Forming method of curled-arc wing

Abstract

The invention discloses a forming method of a curled-arc wing. The forming method comprises the steps that a primary curled-arc wing product is manufactured through a selective laser melting forming technology; according to the selective laser melting forming technology, a rolled-arc wing primary product is formed in the width direction of a rolled-arc wing, and an insertion shaft connector of the rolled-arc wing and a wing face of the rolled-arc wing are sequentially formed from bottom to top; the selective laser melting forming technology is further set to design a solid support on the bottom face of the airfoil and design a grid support on the lower portion of the outer arc face of the airfoil. And carrying out post-treatment on the primary curled-arc wing product to obtain a finished curled-arc wing product. According to the method, the insertion shaft connector and the airfoil are sequentially formed from bottom to top, the machining allowance and supporting requirements of the insertion shaft connector are lowered, the machining allowance of the insertion shaft connector can be designed to be small, the insertion shaft connector does not need to be provided with a support, and solid supporting and grid supporting are only adopted on the bottom face of the airfoil and the lower portion of the outer arc face respectively; no-allowance forming of the airfoil is achieved, and the workload of the follow-up support removal procedure and the machining treatment procedure is effectively reduced.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft component forming, and in particular, relates to a method for forming a curled wing. Background Art

[0002] The curled wing is a key part of the rotating tail section. The curled wing includes a variable cross-section shaped wing surface and two plug-in shaft interfaces for installation. The wing surface is a solid structure with variable wall thickness and is arc-shaped. The curled wing is a variable cross-section and severely asymmetric shaped structural part. Due to the high requirements for part size accuracy, the traditional casting + machining manufacturing process is complicated and the manufacturing cycle is long. The processing cost remains high due to material utilization and processing cycle.

[0003] With the rapid development of technology, the selective laser melting (SLM) technology has been introduced into the relevant technology, which can realize high-precision and high-efficiency manufacturing of complex structures, and realize high-precision and short-cycle manufacturing of curved wing variable-section special-shaped components, as shown in the Chinese invention patent with patent publication number CN118682147A.

[0004] However, practice has shown that when the selective laser melting forming technology is used to process the curled wing, it is difficult to control the deformation of the curled wing during the forming and post-processing process, and the forming accuracy is poor. Multiple process and structural design iterations are required, and a large amount of allowance and solid support need to be added to ensure the forming accuracy of the curled wing. The production efficiency of the curled wing is low. Summary of the invention

[0005] The present application aims to at least to some extent solve the technical problem of low production efficiency of curled wings when using the selective laser melting forming technology to process curled wings. To this end, the present application provides a curled wing forming method.

[0006] The present application provides a method for forming a curled wing, comprising:

[0007] A preliminary curled wing product is obtained by using a selective laser melting forming technology; the selective laser melting forming technology is configured to form the preliminary curled wing product along the width direction of the curled wing, and to sequentially form the plug-in shaft interface of the curled wing and the wing surface of the curled wing from bottom to top; the selective laser melting forming technology is also configured to design a solid support on the bottom surface of the wing surface, and to design a grid support on the lower part of the outer arc surface of the wing surface;

[0008] The initial curled wing product is post-processed to obtain a finished curled wing product.

[0009] In some embodiments, the selective laser melting forming technology is further configured to reserve machining allowances on both end faces of the shaft plug interface, the inner wall of the plug hole of the shaft plug interface, and the bottom surface of the wing surface.

[0010] In some embodiments, a machining allowance of 0.5 mm to 2 mm is reserved for each of the two end faces of the shaft plug interface; a machining allowance of 3 mm to 5 mm is reserved for the inner wall of the plug hole of the shaft plug interface; and a machining allowance of 1 mm to 3 mm is reserved for the bottom surface of the wing surface.

[0011] In some embodiments, the process parameters of the selective laser melting forming technology are: powder layer thickness is 0.04mm, solid scanning spacing is 0.08mm~0.14mm, solid scanning speed is 860mm / s~1160mm / s, and solid scanning laser power is 250W~400W; inner contour scanning speed is 200mm / s~400mm / s, and inner contour scanning laser power is 140W~165W; outer contour scanning speed is 700mm / s~900mm / s, and outer contour scanning laser power is 70W~90W.

