Argon arc welding device and welding method for exhaust port of turbine casing of aircraft engine

Abstract

The present invention provides an argon arc welding device and a welding method for an aircraft engine turbine casing exhaust port, and relates to the technical field of welding and processing of aircraft engine parts. The device includes a positioning seat, an expansion block, a push block, and a pressure plate. The outer wall of the expansion block is used to tighten the two sides of the welding position of the exhaust pipe and the exhaust connection pipe, ensuring concentricity while positioning the parts, preventing mismatch of the positions to be welded, and ensuring that the misalignment after welding meets the technical conditions. An annular groove is provided on the outside of the expansion block. By aligning with the weld, the annular groove and the exhaust pipe and the inner wall of the exhaust connection pipe form an annular space, thereby providing sufficient space for the generation of the weld, avoiding interference between the weld and the argon arc welding device, and avoiding adhesion between the weld and the argon arc welding device during welding. In addition, the annular space ensures that argon gas fills the root of the weld to prevent oxidation of the parts. The technical problem that the existing welding method cannot meet the various welding processing requirements of the high-pressure turbine casing and the casing exhaust port is solved.

Description

Technical Field

[0001] The present invention relates to the technical field of welding and processing of aircraft engine parts, and in particular to an argon arc welding device and a welding method for an exhaust port of an aircraft engine turbine casing. Background Art

[0002] During the production of aircraft engines, the high-pressure turbine stator casing and the casing exhaust port must be connected by manual argon arc welding. The deformation during the welding process directly affects the subsequent assembly and use of the parts. Figure 1 and Figure 2 As shown, the connection between the exhaust pipe 9 and the exhaust pipe 10 of the casing 12 is tubular. According to the design requirements, the coaxiality, angular deviation and contour of the two welded parts are strictly required. The misalignment requirement is not greater than 0.56mm, the coaxiality requirement is not greater than 0.76mm, the contour requirement is not greater than 0.80mm, and the angular deviation is not greater than 0.3°. Therefore, in order to ensure the above technical conditions, it is necessary to simultaneously position the high-pressure turbine casing 12 and the casing exhaust port. The docking position must ensure good argon protection and avoid the weld 13 from adhering to the fixture after welding. Therefore, in actual operation, it is necessary to position both sides of the docking position of the weld 13. Figure 2 and Figure 3 As shown, after welding, a 0.50mm-0.76mm excess height is left on the back of weld 13, forming a raised structure 11. This causes the inner diameter of weld 13, which is 41.15mm-41.67mm, to be smaller than the positioning diameter of 42.67mm, making it impossible to remove the fixture. Considering the exhaust port's inner diameter of only 42.67mm and the limited space, the conventional expansion-type structure in the prior art cannot meet the above welding processing requirements. Summary of the Invention

[0003] In view of this, the present invention provides an argon arc welding device and a welding method for an aircraft engine turbine casing exhaust port, which are used to solve the technical problem that the existing welding methods in the prior art cannot meet the various welding processing requirements of the high-pressure turbine casing and the casing exhaust port.

[0004] In a first aspect, the present specification provides an argon arc welding device for an exhaust port of a turbine casing of an aircraft engine, the device comprising: a positioning seat, the positioning seat comprising a positioning portion, a connecting portion, and a truncated cone-shaped expansion head arranged in sequence, the positioning portion being used to abut against the inner wall of an exhaust pipe, the connecting portion having a cavity therein, the outer wall of the connecting portion having a plurality of evenly distributed air outlet holes, the air outlet holes being connected to the cavity, a matching hole being provided in the positioning portion, the matching hole penetrating an end surface of the positioning portion away from the truncated cone-shaped expansion head, the matching hole being connected to the cavity, and the large-diameter end of the truncated cone-shaped expansion head being connected to the connecting portion;

[0005] An expansion block, the expansion block comprising a plurality of arc segments surrounding the outer periphery of the truncated cone-shaped expansion head, the arc segments being cooperatively connected to the truncated cone-shaped expansion head by surrounding the truncated cone-shaped expansion head;

[0006] A push block, the push block is located at one end of the truncated cone-shaped expansion head away from the positioning portion, and the push block abuts against one end of the tightening block away from the positioning portion;

[0007] A pressure plate is located on the side of the push block away from the truncated cone-shaped expansion head. The pressure plate is used to abut the inner wall of the exhaust pipe. The pressure plate is fixed to the truncated cone-shaped expansion head by screws. The pressure plate and the push block are provided with through holes for the screws to pass through. A knurled screw is threaded on the pressure plate, and the knurled screw passes through the pressure plate and abuts the push block.

