An aircraft engine combustion chamber flame tube welding device

Abstract

The present invention relates to the technical field of welding devices, and particularly relates to a welding device for an aeroengine combustion chamber flame tube; it includes a bottom plate, a central shaft, an outer ring fixing mechanism, a swirler mounting seat, a cover plate, a fixing nut, and a plurality of tie rod assemblies. Place the inner ring assembly on the end face of the swirler mounting seat, cover the cover plate on the upper surface of the plurality of support bushings, tighten the fixing nut on the threaded part of the central shaft, and fix the cover plate on the upper surface of the plurality of support bushings through tie rods to complete the assembly of the inner ring assembly. Then place the outer ring assembly on the upper surface of the bottom plate, turn the threaded rod so that the sliding seat slides in the chute, thereby using a plurality of brackets to tighten the outer ring assembly, and thus complete the assembly of the outer ring assembly. With the above structure, the concentricity of the inner ring assembly and the outer ring assembly can be improved, effectively ensuring the dimensional requirements from the end face of the swirler mounting seat to the center of the hole of the inner ring assembly, and making the welding accuracy of the flame tube higher.

Description

Technical Field

[0001] The present invention relates to the technical field of welding devices, and in particular to a welding device for an aero-engine combustion chamber flame tube. Background Art

[0002] The aero-engine combustion chamber flame tube bears high-temperature and high-pressure gas, as well as relatively high thermal stress and vibration stress, and the working environment is extremely harsh. With the improvement of aero-engine performance, the combustion chamber working condition temperature is continuously increasing, which puts forward higher requirements for aspects such as the flame tube cooling structure, matrix material, and surface protection. Therefore, the welding technology of the combustion chamber flame tube is the most important technical guarantee.

[0003] However, the design of the existing welding device for the aero-engine combustion chamber flame tube is not reasonable enough, and it is unable to ensure the size and accuracy of the flame tube after welding. It is necessary to repair and fit the nozzle assembly, which increases the workload of rework. Summary of the Invention

[0004] The purpose of the present invention is to provide a welding device for an aero-engine combustion chamber flame tube, so as to solve the problem that the design of the existing welding device for the aero-engine combustion chamber flame tube is not reasonable enough, and it is unable to ensure the size and accuracy of the flame tube after welding. It is necessary to repair and fit the nozzle assembly, which increases the workload of rework.

[0005] To achieve the above purpose, the present invention provides a welding device for an aero-engine combustion chamber flame tube. The welding device for the aero-engine combustion chamber flame tube includes a bottom plate, a central shaft, an outer ring fixing mechanism, a swirler mounting seat, a cover plate, a fixing nut, and a plurality of tie rod assemblies. The central shaft is fixedly connected to the center of the bottom plate. A plurality of chutes are evenly arranged around the bottom plate. The outer ring fixing mechanism is composed of a plurality of outer ring fixing components. Each outer ring fixing component includes a threaded rod, a sliding seat, and a bracket. Each sliding seat is respectively slidably connected to a chute. The threaded rod is threadedly connected to each sliding seat. The bracket is arranged on the upper surface of each sliding seat. The swirler mounting seat is placed on the upper surfaces of the plurality of brackets;

[0006] The cover plate is arranged on the upper surface of the swirler mounting seat. A plurality of support bushings are evenly arranged between the swirler mounting seat and the cover plate. A through hole is arranged at the center of the cover plate. One end of the central shaft away from the bottom plate penetrates through the through hole. A threaded portion is arranged at one end of the central shaft penetrating to the upper surface of the through hole. The fixing nut is adapted to the threaded portion. A plurality of the tie rod assemblies are also evenly arranged around the cover plate. Each tie rod assembly is respectively adapted to a support bushing.

[0007] Among them, the central axis includes an axis body and a clamping rod, the clamping rod is clamped on one end of the axis body close to the through hole, the threaded portion is provided on one end of the clamping rod away from the axis body, a clamping seat is provided on the outer side of the clamping rod, a clamping rod is provided on the clamping seat, a clamping hole is provided on the cover plate, and the clamping rod is adapted to the clamping hole.

