A welding fixture for an aeroengine lobed mixer

Abstract

The application provides a welding fixture for an aero-engine lobe mixer, and belongs to the technical field of aero-engine machining and manufacturing, and specifically comprises a base, a radial driving mechanism, a plurality of uniformly distributed and radially movable sliding blocks, and a tensioning block mounted on the sliding blocks. The radial driving mechanism is used for driving the plurality of sliding blocks to move synchronously in the radial direction. The outer peripheral surface of a single tensioning block comprises a wave crest surface, two wave trough surfaces, and two butt joint surfaces. One wave crest surface of the single tensioning block is located between the two wave trough surfaces. The butt joint surfaces are respectively used for forming a split lobe surface with the butt joint surfaces of another tensioning block. The single tensioning block comprises a main body structure part and a split structure part which is detachably mounted on the main body part. The split structure part is arranged at positions corresponding to the wave crest surface and the butt joint surface. Through the processing scheme, the efficiency of clamping and unloading during the welding process of the lobe mixer is improved.

Description

Technical Field

[0001] This application relates to the field of aero-engine machining and manufacturing, and in particular to a welding fixture for an aero-engine lobe mixer. Background Technology

[0002] A lobe mixer is a waveform component with abrupt changes in cross-section. It is also a key component in the exhaust system of an aero-engine that promotes efficient mixing of internal and external bypass airflow. By enhancing mixing through the flow vortex generated by a special lobe structure, it can significantly improve engine thrust and combustion efficiency.

[0003] Its main form adopts a lobe structure, with the number of lobes generally between 12 and 20, and the tilt angle usually ≤15°. By adjusting the number and tilt angle, and optimizing the inner and outer opening angles and the lobe width ratio, it is beneficial to improve the thermal mixing efficiency by about 10%-15%. However, its structure is relatively complex and requires extremely high manufacturing precision. The key to manufacturing lobe mixers lies in the forming and welding processes, among which segmented welding is a commonly used welding method, which often directly affects the dimensional accuracy and structural quality of the parts, and also indirectly affects the performance and efficiency of the parts.

[0004] For the segmented welding of lobe mixers, selecting a suitable and efficient welding fixture is crucial. Since lobe mixers are typically thin-walled rotating parts of varying sizes, to minimize deformation during welding, welding fixtures generally employ a segmented, individually tensioned method. However, maintaining consistency in the tensioning position and force of each segment places extremely high demands on fixture alignment and assembly, making it very difficult. Furthermore, the dispersed structure results in low processing efficiency. Summary of the Invention

[0005] In view of this, this application provides a welding fixture for aero-engine lobe mixers, which solves the problems in the prior art and improves the efficiency of clamping and unloading during the welding process of lobe mixers.

[0006] This application provides a welding fixture for aero-engine lobe mixers, which adopts the following technical solution: A welding fixture for aero-engine lobe mixer includes a base, a radial drive mechanism, multiple sliders evenly distributed circumferentially and movable radially, and tensioning blocks mounted on the sliders. The radial drive mechanism is mounted on the base, and the radial drive mechanism is provided with multiple output ends that correspond one-to-one with the sliders. The sliders are mounted on the output ends, and the radial drive structure is used to drive the multiple sliders to move synchronously in the radial direction. Each slider is equipped with a tensioning block. The outer periphery of the multiple tensioning blocks forms an annular surface that fits against the inner wall of the aero-engine lobe mixer. The annular surface includes a crest surface corresponding to the wave division position of a single lobe of the aero-engine lobe mixer, a trough surface corresponding to the connection position between two adjacent lobes of the aero-engine lobe mixer, and a lobe-shaped surface of the docking area of ​​two adjacent tensioning blocks. The lobe-shaped surface is used to fit against the inner wall of the crest position of a single lobe. The outer peripheral surface of a single tensioning block includes a crest surface, two trough surfaces and two mating surfaces, and one crest surface of the single tensioning block is located between two trough surfaces. The mating surfaces are used to form a split surface with the mating surfaces of another tensioning block. Each tensioning block includes a main structural part and a detachable split structural part mounted on the main structural part. The split structural part is positioned corresponding to the crest surface and the mating surface. The maximum radial distance between the axis of the mating surface and the axis of the annular surface of the main structural part and the split structural part is a, and the maximum radial distance between the axis of the crest surface and the axis of the annular surface is b. a = b × c, and c ranges from 70% to 90%.