[0012] In some embodiments, the powder used in the selective laser melting forming technology is 17-4PH stainless steel powder, and the particle size of the 17-4PH stainless steel powder is 15 μm to 53 μm.

[0013] In some embodiments, the post-processing includes:

[0014] Performing a solid solution strengthening heat treatment on the initial curled wing product;

[0015] Performing shape correction treatment on the initial curled wing product after the solid solution strengthening heat treatment;

[0016] The initial curled wing product after the shape correction treatment is subjected to an aging strengthening heat treatment to obtain the finished curled wing product.

[0017] In some embodiments, the temperature of the solid solution strengthening heat treatment is 1000° C. to 1100° C., and the holding time is 1 h to 2 h.

[0018] In some embodiments, the temperature of the aging strengthening heat treatment is 480-600° C., and the holding time is 3 h to 5 h.

[0019] In some embodiments, the shaping process includes:

[0020] Prepare the die and dowel pins;

[0021] Placing the outer arc surface of the wing surface on the concave mold, and inserting the positioning pin into the sockets of the two shaft insertion interfaces at the same time;

[0022] The inner arc surface of the wing surface is struck by a striking tool so that the outer arc surface fits with the surface of the concave mold.

[0023] In some embodiments, the post-processing further includes a machining process after the shape correction process.

[0024] The present invention has at least the following beneficial effects:

[0025] The present application forms the plug-in shaft interface and the wing surface sequentially from bottom to top, reducing the requirements for machining allowance and support at the plug-in shaft interface, so that the machining allowance of the plug-in shaft interface can be designed to be smaller and no support is required on the plug-in shaft interface. Only solid support and grid support are used on the bottom surface and the lower part of the outer arc surface of the wing surface, respectively. The wing surface realizes zero-residue forming, effectively reducing the workload of subsequent support removal processes and subsequent machining processes, thereby improving the production efficiency of the curled wing and reducing production costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following is a brief introduction to the drawings required for use in the description of the embodiments. Obviously, the drawings described below are some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0027] Figure 1 A flow chart of a method for forming a curled wing in one or more embodiments of the present application is shown.

[0028] Figure 2 A front view of a curled wing in one or more embodiments of the present application is shown.

[0029] Figure 3 A side view of a curled wing in one or more embodiments of the present application is shown.

[0030] Figure 4 Shows Figure 2 Left view of the mid-curved wing with solid support.

[0031] Figure 5 Shows Figure 2 Right view of the grid support set up on the mid-curved wing.

[0032] Figure 6 A schematic diagram of a concave mold in one or more embodiments of the present application is shown.

[0033] Figure 7 A schematic diagram of a positioning pin in one or more embodiments of the present application is shown.

[0034] Figure 8 The microstructure diagram of the curled wing processed by the forming method of the present application is shown.

[0035] Figure numerals: 100 - curved wing, 110 - wing surface, 110a - bottom surface, 110b - outer arc surface, 110c - inner arc surface, 120 - shaft interface, 120a - end surface, 120b - inner wall of the socket. DETAILED DESCRIPTION

[0036] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0037] It should be noted that all directional indications in the embodiments of the present invention are only used to explain the relative position relationship, movement status, etc. between various components in a certain specific posture. If the specific posture changes, the directional indication will also change accordingly.

[0038] In the present invention, unless otherwise clearly specified and limited, the terms "connection", "fixation", etc. should be understood in a broad sense. For example, "fixation" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0039] In addition, in the present invention, descriptions such as "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In addition, the technical solutions between the various embodiments can be combined with each other, but they must be based on the ability of ordinary technicians in the field to implement them. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such a combination of technical solutions does not exist and is not within the scope of protection required by the present invention.

[0040] When the selective laser melting forming technology is used to process the curled wing, it is difficult to control the deformation of the curled wing during the forming and post-processing process, and the forming accuracy is poor. Multiple process and structural design iterations are required, and a large amount of allowance and solid support need to be added to ensure the forming accuracy of the curled wing. The addition of more allowance and support will bring about a large number of allowance and support removal processes, which will damage the efficient near-net forming advantage of the selective laser melting forming technology and result in low production efficiency of the curled wing.

