Aircraft part machining plasma welding device

Abstract

The application discloses an aviation part machining plasma welding device and relates to the technical field of plasma welding.The device comprises an operating handle, a flexible pipe body and a protective gas cap, and the operating handle and the flexible pipe body are in communication and electrically controlled with each other, a connecting ring is fixedly installed on the flexible pipe body, and a locking structure is arranged in the connecting ring.The device has the advantages that a convenient connecting and locking mode is designed, a special inclined surface matching structure is adopted, when a part is subjected to axial tension or high-frequency vibration, a self-locking effect that becomes tighter and tighter can be formed, meanwhile, a continuous pre-tightening force is provided by cooperating with elastic components, clearance looseness caused by vibration is avoided, and it is ensured that the part does not shake in the radial and axial directions during welding;after the protective gas enters during welding, the protective gas will experience multiple turns, forms severe turbulent flow, different flow rate gases are fully mixed in the turbulent flow, the airflow deviation problem that the center is fast and the edge is slow in the traditional structure is completely eliminated, and the air curtain pressure distribution is more balanced.

Description

Technical Field

[0001] This invention relates to the field of plasma welding technology, and in particular to a plasma welding apparatus for processing aerospace parts. Background Technology

[0002] In the aerospace manufacturing industry, aerospace components (such as engine blades, casings, and ducts) are core components of aircraft. Their materials are mostly high-strength and high-temperature resistant special materials such as titanium alloys and high-temperature alloys. Welding of these materials must meet stringent standards: the weld must be free of defects such as oxidation, porosity, and cracks, and it must also be adapted to the high-precision welding requirements of complex curved surfaces and thin-walled structures. Plasma welding, with its advantages of high energy density, strong arc stability, and small heat-affected zone, has become the core technology for welding aerospace components.

[0003] Existing protective gas caps mostly use straight grooves or single annular airflow channels. After the protective gas enters, the airflow distribution is prone to be fast in the center and slow at the edge due to the difference in flow velocity, resulting in dead corners in the air curtain coverage. When welding complex curved surface welds (such as the arc transition area of ​​blades), protective gas is prone to stagnation in the concave areas of the curved surface, while the protective gas coverage is insufficient in the convex areas. When welding deep groove welds (such as the flange groove of the casing), the bottom of the groove is prone to forming local unprotected areas due to insufficient airflow penetration. At the same time, existing nozzles mostly use threaded connections or multi-bolt fixing structures. The replacement process requires the gradual disassembly with tools such as wrenches, and the coaxiality of the nozzle and tungsten electrode needs to be recalibrated after disassembly. Frequent nozzle replacements result in a high proportion of equipment downtime, which seriously reduces production efficiency. Summary of the Invention

[0004] The purpose of this invention is to solve the problems in the background art, and to propose a plasma welding device for processing aerospace parts.

[0005] To achieve the above objectives, the present invention adopts the following technical solution:

[0006] A plasma welding device for aerospace parts processing includes an operating handle, a flexible tube, and a protective gas cap. The operating handle and the flexible tube are interconnected and electrically controlled. A connecting ring is fixedly installed on the flexible tube, and a locking structure is provided inside the connecting ring. A nozzle is installed inside the protective gas cap, and an airflow homogenization structure is provided inside the protective gas cap to work with the nozzle. The airflow homogenization structure is used to uniformly deliver the protective gas. The nozzle is used in conjunction with the mounting structure and the locking structure to achieve quick connection, disassembly, and replacement of the nozzle and the flexible tube.

[0007] In the aforementioned plasma welding apparatus for aerospace parts processing, the locking structure includes multiple grooves evenly spaced within a connecting ring. Each groove contains a spring II, and one end of each spring II is fixedly fitted with a locking block. Each locking block has sliders fixedly fitted on both sides. The ends of each locking block that are close to each other are wedge-shaped, and each pair of sliders and locking blocks slide within their respective grooves.

[0008] In the aforementioned plasma welding apparatus for aerospace parts processing, the airflow homogenization structure includes two air holes opened on the outside of the protective gas cap. The protective gas cap is provided with a Z-shaped groove and a fan-shaped hole, and both the Z-shaped groove and the fan-shaped hole are arranged circumferentially along the axis of the protective gas cap. The Z-shaped groove is connected to the two air holes and the fan-shaped hole. The airflow forms a violent turbulence in the Z-shaped groove, and gases with different flow rates are fully mixed in the turbulence.

[0009] In the aforementioned plasma welding apparatus for processing aerospace parts, a mounting hole is provided inside the nozzle, a tungsten electrode is fixedly installed inside the nozzle, and a tungsten electrode clamp is installed inside the nozzle to hold the tungsten electrode.