[0007] Optionally, the outer periphery profile corresponding to the radial position of a single lobe crest includes a first profile, a second profile, and a third profile distributed sequentially from the first end to the second end along the axial direction of the aero-engine lobe mixer. The radial distance between the first profile and the axis of the annular surface gradually decreases from the first end to the second end, the radial distance between the second profile and the axis of the annular surface gradually increases from the first end to the second end, and the radial distance between the third profile and the axis of the annular surface gradually decreases from the first end to the second end. The radial distance between the junction of the second and third profiles and the axis of the annular surface is the largest, and the radial distance between the junction of the first and second profiles and the axis of the annular surface is the smallest. The annular face is positioned with the end face of the first end of the aero-engine lobe mixer facing the base. The split structure is located within the range of the second and third profiles, and the end face of the split structure facing away from the base corresponds to the end face of the tensioning block facing away from the base.

[0008] Optionally, the mating surface of the main structure and the split structure includes a first plane parallel to the axis of the annular surface and a second plane perpendicular to the axis of the annular surface. The second plane corresponds to the side of the second profile closer to the first profile, and the side of the first plane away from the second plane extends to the end face of the tensioning block opposite to the base.

[0009] Optionally, the main structure part is provided with a dovetail groove on the surface corresponding to the first plane, and the length direction of the dovetail groove is arranged along the axial direction of the annular surface. The split structure part is provided with a dovetail block that mates with the dovetail groove on the surface corresponding to the first plane. The tensioning block is provided with a pressing block installed on the main structure part on the end face of the back of the base. The pressing block is used to press against the end face of the split structure part that is back of the second plane.

[0010] Optionally, the radial drive mechanism is a multi-jaw chuck, with each jaw of the multi-jaw chuck serving as an output end of the radial drive mechanism.

[0011] Optionally, the tensioning block has a strip-shaped groove at the trough position, with both ends of the strip-shaped groove penetrating both ends of the tensioning block. The bottom of the strip-shaped groove has an air inlet hole penetrating the radial thickness of the tensioning block. A copper strip is provided on the strip-shaped groove, and multiple air outlet holes are provided on the copper strip. When the aero-engine bevel mixer and the tensioning block are in contact, the copper strip and the aero-engine bevel mixer are spaced apart. The air inlet hole is used to connect to an inert gas source.

[0012] Optionally, it also includes multiple outer pressure plates, each of which corresponds one-to-one with each lobe of the aero-engine lobe mixer. The outer pressure plates are used to adhere to and press against the outer peripheral side of each lobe at the crest position.

[0013] Optionally, each outer pressure plate has a support plate mounted on the base on the side facing away from the tensioning block. An adjusting bolt is threaded onto the support plate, and the rod of the adjusting bolt is rotatably connected to the outer pressure plate. A guide rod is provided on the side of the outer pressure plate facing the support plate, and a guide hole is provided on the support plate for the guide rod to pass through.

[0014] In summary, this application includes the following beneficial technical effects: Compared with traditional segmented tensioning mechanisms, this application uses a radial drive mechanism to drive the tensioning structure to move synchronously. The structure is compact, which reduces the difficulty of using and assembling the fixture, making it simple and convenient, reducing the consumption of equipment and other resources, significantly reducing costs, alleviating the processing burden of front-line personnel, and improving processing efficiency.

[0015] For small-diameter, large-capacity retraction tensioning mixers, the welding fixture of this application has significant advantages in terms of processability, convenience, and economy, especially the welding fixture with a split-design tensioning block for synchronous tensioning.

[0016] This fixture is assembled, which can improve the reusability of the fixture.

