Aviation tubing welding fixture

Abstract

The utility model provides a kind of aviation pipeline welding tool, including support beam and three support seats;Three support seats are fixed on support beam along the extension direction of aviation pipeline and are spaced distribution, three support seats are respectively used to support the first elbow pipe section, straight pipe section and second elbow pipe section of aviation pipeline, the upper end of three support seats is respectively provided with first slot, second slot and third slot, first slot, second slot and third slot are respectively used to with first elbow pipe section, straight pipe section and second elbow pipe section Partially embedded;The utility model can bring convenience to the welding of first elbow pipe section and second elbow pipe section and straight pipe section, and after welding is completed, it can guarantee that the relative angle of first elbow pipe section and second elbow pipe section remains in the required angle state.

Description

Technical Field

[0001] This utility model relates to the technical field of auxiliary devices for aviation pipeline welding, and more specifically, to an aviation pipeline welding fixture. Background Technology

[0002] Aviation piping refers to the type of piping used in aircraft to supply fluids. Aviation piping is often irregularly shaped; for example, a typical aviation piping system includes a first bend, a straight section, and a second bend. The straight section is located between the first and second bends, and both ends of the straight section are welded and sealed to one end of the first and second bends, respectively. The other ends of the first and second bends are used to connect to components in the aircraft. However, currently, there are no specialized welding fixtures for welding the first and second bends to the straight section, making it difficult to ensure the relative angles of the first and second bends. Consequently, when connecting the aviation piping to components, after one end of the aviation piping is connected to an interface on one component, the other end will have assembly tolerances with the interface on another component. This leads to inconvenience in assembling aviation piping, and the bending during assembly can easily cause damage to the aviation piping. Utility Model Content

[0003] The technical problem to be solved by this utility model is to provide a welding fixture for aviation pipelines, which can facilitate the welding of the first and second bend pipe sections to the straight pipe section, and ensure that the relative angle between the first and second bend pipe sections is maintained at the required angle after welding.

[0004] This utility model provides a welding fixture for aviation pipelines, including a support beam and three support seats. The three support seats are fixed on the support beam at intervals along the extension direction of the aviation pipeline. The three support seats are used to support the first bend section, the straight section and the second bend section of the aviation pipeline, respectively. The upper end of the three support seats is provided with a first groove, a second groove and a third groove, respectively. The first groove, the second groove and the third groove are used to partially engage with the first bend section, the straight section and the second bend section.

[0005] By adopting the above-described structure, before the first bend, straight section, and second bend are welded to form an aviation pipeline, the first bend, straight section, and second bend can respectively engage with the first, second, and third grooves at the upper ends of the three support seats. This allows for the limiting of the first bend, straight section, and second bend, facilitating the welding of the first and second bends to the straight section. Furthermore, after welding, the relative angle between the first and second bends is maintained at the required angle. This avoids assembly tolerances when connecting the aviation pipeline to corresponding components in the aircraft, thus facilitating the assembly of the aviation pipeline and preventing damage to the aviation pipeline.

[0006] In one possible implementation, a first radial limiting structure is provided between the first bend section and the straight section, and a second radial limiting structure is provided between the second bend section and the straight section. Through the provision of the first and second radial limiting structures, the first radial limiting structure enables radial limiting of the first bend section and the straight section, and the second radial limiting structure enables radial limiting of the second bend section and the straight section. This allows for pre-connection of the first and second bend sections with the straight section, thus preventing the first bend section, the straight section, and the second bend section from falling off the three support seats after the aviation pipeline is supported on them.

[0007] In one possible implementation, the first radial limiting structure includes a first annular slot disposed on the inner wall of the straight pipe section facing the first bend pipe section, and a first annular boss disposed on the end of the first bend pipe section facing the straight pipe section. The first annular boss engages with the first annular slot and provides radial limiting. By adopting this first radial limiting structure, after the first annular boss engages with the first annular slot, pre-connection of the first bend pipe section and the straight pipe section and radial limiting of the first bend pipe section and the straight pipe section can be achieved. After the first annular boss engages with the first annular slot, the first annular boss can achieve rotational engagement with the first annular slot.

[0008] In one possible implementation, the second radial limiting structure includes a second annular slot disposed on the inner wall of the straight pipe section facing the second bend pipe section, and a second annular boss disposed on the end of the second bend pipe section facing the straight pipe section. The second annular boss engages with the second annular slot and provides radial limiting. By adopting this second radial limiting structure, after the second annular boss engages with the second annular slot, pre-connection of the second bend pipe section and the straight pipe section and radial limiting of the second bend pipe section and the straight pipe section can be achieved. After the second annular boss engages with the second annular slot, the second annular boss can achieve rotational engagement with the second annular slot. Attached Figure Description

[0009] Figure 1 A three-dimensional structural diagram of the aviation pipeline placed on this utility model; Figure 2 A three-dimensional structural diagram of the aviation pipeline after it has been separated from this utility model; Figure 3 This is a cross-sectional view of an aviation pipeline. Figure 4 for Figure 3 A magnified structural diagram of point A in the middle; Figure 5 for Figure 3 A magnified structural diagram of section B. Detailed Implementation

[0010] First, those skilled in the art should understand that these embodiments are merely used to explain the technical principles of the embodiments of this application and are not intended to limit the scope of protection of the embodiments of this application. Those skilled in the art can make adjustments as needed to adapt to specific application scenarios.