[0010] In the aforementioned plasma welding apparatus for processing aerospace parts, an insulating sleeve is fixedly provided at one end of the nozzle, a connecting pipe is fixedly provided on one side of the insulating sleeve, and a retaining ring is fixedly installed at one end of the connecting pipe.

[0011] In the aforementioned plasma welding device for processing aerospace parts, an elastic buckle is fixedly installed on the outside of the connecting pipe, and an engaging ridge is fixedly provided inside the elastic buckle. Two elastic grooves are formed on the elastic buckle.

[0012] In the aforementioned plasma welding apparatus for processing aerospace parts, an annular boss is fixedly provided on the protective gas cap, which is used in conjunction with the locking ridge. The protective gas cap is provided with multiple tightening grooves, and the protective gas cap is locked and installed in the elastic buckle for use.

[0013] In the aforementioned plasma welding apparatus for processing aerospace parts, a spring is fixedly installed on one side of the connecting ring, and a fixing ring is fixedly installed on one side of the spring.

[0014] In the aforementioned plasma welding device for aerospace parts processing, the mounting structure includes a lock body fixedly installed at one end of a connecting pipe, a sealing groove fixedly provided on the lock body, and a rubber ring that cooperates with the sealing groove provided around the inner side of the connecting ring.

[0015] In the aforementioned plasma welding device for processing aerospace parts, the lock body is uniformly provided with multiple unlocking slots and multiple locking slots in the circumferential direction, and each locking slot is connected to the corresponding unlocking slot. The end of the locking slot near the connecting pipe is a wedge-shaped surface, and each lock block is slidably engaged in the corresponding locking slot for use.

[0016] Compared with existing technologies, the advantages of this invention are as follows: The device is designed with a convenient connection and locking method: installation only requires an insertion operation to complete the self-locking, without relying on tools such as wrenches; during disassembly, the component can be pushed and rotated to the corresponding position to be pulled out directly. It adopts a special inclined surface mating structure, which can form a self-locking effect that tightens as the component is subjected to axial tension or high-frequency vibration. At the same time, the elastic component provides a continuous pre-tightening force to avoid gap loosening caused by vibration and ensure that the component does not wobble radially or axially during welding. During welding, the protective gas enters and undergoes multiple turns to form violent turbulence. Gases with different flow rates are fully mixed in the turbulence, which completely eliminates the airflow deviation problem of fast airflow at the center and slow airflow at the edge in traditional structures, making the air curtain pressure distribution more balanced. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the structure of a plasma welding device for processing aerospace parts proposed in this invention;

[0018] Figure 2 This is a schematic diagram of the structure of the removed part of the operating handle in this invention;

[0019] Figure 3 In this invention Figure 2 Side view;

[0020] Figure 4 In this invention Figure 3 Cross-sectional view of the structure along the AA direction;

[0021] Figure 5 This is a schematic diagram of the internal structure of the protective cap in this invention;

[0022] Figure 6 This is a side view of the lock body in this invention;

[0023] Figure 7 In this invention Figure 6 A schematic diagram of the three-dimensional structure;

[0024] Figure 8 This is a side view of the protective gas cap in this invention;

[0025] Figure 9 In this invention Figure 8 A cross-sectional view of the structure along the BB direction.

[0026] In the diagram: 1. Operating handle; 2. Flexible tube body; 3. Protective gas cap; 4. Connecting ring; 5. Elastic buckle; 6. Air hole; 7. Tungsten electrode; 8. Nozzle; 9. Spring 1; 10. Fixing ring; 11. Lock body; 12. Spring 2; 13. Slider; 14. Lock block; 15. Insulating sleeve; 16. Connecting tube; 17. Z-shaped groove; 18. Fan-shaped hole; 19. Sealing groove; 20. Tightening groove; 21. Unlocking groove; 22. Locking groove. Detailed Implementation