[0017] Through practical application, the welding fixture of this application has reduced production and processing costs by approximately 42%, reduced equipment resource waste by over 85%, significantly shortened clamping time by nearly 87%, and improved processing efficiency by over 96%. The welding fixture of this application provides an efficient, precise, and reliable solution for welding aero-engine lobe mixers, possessing significant engineering application value and broad market prospects. Attached Figure Description

[0018] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0019] Figure 1 This is a schematic diagram of the structure of the lobe mixer in the embodiments of this application; Figure 2 This is a schematic diagram of the overall structure of the welding fixture used in the aero-engine lobe mixer of this application; Figure 3 This is a top view of a single tensioning block in an embodiment of this application; Figure 4 This is a schematic diagram of the disassembled structure of a single tensioning block in an embodiment of this application; Figure 5 This is a cross-sectional schematic diagram of a single tensioning block in an embodiment of this application; Figure 6 This is a schematic diagram of the structure of the multi-jaw chuck in the embodiments of this application.

[0020] Explanation of reference numerals in the attached drawings: 1. Base; 2. Radial drive mechanism; 21. Mounting seat; 22. Claw; 23. Cylindrical bevel gear; 3. Slider; 4. Tensioning block; 41. Wave crest surface; 411. First profile; 412. Second profile; 413. Third profile; 414. Arc-shaped boss; 42. Wave trough surface; 43. Butt joint surface; 44. Split surface; 5. Main structure part; 51. Split structure part; 52. First plane; 53. Second plane; 54. Dovetail groove; 55. Dovetail block; 551. Threaded hole; 56. Pressing block; 6. Strip groove; 61. Copper strip; 62. Air inlet; 63. Air inlet nozzle; 7. Outer pressure plate; 71. Support plate; 72. Adjusting bolt; 73. Guide rod; 8. Split mixer. Detailed Implementation

[0021] The embodiments of this application will now be described in detail with reference to the accompanying drawings.

[0022] The following specific examples illustrate the implementation of this application. Those skilled in the art can easily understand other advantages and effects of this application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. This application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of this application. It should be noted that, in the absence of conflict, the following embodiments and features in the embodiments can be combined with each other. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0023] It should be noted that various aspects of embodiments within the scope of the appended claims are described below. It will be apparent that the aspects described herein can be embodied in a wide variety of forms, and any particular structure and / or function described herein is merely illustrative. Based on this application, those skilled in the art will understand that one aspect described herein can be implemented independently of any other aspect, and two or more of these aspects can be combined in various ways. For example, any number of aspects set forth herein can be used to implement the device and / or practice the method. Additionally, this device and / or method can be implemented using structures and / or functionalities other than one or more of the aspects set forth herein.

[0024] It should also be noted that the illustrations provided in the following embodiments are only schematic representations of the basic concept of this application. The illustrations only show the components related to this application and are not drawn according to the number, shape and size of the components in actual implementation. In actual implementation, the form, quantity and proportion of each component can be arbitrarily changed, and the layout of the components may also be more complex.

[0025] Furthermore, specific details are provided in the following description to facilitate a thorough understanding of the examples. However, those skilled in the art will understand that the described aspects can be practiced without these specific details.

[0026] This application provides a welding fixture for aero-engine lobe mixers.

[0027] like Figures 1 to 5 As shown, a welding fixture for aero-engine lobe mixer includes a base 1, a radial drive mechanism 2, multiple sliders 3 evenly distributed circumferentially and moving radially, and tensioning blocks 4 mounted on the sliders 3.

[0028] The radial drive mechanism 2 is mounted on the base 1. The radial drive mechanism 2 has multiple output ends that correspond one-to-one with the sliders 2. The sliders 3 are mounted on the output ends. The radial drive mechanism is used to drive the multiple sliders 3 to move synchronously in the radial direction. Each slider 3 is equipped with a tension block 4. The outer periphery of the multiple tension blocks 4 forms an annular surface that fits against the inner wall of the aero-engine lobe mixer 8. The annular surface includes a crest surface 41 corresponding to the wave division position of a single lobe of the aero-engine lobe mixer 8, a trough surface 42 corresponding to the contact position between two adjacent lobes of the aero-engine lobe mixer 8, and a segmented surface 44 for the docking area of ​​two adjacent tension blocks 4. The segmented surface 44 is used to fit against the inner wall of the crest position of a single lobe. The outer peripheral surface of a single tensioning block 4 includes a crest surface 41, two trough surfaces 42, and two mating surfaces 43. One crest surface 41 of the single tensioning block 4 is located between two trough surfaces 42. The mating surfaces 43 are used to form a segmented surface 44 with the mating surfaces 43 of another tensioning block 4. A single tensioning block 4 includes a main structure portion 5 and a detachable split structure portion 51 mounted on the main structure portion. The split structure portion 51 is positioned corresponding to the crest surface 41 and the mating surfaces 43. The maximum radial distance between the mating surfaces of the main structure portion 5 and the split structure portion 51 and the axis of the annular surface is 'a'. The maximum radial distance between the crest surface 41 and the axis of the annular surface is 'b'. 'a' = 'b' × 'c', where 'c' ranges from 70% to 90%. In this embodiment, the slider 3 and the main structure portion 5 are integrally formed.

