Combination welding machining method for aero-engine jet pipe receiver

Abstract

The invention discloses a combined welding machining method for a jet pipe receiver of an aero-engine. The combined welding machining method comprises the following steps that S1, parting treatment is conducted on a jet pipe flow channel; s2, punching and forming a semi-finished product; s3, the semi-finished products are welded into a spray pipe runner and a cartridge receiver barrel; s4, a nozzle flow channel is cut open along the symmetrical middle; s5, the workpieces are combined and fixed through a sealing clamp; s6, the sealing clamp is filled with protective gas, and then welding is conducted; s7, a window for the spraying pipe flow channel to stretch out is machined in the cartridge receiver barrel; and S8, the two symmetrically-cut flow channels extend into the casing through the window to be combined, and the symmetrically-cut portions are welded again. According to the method, the problem of size out-of-tolerance caused by springback and deformation of the cartridge receiver barrel is solved, repeated reworking and quality problem treatment after disqualification are avoided, the one-time machining and welding qualification rate of parts is increased, the quality of welding seams is guaranteed, and the overall performance and reliability of the spray pipe cartridge receiver are effectively improved.

Description

Technical Field

[0001] The present invention belongs to the technical field of aero-engine processing, and more specifically, relates to a combined welding processing method for an aero-engine nozzle casing. Background Art

[0002] Currently, most engine nozzles utilize a dual-exhaust aerodynamic layout. After entering the exhaust system, the gas flows into an internal bifurcated flow channel, splitting into two streams before being discharged through two horizontal outlets. The nozzle sheet metal components have complex profiles, large cross-sectional variations, numerous small local features, and some asymmetric structures. The forming and fitting precision between the parts is extremely high, and the sheet metal precision must meet the argon arc welding gap requirement of less than 0.2mm. Failure to do so will not only impact production schedules, but also weld quality and flow channel dimensions, ultimately affecting overall engine performance. Conventional combined processes and parting methods struggle to guarantee machining accuracy, stability, and surface quality, posing significant challenges to the manufacturing process.

[0003] Parts of a certain aircraft engine nozzle casing such as Figure 1 As shown, it is composed of two mounting edges, a casing barrel and a nozzle flow channel welded together. The nozzle needs to guide the airflow to be discharged from two outlets on both sides of the horizontal plane. The shape is mostly a special-shaped curved surface structure. Due to the complex shape and multiple negative angles, it cannot be formed as a whole, so it is basically formed in blocks, and then combined and welded into an independent flow channel, and then welded in pairs.

[0004] Conventional process routes such as Figure 3 As shown, the nozzle flow channels are first grouped and typed, and the nozzle casing is assembled and welded after the combination welding of the nozzle flow channels is completed. Since the nozzle flow channels cannot be normally assembled into the nozzle casing after assembly, it is necessary to first assemble and weld the casing barrel in half, and finally weld the upper and lower mounting edges. Four welds will be generated on the casing barrel; at the same time, when welding the upper and lower mounting edges, the automatic argon arc welding torch will interfere due to the nozzle flow channel structure, and the argon arc welding cannot be protected, the operation is more difficult, and the weld strength will also decrease; at the same time, assembly flow channel windows are processed on both sides of the casing barrel, which will cause the rigidity of the overall part to deteriorate. When welding the upper and lower edges, the welding deformation after clamping is difficult to control, which ultimately leads to problems such as springback and fitting clearance in the forming process, resulting in the size of the part and the quality of the weld not meeting the processing requirements.

[0005] Application No. 202410352149.X discloses a method for processing the inner flow channel casing of a gas turbine. This method can enhance the rigidity of the inner flow channel casing to a certain extent, but the processing method only involves the processing method of the casing, and does not involve the combination method of the casing and the flow channel. Moreover, the casing structure of this method is quite different from the casing structure of this application, and this method cannot be used to solve the above-mentioned technical problems. Summary of the Invention

[0006] The purpose of the present invention is to propose a combined welding processing method for an aircraft engine nozzle casing to solve technical problems such as unqualified size and weld quality of the nozzle casing and a large number of welds caused by conventional processing.