[0027] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0028] Reference Figure 1 A plasma welding device for aerospace parts processing includes an operating handle 1, a flexible tube 2, and a protective gas cap 3. The operating handle 1 and the flexible tube 2 are interconnected and electrically controlled. The operating handle 1 has an ergonomic arc design with anti-slip textures (such as knurling or rubber coating) on ​​its surface and a balanced weight distribution (center of gravity close to the grip area). Operators can precisely control the movement trajectory of the device (such as thin-walled welds and complex curved surface welding paths of aerospace parts) through the operating handle 1, reducing trajectory deviation caused by hand fatigue. The operating handle 1 is equipped with an on / off valve to control the operation of the device. At the same time, the operating handle 1 integrates a lightweight metal frame (such as aluminum alloy), balancing rigidity and weight reduction, avoiding arm pain caused by prolonged gripping, and adapting to the long-cycle, high-precision welding requirements of aerospace parts. The operating handle 1 has pre-installed wiring and air passages, integrating control signal and cooling water lines to prevent tangling or damage caused by exposed lines. Simultaneously, the connection between the operating handle 1 and the flexible tube 2 is equipped with a sealing structure (such as a rubber sealing ring) to prevent cooling water or protective gas leakage, ensuring operational safety. The protective gas cap 3 is used to deliver protective gas and generate a protective gas curtain.

[0029] Reference Figures 1-4 A connecting ring 4 is fixedly installed on the flexible tube body 2. A locking structure is provided inside the connecting ring 4. The locking structure includes multiple sliding grooves evenly opened inside the connecting ring 4. A spring 12 is fixedly installed in each of the multiple sliding grooves. A locking block 14 is fixedly installed at one end of each spring 12. A slider 13 is fixedly installed on both sides of each locking block 14. The ends of each locking block 14 that are close to each other are wedge-shaped. Each pair of sliders 13 and locking blocks 14 slide in the corresponding sliding groove.

[0030] A nozzle 8 is installed inside the protective gas cap 3. The nozzle 8 has an installation hole, and a tungsten electrode 7 is fixedly installed inside it. A tungsten electrode clamp is also installed inside the nozzle 8 to hold the tungsten electrode 7. An insulating sleeve 15 is fixedly installed at one end of the nozzle 8, and a connecting pipe 16 is fixedly installed on one side of the insulating sleeve 15. The nozzle 8 serves as the mounting carrier for the tungsten electrode 7 and the tungsten electrode clamp. One end of the nozzle cooperates with the protective gas cap 3 to form a gas flow guide space, while the other end is electrically isolated from other components of the device through the insulating sleeve 15. The nozzle 8 employs a variable-diameter contraction and diffusion channel (similar to the principle of a rocket nozzle). The ion gas undergoes compression and expansion within the channel, forming a supersonic airflow ring that forcibly confines the plasma arc into a cone-shaped energy beam, solving the problem of incomplete fusion caused by insufficient heat input during welding of aerospace materials (such as titanium alloys). The tungsten electrode 7 is precisely fixed by a tungsten electrode clamp to ensure the coaxiality of critical components. A mounting hole is provided on the central axis of the nozzle 8, the diameter of which precisely matches the outer diameter of the tungsten electrode 7 and the tungsten electrode clamp. Through the positioning of the mounting hole, the tungsten electrode 7 can be strictly positioned at the center of the nozzle 8 channel, ensuring that the plasma arc is ejected from the center of the nozzle 8 outlet, avoiding arc skew caused by the offset of the tungsten electrode 7 (a skew exceeding 0.1mm will directly cause asymmetrical defects in the welds of aerospace components). Furthermore, the inner wall of the mounting hole is precision ground to reduce friction and wear with the tungsten electrode clamp, extending the service life of the component.

[0031] Reference Figures 4-9 An elastic buckle 5 is fixedly installed on the outside of the connecting pipe 16. An engaging ridge is fixedly provided inside the elastic buckle 5. Two elastic grooves are formed on the elastic buckle 5. An annular boss is fixedly provided on the protective air cap 3. Multiple tightening grooves 20 are formed on the protective air cap 3. The protective air cap 3 is engaged and installed within the elastic buckle 5 for use. Without tools, the protective air cap 3 is manually aligned with the center hole of the elastic buckle 5, and axial pressure is applied. The outer wall of the protective air cap 3 will press against the inner inclined surface of the elastic buckle 5, forcing the elastic buckle 5 to expand radially along the elastic groove. When the annular boss on the protective air cap 3 passes the engaging ridge of the elastic buckle 5, the elastic buckle 5 returns to its original position and contracts under its own elastic force, firmly locking the protective air cap 3. At this time, the coaxiality of the protective air cap 3 and the nozzle 8 is automatically calibrated.

[0032] A retaining ring is fixedly installed at one end of the connecting pipe 16. An airflow equalization structure, used in conjunction with the nozzle 8, is provided inside the protective gas cap 3. This structure is used to uniformly deliver the protective gas. The airflow equalization structure includes two air holes 6 located on the outside of the protective gas cap 3. A Z-shaped groove 17 and a fan-shaped hole 18 are provided inside the protective gas cap 3, both circumferentially arranged along the axis of the protective gas cap 3. The Z-shaped groove 17 is connected to the two air holes 6 and the fan-shaped hole 18. A spring 9 is fixedly installed on one side of the connecting ring 4, and a retaining ring 10 is fixedly installed on one side of the spring 9.

