to facilitate and improve the reliability of the connection of the harnesses with the fixed structure of the turbomachine. Description of the invention

[0012] The invention proposes an aircraft turbomachine with a main axis A comprising:

[0013] - a radial arm with respect to the main axis A extending through a vein airflow;

[0014] - a support wall belonging to the radial arm and which has two openings;

[0015] - a plurality of harnesses extending partly through the radial arm and of which one section of each harness is fixed to said arm support wall;

[0016] characterized in that it comprises two mounting blocks, each of which is associated with a group of harness sections.

[0017] Preferably, the turbomachine includes means for fixing one mounting block to the support wall which are independent of the means for fixing the other mounting block to the support wall.

[0018] Preferably, each mounting block is fixed to the support wall by bolting.

[0019] Preferably, each mounting block comprises a body that is connected to the wall of support and a shaft that receives an associated harness section

[0020] Preferably, the body has a face which is in contact with the support wall and has a shoulder projecting from said face of the body, the section of the shoulder being complementary to said opening.

[0021] Preferably, the support wall extends in a plane substantially perpendicular to a radial direction with respect to the main axis A of the Turbomachine, and said face of the body is fixed to a face of the support wall which is radially external with respect to the main axis A of the Turbomachine.

[0022] Preferably, each mounting block consists of two parts mounted on either side of the harness sections to which the mounting block is associated.

[0023] Preferably, the two parts of a mounting block are connected with the associated harness sections before the mounting block is assembled on the support wall.

[0024] Preferably, each part of the mounting block comprises a part of each barrel of said mounting block.

[0025] Preferably, the radial arm is located at a 6 o'clock position, by analogy with the dial of a clock. Brief description of the drawings

[0026] [Fig. 1] is a schematic partial section representation of a turbomachine showing the location of the harness sections to be connected to the support arm.

[0027] [Fig.2] is a view along a radial direction outwards of the mounting blocks which are assembled on the support wall.

[0028] [Fig.3] is a view along a radial direction towards the inside of the mounting blocks shown in [Fig.2].

[0029] [Fig.4] is a section along a radial plane perpendicular to the main axis A of the turbomachine showing the two mounting blocks assembled on the support wall.

[0030] [Fig.5] is a schematic perspective representation of a mounting block separated into two parts, before its assembly with the harness sections.

[0031] [Fig.6] is a schematic perspective representation of a mounting block separated into two parts, before its assembly with the harness sections. DETAILED DESCRIPTION OF THE INVENTION

[0032] Figure [1] shows part of a turbomachine 10 with main axis A.

[0033] The turbomachine 10 comprises a radially internal primary 12 for circulating a primary airflow and a radially external secondary 14 for circulating a secondary airflow, the two 12, 14 are coaxial with the main axis A of the turbomachine 10.

[0034] The turbomachine 10 comprises a plurality of components which are distributed at many points and which must be connected electrically or fluidly to other components.

[0035] The electrical or fluidic connection of the components is made by means of electrical cables or pipes, respectively, some of which extend through one or the other of the primary vein 12 or the secondary vein 14.

[0036] For this purpose, the cables or pipes are gathered into several groups arranged in sheaths commonly called harnesses 16, which pass through radial arms 18 extending through each vein 12, 14.

[0037] The harnesses 16 are held in place at each radial end of a radial arm 18 by the use of mounting blocks 20 which will be described in more detail later.

[0038] Preferably, each radial end of a radial arm 18 has a support wall 22 which extends perpendicularly to the radial direction of the radial arm 18 and it has openings 24, here two in number, through which the harnesses 16 extend.

[0039] In the description that follows, reference will be made to a section 26 of each harness 16.

[0040] This section 26 of a harness 16 is the part of the harness 16 which extends through an opening 24 in the support wall 22 when the harness 16 is mounted in the turbomachine.

[0041] The sections 26 of the harnesses 16 are held in position relative to the support wall 22 by means of the mounting blocks 20.

[0042] Each mounting block 20 is associated with an opening 24 in the support wall 22, i.e. here, two mounting blocks 20 are associated with the support wall and the harnesses 16 to be attached to it.

[0043] In the following description, reference will be made to only one assembly block 20. It will be understood that the description of the other assembly block 20 will be deduced from the description of the first assembly block by similarity.

[0044] The mounting block 20 comprises several barrels 28, each barrel 28 being associated with a section 26 of a harness 16 associated with the mounting block 20. The dimensions of each fut 28, that is to say in particular the diameter of the latter is defined according to the diameter of the section 26 of harness which is associated with it.

[0045] Each section 26 is further mounted tightly in the barrel 28 associated with it.

