Turbine engines including improved wiring harness support

Abstract

The present invention relates to an aircraft turbine engine (10) having a main axis A, comprising: an arm (18) radially relative to the main axis A, the arm extending through an airflow duct (14); a support wall (22) belonging to the radial arm (18) and including two openings (24); a plurality of wire harnesses (16) partially extending through the radial arm (18), and a segment (26) of each wire harness (16) being fastened to the support wall (22) of the arm (18); characterized in that it comprises two mounting blocks (20), each mounting block (20) being associated with a set of segments (26) of the wire harnesses (16).

Description

Technical Field

[0001] The present invention relates to a turbine engine, which includes a simplified means for assembling an electrical wiring harness to a radial support arm. Existing technology

[0002] An aircraft turbine engine includes multiple cables and hoses for connecting turbine engine components located in one location to other components, or to an electrical or fluid source circulating in the hoses.

[0003] It is well known that wire harnesses, in which cables and hoses are combined, are used to ensure the wiring of these cables and conduits.

[0004] Furthermore, these wiring harnesses are secured to the turbine engine's mounting structure via mounting blocks.

[0005] According to an embodiment of the mounting block, the mounting block is made of three parts, which are screwed in pairs onto both sides of the aligned wire harness section.

[0006] The assembly of the various parts of the mounting block with the wire harness is relatively complex because the first set of wire harness sections should be fastened to the mounting block before the rest of the wire harness sections are fastened.

[0007] Assembly is even more difficult because the mounting block should be assembled with the wire harness after the wire harness passes through the opening formed in the fixed structure.

[0008] Different assemblies are achieved by threading the various parts of the mounting block together with each other and threading them together on a fixed structure.

[0009] However, because the wiring harness is already positioned in the appropriate location relative to the fixed structure, it is difficult to access the fastening screws.

[0010] This can lead to the risk of poor assembly, such as the wire harness being caught, improper positioning of the mounting block, or insufficient tightening of screws.

[0011] The present invention aims to provide a solution that allows for the connection of wiring harnesses to the fixed structure of a turbine engine and makes it reliable. Summary of the Invention

[0012] This invention proposes an aircraft turbine engine with a main axis A, comprising:

[0013] - An arm that extends radially relative to the main axis A through the airflow duct;

[0014] - A support wall, which is part of a radial arm and includes two openings;

[0015] - Multiple wire harnesses, which partially extend through the radial arm and a section of each wire harness is fastened to the support wall of the arm;

[0016] Its characteristic feature is that it includes two mounting blocks, each of which is associated with a set of wire harness segments.

[0017] Preferably, the turbine engine includes means for securing a mounting block to a support wall, the means being independent of means for securing another mounting block to the support wall.

[0018] Preferably, each mounting block is fastened to the support wall by bolts.

[0019] Preferably, each mounting block includes a body connected to a support wall and a cylinder for receiving an associated wire harness segment.

[0020] Preferably, the body includes a surface that contacts the support wall and includes a shoulder that protrudes relative to the surface of the body, the segment of the shoulder being complementary to the opening.

[0021] Preferably, the support wall extends along a plane substantially perpendicular to a direction radially relative to the main axis A of the turbine engine, and the surface of the body is fastened to the surface of the support wall that is radially outward relative to the main axis A of the turbine engine.

[0022] Preferably, each mounting block comprises two portions mounted on both sides of a segment of the wire harness, and the mounting block is associated with the segment of the wire harness.

[0023] Preferably, the two parts of the mounting block are connected to the associated wire harness section before the mounting block is assembled onto the support wall.

[0024] Preferably, each part of the mounting block includes a portion of each cylinder of the mounting block.

[0025] Preferably, the dial resembles a clock, with the radial arm positioned at the 6 o'clock position.

[0026] Brief description of the attached figures

[0027] Figure 1 This is a schematic diagram of a section of a turbine engine, showing the location of the wiring harness section to be connected to the support arm.

[0028] Figure 2 It is a view in the radial outward direction based on the mounting block assembled on the support wall.