[0041] In the related art, when the selective laser melting forming technology is used to process the curled wing, there is a technical problem of low production efficiency of the curled wing. The embodiment of the present application provides a method for forming the curled wing, which can at least solve the technical problem of low production efficiency of the curled wing when the selective laser melting forming technology is used to process the curled wing to a certain extent.

[0042] The present application is described below with reference to the accompanying drawings and specific embodiments:

[0043] like Figure 2 and Figure 3 As shown, the curled wing 100 includes an airfoil 110 and two shaft insertion interfaces 120, and the shaft insertion interfaces 120 are fixedly connected to the airfoil 110. The airfoil 110 is a variable cross-section special-shaped structure, and the shaft insertion interfaces 120 are used to connect with other components of the aircraft.

[0044] like Figure 1 As shown, the forming method of the curling wing 100 includes:

[0045] S100, a preliminary product of the curled wing is manufactured by using the selective laser melting forming technology; the selective laser melting forming technology is configured to form the preliminary product of the curled wing along the width direction of the curled wing 100, and to form the shaft plug interface 120 of the curled wing 100 and the wing surface 110 of the curled wing 100 in sequence from bottom to top; the selective laser melting forming technology is also configured to design a solid support on the bottom surface 110a of the wing surface 110, and to design a grid support on the lower part of the outer arc surface 110b of the wing surface 110.

[0046] S200, post-processing the initial curled wing product to obtain the finished curled wing product.

[0047] Figure 2 The forming direction and the front view after forming of the curled wing 100 are shown. The curled wing 100 is gradually formed from bottom to top along the width direction, first forming the plug-in shaft interface 120, and then forming the wing surface 110. The wing surface 110 of the initial curled wing made by the selective laser melting forming technology is arranged vertically as a whole, with the plug-in shaft interface 120 located at the bottom and the wing surface 110 located at the top. Forming the plug-in shaft interface 120 and the wing surface 110 in sequence from bottom to top helps to reduce the deformation of the plug-in shaft interface 120 during the processing process, and reduces the requirements for machining allowance and support at the plug-in shaft interface 120. Such a design can improve the forming accuracy of the curled wing 100 to ensure the performance after forming, and help to achieve the zero-residue forming of the wing surface 110. During the processing, the bottom surface 110a of the airfoil 110 is a 0° suspended surface, that is, parallel to the horizontal plane. A solid support is designed on the bottom surface 110a of the airfoil 110 to ensure the dimensional stability of the airfoil 110 during the forming process and the dimensional accuracy of the curled airfoil 100 after forming. Figure 4There is a low-angle forming surface at the lower part of the outer arc surface 110b of the airfoil 110. Adding an easily removable grid support (non-solid block support) at the lower part of the outer arc surface 110b of the airfoil 110 can prevent the airfoil 110 of the curled airfoil 100 from warping during forming and ensure the forming accuracy of the airfoil 110. Figure 5 shown.

[0048] The present application forms the plug-in shaft interface 120 and the wing surface 110 in sequence from bottom to top, reducing the requirements for machining allowance and support at the plug-in shaft interface 120, so that the machining allowance of the plug-in shaft interface 120 can be designed to be smaller and no support is required on the plug-in shaft interface 120. Only the bottom surface 110a of the wing surface 110 and the lower part of the outer arc surface 110b are respectively used for solid support and grid support. The wing surface 110 realizes zero-residue forming, effectively reducing the workload of the subsequent support removal process and the workload of the subsequent machining process, thereby improving the production efficiency of the curled arc wing 100 and reducing the production cost.

[0049] See also Figure 3 As shown, in some embodiments, the selective laser melting forming technology is also configured to reserve machining allowances on both end faces 120a of the shaft plug interface 120, the inner wall 120b of the plug hole of the shaft plug interface 120, and the bottom surface 110a of the wing surface 110. By reserving allowances only on the end face 120a of the shaft plug interface 120, the inner wall 120b of the plug hole, and the bottom surface 110a of the wing surface 110, the addition of overall allowances is avoided, material waste and subsequent processing volume are reduced, material utilization and processing efficiency are improved, and the reserved machining allowances facilitate the processing volume during subsequent correction operations, thereby improving the convenience of subsequent mechanical finishing.