[0007] The technical solution adopted in the present invention is:

[0008] A method for welding an aircraft engine nozzle casing assembly is disclosed. The aircraft engine nozzle casing includes a casing barrel, an upper mounting edge and a lower mounting edge welded to both ends of the casing barrel, and a nozzle flow channel welded to the casing barrel fuselage. The nozzle flow channels are distributed on both horizontal sides of the casing barrel, including a left flow channel and a right flow channel. The nozzle flow channels are curved channel structures. The processing method comprises the following steps:

[0009] S1. Performing a parting process on the nozzle flow channel, dividing the nozzle flow channel into a left shell, a right shell, an inner shell 1, an inner shell 2, an outer shell 1, and an outer shell 2;

[0010] S2. Cut the sheet metal according to size and stamp it on the die to obtain the left shell, right shell, inner shell 1, inner shell 2, outer shell 1, outer shell 2 and the casing reel. The parameters of the stamping equipment are set to: blank holding force: 80T~90T, main cylinder force: 100T~110T;

[0011] S3. Using the left and right shells as reference, weld together inner shell 1, inner shell 2, outer shell 1, and outer shell 2, with the misalignment requirement of no more than 0.2mm and the trimming clearance requirement of no more than 0.2mm, to obtain the nozzle flow path. Simultaneously, roll-weld the casing drum stamped in S2.

[0012] S4, cutting the nozzle flow channel obtained by welding in step S3 along the symmetrical middle of the left flow channel and the right flow channel;

[0013] S5. The casing barrel and the upper and lower mounting edges are combined and fixed by a sealing fixture to support the casing barrel; the sealing fixture includes a core shaft, a cover plate and a bottom plate installed at both ends of the core shaft, and a supporting device arranged on the bottom plate; the cover plate is provided with an annular groove, the upper mounting edge is clamped in the annular groove, and the extension of the upper mounting edge is pressed by a pressure plate arranged on the cover plate; the bottom plate is provided with a pressure plate to press the extension of the lower mounting edge; the supporting device includes a connecting rod threadedly connected to the core shaft, one end of the connecting rod is provided with a bolt head, and the other end is connected to a conical wedge block slidably arranged on the core shaft, the conical surface of the conical wedge block contacts one end of a plurality of arc wedge blocks slidably connected to the bottom plate, and the other end of the arc wedge block is in contact with the surface of the casing barrel, and a tool is used to cover the bolt head to adjust the supporting device so that the arc wedge block is close to the inner wall of the casing barrel;

[0014] S6. Fill the sealing fixture with protective gas and then perform welding;

[0015] S7. Cut and process a window for the nozzle flow channel to extend out of the casing barrel after the upper and lower mounting edges are welded;

[0016] S8. Extend the two flow channels symmetrically cut in S4 into the interior of the casing through the window and combine them, and re-weld the symmetrically cut parts to combine the flow channels into one and install them in the casing barrel.

[0017] Furthermore, the left shell and the right shell are symmetrical in appearance, the inner shell 1 and the inner shell 2 are symmetrical in appearance, and the outer shell 1 and the outer shell 2 are symmetrical in appearance.

[0018] Furthermore, in S4, the nozzle flow channel is cut using a wire cutting process.

[0019] Furthermore, the sealing fixture is provided with an air pipe joint on the cover plate or the bottom plate.

[0020] Furthermore, a through slot is provided on the arc-shaped wedge-locking block, a spring is inserted into the through slot, one end of the spring contacts the arc-shaped wedge-locking block, and the other end is connected to a stop pin, which is fixedly connected to the base plate.

[0021] Furthermore, the bottom plate is fixedly connected to a base, and a handle is provided on the base.

[0022] Furthermore, in S6, argon arc welding is used to weld the combined fixed casing barrel and the upper and lower mounting edges.

[0023] Furthermore, in S7, a laser cutting process is used to process a window through which the nozzle flow channel extends.

[0024] Furthermore, after step S8, step S9 is also included: performing post-welding heat treatment on the assembled parts.

[0025] Furthermore, after the heat treatment, the holes of the upper and lower mounting edges are machined.