[0008] Furthermore, the positioning portion includes a base and a positioning cylinder that are connected to each other, the base abuts the end surface of the exhaust pipe facing the interior of the casing, the positioning cylinder fits the inner wall of the exhaust pipe, and the positioning cylinder is connected to the connecting portion.

[0009] Furthermore, the inner ring of the expansion block gradually shrinks from the large diameter end to the small diameter end of the truncated cone-shaped expansion head.

[0010] Furthermore, an elastic ring is provided on the outer periphery of the expansion block.

[0011] Furthermore, an annular groove is provided on the outer periphery of the expansion block.

[0012] Furthermore, there are four arc segments, and the central angle of each arc segment is 80°.

[0013] Furthermore, the aircraft engine turbine casing exhaust port argon arc welding device also includes: a vent nozzle, the vent nozzle includes a fixing portion and a connecting portion, the fixing portion is fixedly connected to the positioning seat, the connecting portion is connected to an external argon gas delivery pipeline, and the vent nozzle is connected to the matching hole.

[0014] The second aspect of the present invention further provides an argon arc welding method, which uses the above-mentioned aircraft engine turbine casing exhaust port argon arc welding device to perform welding operations.

[0015] Compared with the existing technology, the beneficial effects that can be achieved by at least one of the above-mentioned technical solutions adopted in the embodiments of this specification include at least: by providing an argon arc welding device for the exhaust port of the turbine casing of an aircraft engine, the various dimensional technical conditions of the high-pressure turbine casing and the casing exhaust port are guaranteed, while meeting the requirements of gas protection on the back of the weld and convenient clamping and disassembly. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following briefly introduces the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0017] Figure 1 This is a schematic diagram of the structure of the high-pressure turbine case of an aircraft engine;

[0018] Figure 2 for Figure 1 Cross-sectional view in the middle RR direction;

[0019] Figure 3 yes Figure 2 Magnified view of the weld in ;

[0020] Figure 4 This is a schematic structural diagram of an argon arc welding device for an exhaust port of a turbine casing of an aircraft engine provided by an embodiment of the present invention;

[0021] Figure 5 A front view of the structure of an argon arc welding device for an exhaust port of a turbine casing of an aircraft engine provided by an embodiment of the present invention;

[0022] Figure 6 for Figure 5 Cross-sectional view in the AA direction;

[0023] Figure 7 A schematic diagram of the structure of the vent nozzle provided in an embodiment of the present invention;

[0024] Figure 8 A schematic diagram of the positioning seat structure provided by an embodiment of the present invention;

[0025] Figure 9 A schematic diagram of the structure of an expansion block provided in an embodiment of the present invention;

[0026] Figure 10 A cross-sectional view of the push block structure provided by an embodiment of the present invention

[0027] Figure 11 This is a schematic diagram of the pressure plate structure provided by an embodiment of the present invention.

[0028] Reference numerals in the figure: 1. vent nozzle; 2. positioning seat; 2-1. base; 2-2. positioning cylinder; 2-3. air outlet; 2-4. truncated cone-shaped expansion head; 2-5. threaded hole; 3. expansion block; 3-1. annular groove; 4. elastic ring; 5. push block; 5-1. cylindrical groove; 5-2. first through hole; 6. pressure plate; 6-1. exhaust hole; 6-2. threaded through hole; 6-3. second through hole; 7. screw; 8. knurled screw; 9. exhaust pipe; 10. exhaust pipe; 11. raised structure; 12. casing; 13. weld. DETAILED DESCRIPTION

[0029] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0030] The following describes the embodiments of the present application through specific examples, and those skilled in the art can easily understand other advantages and effects of the present application from the contents disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The present application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, in the absence of conflict, the features in the following embodiments and embodiments can be combined with each other. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without making creative work are within the scope of protection of this application.

[0031] like Figure 4 As shown, an embodiment of the present invention provides an argon arc welding device for an exhaust port of a turbine casing of an aircraft engine, comprising: a vent nozzle 1, a positioning seat 2, a tightening block 3, a push block 5, a pressure plate 6, a screw 7 and a knurled screw 8.