[0046] The shafts 28 are located in the opening 24 of the support wall 22 associated with the block assembly 20.

[0047] The mounting block 20 also includes a mainly flat body 30 which extends substantially parallel to the plane of the support wall 22 and which is connected to the shafts 28 and to the support wall 22.

[0048] The body 30 has a peripheral face 32 parallel to the plane of the support wall 22, which is located opposite and is in contact with a contact face 34 of the support wall 22.

[0049] The body 30 also includes a shoulder 36 which is of complementary shape to the associated opening 24 of the support wall 22 and which protrudes from the peripheral face 32.

[0050] This shoulder 36 extends inside the opening 24 of the support wall 22 which is associated with the mounting block 20, ensuring a positioning of the mounting block 20 relative to the support wall 22.

[0051] The means for fixing the mounting block 20 to the support wall 22 consist here of a bolting system 38, which achieves the fixing of the mounting block 20 to the support wall 22 by tightening the peripheral face 32 of the body 30 against the contact face 34 of the support wall 22.

[0052] Each mounting block 20 is made of two parts 40 which are mounted on either side of the harness sections 26 16.

[0053] Preferably, each of the two parts 40 of the mounting block 20 comprises a part of each barrel 28 of the mounting block 20, that is to say that each barrel is formed partly in each part 40 of the mounting block 20.

[0054] According to a preferred embodiment, the two parts 40 of the mounting block 20 are separated by a parting plane P passing through all the barrels 28 of the mounting block 20.

[0055] Thus, when the two parts 40 are separated from each other, it is possible to insert each section 26 of harness 16 into its associated portion of the barrel 28. Then, by assembling the two parts 40 to form the mounting block 20, they clamp the harness sections 26 of harness 16 together.

[0056] According to a preferred embodiment, the barrels 28 are aligned with each other, in a direction parallel to the main plane of the body 30. The joint plane P is thus planar and parallel to the radial direction with respect to the main axis A.

[0057] The two parts 40 of the mounting block 20 are fixed to each other by any known means, for example by bolts 42; these means of fixing the two parts 40 of the mounting block 20 are independent of the means of fixing the mounting block 20 on the support wall 22.

[0058] In the embodiment shown in the figures, the support wall 22 has two openings 24.

[0059] The sections 26 of the harnesses 16 are thus divided into two groups of sections 26, each group of harness sections 26 of harness 16 being associated with an opening 24. Also, the harness sections 26 of the two groups form two alignments which are parallel to each other.

[0060] Each group of harness sections 26 is fixed to the support wall 22 by means of a mounting block 20 associated with it, i.e. that all the harness sections 26 are fixed to the support wall 22 by two mounting blocks 20.

[0061] The means of fixing a mounting block 20 to the support wall 22, i.e. here each bolting system 38, are independent of the means of fixing the other mounting block 20 to the support wall 22.

[0062] Thus, it is possible to mount one group of harness sections 26 of harness 16 on the support wall independently of the other group of harness sections 26 of harness 16.

[0063] As mentioned above, the two parts 40 of a mounting block 20 are fixed to the harness sections 26 16 by bolts 42, which are independent of the means of fixing the mounting block 20 to the support wall 22. Thus, the two parts 40 of the mounting block 20 can be assembled on the harness sections 26 16 before the fixing of the mounting block 20 to the support wall 22.

[0064] Thus, a process for assembling all the harness sections 26 16 on the support wall 22 includes a first phase of linking the harness sections 26 16 of each group of harness sections 26 16, with the mounting block 20 associated with it to form two sub-assemblies, a first sub-assembly comprising a first group of harness sections 26 16 and the mounting block associated with this first group of harness sections 26 16, the second sub-assembly comprising the other group of harness sections 26 16 and the mounting block 20 associated with this other group of harness sections 26 16.

[0065] For this purpose, the harness sections 26 of 16 are put in place in the barrel portions 28 of a first part 40 of the mounting block 20.

[0066] Next, the second part 40 of the mounting block 20 is fixed to the first part 40 of the mounting block by the bolts 42, the harness sections 16 are then tightened in the mounting block 20.

[0067] At the end of this first phase, each group of harness sections 26 is fixed to the mounting block 20 associated with it.

[0068] It will be understood that this first phase of linking the harness sections 26 of the harness 16 can be implemented before or after a phase consisting of passing the harnesses 16 to through openings 24 in the supporting wall 22.

[0069] According to a second phase of the assembly process, the first sub-assembly, which is formed by the first group of harness sections 26 and the mounting block 20 which is associated with this first group of harness sections 26, is fixed to the support wall 22. Then, the second sub-assembly which is formed by the other group of harness sections 26 and the mounting block 20 which is associated with this other group of harness sections 26 is fixed to the support wall 22.