[0026] Compared with the prior art, the present invention has the following beneficial effects:

[0027] The combined welding processing method of the present invention reduces the four welds of the casing barrel in the original process to three welds, and optimizes the complex casing combined welding problem into a simple welding problem of the upper and lower mounting edges and the casing barrel. Moreover, through the design of the sealing fixture, the dimensional tolerance problem of the casing barrel due to springback and deformation is reduced, and repeated rework and quality problem handling after unqualified parts are avoided, thereby improving the one-time processing and welding pass rate of parts, ensuring the quality of the welds, and effectively improving the overall performance and reliability of the nozzle casing. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 This is a schematic diagram of the structure of the nozzle casing parts of an aero-engine according to the present invention;

[0029] Figure 2 Schematic diagram of the nozzle flow channel structure of the present invention;

[0030] Figure 3 This is a schematic diagram of the casing structure of the present invention;

[0031] Figure 4 This is a schematic diagram of the processing steps of the conventional process route;

[0032] Figure 5 This is a schematic diagram of the processing steps of the process route of the present invention;

[0033] Figure 6 This is a schematic diagram of the nozzle flow channel structure of the present invention;

[0034] Figure 7 This is a schematic structural diagram of the sealing fixture of the present invention;

[0035] Figure 8 This is a schematic diagram of the bottom plate structure of the present invention.

[0036] Among them: 1. Receiver barrel; 2. Upper mounting edge; 3. Lower mounting edge; 4. Nozzle flow channel; 41. Left shell; 42. Right shell; 43. Inner shell one; 44. Inner shell two; 45. Outer shell one; 46. Outer shell two; 5. Left flow channel; 6. Right flow channel; 7. Core shaft; 8. Cover plate; 9. Bottom plate; 10. Pressure plate; 11. Connecting rod; 12. Bolt head; 13. Conical wedge block; 14. Arc wedge block; 15. Wrench; 16. Air pipe joint; 17. Base; 18. Handle; 19. Spring; 20. Stop pin. DETAILED DESCRIPTION

[0037] To clearly illustrate the technical features of this solution, the present invention is described in detail below through specific implementation methods and in conjunction with the accompanying drawings. Many specific details are described in the following description to facilitate a full understanding of the present application. However, the present application can also be implemented in other ways different from those described herein. Therefore, the scope of protection of the present application is not limited by the specific embodiments disclosed below. In addition, in the description of the present application, it should be understood that the terms "center", "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "axial", "radial", "circumferential", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings. They are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation. Therefore, they should not be understood as limiting the present application. In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood to indicate or imply relative importance or implicitly indicate the number of technical features indicated. Therefore, features defined as "first" or "second" can explicitly or implicitly include one or more of such features. In the description of this application, "plurality" means two or more, unless otherwise specified or specifically defined. In this application, unless otherwise specified or defined, terms such as "mounted," "connected," "connected," and "fixed" should be interpreted broadly. For example, they can refer to fixed, removable, or integrated connections; mechanical, electrical, or communication connections; direct or indirect connections through an intermediary; internal communication between two components; or interaction between two components. A person skilled in the art will understand the specific meanings of these terms in this application based on the specific circumstances. In this application, unless otherwise specified or defined, a first feature being "above" or "below" a second feature can mean that the first and second features are in direct contact, or that the first and second features are in indirect contact through an intermediary. In this specification, references to the terms "one embodiment," "some embodiments," "examples," "specific examples," or "some examples" mean that the specific features, structures, materials, or characteristics described in connection with that embodiment or example are included in at least one embodiment or example of this application. In this specification, schematic representations of these terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