[0032] Specifically, if Figure 4 、 Figure 5 、 Figure 6 As shown, the positioning seat 2 includes a positioning portion, a connecting portion, and a truncated cone-shaped expansion head 2-4, which are arranged in sequence. The large-diameter end of the truncated cone-shaped expansion head 2-4 is connected to the connecting portion. The positioning portion includes a base 2-1 and a positioning cylinder 2-2, which are connected to each other. The base 2-1 abuts the end surface of the exhaust pipe 9 facing the interior of the casing 12. The positioning cylinder 2-2 fits the inner wall of the exhaust pipe 9 and is connected to the connecting portion. The positioning portion is used to seal the inner wall of one end of the casing exhaust port. The connecting portion has a cavity inside. The outer wall of the connecting portion has a plurality of evenly distributed air outlet holes 2-3, which are connected to the cavity. The positioning portion is provided with a matching hole, which passes through the end surface of the positioning portion away from the truncated cone-shaped expansion head 2-4 and is connected to the cavity.

[0033] The expansion block 3 includes a plurality of arc segments surrounding the outer circumference of the truncated cone-shaped expansion head 2-4, and the arc segments are connected with the truncated cone-shaped expansion head 2-4 by surrounding the truncated cone-shaped expansion head 2-4; the push block 5 is located at the end of the truncated cone-shaped expansion head 2-4 away from the positioning portion, and the push block 5 abuts the end of the expansion block 3 away from the positioning portion; the pressure plate 6 is located at the end of the push block 5 away from the truncated cone-shaped expansion head 2-4, and the pressure plate 6 is used for the inner wall of the exhaust pipe 10. The pressure plate is fixed to the truncated cone-shaped expansion head 2-4 by screws 7. The pressure plate 6 and the push block 5 are provided with through holes for the screws 7 to pass through. The pressure plate 6 is threaded with a knurled screw 8, and the knurled screw 8 passes through the pressure plate 6 and abuts the push block 5.

[0034] An annular groove 3 - 1 is provided on the outer periphery of the expansion block 3 , and the annular groove 3 - 1 is used to align with the weld during welding.

[0035] The present invention provides an aircraft engine turbine casing exhaust port argon arc welding device. When working, by tightening the knurled screw 8, the end of the knurled screw 8 pushes the push block 5, and the push block 5 pushes the expansion block 3 to move along the axial direction of the truncated cone-shaped expansion head 2-4 toward the large diameter end of the truncated cone-shaped expansion head 2-4, so that the outer diameter of the expansion block 3 increases. At this time, the outer wall of the expansion block 3 presses against both sides of the welding position of the exhaust pipe 9 and the exhaust connecting pipe 10, ensuring concentricity while positioning the parts. At the same time, the annular groove 3-1 is aligned with the weld, and the annular groove 3-1 and the inner walls of the exhaust pipe 9 and the exhaust connecting pipe 10 form an annular space. The annular space provides sufficient space for the generation of the weld, avoids interference between the weld and the argon arc welding device, and thus avoids adhesion between the weld and the argon arc welding device during welding. After welding is completed, knurled screw 8 is loosened, and push block 5 no longer applies pressure to expansion block 3. Due to the contraction force of elastic ring 4, expansion block 3 moves along the axial direction of truncated cone-shaped expansion head 2-4 of positioning seat 2 toward the smaller diameter end of truncated cone-shaped expansion head 2-4, reducing the outer diameter of expansion block 3. Screw 7 is loosened with a wrench, allowing screw 7 to exit threaded hole 2-5 of positioning seat 2. At this point, the components can be removed from the side of exhaust pipe 9 near casing 12 and the side of exhaust pipe 10 away from casing 12, respectively. By providing an argon arc welding device for an aircraft engine turbine casing exhaust port, high-precision technical conditions can be ensured during the welding process. Good expansion assembly of components can be achieved in a narrow space (42.67 mm in diameter), preventing the weld seam from adhering to the argon arc welding device during welding. When the argon arc welding device is disassembled, expansion block 3 contracts, reducing its outer diameter, allowing it to easily pass through the weld seam. The pressure plate and positioning portion can be removed from different sides of the weld seam, avoiding interference between the weld seam and the argon arc welding device.