[0029] In this application, multiple tensioning blocks 4 form an annular surface corresponding to the inner wall surface of the aero-engine lobe mixer 8. When the radial drive mechanism 2 drives the multiple tensioning blocks 4 to move away from each other to the welding position simultaneously through the slider 3, the lobe is attached to the tensioning blocks 4. Adjacent lobes are welded on the tensioning blocks 4. Under the constraint of the annular surface formed by the multiple tensioning blocks 4, the shape of the multiple lobes after welding conforms to the design shape of the lobe mixer 8. In this application, the radial drive mechanism 2 drives the multiple tensioning blocks 4 to move synchronously through the slider 3 to achieve synchronous tensioning, shorten the clamping time of parts, reduce the easy deformation of sheet metal thin-walled parts, and reduce the impact of operation and assembly errors. Furthermore, considering the axial contraction and expansion shape of the beam mixer 8, this application designs a detachable split part at the crest position of the tension block 4. After the split part is disassembled, the size of the fixture can be quickly reduced. Then, the radial drive mechanism 2 drives multiple tension blocks 4 to retract within a small range, so that the maximum outer diameter of multiple tension blocks 4 is smaller than the minimum inner diameter of the beam mixer 8, which facilitates the complete separation of the fixture and the parts. At the same time, it can effectively reduce the stroke requirements of the radial drive mechanism 2.

[0030] like Figure 5 As shown, for the beam mixer 8, the outer circumferential profile corresponding to the radial position of a single beam crest includes a first profile 411, a second profile 412, and a third profile 413 sequentially distributed from the first end to the second end along the axial direction of the aero-engine beam mixer 8. The radial distance between the first profile 411 and the axis of the annular surface gradually decreases from the first end to the second end; the radial distance between the second profile 412 and the axis of the annular surface gradually increases from the first end to the second end; and the radial distance between the third profile 413 and the axis of the annular surface gradually decreases from the first end to the second end. The radial distance between the junction of the second profile 412 and the third profile 413 and the axis of the annular surface is the largest, and the radial distance between the junction of the first profile 411 and the second profile 412 and the axis of the annular surface is the smallest. The annular facet of the aero-engine bevel mixer 8 is positioned with its first end face facing the base 1. The split structure portion 51 is located within the range of the second profile 412 and the third profile 413, and the end face of the split structure portion 51 facing away from the base 1 corresponds to the end face of the tensioning block 4 facing away from the base. During welding, the large-diameter end of the aero-engine bevel mixer 8 is positioned away from the base 1. When removing the part after welding, the split structure portion 51 of the tensioning block 4, which is away from the base 1 and corresponds to the large-diameter protrusion, is disassembled, and the part can be easily removed from the side away from the base 1, thus allowing for quick removal of the part.

[0031] In one specific embodiment, the mating surface of the main structure portion 5 and the split structure portion 51 includes a first plane 52 parallel to the axis of the annular surface and a second plane 53 perpendicular to the axis of the annular surface. The second plane 53 corresponds to the side of the second profile 412 closer to the first profile 411, and the side of the first plane 52 away from the second plane 53 extends to the end face of the tensioning block 4 opposite to the base 1. In other embodiments, the second plane 53 may also be aligned with the intersection point of the first profile 411 and the second profile 412.