[0029] Figure 3 It is based on Figure 2 The view of the mounting block in the radial inward direction is shown.

[0030] Figure 4The section shown illustrates two mounting blocks assembled on the support wall, based on a radial plane perpendicular to the turbine engine's main axis A.

[0031] Figure 5 This is a perspective view of the mounting block, which is divided into two parts before the mounting block and the wire harness section are assembled together.

[0032] Figure 6 This is a perspective view of the mounting block, which is divided into two parts before the mounting block and the wire harness section are assembled together. Detailed Implementation

[0033] exist Figure 1 The image shows a portion of a turbine engine 10 with a main axis A.

[0034] The turbine engine 10 includes a radially inner primary duct 12 for primary airflow circulation and a radially outer secondary duct 14 for secondary airflow circulation. These two ducts 12 and 14 are coaxial with the main axis A of the turbine engine 10.

[0035] The turbine engine 10 includes multiple components distributed at multiple locations and must be electrically or fluidly connected to other components.

[0036] The electrical or fluid connections of the components are achieved by cables or hoses, some of which extend through the primary conduit 12 or the secondary conduit 14.

[0037] For this purpose, the cables or hoses are grouped together into several sets, which are housed in a sheath commonly referred to as harness 16, which passes through radial arms 18 that extend through each conduit 12, 14.

[0038] The harness 16 is held in place at each radial end of the radial arm 18 by using the mounting block 20, which will be described in more detail later.

[0039] Preferably, each radial end of the radial arm 18 includes a support wall 22 extending in a radial direction perpendicular to the radial arm, and the support wall includes two openings 24 through which the wire harness 16 extends.

[0040] In the following description, reference will be made to segment 26 of each harness 16.

[0041] This section 26 of the wiring harness 16 is the portion of the wiring harness 16 that extends through the opening 24 of the support wall 22 when the wiring harness 16 is installed in the turbine engine.

[0042] Section 26 of the wiring harness 16 is held in place relative to the support wall 22 by mounting block 20.

[0043] Each mounting block 20 is associated with an opening 24 in the support wall 22, that is, here two mounting blocks 20 are associated with the support wall and with the wiring harness 16 to be fastened to the support wall.

[0044] In the following description, reference will be made to a single mounting block 20. It should be understood that the description of another mounting block 20 will be derived from the description of the first mounting block by means of similarity.

[0045] Mounting block 20 includes several cylinders 28, each of which is associated with a segment 26 of a wire harness 16 associated with mounting block 20. The dimensions of each cylinder 28, specifically its diameter, are defined according to the diameter of the wire harness segment 26 associated with it.

[0046] In addition, each section 26 is tightly installed in the cylinder 28 to which it is associated.

[0047] The cylinder 28 is located in the opening 24 of the support wall 22 associated with the mounting block 20.

[0048] Mounting block 20 also includes a body 30 of a basic plane, which extends generally parallel to the plane of support wall 22 and is connected to cylinder 28 and support wall 22.

[0049] The body 30 includes an outer peripheral surface 32 that is parallel to the plane of the support wall 22, the outer peripheral surface 32 being opposite to and in contact with the contact surface 34 of the support wall 22.

[0050] The body 30 also includes a shoulder 36 having a shape that is complementary to the opening 24 of the associated support wall 22 and protrudes relative to the outer peripheral surface 32.

[0051] The shoulder 36 extends inside the opening 24 of the support wall 22 associated with the mounting block 20, ensuring the positioning of the mounting block 20 relative to the support wall 22.

[0052] Here, the means for fastening the mounting block 20 to the support wall 22 includes a bolt connection system 38, which fastens the mounting block 20 to the support wall 22 by clamping the outer peripheral surface 32 of the body 30 onto the contact surface 34 of the support wall 22.

[0053] Each mounting block 20 is made into two parts 40 that are mounted on either side of a segment 26 of the harness 16.

[0054] Preferably, each of the two portions 40 of the mounting block 20 includes a portion of each cylinder 28 of the mounting block 20, that is, each cylinder is partially formed in each portion 40 of the mounting block 20.