[0050] In some embodiments, a machining allowance of 0.5 mm to 2 mm is reserved on the two end surfaces 120a of the shaft insertion interface 120; a machining allowance of 3 mm to 5 mm is reserved on the inner wall 120b of the insertion hole of the shaft insertion interface 120; and a machining allowance of 1 mm to 3 mm is reserved on the bottom surface 110a of the wing surface 110. Setting the machining allowance within the above range helps to reduce the machining allowance, reduce the workload of the subsequent allowance removal process, improve the processing efficiency, and ensure the advantage of efficient near-net forming of the selective laser melting forming technology.

[0051] In order to ensure the forming accuracy of the arc wing 100, in some embodiments, the additive manufacturing dedicated simulation software SIMUFACT ADDITIVE is used to simulate and calculate the deformation of the selected laser melting of the arc wing 100, and the anti-deformation module of SIMUFACT ADDITIVE is used to perform multiple optimization iterative deformation compensation, and finally the selective laser melting deformation of the arc wing 100 is optimized from the previous maximum of 6mm to the maximum of 0.3mm.

[0052] Selective laser melting uses single-layer scanning to pre-sinter the first layer of powder, and then sinter and solidify layer by layer to form a compact metal structure. In some embodiments, the process parameters of the selective laser melting forming technology are: the powder layer thickness is 0.04mm, the solid scanning spacing is 0.08mm~0.14mm, the solid scanning speed is 860mm / s~1160mm / s, and the solid scanning laser power is 250W~400W; the inner contour scanning speed is 200mm / s~400mm / s, and the inner contour scanning laser power is 140W~165W; the outer contour scanning speed is 700mm / s~900mm / s, and the outer contour scanning laser power is 70W~90W. The above numerical range enables the arc wing 100 to achieve better surface quality while meeting the performance and density requirements.

[0053] In some embodiments, the powder used in the selective laser melting forming technology is 17-4PH stainless steel powder, and the powder particle size is 15μm to 53μm, which helps to ensure the performance of the finished curved wing.

[0054] In some embodiments, the substrate formed by selective laser melting is a 304 stainless steel substrate having good wettability with the material of the curling wing 100 and a linear expansion coefficient similar to that of the curling wing 100 , with a thickness of t=45 mm.

[0055] Post-processing can include:

[0056] S210, removing the solid support and mesh support on the initial curved wing product to facilitate subsequent steps.

[0057] S220, solid solution strengthening heat treatment is performed on the initial rolled wing product.

[0058] Solid solution strengthening heat treatment is to heat the alloy to a certain temperature so that the second phase in the alloy is fully dissolved into the matrix to form a uniform solid solution, and then fix this state by rapid cooling. Solid solution strengthening heat treatment of the initial curling wing can improve the uniformity of the curling wing 100, reduce local stress concentration, and enhance the overall performance of the curling wing 100.

[0059] If the holding temperature of the solution strengthening heat treatment is too high, it may lead to grain growth, reduced supersaturation of the solid solution, and deformation and cracking of the material, while if it is too low, the solid solution may not be complete, the precipitation phase may increase, and the treatment efficiency may be low. Too short a holding time may lead to uneven distribution of solute elements, while too long a holding time may cause adverse effects such as grain growth. In some embodiments, the temperature of the solution strengthening heat treatment is 1000°C to 1100°C, and the holding time is 1h to 2h. Carrying out the solution strengthening heat treatment according to this parameter can ensure that the solute elements are fully dissolved and form a uniform solid solution, while avoiding excessive grain growth, which can improve the strength and hardness of the curling wing 100, so that the curling wing 100 obtains excellent mechanical properties.

[0060] S230, the initial curled wing product after the solid solution strengthening heat treatment is subjected to shape correction treatment.