[0038] Example 1

[0039] The nozzle casing of the aircraft engine is as follows Figures 1 to 3As shown, it includes a casing barrel 1, an upper mounting edge 2 and a lower mounting edge 3 welded at both ends of the casing barrel 1, and a nozzle flow channel 4 welded to the fuselage of the casing barrel 1. The nozzle flow channel 4 is distributed on both horizontal sides of the casing barrel 1, including a left flow channel 5 and a right flow channel 6. The nozzle flow channel 4 is a curved channel structure. According to the conventional process route, as shown in FIG. Figure 4 As shown, in processes (a) and (b), the nozzle flow channel 4 is first welded, and then the casing barrel 1 is assembled and welded. Since the flow channel is large in size and is a curved surface, it cannot be directly placed in the casing barrel 1. At this time, the casing barrel 1 needs to be divided into two semicircular arcs for welding, and then assembled into a cylindrical structure after welding. In process (c), it is welded with the upper and lower mounting edges. At this time, four welds will be generated on the casing barrel 1. At the same time, assembly flow channel windows are processed on both sides of the casing barrel, which will cause the rigidity of the overall parts to deteriorate. When welding the upper and lower mounting edges, the welding deformation after clamping is difficult to control, which ultimately leads to problems such as springback and fitting clearance in the forming process, resulting in the size of the parts and the quality of the welds not meeting the processing requirements. In response to the above-mentioned process defects, this embodiment proposes a new processing method and process scheme, such as Figure 5 As shown, the process routes are af, where (a)-(b) are welding the upper and lower mounting edges on the casing barrel 1, (c) is processing a window for the nozzle flow channel to extend out of the casing barrel 1, (d) is cutting the nozzle flow channel, and (e)-(f) are combined welding of the nozzle flow channel. This method reduces the original 4 welds to 3 welds, and the complex casing combined welding gap and protection problems are optimized to simple welding of the upper and lower mounting edges and the casing barrel. The welding gap is controlled within 0.1mm, and the welding deformation and residual stress are reduced at the same time. The welding deformation of the entire part is less than 0.5mm, which is of great significance to improving the overall performance and reliability of the nozzle.

[0040] Specifically, a method for welding an aircraft engine nozzle casing assembly includes the following steps:

[0041] S1. The nozzle flow channel 4 is divided into a left shell 41, a right shell 42, an inner shell 1 43, an inner shell 2 44, an outer shell 1 45, and an outer shell 2 46. The nozzle flow channel is divided into a left shell 41, a right shell 42, an inner shell 1 43, an inner shell 2 44, an outer shell 1 45, and an outer shell 2 46 according to the nozzle flow channel shape design. Figure 6 As shown, the left shell 41 and the right shell 42 are symmetrical in appearance, the inner shell 1 42 and the inner shell 2 43 are symmetrical in appearance, and the outer shell 1 44 and the outer shell 2 45 are symmetrical in appearance.

[0042] S2. Cut the sheet metal according to size and stamp it on the mold to obtain the left shell 41, the right shell 42, the inner shell 1 43, the inner shell 2 44, the outer shell 1 45, the outer shell 2 46 and the casing reel 1. The stamping equipment parameters are set to: blank holding force: 80T, main cylinder force: 100T.

[0043] S3. With the left and right shells as the reference, the inner shell 1 43, the inner shell 2 44, the outer shell 1 45, and the outer shell 2 46 are welded together, with the requirement that the misalignment is no more than 0.2 mm and the repair clearance is no more than 0.2 mm, to obtain the nozzle flow channel 4. With the left and right shells as the reference, it can be ensured that the two outlets are on the same axis, and the surface consistency and profile of the entire flow channel are met; at the same time, the casing drum stamped in S2 is rolled and welded.

[0044] S4. Cut the nozzle flow channel 4 obtained by welding in step S3 along the symmetrical middle of the left flow channel 5 and the right flow channel 6. The cutting operation can be performed using a wire cutting process to ensure the consistency of the two separate flow channels.

[0045] S5. The casing barrel 1 and the upper and lower mounting edges are assembled and fixed by a sealing fixture, and the casing barrel 1 is supported.