[0036] Further, such as Figure 4 and Figure 7 、 Figure 8As shown, the vent nozzle 1 includes a fixing portion and a connecting portion, wherein the fixing portion is fixedly connected to the positioning seat 2, and the connecting portion is connected to the external argon gas delivery pipeline, and the connecting portion is formed by connecting multiple conical tubular structures. The vent nozzle 1 is connected to the bottom of the positioning seat 2 in a threaded manner, and the vent nozzle 1 is connected to the external argon gas delivery pipeline. Argon gas enters the interior of the positioning seat 2 from the vent nozzle 1 and is evenly injected from the annular gas outlet holes 2-3 uniformly distributed on the outer wall of the connection part of the positioning seat 2. At the same time, the positioning portion of the positioning seat 2 is used to seal the inner wall of the exhaust pipe 9, and the pressure plate 6 is used to abut the inner wall of the exhaust pipe 10 to achieve a seal with the exhaust pipe 10. The argon gas is sealed near the weld 13 (inside the exhaust port of the casing) through the positioning portion and the pressure plate 6, thereby ensuring that the weld 13 is protected by an inert atmosphere throughout the welding process. The exhaust hole 6-1 on the pressure plate 6 is an air exhaust hole, which is used to exhaust the air inside the cavity during the process of introducing argon gas.

[0037] Further, such as Figure 4 、 Figure 8 、 Figure 9 and Figure 10 As shown, the positioning seat 2 serves as a main support body, and the base 2-1 is a boss structure with uneven thickness, so that the side of the base 2-1 facing the exhaust pipe 9 can better fit with the end face of the exhaust pipe 9. The thickness of the boss is determined by the connection between the high-pressure turbine stator casing exhaust port ( Figure 2 The inner contact surface of the exhaust pipe 9 is designed to better fit the contact surface, thereby achieving better support and sealing. Figure 2 The inner wall of the middle exhaust pipe 9 cooperates for positioning. The connection between the truncated cone shaped expansion head 2-4 and the connection part has a boss structure, and the side of the boss structure close to the truncated cone shaped expansion head 2-4 has a groove structure. The end face of the truncated cone shaped expansion head 2-4 has a threaded hole 2-5 that cooperates with the screw 7.

[0038] Further, such as Figure 4 and Figure 9 As shown, the inner ring of the expansion block 3 gradually decreases from the large diameter end to the small diameter end of the truncated cone-shaped expansion head 2-4. The expansion block 3 includes a plurality of arc segments, which are connected to the positioning seat 2 by surrounding the positioning seat 2. In this embodiment, preferably, the expansion block 3 includes four identical arc segments, each with a center angle of 80°; the outer side of the arc segment is a cylindrical surface, and each arc segment is provided with an arc groove on the outer periphery. The arc grooves on the four arc segments are combined to form an annular groove 3-1. The annular groove 3-1 is used to avoid the raised structure 11 formed by the excess height on the back of the weld 13 to prevent the parts from adhering to the argon arc welding device.

[0039] The inner side of the expansion block 3 is a conical surface for matching with the truncated cone-shaped expansion heads 2-4.

[0040] Further, such as Figure 4 、 Figure 5 and Figure 6 As shown, an elastic ring 4 is disposed within the annular groove 3-1 of the arc segment. The elastic ring 4 primarily maintains a tight fit between the four expansion blocks 3 and the truncated cone-shaped expansion heads 2-4 of the positioning seat 2, ensuring that the radial dimensions of the expansion blocks 3 smoothly increase or decrease during axial movement. In this embodiment, the elastic ring 4 is preferably a spring.

[0041] Further, such as Figure 4 and Figure 10 As shown, the push block 5 has a cylindrical groove 5-1 on its end face facing the truncated cone-shaped expansion head 2-4, and a first through hole 5-2 is provided on the push block 5 for the screw 7 to pass through; the cylindrical groove 5-1 corresponds to the truncated cone-shaped expansion head 2-4, and when the push block 5 moves axially, the cylindrical groove 5-1 avoids interference with the truncated cone-shaped expansion head 2-4.