[0061] The treatment temperature of the solid solution strengthening heat treatment is relatively high, and oil cooling treatment will be performed after the heat treatment. Since the structure of the airfoil 110 is uneven, the airfoil 110 is prone to deformation under the action of thermal stress after the solid solution strengthening heat treatment. Therefore, a shape correction treatment is performed after the solid solution strengthening heat treatment to ensure that the dimensional accuracy of the airfoil 110 is within the required range and the net size of the airfoil 110 is formed. There is no need to perform mechanical processing on the airfoil 110, thereby improving the processing efficiency.

[0062] Correction processing includes:

[0063] S231, prepare the die and locating pins. Figure 6 As shown, a groove corresponding to the shape of the outer arc surface 110 b of the airfoil 110 is opened in the middle of the die, which is used for aligning and checking the outer arc surface 110 b of the airfoil 110 .

[0064] S232, placing the outer arc surface 110b of the wing surface 110 on the concave mold, and inserting the positioning pin into the insertion holes of the two shaft insertion interfaces 120 at the same time. The positioning pin is inserted into the two insertion holes at the same time, and the positioning pin limits the relative deformation between the two shaft insertion interfaces 120.

[0065] S233, using a striking tool to strike the inner arc surface 110c of the wing surface 110 so that the outer arc surface 110b fits with the surface of the concave mold. The inner arc surface 110c of the wing surface 110 can be struck with a hammer so that the outer arc surface 110b fits with the surface of the concave mold, ensuring that the accuracy of the wing surface 110 of the curled wing 100 is within 0.5 mm, achieving the net size forming of the wing surface 110, and no longer performing mechanical processing of the profile.

[0066] S240, the initial curved wing after the shape correction is subjected to mechanical processing. The inner wall 120b of the insertion hole of the shaft insertion interface 120, the end face 120a of the shaft insertion interface 120, the bottom end of the shaft insertion interface 120 and the bottom face 110a of the wing surface 110 are finely processed by mechanical processing, so that the inner diameter of the insertion hole, the end face 120a of the shaft insertion interface 120, the bottom end of the shaft insertion interface 120 and the bottom face 110a of the wing surface 110 meet the installation requirements.

[0067] S250, the initial curled wing product after the shape correction treatment is subjected to aging heat treatment to obtain the finished curled wing product. The aging heat treatment is to keep the alloy that has undergone solid solution treatment at a relatively low temperature for a period of time, so that the supersaturated solute atoms in the solid solution are precipitated to form fine second phase particles (such as precipitation phase), which can improve the strength and hardness of the curled wing 100. After the initial curled wing product is subjected to aging heat treatment, a finished curled wing product with dimensions that meet the requirements and stable and reliable shapes and performance is obtained.

[0068] In some embodiments, the temperature of the aging heat treatment is 480-600°C, and the holding time is 3h-5h. Performing the aging heat treatment according to these parameters helps to improve the strength, hardness, dimensional stability and toughness of the curling wing 100, while effectively reducing the residual stress, thereby optimizing the comprehensive performance of the curling wing 100. The temperature of the aging heat treatment can be 480°C, 500°C, 550°C, 600°C, etc.

[0069] It should be noted that the selective laser melting forming technology can be implemented by corresponding equipment, such as a metal powder printer. The structures of these devices are known to those skilled in the art. The setting of the processing allowance, the setting of the laser process parameters, the support type, the support position and the processing direction can all be achieved through the control equipment and will not be elaborated in this application.

[0070] In some embodiments, the scraper used in the selective laser melting forming technology is a flexible scraper, and the material of the flexible scraper is wear-resistant plastic.

[0071] The wing surface 110 of the 17-4PH stainless steel curved wing 100 processed according to the above steps and parameters is controlled within 0.5 mm in size accuracy, and no defects are found in the parts after fluorescence and X-ray inspection. In addition, Figure 8As shown, through the high-magnification metallographic structure analysis of the SLM forming metallographic structure, no defects such as cracks, unfused and pores were found. The outer arc surface 110b and the inner arc surface 110c of the wing surface 110 of the 17-4PH stainless steel curled wing 100 formed by the present invention realize net size forming, and only the plug-in shaft interface 120 and the bottom surface 110a of the wing surface 110 use less margin and support, which significantly reduces the amount of machining after forming, improves the production efficiency of parts, and reduces costs. The method of the present invention is simple and effective, the process is stable and reliable, the part performance is excellent, and it meets the forging standard.