[0070] According to this second phase, the body 30 of each mounting block 20 is positioned on the support wall 22 with the shoulder 36 inserted into the associated opening 24. Then, the mounting block 20 is fixed to the support wall 22 by the bolting system 38.

[0071] Preferably, the contact face 34 of the support wall 22 on which the peripheral face is made in contact, is the radially external face of the support wall 22, with respect to the main axis A of the turbomachine.

[0072] Thus, the body 30 of the mounting block 20 is mounted on the support wall 22 in a radial movement in the direction of the main axis A of the turbomachine. This movement is more natural and easier to achieve than an outward radial movement since access to an inward radial side of the support wall 22 is more restricted than access to the radially external face of the support wall.

[0073] During this second phase, each sub-assembly formed by a group of harness sections 26 16 and the mounting block 20 associated with them, is fixed independently of the other sub-assembly.

[0074] This makes it easier for the operator in charge of the assembly to handle the operation since he only has one sub-assembly to manipulate, the other sub-assembly being either fixed to the support wall 22 or being at a distance from it.

[0075] Also, when a maintenance operation on the turbomachine is to be carried out on a harness 16, there is only one mounting block 20, and the harness sections 26 associated with it, to be dismantled, the whole of the maneuvers is thus even easier for the operator than when all the harness sections 16 are fixed to a single mounting block.

[0076] Furthermore, the first phase of connecting the sections with the mounting blocks 20 can be implemented at a distance from the support wall 22, which further facilitates the manipulations of the operator who has more space when operating at a distance from the support wall 22.

[0077] This advantage is all the more important when the radial arm 18 to which the harnesses are attached is located in the position commonly called 6 o'clock, by analogy with the dial of a clock, that is to say the radial arm 18 which is located in the lower part of the turbomachine 10 and which is vertical.

[0078] This position is particularly difficult for an operator to access. Thus, assembling the harness sections 16 with the mounting blocks 20 before mounting them on the support wall 22 allows certain operations to be carried out in a more easily accessible location.

[0079] The risk of damaging the harnesses 16 by tightening the mounting block 20 is thus reduced since the operator can control the relative positioning of the harness sections 26 16 with respect to each part 40 of the mounting block 20.

Claims

Demands

1. Aircraft turbomachine (10) of main axis A comprising: - a radial arm (18) with respect to the main axis A extending through an airflow channel (14); - a support wall (22) belonging to the radial arm (18) and having two openings (24); - a plurality of harnesses (16) extending partly through the radial arm (18) and of which a section (26) of each harness (16) is fixed to said support wall (22) of the arm (18); the turbomachine comprising includes two mounting blocks (20) of which each mounting block (20) is associated with a group of harness sections (26), characterized in that each mounting block (20) comprises a body (30) which is connected to the support wall (22) and a shaft (28) which receives an associated harness section (26).

2. Turbomachine (10) according to the preceding claim, characterized in that it comprises means for fixing a mounting block (20) on the support wall (22) which are independent of the means for fixing the other mounting block (20) on the support wall (22).

3. Turbomachine (10) according to claim 1 or 2, characterized in that each mounting block (20) is fixed to the support wall (22) by bolting.

4. Turbomachine (10) according to any one of the preceding claims, characterized in that the body (30) has a face (32) which is in contact with the support wall (22) and has a shoulder (36) projecting out from said face (32) of the body (30), the cross-section of the shoulder (36) being complementary to said opening (24).

5. Turbomachine (10) according to the preceding claim, wherein the support wall (22) extends in a plane substantially perpendicular to a radial direction with respect to the main axis A of the Turbomachine (10), characterized in that said face (32) of the body (30) is fixed to a face (34) of the support wall (22) which is radially external with respect to the main axis A of the Turbomachine (10).

6. Turbomachine (10) according to any one of the preceding claims, characterized in that each mounting block (20) consists of two parts (40) mounted on either side of the sections (26) of harnesses (16) to which the mounting block (20) is associated.

7. Turbomachine (10) according to the preceding claim, characterized in that the two parts (40) of a mounting block (20) are connected with the associated harness sections (26) (16) before the mounting block (20) is assembled on the support wall (22).

8. Turbomachine (10) according to the preceding claim, characterized in that each part (40) of the mounting block (20) comprises a part of each barrel (28) of said mounting block (20).

9. Turbomachine (10) according to the preceding claim, characterized in that the radial arm (18) is located at a 6 o'clock position, by analogy with the dial of a clock.

Images