[0008] Among them, each of the sliding seats includes a sliding plate, two wing plates and a limit plate, the sliding plate passes through the sliding groove, the wing plates are arranged on both sides of the upper surface of the sliding plate, and the limit plate is detachably connected to the sliding plate and is located at the bottom of the sliding plate.

[0009] Wherein, each of the brackets includes a connecting plate and an expansion block, one end of the connecting plate is fixedly connected to the sliding plate, the other end of the connecting plate is provided with the expansion block, the outer side of the expansion block is provided with a first mounting groove and a second mounting groove, the first mounting groove is used to place the vortex finder mounting seat, the second mounting groove is used to place the inner ring assembly of the flame tube, and the outer side wall of the mounting seat is in contact with the inner side wall of the flame tube.

[0010] Among them, a plurality of positioning frames are also arranged on the base plate, and the plurality of positioning frames are evenly distributed on the upper surface of the base plate. A positioning frame is arranged between every two outer ring fixing components, and a positioning pin is arranged on each positioning frame, and the positioning pin is adapted to the positioning hole of the outer ring component of the flame tube.

[0011] Each of the positioning frames comprises a mounting plate and a frame body, wherein the mounting plate is detachably connected to the base plate, the frame body is fixedly connected to the upper surface of the mounting plate, and the positioning pin is provided at one end of the frame body away from the mounting plate.

[0012] Among them, each of the tie rod assemblies includes a tie rod screw, a tie rod nut and a gasket. The tie rod screw passes through the vortex finder mounting seat, a limit block is provided at the bottom of the tie rod screw, the upper end of the tie rod screw is threadedly connected to the tie rod nut, and the gasket is provided between the tie rod nut and the upper surface of the cover plate.

[0013] An aero-engine combustion chamber flame tube welding device of the present invention includes a bottom plate, a central shaft, an outer ring fixing mechanism, a swirler mounting seat, a cover plate, a fixing nut, and a plurality of tie rod assemblies. Place the inner ring assembly of the flame tube on the end face of the swirler mounting seat. After the support bushing passes through the through hole on the inner ring assembly of the flame tube, cover the cover plate on the upper surfaces of the plurality of support bushings. Tighten the fixing nut on the threaded portion of the central shaft, and turn the tie rod so as to fix the cover plate on the upper surfaces of the plurality of support bushings, thereby completing the assembly of the inner ring assembly of the flame tube. Then, place the outer ring assembly of the flame tube on the upper surface of the bottom plate, and after sleeving it outside the plurality of outer ring fixing mechanisms, turn the threaded rod so that the sliding seat slides in the chute, thereby causing the bracket to move towards the inner wall direction of the outer ring assembly, thereby using the plurality of brackets to tighten the outer ring assembly, thereby completing the assembly of the outer ring assembly. With the above structure, the concentricity of the inner ring assembly and the outer ring assembly of the flame tube can be improved, effectively ensuring the dimensional requirements from the end face of the swirler mounting seat to the center of the hole of the inner ring assembly of the flame tube, and making the welding accuracy of the flame tube higher. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the following drawings are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0015] Figure 1 It is a schematic structural diagram of the aero-engine combustion chamber flame tube welding device provided by the present invention with a flame tube assembled thereon.

[0016] Figure 2 It is a schematic structural diagram of the aero-engine combustion chamber flame tube welding device provided by the present invention.

[0017] Figure 3 It is provided by the present invention Figure 2 A partial enlarged structural view of part A.

[0018] Figure 4 It is a schematic structural diagram of the outer ring fixing assembly provided by the present invention.

[0019] Figure 5 It is a schematic structural diagram of the central shaft provided by the present invention.

[0020] Figure 6 It is a schematic structural diagram of the tie rod assembly provided by the present invention.

[0021] 101 - Bottom plate, 102 - Central axis, 103 - Swirler mounting seat, 104 - Cover plate, 105 - Fixed nut, 106 - Tie rod assembly, 107 - Slide groove, 108 - Outer ring fixing assembly, 109 - Threaded rod, 110 - Slide seat, 111 - Bracket, 112 - Support bushing, 113 - Through hole, 114 - Threaded part, 115 - Shaft body, 116 - Clamping rod, 117 - Clamping seat, 118 - Card rod, 119 - Card hole, 120 - Slide plate, 121 - Wing plate, 122 - Limiting plate, 123 - Connecting plate, 124 - Expansion block, 125 - First mounting groove, 126 - Second mounting groove, 127 - Positioning frame, 128 - Positioning pin, 129 - Mounting plate, 130 - Frame body, 131 - Tie rod screw, 132 - Tie rod nut, 133 - Gasket, 134 - Limiting block, 135 - Connecting block. Detailed implementation manners

[0022] The embodiments of the present invention will be described in detail below. Examples of the embodiments are shown in the drawings, where the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below by referring to the drawings are exemplary and are intended to explain the present invention and should not be construed as a limitation of the present invention.