[0046] The sealing fixture is as follows Figure 7 and Figure 8 As shown, it includes a core shaft 7, a cover plate 8 and a bottom plate 9 installed at both ends of the core shaft 7, and a supporting device arranged on the bottom plate 9; the cover plate 8 is provided with an annular groove, and the upper mounting edge 2 is clamped into the annular groove. The inner wall of the groove will support the upper mounting edge, and the extension of the upper mounting edge 2 is pressed by a pressing plate 10 provided on the cover plate; the bottom plate 9 is provided with a pressing plate 10 to press the extension of the lower mounting edge 3; the supporting device includes a connecting rod 11 threadedly connected to the core shaft 7, A bolt head 12 is provided at one end of the connecting rod 11, and the other end is connected to a conical wedge block 13 slidably provided on the core shaft 7. The conical surface of the conical wedge block 13 contacts one end of a plurality of arc-shaped wedge blocks 14 slidably connected to the base plate 9. The plurality of arc-shaped wedge blocks 14 are combined into a circular ring shape. The other end of the arc-shaped wedge block 14 abuts against the surface of the casing barrel 1. The support device is adjusted by putting a wrench 15 on the bolt head 12 so that the arc-shaped wedge block 14 is close to the inner wall of the casing barrel 1 to form a support. Support; the sealing fixture is provided with a trachea connector 16 on the cover plate 8, and the trachea connector 16 is connected to the external air source; the arc-shaped wedge block 14 is provided with a through groove, and a spring 19 is inserted into the through groove. One end of the spring 19 contacts the arc-shaped wedge block 14, and the other end is connected to the stop pin 20. The stop pin 20 is fixedly connected to the base plate. When the bolt head 12 is loosened, the spring 19 assists the arc-shaped wedge block 14 to move away from the casing barrel 1; the base plate 9 is also fixedly connected to the base 17, and the base 17 is fixedly connected to the base 17. A handle 18 is provided, and the base 17 and the handle 18 are convenient for placing or moving the entire fixture; the casing barrel 1 is combined with the upper and lower mounting edges for automatic argon arc welding, and the steps are simpler. The sealing fixture is used for restraint, and the fitting clearance and misalignment can reach 0.1mm. The fixture is sealed as a whole, and argon gas is filled into the air pipe joint on the end face to protect the entire inner cavity. The fixture is designed with internal support pressure plates in the inner holes of the two mounting edges for restraint, so that the weld quality and welding deformation of the entire part are guaranteed.

[0047] S6. After filling the sealing fixture with protective gas, welding can be carried out using argon arc welding.

[0048] S7. A window for the nozzle flow channel 4 to extend out is cut on the casing barrel 1 with the upper and lower mounting edges welded thereto. Laser cutting can be used for the cutting operation.

[0049] S8. Extend the two flow channels symmetrically cut in S4 into the interior of the casing through the window and combine them, and re-weld the symmetrically cut parts to combine the flow channels into one and install them in the casing barrel.

[0050] The method used in the present invention has been put into actual production and has produced qualified parts. It has been proven feasible in practice and has been applied to the production of other parts.

[0051] Example 2

[0052] This embodiment provides a method for welding an aircraft engine nozzle casing assembly, comprising the following steps:

[0053] S1. The nozzle flow channel 4 is divided into a left shell 41, a right shell 42, an inner shell 1 43, an inner shell 2 44, an outer shell 1 45, and an outer shell 2 46. The nozzle flow channel is divided into a left shell 41, a right shell 42, an inner shell 1 43, an inner shell 2 44, an outer shell 1 45, and an outer shell 2 46 according to the nozzle flow channel shape design. Figure 6 As shown, the left shell 41 and the right shell 42 are symmetrical in appearance, the inner shell 1 42 and the inner shell 2 43 are symmetrical in appearance, and the outer shell 1 44 and the outer shell 2 45 are symmetrical in appearance.

[0054] S2. Cut the sheet metal according to size and stamp it on the mold to obtain the left shell 41, the right shell 42, the inner shell 1 43, the inner shell 2 44, the outer shell 1 45, the outer shell 2 46 and the casing reel 1. The stamping equipment parameters are set to: blank holding force: 90T, main cylinder force: 110T.

[0055] S3. With the left and right shells as the reference, the inner shell 1 43, the inner shell 2 44, the outer shell 1 45, and the outer shell 2 46 are welded together, with the requirement that the misalignment is no more than 0.2 mm and the repair clearance is no more than 0.2 mm, to obtain the nozzle flow channel 4. With the left and right shells as the reference, it can be ensured that the two outlets are on the same axis, and the surface consistency and profile of the entire flow channel are met; at the same time, the casing drum stamped in S2 is rolled and welded.

[0056] S4. Cut the nozzle flow channel 4 obtained by welding in step S3 along the symmetrical middle of the left flow channel 5 and the right flow channel 6. The cutting operation can be performed using a wire cutting process to ensure the consistency of the two separate flow channels.