[0055] According to a preferred embodiment, the two portions 40 of the mounting block 20 are separated by a parting surface P that passes through all the cylinders 28 of the mounting block 20.

[0056] Therefore, when the two parts 40 are separated from each other, each segment 26 of the wire harness 16 can be inserted into a part of the associated cylinder 28. Then, by assembling the two parts 40 to form mounting blocks 20, the segments 26 of the wire harness 16 are held between them.

[0057] According to a preferred embodiment, the cylinders 28 are aligned with each other in a direction parallel to the main plane of the body 30. Therefore, the parting surface P is a plane, and it is parallel to the radial direction relative to the main axis A.

[0058] The two parts 40 of the mounting block 20 are fastened to each other by any known means, such as by bolts 42, and these means for securing the two parts of the mounting block 20 are independent of the means for fastening the mounting block 20 to the support wall 22.

[0059] In the embodiment shown in the figure, the support wall 22 includes two openings 24.

[0060] Therefore, the segments 26 of the wire harness 16 are divided into two groups of segments 26, each group of segments 26 of the wire harness 16 being associated with the opening 24. Moreover, the two groups of segments 26 of the wire harness 16 form two parallel alignments.

[0061] Each group of segments 26 of the wire harness 16 is fastened to the support wall 22 by the mounting block 20 associated with it; that is, all segments 26 of the wire harness 16 are fastened to the support wall 22 by two mounting blocks 20.

[0062] The means for fastening the mounting block 20 to the support wall 22, namely each bolt connection system 38 here, is independent of the means for fastening another mounting block 20 to the support wall 22.

[0063] Therefore, a set of sections of the harness 16 can be mounted on the support wall independently of another set of sections 26 of the harness 16.

[0064] As described above, the two portions 40 of the mounting block 20 are fastened to the section 26 of the wire harness 16 by bolts 42, which are independent of the means for fastening the mounting block 20 to the support wall 22. Therefore, the two portions 40 of the mounting block 20 can be assembled onto the section 26 of the wire harness 16 before the mounting block 20 is fastened to the support wall 22.

[0065] Therefore, the process for assembling all segments 26 of the wire harness 16 onto the support wall 22 includes linking each group of segments 26 of the wire harness 16 and the associated mounting block 20 to form a first stage of two sub-assemblies. The first sub-assembly includes a first group of segments 26 of the wire harness 16 and a mounting block associated with the first group of segments 26a of the wire harness 16, and the second sub-assembly includes another group of segments 26 of the wire harness 16 and a mounting block 20 associated with the other group of segments 26 of the wire harness 16.

[0066] For this purpose, section 26 of the wire harness 16 is positioned in the appropriate location within the cylinder 28 portion of the first part 40 of the mounting block 20.

[0067] Then, the second part 40 of the mounting block 20 is fastened to the first part 40 of the mounting block by bolt 42, and the wire harness section 16 is then tightened in the mounting block 20.

[0068] Upon completion of this first phase, each group of segments 26 of the harness 16 is secured to its associated mounting block 20.

[0069] It should be understood that the first stage of connecting the section 26 of the wire harness 16 can be carried out before or after the stage of allowing the wire harness 16 to pass through the opening 24 of the support wall 22.

[0070] According to the second stage of the assembly process, a first sub-assembly formed by a first set of segments 26 of the wire harness 16 and mounting blocks 20 associated with the first set of segments 26 of the wire harness 16 is fastened to the support wall 22. Then, a second sub-assembly formed by another set of segments 26 of the wire harness 16 and mounting blocks 20 associated with the other set of segments 26 of the wire harness 16 is fastened to the support wall 22.

[0071] According to this second stage, 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. The mounting block 20 is then fastened to the support wall 22 by a bolt connection system 38.

[0072] Preferably, the contact surface 34 of the support wall 22 is the radial outer surface of the support wall 22 relative to the main axis A of the turbine engine, and the outer peripheral surface contacts the contact surface.

[0073] Therefore, the body 30 of the mounting block 20 is mounted on the support wall 22 according to the radial movement along the main axis A of the turbine engine. This movement is more natural and easier to implement than radial outward movement because the radially inner side of the support wall 22 is more restricted than the radially outer surface of the support wall.