[0042] Further, such as Figure 4 、 Figure 11 As shown, the pressure plate 6 has a threaded through hole 6-2 and a second through hole 6-3. The threaded through hole 6-2 is used to connect the knurled screw 8. The second through hole 6-3 is corresponding to the first through hole 5-2 and is provided for the screw 7 to pass through. In this embodiment, the screw 7 is preferably a hexagon head screw. The screw 7 passes through the second through hole 6-3, then through the first through hole 5-2, and finally connects with the threaded hole 2-5, thereby playing a role. Figure 2 The compression and fixing effect between the middle exhaust pipe 10 and the exhaust pipe 9; the threaded through hole 6-2 on the pressure plate 6 is threadedly connected to the knurled screw 8 until it reaches the center of the push block 5, pushing the push block 5 and the expansion block 3 to move, thereby increasing the outer diameter of the expansion block 3, and vice versa reducing the outer diameter of the expansion block 3.

[0043] Furthermore, the pressing plate 6 includes a large-diameter end and a small-diameter end, and a groove structure is provided at the connection between the large-diameter end and the small-diameter end.

[0044] In addition, an embodiment of the present invention further provides an argon arc welding method, which uses the above-mentioned aircraft engine turbine casing exhaust port argon arc welding device to perform welding operations.

[0045] Specifically, in an embodiment of the present invention, a argon arc welding method is provided, in which the first component includes a vent nozzle 1 and a positioning seat 2, the second component includes an elastic ring 4 and a tightening block 3, and the third component includes a push block 5, a pressure plate 6, a screw 7, and a knurled screw 8. The method specifically includes the following steps:

[0046] Step 1: Clean the exhaust pipe 9, exhaust pipe 10 welding position, and the aircraft engine high-pressure turbine casing exhaust port argon arc welding device. Insert the first component's frustum-shaped expansion head 2-4 from the exhaust pipe 9 near the casing 12 into the casing exhaust port;

[0047] Step 2: Install the second component into the side of the exhaust pipe 9 away from the casing 12;

[0048] Step 3: Insert the push block 5 of the third component from the side of the exhaust pipe 10 away from the casing 12;

[0049] Step 4: Match the assembly parts formed in Step 3 with those in Step 1. Rotate the assembly parts formed in Step 3 to ensure that the position of screw 7 is consistent with threaded hole 2-5. At the same time, ensure that the exhaust hole 6-1 of the pressure plate 6 is vertically upward, and manually tighten screw 7. Screw 7 passes through the second through hole 6-3 of the pressure plate 6 and the first through hole 5-2 of the push block 5, and finally connects with the threaded hole 2-5 on the positioning seat 2 to ensure the fixation and compression of the entire device.

[0050] Step 5: Expand the part. Tighten the knurled screw 8 and push the push block 5 through the end of the knurled screw 8. The push block 5 pushes the expansion block 3 to move axially, increasing the outer diameter of the expansion block 3 and stretching the elastic ring 4. At this time, the outer diameter of the expansion block 3 presses against the exhaust pipe 9 and the exhaust pipe 10 on both sides of the welding position, positioning the parts and ensuring concentricity. When the push block 5 moves axially, the cylindrical groove 5-1 avoids interference with the frustoconical expansion head 2-4.

[0051] Step 6: Use a wrench to tighten screw 7 again to compress the parts as much as possible, apply force evenly on both sides to ensure uniform force. Tighten the knurled screw 8 again to compress the expansion block 3 as much as possible to ensure that the parts do not produce dislocation and deformation during the welding process;

[0052] Step 7: Connect the argon vent tube to the serrated end of the vent nozzle 1, open it and let in argon gas;

[0053] Step 8: After the air inside the pipe is exhausted, welding is carried out. During the welding process, argon gas continuously enters from the vent nozzle 1 and is continuously discharged from the exhaust hole 6-1 of the pressing plate 6;

[0054] Step 9: After welding is completed, wait for the weld 13 to cool for 30 seconds. Loosen the knurled screw 8. Due to the contraction force of the elastic ring 4, the expansion block 3 moves axially along the conical expansion head 2-5 of the positioning seat 2, while pushing the push block 5 axially, and the outer diameter of the expansion block 3 decreases.