[0023] Please refer to Figures 1 to 6 The present invention provides a welding device for an aero - engine combustion chamber flame tube. The welding device for the aero - engine combustion chamber flame tube includes a bottom plate 101, a central axis 102, an outer ring fixing mechanism, a swirler mounting seat 103, a cover plate 104, a fixed nut 105, and a plurality of tie rod assemblies 106. The central axis 102 is fixedly connected to the center of the bottom plate 101. A plurality of slide grooves 107 are evenly arranged around the bottom plate 101. The outer ring fixing mechanism is composed of a plurality of outer ring fixing assemblies 108. Each outer ring fixing assembly 108 includes a threaded rod 109, a slide seat 110, and a bracket 111. Each slide seat 110 is slidably connected to one of the slide grooves 107. The threaded rod 109 is threadedly connected to each slide seat 110. The bracket 111 is arranged on the upper surface of each slide seat 110. The swirler mounting seat 103 is placed on the upper surfaces of the plurality of brackets 111;

[0024] The upper surface of the swirler mounting seat 103 is provided with the cover plate 104. A plurality of support bushings 112 are evenly arranged between the swirler mounting seat 103 and the cover plate 104. A through hole 113 is provided at the center of the cover plate 104. One end of the central shaft 102 far from the bottom plate 101 penetrates through the through hole 113. A threaded portion 114 is provided at one end of the central shaft 102 penetrating to the upper surface of the through hole 113. The fixing nut 105 is adapted to the threaded portion 114. A plurality of the tie rod assemblies 106 are also evenly arranged around the cover plate 104. Each of the tie rod assemblies 106 is respectively adapted to one of the support bushings 112.

[0025] In this embodiment, the inner ring assembly of the flame tube is placed on the end face of the swirler mounting seat 103. After the support bushings 112 penetrate through the through holes 113 on the inner ring assembly of the flame tube, the cover plate 104 is covered on the upper surfaces of the plurality of support bushings 112. The fixing nut 105 is tightened on the threaded portion 114 of the central shaft 102, and the tie rod is turned, so as to fix the cover plate 104 on the upper surfaces of the plurality of support bushings 112, thereby completing the assembly of the inner ring assembly of the flame tube. Then, the outer ring assembly of the flame tube is placed on the upper surface of the bottom plate 101 and sleeved outside the plurality of outer ring fixing mechanisms. Then, the threaded rod 109 is turned, so that the sliding seat 110 slides in the chute 107, thereby enabling the bracket 111 to move towards the inner wall direction of the outer ring assembly, thereby using the plurality of brackets 111 to tighten the outer ring assembly, thereby completing the assembly of the outer ring assembly. With the above structure, the concentricity of the inner ring assembly and the outer ring assembly of the flame tube can be improved, effectively ensuring the dimensional requirements from the end face of the swirler mounting seat 103 to the center of the hole of the inner ring assembly of the flame tube, and making the welding precision of the flame tube higher.

[0026] Further, the central shaft 102 includes a shaft body 115 and a clamping rod 116. The clamping rod 116 is clamped at one end of the shaft body 115 close to the through hole 113. The threaded portion 114 is provided at one end of the clamping rod 116 far from the shaft body 115. A clamping seat 117 is arranged on the outer side of the clamping rod 116. A clamping rod 118 is provided on the clamping seat 117. A clamping hole 119 is provided on the cover plate 104. The clamping rod 118 is adapted to the clamping hole 119.

[0027] In this embodiment, when installing the cover plate 104, the clamping hole 119 on the cover plate 104 is clamped onto the clamping rod 118 of the clamping seat 117, so that the installation of the cover plate 104 has higher precision and is convenient for subsequently turning the fixing nut 105.