[0032] The main structural part 5 has a dovetail groove 54 on the surface corresponding to the first plane 52. The length direction of the dovetail groove 54 is arranged along the axial direction of the annular surface. The split structural part 51 has a dovetail block 55 on the surface corresponding to the first plane 52 that mates with the dovetail groove 54. The tensioning block 4 has a clamping block 56 mounted on the main structural part 5 on its end face opposite to the base 1. The clamping block 56 is used to press against the end face of the split structural part 51 opposite to the second plane 53. In this embodiment, the clamping block 56 is mounted on the main structural part 5 with bolts. Alternatively, a threaded hole 551 can be provided on the end face of the dovetail block 55 opposite to the base 1, allowing the split structural part 51 to be quickly removed by screwing in a screw.

[0033] Combination Figure 5 The split design of the tensioning block implemented in this application is described in detail as follows: The tensioning block 4 also has an arc-shaped boss 414 at its first end. The outer diameter of the arc-shaped boss 414 is greater than the radial distance from the first profile 411 to the axis of the annular surface. It is used to support the end face of the part. The outer circumferential profile of the radial position corresponding to the crest of a single lobe, from the arc-shaped boss 414 to the second end line, are the first profile 411, the second profile 412, and the third profile 413 in sequence. The maximum radial distance between the mating surface of the main structure part 5 and the split structure part 51 and the axis of the annular surface is a. The maximum radial distance between the crest profile 41 and the axis of the annular surface is a. The maximum value is b, a = b × c, and c ranges from 70% to 90%. In this embodiment, the radial distance between the outer edge of the second plane 53 and the axis of the annular surface is a, and the radial distance between the intersection of the second profile 412 and the third profile 413 and the axis of the annular surface is b. In this application, the protruding part of the tension block 4 is removed, and the outer diameter of the clamp located inside the part is quickly reduced, i.e., a is less than b, thereby greatly reducing the amount of displacement that the tension block 4 needs to retract when disassembling the part. Similarly, when welding parts in large batches, the amount of displacement of the tension block 4 each time can also be reduced. In this application, during the process of multiple tensioning blocks 4 expanding from their retracted limit position to match the inner wall design dimensions of the part, the radial displacement of a single tensioning block 4 is d. Due to the split design of the tensioning blocks 4 in this application, and the design of the second plane 53 close to the first profile 411, when the part needs to be removed after welding, the tensioning blocks 4 are controlled to move inward by e. After removing the split structure part 51, the maximum outer diameter of the annular structure formed by the multiple tensioning blocks 5 is smaller than the minimum inner diameter of the part, so the part can be removed. In the embodiment of this application, e=d×f, and the value of f is 40-60%. This application can remove the part without retracting the tensioning blocks 5 to the limit position, thus improving the efficiency of disassembling the part.

[0034] like Figure 6 As shown, the radial drive mechanism 2 is a multi-jaw chuck, with each jaw 22 of the multi-jaw chuck serving as an output end of the radial drive mechanism 2. This application achieves synchronous displacement of multiple sliders 3 through a multi-jaw chuck.

[0035] A multi-jaw chuck typically includes a mounting base 21, a rotating ring bevel gear mounted on the mounting base 21, a rotating cylindrical bevel gear 23 mounted on the mounting base 21, and sliding jaws 22 mounted on the mounting base. The length direction of both the cylindrical bevel gear 23 and the jaws 22 is along the radial direction of the ring bevel gear, and the sliding direction of the jaws 22 is also along the radial direction of the ring bevel gear. The cylindrical bevel gear 23 meshes with the ring bevel gear. A flat thread is provided on the end face of the ring bevel gear facing away from the cylindrical bevel gear 23. One side of the jaws 22 is threaded into the flat thread of the bevel gear. Rotating the cylindrical bevel gear 23 drives the ring bevel gear to rotate, which in turn drives the jaws 22 to slide radially. The mounting base 21 has a through hole corresponding to the cylindrical bevel gear 23, and the outward-facing end face of the cylindrical bevel gear 23 has an internal hexagonal hole that mates with a hexagonal wrench. The principle of a multi-jaw chuck is the same as that of a three-jaw chuck. Both three-jaw and multi-jaw chucks are existing technologies. In this application, only the key structure of the multi-jaw chuck is described in the embodiments. The specific design of the multi-jaw chuck is not the innovation of this application. The innovation of this application lies in the principle of the multi-jaw chuck. Therefore, more details about the multi-jaw chuck will not be elaborated here.