[0011] In the description of the embodiments of this application, it should be noted that, unless otherwise explicitly specified and limited, the terms "connected" and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in the embodiments of this application based on the specific circumstances.

[0012] In the embodiments of this application, unless otherwise expressly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "on top of," and "over" the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0013] The present application will now be described in further detail with reference to the accompanying drawings and specific embodiments.

[0014] See Figures 1-5As shown in the figure, this application discloses an aviation pipeline welding fixture, including a support beam 1 and three support seats 2. The three support seats 2 are fixed on the support beam 1 at intervals along the extension direction of the aviation pipeline 3. The three support seats 2 are respectively used to support the first bend section 31, the straight section 32 and the second bend section 33 of the aviation pipeline 3. The upper ends of the three support seats 2 are respectively provided with a first groove 21, a second groove 22 and a third groove 23. The first groove 21, the second groove 22 and the third groove 23 are respectively used to partially fit with the first bend section 31, the straight section 32 and the second bend section 33.

[0015] A first radial limiting structure is provided between the first bend section 31 and the straight section 32, and a second radial limiting structure is provided between the second bend section 33 and the straight section 32. Through the setting of the first and second radial limiting structures, the first radial limiting structure can achieve radial limiting of the first bend section and the straight section, and the second radial limiting structure can achieve radial limiting of the second bend section and the straight section. This enables the pre-connection of the first bend section, the second bend section and the straight section, and prevents the first bend section, the straight section and the second bend section from falling off the three support seats after the aviation pipeline is supported on the three support seats.

[0016] The first radial limiting structure includes a first annular slot 321 disposed on the inner wall of the straight pipe section 32 facing the first bend pipe section 31, and a first annular boss 311 disposed on the end of the first bend pipe section 31 facing the straight pipe section 32. The first annular boss 311 is engaged with the first annular slot 321 and radially limited. By adopting this first radial limiting structure, after the first annular boss is engaged with the first annular slot, the pre-connection of the first bend pipe section and the straight pipe section and the radial limiting of the first bend pipe section and the straight pipe section can be realized. After the first annular boss is engaged with the first annular slot, the first annular boss can achieve rotational engagement with the first annular slot.

[0017] The second radial limiting structure includes a second annular slot 322 disposed on the inner wall of the straight pipe section 32 facing the second bend pipe section 33, and a second annular boss 331 disposed on the end of the second bend pipe section 33 facing the straight pipe section 32. The second annular boss 331 is engaged with the second annular slot 322 and radially limited. By adopting this second radial limiting structure, after the second annular boss is engaged with the second annular slot, the pre-connection of the second bend pipe section and the straight pipe section and the radial limiting of the second bend pipe section and the straight pipe section can be realized. After the second annular boss is engaged with the second annular slot, the second annular boss can achieve rotational engagement with the second annular slot.

[0018] When using this utility model, the first bend, the straight section, and the second bend are respectively fitted into the first, second, and third grooves at the upper end of the three support seats. At this time, the positioning and limiting of the first bend, the straight section, and the second bend can be achieved. Then, the workers weld and fix one end of the straight section to one end of the first bend and circumferentially seal it, and weld and fix the other end of the straight section to one end of the second bend and circumferentially seal it. Through the above process, after the welding is completed, the relative angle of the first bend and the second bend can be maintained at the required angle.

[0019] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A welding fixture for aviation pipelines, characterized in that: It includes a support beam (1) and three support seats (2); the three support seats (2) are fixed on the support beam (1) at intervals along the extension direction of the aviation pipeline (3). The three support seats (2) are used to support the first bend section (31), the straight section (32) and the second bend section (33) of the aviation pipeline (3). The upper ends of the three support seats (2) are respectively provided with a first groove (21), a second groove (22) and a third groove (23). The first groove (21), the second groove (22) and the third groove (23) are used to partially fit with the first bend section (31), the straight section (32) and the second bend section (33).

2. The aviation pipeline welding fixture according to claim 1, characterized in that: A first radial limiting structure is provided between the first bend section (31) and the straight section (32), and a second radial limiting structure is provided between the second bend section (33) and the straight section (32).

3. The aviation pipeline welding fixture according to claim 2, characterized in that: The first radial limiting structure includes a first annular slot (321) disposed on the inner wall of the straight pipe section (32) facing the first bend pipe section (31), and a first annular boss (311) disposed at the end of the first bend pipe section (31) facing the straight pipe section (32). The first annular boss (311) and the first annular slot (321) are engaged and radially limited.

4. The aviation pipeline welding fixture according to claim 2, characterized in that: The second radial limiting structure includes a second annular slot (322) disposed on the inner wall of the straight pipe section (32) facing the second bend pipe section (33), and a second annular boss (331) disposed at the end of the second bend pipe section (33) facing the straight pipe section (32). The second annular boss (331) and the second annular slot (322) are engaged and radially limited.

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