[0057] S5. The casing barrel 1 and the upper and lower mounting edges are assembled and fixed by a sealing fixture, and the casing barrel 1 is supported.

[0058] The sealing fixture is as follows Figure 7 and Figure 8 As shown, it includes a core shaft 7, a cover plate 8 and a bottom plate 9 installed at both ends of the core shaft 7, and a supporting device arranged on the bottom plate 9; the cover plate 8 is provided with an annular groove, and the upper mounting edge 2 is clamped into the annular groove. The inner wall of the groove will support the upper mounting edge, and the extension of the upper mounting edge 2 is pressed by a pressing plate 10 provided on the cover plate; the bottom plate 9 is provided with a pressing plate 10 to press the extension of the lower mounting edge 3; the supporting device includes a connecting rod 11 threadedly connected to the core shaft 7, A bolt head 12 is provided at one end of the connecting rod 11, and the other end is connected to a conical wedge block 13 slidably provided on the core shaft 7. The conical surface of the conical wedge block 13 contacts one end of a plurality of arc-shaped wedge blocks 14 slidably connected to the base plate 9. The plurality of arc-shaped wedge blocks 14 are combined into a circular ring shape. The other end of the arc-shaped wedge block 14 abuts against the surface of the casing barrel 1. The support device is adjusted by putting a wrench 15 on the bolt head 12 so that the arc-shaped wedge block 14 is close to the inner wall of the casing barrel 1 to form a support. Support; the sealing fixture is provided with a trachea connector 16 on the cover plate 8, and the trachea connector 16 is connected to the external air source; the arc-shaped wedge block 14 is provided with a through groove, and a spring 19 is inserted into the through groove. One end of the spring 19 contacts the arc-shaped wedge block 14, and the other end is connected to the stop pin 20. The stop pin 20 is fixedly connected to the base plate. When the bolt head 12 is loosened, the spring 19 assists the arc-shaped wedge block 14 to move away from the casing barrel 1; the base plate 9 is also fixedly connected to the base 17, and the base 17 is fixedly connected to the base 17. A handle 18 is provided, and the base 17 and the handle 18 are convenient for placing or moving the entire fixture; the casing barrel 1 is combined with the upper and lower mounting edges for automatic argon arc welding, and the steps are simpler. The sealing fixture is used for restraint, and the fitting clearance and misalignment can reach 0.1mm. The fixture is sealed as a whole, and argon gas is filled into the air pipe joint on the end face to protect the entire inner cavity. The fixture is designed with internal support pressure plates in the inner holes of the two mounting edges for restraint, so that the weld quality and welding deformation of the entire part are guaranteed.

[0059] S6. After filling the sealing fixture with protective gas, welding can be carried out using argon arc welding.

[0060] S7. A window for the nozzle flow channel 4 to extend out is cut on the casing barrel 1 with the upper and lower mounting edges welded thereto. Laser cutting can be used for the cutting operation.

[0061] S8. Extend the two flow channels symmetrically cut in S4 into the interior of the casing through the window and combine them, and re-weld the symmetrically cut parts to combine the flow channels into one and install them in the casing barrel.

[0062] S9: Perform post-weld heat treatment on the assembled parts.

[0063] The method used in the present invention has been put into actual production and has produced qualified parts. It has been proven feasible in practice and has been applied to the production of other parts.

[0064] Example 3

[0065] This embodiment provides a method for welding and processing the nozzle casing of an aircraft engine. Different from the second embodiment, this embodiment also performs hole processing operations on the upper and lower mounting edges of the combined parts that have been heat treated after S9 welding.

[0066] Obviously, the above embodiments of the present invention are merely examples for the purpose of clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention. Those skilled in the art will appreciate that other variations or modifications can be made based on the above description. It is not necessary and impossible to enumerate all embodiments here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention shall be included within the scope of protection of the claims of the present invention.