[0074] During this second phase, each sub-assembly formed by a set of segments 26 of the harness 16 and the associated mounting block 20 is fastened independently of the other sub-assembly.

[0075] This makes it easier for the operator responsible for the component to operate, as he only has one sub-component to handle, while the other sub-component is either fastened to the support wall 22 or at a certain distance from the support wall.

[0076] Furthermore, when maintenance operations on the turbine engine should be performed on the wiring harness 16, there is only one mounting block 20 and the associated section 26 of the wiring harness 16 to be removed, so all operations here are even easier for the operator than when all the wiring harness sections 16 are secured to a single mounting block.

[0077] Furthermore, the first stage of linking the section to the mounting block 20 can be carried out at a certain distance from the support wall 22, which further facilitates the operator's operation, as the operator has more available space when operating at a certain distance from the support wall 22.

[0078] Similar to a clock face, this advantage is even more important when the wiring harness is fastened to the radial arm 18 at the position commonly referred to as the 6 o'clock position, that is, positioned below the turbine engine 10 and vertically.

[0079] This location is particularly difficult for the operator to access. Therefore, assembling the harness section 16 with the mounting block 20 before mounting the harness section 16 onto the support wall 22 allows certain operations to be performed from a more accessible location.

[0080] Because the operator can control the relative positioning of the section 26 of the harness 16 with respect to each part 40 of the mounting block 20, the risk of damaging the harness 16 by tightening the mounting block 20 is reduced.

Claims

1. An aircraft turbine engine (10) having a main shaft A, and comprising: - Arm (18), which is radial relative to the main axis A extending through the airflow duct (14); - Support wall (22), which belongs to radial arm (18) and includes two openings (24); - Multiple wire bundles (16) that extend partially through the radial arm (18) and a segment (26) of each wire bundle (16) is fastened to the support wall (22) of the arm (18); The feature is that it further includes two mounting blocks (20), each of which is associated with a set of segments (26) of the wire harness (16).

2. The turbine engine (10) according to claim 1, characterized in that, It also includes means for fastening the mounting block (20) to the support wall (22), the means being independent of the means for fastening another mounting block (20) to the support wall (22).

3. The turbine engine (10) according to claim 1 or 2, characterized in that, Each of the mounting blocks (20) is fastened to the support wall (22) by bolts.

4. The turbine engine (10) according to claim 1 or 2, characterized in that, Each of the mounting blocks (20) includes a body (30) connected to the support wall (22) and a cylinder (28) for receiving an associated segment (26) of the wire harness (16).

5. The turbine engine (10) according to claim 4, characterized in that, The body (30) includes a surface (32) that contacts the support wall (22) and includes a shoulder (36) that protrudes from the surface (32) of the body (30), a section of the shoulder (36) being complementary to the opening (24).

6. The turbine engine (10) according to claim 5, wherein, The support wall (22) extends along a plane that is substantially perpendicular to the radial direction of the main axis A of the turbine engine (10). The characteristic feature is that the surface (32) of the body (30) is fastened to the surface (34) of the support wall (22) which is radially outward relative to the main axis A of the turbine engine (10).

7. The turbine engine (10) according to claim 1 or 2, characterized in that, Each of the mounting blocks (20) includes two portions (40) mounted on either side of the segment (26) of the harness (16) associated with the mounting block (20).

8. The turbine engine (10) according to claim 7, characterized in that, Before the mounting block (20) is assembled onto the support wall (22), the two portions (40) of the mounting block (20) are connected to the associated segment (26) of the wire harness (16).

9. The turbine engine (10) according to claim 4, characterized in that, Each of the mounting blocks (20) includes two portions (40) mounted on either side of the section (26) of the wire harness (16) associated with the mounting block (20), and each portion (40) of the mounting block (20) includes a portion of each cylinder (28) of the mounting block (20).

10. The turbine engine (10) according to claim 9, characterized in that, Similar to a clock face, the radial arm (18) is positioned at the 6 o'clock position.

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