[0033] Protective gas is introduced into the protective gas cap 3 through two vents 6. The protective gas is ejected through the fan-shaped hole 18 via the Z-shaped groove 17, maintaining the pre-flow state of the protective gas. The start / stop valve on the operating handle 1 is pressed to the second position (welding position), so that the tungsten electrode 7 briefly contacts the workpiece and then quickly separates. When the tungsten electrode 7 contacts the workpiece, the welding circuit is turned on and current is generated. At the moment of separation, the ionized gas is ionized under the action of the current (argon molecules are ionized into argon ions and electrons, and hydrogen gas assists in enhancing the ionization effect), forming a high-temperature plasma arc. At this time, the protective gas ejected from the protective gas cap 3 continuously surrounds the arc, preventing the arc from being disturbed by air. The tortuous path of the Z-shaped groove 17 forces the protective gas to make multiple turns during the flow process (similar to a maze structure). The airflow forms a violent turbulence in the Z-shaped groove 17, and the gas with different flow velocities is fully mixed in the turbulence, eliminating the defects of uneven initial airflow distribution (such as the phenomenon that the airflow in the pipe may be fast in the center and slow at the edge), so that the pressure distribution of the protective gas curtain ejected from the outlet of the protective gas cap 3 is more uniform. This uniform air curtain can more tightly envelop the plasma arc, especially for complex welds on aerospace components (such as corners and deep grooves), preventing localized oxidation caused by dead zones in the airflow. The protective air curtain has a higher flow rate in the fan-shaped orifice 18, resulting in a stronger compression effect on the arc. The lateral thrust of the fan-shaped air curtain can also suppress the flow of molten metal in the pool (such as the molten metal falling during vertical welding). Combined with the directional distribution of arc energy, this keeps the weld reinforcement within an ideal range.

[0034] The nozzle 8, through the cooperation of the mounting structure and the locking structure, enables quick connection and disassembly / replacement of the nozzle 8 and the flexible tube 2. The mounting structure includes a lock body 11 fixedly mounted on one end of the connecting tube 16. One end of the lock body 11 is inclined, which helps to smoothly insert the lock body 11 into the connecting ring 4 for connection when installing the nozzle 8 and the flexible tube 2. A sealing groove 19 is fixedly provided on the lock body 11, and a rubber ring that matches the sealing groove 19 is provided around the inner side of the connecting ring 4. The lock body 11 has multiple unlocking grooves 21 and multiple locking grooves 22 evenly distributed around its circumference, and each locking groove 22 is connected to the corresponding unlocking groove 21. The end of the locking groove 22 near the connecting tube 16 is wedge-shaped, and each locking block 14 slides and engages in the corresponding locking groove 22.

[0035] The lock body 11 serves as the connecting carrier between the flexible tube 2 and the nozzle 8. The locking blocks 14 distributed circumferentially on the connecting ring 4 can slide along the locking groove 22, achieving a rigid connection through mechanical engagement. When the connecting ring 4 mates with the lock body 11, the locking blocks 14 first slide along the inclined surface of the lock body 11 until they engage in the locking groove 22 to form a connection. At the same time, the retaining ring and the fixing ring 10 abut against each other. At this point, a sudden force can be felt as the lock body 11 and multiple locking blocks 14 engage and connect. Finally, they are locked in the locking groove 22 to form a self-locking mechanism, which can be fixed without tools. The sealing groove 19 is opened on the end face of the lock body 11. When the self-locking is completed, the rubber ring (usually heat-resistant fluororubber) inside the connecting ring 4 forms a seal with the sealing groove 19. The rubber ring is deformed by the compression of the connecting ring 4 and the lock body 11, filling the gap of the sealing groove 19, while blocking the leakage channels of ion gas and protective gas, as well as the leakage path of the cooling water circuit.