Claims

1. A method for welding an aircraft engine nozzle casing assembly, wherein the aircraft engine nozzle casing comprises a casing barrel, an upper mounting edge and a lower mounting edge welded to both ends of the casing barrel, and a nozzle flow channel welded to the casing barrel fuselage, wherein the nozzle flow channel is distributed on both horizontal sides of the casing barrel, including a left flow channel and a right flow channel, and has a curved channel structure, characterized in that: The processing method comprises the following steps: S1. Performing a parting process on the nozzle flow channel, dividing the nozzle flow channel into a left shell, a right shell, an inner shell 1, an inner shell 2, an outer shell 1, and an outer shell 2; S2. Cut the sheet metal according to size and stamp it on the die to obtain the left shell, right shell, inner shell 1, inner shell 2, outer shell 1, outer shell 2 and the casing reel. The parameters of the stamping equipment are set to: blank holding force: 80T~90T, main cylinder force: 100T~110T; S3. Using the left and right shells as reference, weld together inner shell 1, inner shell 2, outer shell 1, and outer shell 2, with the misalignment requirement of no more than 0.2mm and the trimming clearance requirement of no more than 0.2mm, to obtain the nozzle flow path. Simultaneously, roll-weld the casing drum stamped in S2. S4, cutting the nozzle flow channel obtained by welding in step S3 along the symmetrical middle of the left flow channel and the right flow channel; S5. The casing barrel and the upper and lower mounting edges are combined and fixed by a sealing fixture to support the casing barrel; the sealing fixture includes a core shaft, a cover plate and a bottom plate installed at both ends of the core shaft, and a supporting device arranged on the bottom plate; the cover plate is provided with an annular groove, the upper mounting edge is clamped in the annular groove, and the extension of the upper mounting edge is pressed by a pressure plate arranged on the cover plate; the bottom plate is provided with a pressure plate to press the extension of the lower mounting edge; the supporting device includes a connecting rod threadedly connected to the core shaft, one end of the connecting rod is provided with a bolt head, and the other end is connected to a conical wedge block slidably arranged on the core shaft, the conical surface of the conical wedge block contacts one end of a plurality of arc wedge blocks slidably connected to the bottom plate, and the other end of the arc wedge block is in contact with the surface of the casing barrel, and a tool is used to cover the bolt head to adjust the supporting device so that the arc wedge block is close to the inner wall of the casing barrel; S6. Fill the sealing fixture with protective gas and then perform welding; S7. Cut and process a window for the nozzle flow channel to extend out of the casing barrel after the upper and lower mounting edges are welded; S8. Extend the two flow channels symmetrically cut in S4 into the interior of the casing through the window and combine them, and re-weld the symmetrically cut parts to combine the flow channels into one and install them in the casing barrel.

2. The method for welding an aircraft engine nozzle casing assembly according to claim 1, characterized in that: The left shell and the right shell are symmetrical in appearance, the inner shell 1 and the inner shell 2 are symmetrical in appearance, and the outer shell 1 and the outer shell 2 are symmetrical in appearance.

3. The method for welding an aircraft engine nozzle casing assembly according to claim 1, characterized in that: In S4, the nozzle flow channel is cut using wire cutting technology.

4. The method for welding an aircraft engine nozzle casing assembly according to claim 1, characterized in that: The sealing fixture is provided with an air pipe joint on the cover plate or the bottom plate.

5. The method for welding an aircraft engine nozzle casing assembly according to claim 1, characterized in that: The arc-shaped wedge-tightening block is provided with a through slot, in which a spring is inserted. One end of the spring contacts the arc-shaped wedge-tightening block, and the other end is connected to a stop pin, which is fixedly connected to the base plate.

6. The method for welding an aircraft engine nozzle casing assembly according to claim 1, characterized in that: The bottom plate is also fixedly connected with a base, and the base is provided with a handle.

7. The method for welding an aircraft engine nozzle casing assembly according to claim 1, characterized in that: In S6, argon arc welding is used to weld the combined fixed casing barrel and the upper and lower mounting edges.

8. The method for welding an aircraft engine nozzle casing assembly according to claim 1, characterized in that: In the S7, a laser cutting process is used to machine the window through which the nozzle flow channel extends.

9. The method for welding an aircraft engine nozzle casing assembly according to claim 1, characterized in that: After step S8, the method further includes step S9: performing post-welding heat treatment on the assembled parts.

10. The method for welding an aircraft engine nozzle casing assembly according to claim 9, characterized in that: After heat treatment, the holes for the upper and lower mounting edges are machined.

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