[0072] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present application. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine different embodiments or examples described in this specification.

[0073] In addition, the technical solutions between the various embodiments can be combined with each other, but they must be based on the fact that they can be implemented by ordinary technicians in this field. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such combination of technical solutions does not exist and is not within the scope of protection required by this application.

[0074] Although the embodiments of the present application have been shown and described, those skilled in the art will appreciate that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present application, and that the scope of the present application is defined by the claims and their equivalents.

Claims

1. A method for forming a curled wing, characterized in that: include: The initial product of the curled wing is produced by using the selective laser melting forming technology; The selective laser melting forming technology is configured to form the initial product of the curled wing along the width direction of the curled wing (100), and to sequentially form the shaft insertion interface (120) of the curled wing (100) and the wing surface (110) of the curled wing (100) from bottom to top; the selective laser melting forming technology is also configured to design a solid support on the bottom surface (110a) of the wing surface (110), and to design a grid support on the lower part of the outer arc surface (110b) of the wing surface (110); The initial curled wing product is post-processed to obtain a finished curled wing product.

2. The method for forming a curled wing according to claim 1, characterized in that: The selective laser melting forming technology is also configured to reserve machining allowances on both end faces (120a) of the shaft plug interface (120), the inner wall (120b) of the plug hole of the shaft plug interface (120), and the bottom surface (110a) of the wing surface (110).

3. The method for forming a curled wing according to claim 2, characterized in that: A machining allowance of 0.5 mm to 2 mm is reserved on each of the two end faces (120a) of the shaft insertion interface (120); a machining allowance of 3 mm to 5 mm is reserved on the inner wall (120b) of the insertion hole of the shaft insertion interface (120); and a machining allowance of 1 mm to 3 mm is reserved on the bottom surface (110a) of the wing surface (110).

4. The method for forming a curled wing according to any one of claims 1 to 3, characterized in that: The process parameters of the selective laser melting forming technology are: powder layer thickness is 0.04mm, solid scanning spacing is 0.08mm~0.14mm, solid scanning speed is 860mm / s~1160mm / s, and solid scanning laser power is 250W~400W; inner contour scanning speed is 200mm / s~400mm / s, and inner contour scanning laser power is 140W~165W; outer contour scanning speed is 700mm / s~900mm / s, and outer contour scanning laser power is 70W~90W.

5. The method for forming a curled wing according to any one of claims 1 to 3, characterized in that: The powder used in the selective laser melting forming technology is 17-4PH stainless steel powder, and the particle size of the 17-4PH stainless steel powder is 15 μm to 53 μm.

6. The method for forming a curled wing according to any one of claims 1 to 3, characterized in that: The post-processing includes: Performing a solid solution strengthening heat treatment on the initial curled wing product; Performing shape correction treatment on the initial curled wing product after the solid solution strengthening heat treatment; The initial curled wing product after the shape correction treatment is subjected to an aging strengthening heat treatment to obtain the finished curled wing product.

7. The method for forming a curled wing according to claim 6, characterized in that: The temperature of the solid solution strengthening heat treatment is 1000° C. to 1100° C., and the holding time is 1 h to 2 h.

8. The method for forming a curled wing according to claim 6, characterized in that: The temperature of the aging strengthening heat treatment is 480-600° C., and the insulation time is 3h-5h.

9. The method for forming a curled wing according to claim 6, characterized in that: The shape correction process comprises: Prepare the die and dowel pins; Placing the outer arc surface (110b) of the wing surface (110) on the concave mold, and inserting the positioning pin into the insertion holes of the two shaft insertion interfaces (120) at the same time; The inner arc surface (110c) of the wing surface (110) is struck by a striking tool so that the outer arc surface (110b) fits with the surface of the concave mold.

10. The method for forming a curled wing according to claim 6, characterized in that: The post-processing also includes a machining process after the shape correction process.

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