[0036] The tensioning block 4 has a strip-shaped groove 6 at the trough surface 42 position. The two ends of the strip-shaped groove 6 penetrate the two ends of the tensioning block 4. The bottom of the strip-shaped groove 6 has an air inlet 62 that penetrates the radial thickness of the tensioning block 4. The strip-shaped groove 6 has a copper strip 61 with multiple air outlets. When the aero-engine bevel mixer 8 and the tensioning block 4 are in contact, the copper strip 61 and the aero-engine bevel mixer 8 are spaced apart. An air inlet 63 is installed on the air inlet 62 and is used to connect to an inert gas source. In this application, the strip groove 6 is T-shaped. The wide part of the T-shaped strip groove 6 matches the copper strip 61, and the narrow side of the T-shaped strip groove 6 forms an air inlet chamber. The position of the trough surface 42 of the tensioning block 4 corresponds to the welding position of the beam mixer 8. After an inert gas such as argon is introduced into the strip groove 6 through the air inlet 63, the argon in the air inlet chamber passes through the air outlet on the copper strip 61 and forms an argon environment between the copper strip 61 and the beam mixer 8. This can prevent the weld formed at the same position from being oxidized, so as to achieve the effect of argon protection and ensure the welding quality.

[0037] It also includes multiple outer pressure plates 7, each corresponding to a lobe of the aero-engine lobe mixer 8. The outer pressure plates 7 are used to adhere to and press against the outer peripheral side of each lobe's crest position. By having multiple tensioning blocks 4 and multiple outer pressure plates 7 jointly abut against the inner and outer rings of the lobe mixer 8, the positioning and shaping effect of the parts is improved, and the welding quality is enhanced.

[0038] Each outer pressure plate 7 has a support plate 71 mounted on the base 1 on the side opposite to the tensioning block 4. An adjusting bolt 72 is threaded onto the support plate 71, and the rod of the adjusting bolt 72 is rotatably connected to the outer pressure plate 7. A guide rod 73 is provided on the side of the outer pressure plate 7 facing the support plate 71, and a guide hole is provided on the support plate 71 for the guide rod 73 to pass through. By rotating the adjusting bolt 72, the outer pressure plate 7 can be moved closer to or away from the tensioning block 4, thus controlling whether the outer pressure plate 7 is in contact with or away from the part. In this embodiment, each support plate 71 has two adjusting bolts 72, and each outer pressure plate 7 has two guide rods 73.

[0039] 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 aero-engine lobe mixer, characterized in that, Includes a base (1), a radial drive mechanism (2), multiple sliders (3) evenly distributed circumferentially and moving radially, and tensioning blocks (4) mounted on the sliders (3): The radial drive mechanism (2) is mounted on the base (1). The radial drive mechanism (2) has multiple output ends that correspond one-to-one with the sliders (3). The sliders (3) are mounted on the output ends. The radial drive structure is used to drive multiple sliders (3) to move synchronously in the radial direction. Each slider (3) is equipped with a tension block (4). The outer periphery of the multiple tension blocks (4) forms an annular surface that fits against the inner wall of the aero-engine lobe mixer (8). The annular surface includes a crest surface (41) corresponding to the wave division position of a single lobe of the aero-engine lobe mixer (8), a trough surface (42) corresponding to the connection position between two adjacent lobes of the aero-engine lobe mixer (8), and a split surface (44) of the docking area of ​​two adjacent tension blocks (4). The split surface (44) is used to fit against the inner wall of the crest position of a single lobe. The outer peripheral surface of a single tensioning block (4) includes a crest surface (41), two trough surfaces (42) and two mating surfaces (43), and a crest surface (41) of a single tensioning block (4) is located between two trough surfaces (42), and the mating surfaces (43) are used to form a split surface (44) with the mating surfaces (43) of another tensioning block (4); Each tensioning block (4) includes a main structure part (5) and a detachable split structure part (51) mounted on the main structure part. The split structure part (51) is positioned corresponding to the crest surface (41) and the mating surface (43). The maximum radial distance between the mating surface of the main structure part (5) and the axis of the annular surface is a, and the maximum radial distance between the crest surface (41) and the axis of the annular surface is b. a = b × c, and c ranges from 70% to 90%.