[0028] Further, each of the sliding seats 110 includes a sliding plate 120, two wing plates 121 and a limiting plate 122. The sliding plate 120 penetrates through the sliding groove 107. The wing plates 121 are arranged on both sides of the upper surface of the sliding plate 120. The limiting plate 122 is detachably connected to the sliding plate 120 and is located at the bottom of the sliding plate 120.

[0029] In this embodiment, after the sliding plate 120 penetrates through the sliding groove 107, the limiting plate 122 is fixed to the sliding plate 120 by screws, thereby completing the installation of the sliding seat 110. The sliding seat 110 is limited by the limiting plate 122 and the two wing plates 121 on the sliding plate 120, so that the structure of the sliding seat 110 is more stable when it slides on the sliding groove 107.

[0030] Further, each of the brackets 111 includes a connecting plate 123 and a swelling block 124. One end of the connecting plate 123 is fixedly connected to the sliding plate 120. The other end of the connecting plate 123 is provided with the swelling block 124. The outer side of the swelling block 124 is provided with a first installation groove 125 and a second installation groove 126. The first installation groove 125 is used for placing the swirler mounting seat 103. The second installation groove 126 is used for placing the inner ring assembly of the combustion chamber liner. The outer side wall of the mounting seat is fitted with the inner side wall of the combustion chamber liner.

[0031] In this embodiment, the connecting plate 123 is fixedly connected to the sliding plate 120, and the swelling block 124 is fixedly connected to the bottom plate 101. When manufacturing the sliding plate 120, the connecting plate 123 and the swelling block 124, an integral forming technology can be adopted, and the structure is more firm. And because the first installation groove 125 is used for placing the swirler mounting seat 103, the second installation groove 126 is used for placing the inner ring assembly of the combustion chamber liner, and the outer side wall of the mounting seat is fitted with the inner side wall of the combustion chamber liner, when the welding device for the inner ring and outer ring components of the combustion chamber liner of the aero-engine is used for fixing the inner ring component and the outer ring component of the combustion chamber liner, the inner ring component and the outer ring component can remain concentric.

[0032] Further, a plurality of positioning frames 127 are further arranged on the bottom plate 101. The plurality of positioning frames 127 are evenly distributed on the upper surface of the bottom plate 101. One positioning frame 127 is arranged between every two outer ring fixing components 108. A positioning pin 128 is arranged on each positioning frame 127. The positioning pin 128 is adapted to the positioning hole of the outer ring component of the combustion chamber liner.

[0033] In this embodiment, a positioning frame 127 is arranged between every two of the outer ring fixing components 108. After the outer ring component is placed on the upper surface of the bottom plate 101, the positioning pin 128 is inserted into the positioning hole of the outer ring component, so as to complete the fixation of the position of the outer ring component, thereby preventing the outer ring component from rotating axially.

[0034] Furthermore, each positioning frame 127 includes a mounting plate 129 and a frame body 130. The mounting plate 129 is detachably connected to the bottom plate 101. The upper surface of the mounting plate 129 is fixedly connected with the frame body 130, and the positioning pin 128 is arranged at one end of the frame body 130 away from the mounting plate 129.

[0035] In this embodiment, the mounting plate 129 is fixed on the upper surface of the bottom plate 101 by using screws, so as to complete the installation of the positioning frame 127. The frame body 130 is fixedly connected with the mounting plate 129 and is manufactured by using an integral molding technology, and the structure is more firm.

[0036] Furthermore, each pull rod assembly 106 includes a pull rod screw 131, a pull rod nut 132 and a gasket 133. The pull rod screw 131 penetrates through the swirler mounting seat 103. A limit block 134 is arranged at the bottom of the pull rod screw 131. The upper end of the pull rod screw 131 is threadedly connected with the pull rod nut 132, and the gasket 133 is arranged between the pull rod nut 132 and the upper surface of the cover plate 104.

[0037] In this embodiment, by screwing the pull rod nut 132 and cooperating with the gasket 133, the cover plate 104 is moved towards the direction of the support bushing 112, so as to fix the inner ring component of the flame tube on the end face of the swirler mounting seat 103.