[0055] Step 10: Use a wrench to loosen screw 7 so that it exits threaded hole 2-5 of locating seat 2. You can now remove the first component from the side of exhaust pipe 9 close to casing 12, and the third and second components from the side of exhaust pipe 10 away from casing 12. The welding of the high-pressure turbine casing exhaust port is now complete. The remaining seven exhaust ports are welded in the same manner. To ensure good deformation prevention, all eight exhaust ports are equipped with fixtures simultaneously. After welding each one, wait 20 minutes for cooling before removing the fixtures.

[0056] In summary, the argon arc welding device and welding method for an aircraft engine turbine case exhaust port provided in the embodiments of the present application can achieve at least the following technical effects compared with the prior art:

[0057] 1. It can ensure high-precision technical conditions of parts during the welding process;

[0058] 2. Even in a small space (diameter 42.67mm), it ensures good expansion assembly effect of parts.

[0059] The above description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in the present application should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection of the claims.

Claims

1. An argon arc welding device for an aircraft engine turbine casing exhaust port, characterized in that: include: A positioning seat (2), the positioning seat (2) comprising a positioning portion, a connecting portion and a truncated cone-shaped expansion head (2-4) arranged in sequence, the positioning portion being used to abut against the inner wall of an exhaust pipe (9), the connecting portion having a cavity therein, the outer wall of the connecting portion having a plurality of evenly distributed air outlet holes (2-3), the air outlet holes (2-3) being connected to the cavity, a matching hole being provided in the positioning portion, the matching hole penetrating the end face of the positioning portion away from the truncated cone-shaped expansion head (2-4), the matching hole being connected to the cavity, and the large-diameter end of the truncated cone-shaped expansion head (2-4) being connected to the connecting portion; An expansion block (3), the expansion block (3) comprising a plurality of arc segments surrounding the outer periphery of a truncated cone-shaped expansion head (2-4), the arc segments being cooperatively connected to the truncated cone-shaped expansion head (2-4) by surrounding the truncated cone-shaped expansion head (2-4); A push block (5), the push block (5) is located at one end of the truncated cone-shaped expansion head (2-4) away from the positioning portion, and the push block (5) abuts against one end of the expansion block (3) away from the positioning portion; A pressure plate (6), the pressure plate (6) is located at one end of the push block (5) away from the truncated cone-shaped expansion head (2-4), the pressure plate (6) is used to abut the inner wall of the exhaust pipe (10), the pressure plate is fixed to the truncated cone-shaped expansion head (2-4) by a screw (7), the pressure plate (6) and the push block (5) are provided with a through hole for the screw (7) to pass through, the pressure plate (6) is threadedly connected with a knurled screw (8), the knurled screw (8) passes through the pressure plate (6) and abuts the push block (5).

2. The argon arc welding device for an aircraft engine turbine casing exhaust port according to claim 1, characterized in that: The positioning portion comprises a base (2-1) and a positioning cylinder (2-2) connected to each other, the base (2-1) being fitted to one end of the exhaust pipe (9) away from the exhaust pipe (10), the positioning cylinder (2-2) being fitted to the inner wall of the exhaust pipe (9), and the positioning cylinder (2-2) being connected to the connection portion.

3. The argon arc welding device for an aircraft engine turbine casing exhaust port according to claim 1, characterized in that: The inner ring of the expansion block (3) gradually shrinks in a direction from the large diameter end to the small diameter end of the truncated cone-shaped expansion head (2-4).

4. The argon arc welding device for an aircraft engine turbine casing exhaust port according to claim 3, characterized in that: An elastic ring (4) is sleeved on the outer periphery of the expansion block (3).

5. The argon arc welding device for an aircraft engine turbine casing exhaust port according to claim 4, characterized in that: An annular groove (3-1) is provided on the outer periphery of the expansion block (3).

6. The argon arc welding device for an aircraft engine turbine casing exhaust port according to claim 5, characterized in that: There are four arc segments, and the central angle of each arc segment is 80°.

7. The argon arc welding device for an aircraft engine turbine casing exhaust port according to claim 1, characterized in that: Also includes: A vent nozzle (1) comprises a fixing portion and a connecting portion, wherein the fixing portion is fixedly connected to a positioning seat (2), the connecting portion is connected to an external argon gas delivery pipeline, and the vent nozzle (1) is connected to the matching hole.

8. A argon arc welding method, characterized in that: The argon arc welding method uses an aircraft engine turbine case exhaust argon arc welding device according to any one of claims 1 to 7 to perform welding operations.

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