2. The welding fixture for aero-engine lobe mixer according to claim 1, characterized in that, The outer periphery profile corresponding to the radial position of the peak of a single lobe includes a first profile (411), a second profile (412), and a third profile (413) distributed sequentially from the first end to the second end along the axial direction of the aero-engine lobe mixer (8). The radial distance between the first profile (411) and the axis of the annular surface gradually decreases from the first end to the second end. The radial distance between the second profile (412) and the axis of the annular surface gradually increases from the first end to the second end. The radial distance between the third profile (413) and the axis of the annular surface gradually decreases from the first end to the second end. The radial distance between the junction of the second profile (412) and the third profile (413) and the axis of the annular surface is the largest. The radial distance between the junction of the first profile (411) and the second profile (412) and the axis of the annular surface is the smallest. The annular face is positioned with the end face of the first end of the aero-engine lobe mixer (8) facing the base (1). The split structure part (51) is located within the range of the second profile (412) and the third profile (413). The end face of the split structure part (51) facing away from the base (1) corresponds to the end face of the tensioning block (4) facing away from the base.

3. The welding fixture for aero-engine lobe mixer according to claim 2, characterized in that, The mating surfaces of the main structure part (5) and the split structure part (51) include a first plane (52) parallel to the axis of the annular surface and a second plane (53) perpendicular to the axis of the annular surface. The second plane (53) corresponds to the side of the second profile (412) close to the first profile (411). The side of the first plane (52) away from the second plane (53) extends to the end face of the tensioning block (4) facing away from the base (1).

4. The welding fixture for aero-engine lobe mixer according to claim 3, characterized in that, The main structure part (5) has a dovetail groove (54) on the surface corresponding to the first plane (52). The length direction of the dovetail groove (54) is arranged along the axial direction of the annular surface. The split structure part (51) has a dovetail block (55) that mates with the dovetail groove (54) on the surface corresponding to the first plane (52). The tensioning block (4) has a pressing block (56) installed on the main structure part (5) on the end face opposite to the base (1). The pressing block (56) is used to press against the end face of the split structure part (51) opposite to the second plane (53).

5. The welding fixture for an aero-engine lobe mixer according to claim 1, characterized in that, The radial drive mechanism (2) is a multi-jaw chuck, and each jaw (22) of the multi-jaw chuck serves as an output end of the radial drive mechanism (2).

6. The welding fixture for an aero-engine lobe mixer according to claim 1, characterized in that, The tensioning block (4) has a strip groove (6) on its trough surface (42). The two ends of the strip groove (6) penetrate the two ends of the tensioning block (4). The bottom of the strip groove (6) has an air inlet (62) that penetrates the radial thickness of the tensioning block (4). The strip groove (6) has a copper strip (61) with multiple air outlets. When the aero-engine bevel mixer (8) and the tensioning block (4) are in contact, the copper strip (61) and the aero-engine bevel mixer (8) are spaced apart. The air inlet (62) is used to connect to an inert gas source.

7. The welding fixture for an aero-engine lobe mixer according to claim 1, characterized in that, It also includes multiple outer pressure plates (7), each of which corresponds to one of the lobes of the aero-engine lobe mixer (8). The outer pressure plates (7) are used to attach and press against the outer peripheral side of each lobe at the crest position.

8. The welding fixture for an aero-engine lobe mixer according to claim 7, characterized in that, Each outer pressure plate (7) has a support plate (71) mounted on the base (1) on the side opposite to the tensioning block (4). An adjusting bolt (72) is threaded onto the support plate (71). The rod of the adjusting bolt (72) is rotatably connected to the outer pressure plate (7). A guide rod (73) is provided on the side of the outer pressure plate (7) facing the support plate (71). A guide hole is provided on the support plate (71) for the guide rod (73) to pass through.

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