[0038] Furthermore, a connecting block 135 is arranged at one end of each threaded rod 109 away from the sliding seat 110, and the connecting block 135 is connected to the driving motor through a coupling.

[0039] In this embodiment, since the connecting block 135 is arranged at one end of each threaded rod 109 away from the sliding seat 110, and the connecting block 135 can be connected to the driving motor through a coupling, when the threaded rod 109 is rotated by the driving motor, it is more convenient to rotate the threaded rod 109.

[0040] The above-disclosed is only a preferred embodiment of the present invention. Of course, the scope of the rights of the present invention cannot be limited thereby. Those of ordinary skill in the art can understand all or part of the processes of implementing the above embodiments, and the equivalent changes made according to the claims of the present invention still fall within the scope covered by the present invention.

Claims

1. An aircraft engine combustion chamber flame tube welding device, characterized in that, it includes a bottom plate, a central shaft, an outer ring fixing mechanism, a swirler mounting seat, a cover plate, a fixing nut, and a plurality of tie rod assemblies. The central shaft is fixedly connected to the center of the bottom plate. A plurality of chutes are evenly arranged around the bottom plate. The outer ring fixing mechanism is composed of a plurality of outer ring fixing components. Each outer ring fixing component includes a threaded rod, a sliding seat, and a bracket. Each sliding seat is respectively slidably connected to a chute. The threaded rod is threadedly connected to each sliding seat. The bracket is arranged on the upper surface of each sliding seat. The swirler mounting seat is placed on the upper surfaces of a plurality of brackets; The cover plate is arranged on the upper surface of the swirler mounting seat. A plurality of support bushings are evenly arranged between the swirler mounting seat and the cover plate. A through hole is arranged at the center of the cover plate. One end of the central shaft away from the bottom plate penetrates through the through hole. A threaded portion is arranged at one end of the central shaft penetrating to the upper surface of the through hole. The fixing nut is adapted to the threaded portion. A plurality of the tie rod assemblies are also evenly arranged around the cover plate. Each tie rod assembly is respectively adapted to a support bushing; Each sliding seat includes a sliding plate, two wing plates, and a limiting plate. The sliding plate penetrates through the chute. The wing plates are arranged on both sides of the upper surface of the sliding plate. The limiting plate is detachably connected to the sliding plate and is located at the bottom of the sliding plate; Each bracket includes a connecting plate and a swelling block. One end of the connecting plate is fixedly connected to the sliding plate. The swelling block is arranged at the other end of the connecting plate. A first installation groove and a second installation groove are arranged on the outer side of the swelling block. The first installation groove is used for placing the swirler mounting seat. The second installation groove is used for placing the inner ring assembly of the flame tube. The outer side wall of the mounting seat is attached to the inner side wall of the flame tube; The central shaft includes a shaft body and a clamping rod. The clamping rod is clamped to one end of the shaft body close to the through hole. The threaded portion is arranged at one end of the clamping rod away from the shaft body. A clamping seat is arranged on the outer side of the clamping rod. A clamping rod is arranged on the clamping seat. A clamping hole is arranged on the cover plate. The clamping rod is adapted to the clamping hole.

2. The aircraft engine combustion chamber flame tube welding device according to claim 1, characterized in that, a plurality of positioning frames are further arranged on the bottom plate. The plurality of positioning frames are evenly distributed on the upper surface of the bottom plate. One positioning frame is arranged between every two outer ring fixing components. A positioning pin is arranged on each positioning frame. The positioning pin is adapted to the positioning hole of the outer ring assembly of the flame tube.

3. The aircraft engine combustion chamber flame tube welding device according to claim 2, characterized in that, each positioning frame includes a mounting plate and a frame body. The mounting plate is detachably connected to the bottom plate. The frame body is fixedly connected to the upper surface of the mounting plate. The positioning pin is arranged at one end of the frame body away from the mounting plate.

4. The aircraft engine combustion chamber flame tube welding device according to claim 1, characterized in that, Each of the tie rod assemblies comprises a tie rod screw, a tie rod nut and a gasket. The tie rod screw passes through the vortex finder mounting seat, a limit block is arranged at the bottom of the tie rod screw, the upper end of the tie rod screw is threadedly connected with the tie rod nut, and the gasket is arranged between the tie rod nut and the upper surface of the cover plate.

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