[0036] The locking groove 22 is an axial arc groove, and the wedge-shaped surface at the end matches the wedge-shaped setting of the locking block 14. When the nozzle 8 is subjected to axial tension, the locking groove 22 limits the locking block 14, forcing the locking block 14 to lock tighter and tighter, forming an anti-loosening self-locking effect. When replacing or disassembling nozzle 8, push nozzle 8 towards connecting ring 4. At this time, the retaining ring and fixing ring 10 compress spring 9 (spring 9 has high rigidity and requires a large force to push, ensuring that the device will not wobble radially during welding; at the same time, the locking groove 22 on the lock body 11 has an axial limiting function to ensure stability during welding). At this time, multiple locking blocks 14 are at one end of the lock body 11 (the end where the sealing groove 19 is located). Rotate nozzle 8 or flexible tube 2 by hand so that each locking block 14 is aligned with the corresponding unlocking groove 21 (the rotation direction and positioning lines are marked on connecting ring 4 and connecting tube 16, allowing operators to visually confirm whether it is locked and unlocked, ensuring installation quality without professional skills, and meeting the requirements of standardized operations in aerospace manufacturing). Then, pull nozzle 8 out axially along unlocking groove 21 to complete the disassembly and replacement of nozzle 8. For mass-produced aerospace components, rapid replacement capability can improve equipment utilization and indirectly reduce manufacturing costs.

[0037] To further clarify, the aforementioned fixed connection should be interpreted broadly unless otherwise explicitly specified and limited. For example, it may be welding, gluing, or integral molding, or other conventional methods well known to those skilled in the art.

[0038] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. An aviation part processing plasma welding device, comprising an operating handle (1), a flexible tube body (2) and a protective gas cap (3), and the operating handle (1) and the flexible tube body (2) are communicated and electrically controlled, characterized in that, A connecting ring (4) is fixedly installed on the flexible tube (2). A locking structure is provided inside the connecting ring (4). A nozzle (8) is installed inside the protective gas cap (3). An airflow equalization structure is provided inside the protective gas cap (3) to cooperate with the nozzle (8). The airflow equalization structure is used to uniformly deliver protective gas. The nozzle (8) completes the quick connection and disassembly / replacement of the nozzle (8) and the flexible tube (2) through the cooperation of the installation structure and the locking structure. The locking structure includes multiple grooves evenly opened in the connecting ring (4), and springs (12) are fixedly installed in each of the multiple grooves. A locking block (14) is fixedly installed at one end of each spring (12). Slider blocks (13) are fixedly installed on both sides of each locking block (14). The ends of each locking block (14) that are close to each other are wedge-shaped, and every two sliders (13) and locking blocks (14) slide in the corresponding grooves. The airflow homogenization structure includes two air holes (6) opened on the outside of the protective air cap (3). The protective air cap (3) is provided with a Z-shaped groove (17) and a fan-shaped hole (18). The Z-shaped groove (17) and the fan-shaped hole (18) are arranged circumferentially along the axis of the protective air cap (3). The Z-shaped groove (17) is connected to the two air holes (6) and the fan-shaped hole (18). The airflow forms a violent turbulence in the Z-shaped groove (17), and the gases with different flow rates are fully mixed in the turbulence. An insulating sleeve (15) is fixedly provided at one end of the nozzle (8), a connecting pipe (16) is fixedly provided on one side of the insulating sleeve (15), and a retaining ring is fixedly installed at one end of the connecting pipe (16). The installation structure includes a lock body (11) fixedly installed at one end of the connecting pipe (16), a sealing groove (19) fixedly provided on the lock body (11), and a rubber ring that cooperates with the sealing groove (19) is provided around the inner side of the connecting ring (4). The lock body (11) is evenly provided with multiple unlocking slots (21) and multiple locking slots (22) in the circumference, and each locking slot (22) is connected to the corresponding unlocking slot (21). The end of the locking slot (22) near the connecting pipe (16) is a wedge-shaped surface, and each lock block (14) is slidably engaged in the corresponding locking slot (22) for use.

2. The plasma welding apparatus for aerospace parts processing according to claim 1, characterized in that, The nozzle (8) has an installation hole, a tungsten electrode (7) is fixedly installed inside the nozzle (8), and a tungsten electrode clamp is installed inside the nozzle (8) to hold the tungsten electrode (7).

3. The plasma welding apparatus for aerospace parts processing according to claim 1, characterized in that, An elastic buckle (5) is fixedly installed on the outside of the connecting pipe (16). An engaging ridge is fixedly provided inside the elastic buckle (5). Two elastic grooves are opened on the elastic buckle (5).

4. The plasma welding apparatus for aerospace parts processing according to claim 3, characterized in that, The protective gas cap (3) is fixedly provided with an annular boss, which is used in conjunction with the locking ridge. The protective gas cap (3) is provided with multiple tightening grooves (20), and the protective gas cap (3) is locked in the elastic buckle (5) for use.

5. The plasma welding apparatus for aerospace parts processing according to claim 1, characterized in that, A spring (9) is fixedly installed on one side of the connecting ring (4), and a fixing ring (10) is fixedly installed on one side of the spring (9).

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