Aircraft engine lip integral forming device and method

Abstract

The invention belongs to the technical field of engine lip manufacturing, and specifically relates to an aircraft engine lip integral forming device and method. The device comprises a rotary worktable, a clamping mechanism arranged on the rotary worktable, and a forming mechanism. The clamping mechanism comprises a replaceable clamping component one and a clamping component two. The clamping component one is used to clamp the edge of a plate blank. The clamping component two comprises a mold, and a detachable pressing ring two and a pressing ring three which are respectively arranged on the inner and outer sides of the mold. The pressing ring two and the pressing ring three are used to respectively clamp the lip tip and fix it to the mold. The forming mechanism comprises a plurality of tool heads whose positions can be adjusted in a three-dimensional coordinate system. By means of the aircraft engine lip integral forming device and method, a lip composed of a ring shape and a plurality of arc segments with different radii can be integrally formed and manufactured, thereby improving the accuracy of the lip contour, the uniformity of the wall thickness, the mechanical strength and the assembly accuracy. At the same time, the processing technology is simplified and the production efficiency is improved.

Description

Technical Field

[0001] The invention belongs to the technical field of engine lip manufacturing, and in particular relates to an aircraft engine lip integral forming device and method. Background Art

[0002] During the flight, the lip of the aircraft engine is affected by high-speed and high-pressure airflow, and the engine lip is in an ultra-high-intensity complex load working environment for a long time. Therefore, high requirements are placed on the assembly accuracy, wall thickness uniformity and performance of the lip parts. Due to the large diameter of the aircraft engine lip, the traditional lip forming process is achieved through the split-flap welding process. However, the traditional manufacturing process not only leads to poor film adhesion and thickness distribution of parts, but also low assembly accuracy. Moreover, the split-flap welding method is prone to microscopic defects in the weld, which is not conducive to the improvement of overall performance. Higher wall thickness uniformity can effectively improve the service life of the lip and significantly improve the assembly accuracy. Reducing the welding process of the lip or realizing the overall forming of the lip is conducive to the improvement of overall performance and lightweight development, which is very important for the safety and economy of the aircraft.

[0003] At present, most engine lip forming methods require large-scale special molds for large-tonnage stamping. When thin plate parts undergo large plastic deformation, they are very sensitive to thickness deviations, and the deformation is uneven during forming. It is inevitable that the wall thickness of the lip is uneven, and the contour accuracy of the lip is difficult to guarantee and difficult to form. The reason for the uneven wall thickness is that the stamping of the engine lip is relatively high. While forming a large diameter, it is also necessary to ensure that the lip needs to have a certain height. If conventional stamping is used, it will inevitably exceed the stamping forming limit and be forced to stamp multiple times. Finally, the processing cost will rise sharply, and the problem of uneven wall thickness has not been completely solved. Such problems will still affect the service life of the engine lip, flight quality and assembly accuracy. Moreover, when the material reaches the plastic limit during the forming process, wrinkles and even material ruptures are prone to occur.

[0004] At present, there are also some methods of using spin forming to manufacture aircraft lips. It is necessary to press and fix the edge of the slab, and the annular mold is displaced below the slab. During processing, the slab and the annular mold rotate synchronously, and the slab is gradually fitted to the mold through the tool head located above the slab to form the lip of the aircraft engine. Although there are certain improvements in the uniformity of the lip wall thickness, wrinkles and material rupture. However, during the forming process, the slab needs to be spun from both sides of the mold, and the material will undergo plastic deformation. The lip tip (located at the top of the mold during processing) will produce unpredictable deformation due to the inconsistent plastic deformation of the material on both sides of the mold, so the lip tip needs to be reshaped, otherwise it will affect the contour accuracy of the lip. In addition, the current spin forming equipment is usually only suitable for the manufacture of annular lips, and it is difficult to process and form lips with varying curvatures as a whole. Summary of the invention

[0005] The invention provides an aircraft engine lip integral forming device and method, which solves the problem that the lip tip is easily deformed when the lip is manufactured by the existing spinning forming equipment.

[0006] Based on the above purpose, the present invention provides an aircraft engine lip integral forming device, comprising:

[0007] Rotating table;

[0008] A clamping mechanism is arranged on the rotating workbench, the clamping mechanism includes a replaceable clamping assembly 1 and a clamping assembly 2, the clamping assembly 1 is used to clamp the edge of the slab, the clamping assembly 2 includes a mold, and a detachable pressing ring 2 and a pressing ring 3 which are respectively arranged on the inner and outer sides of the mold, the pressing ring 2 and the pressing ring 3 are used to respectively clamp the lip tip and fix it to the mold; and

[0009] The forming mechanism comprises a plurality of tool heads whose positions can be adjusted in a three-dimensional coordinate system.

[0010] Optionally, the clamping assembly 1 includes a plurality of brackets 1 and a pressure ring 1, and the pressure ring 1 is rigidly arranged on the bracket 1.

[0011] Optionally, the first bracket is a ring bracket or an arc bracket.

[0012] Optionally, when the bracket 1 is an arc-shaped bracket, two brackets 1 are symmetrically arranged on both sides of the rotation axis of the rotating workbench.

[0013] Optionally, the clamping mechanism further includes a plurality of claws, and the claws are used to clamp and fix the clamping component one and the clamping component two respectively.

[0014] Optionally, the second and third pressing rings are provided with arc-shaped surfaces fitting with the lip tip.

[0015] Optionally, the mold is a circular ring-shaped member or a closed-loop member composed of multiple arc segments.

[0016] Optionally, the clamping assembly 2 further includes a plurality of brackets 2, and the pressing rings 2 and 3 are detachably mounted on the brackets 2.

[0017] Optionally, the rotary workbench is provided with a plurality of linear drive components 1, a plurality of linear drive components 2 and a plurality of groups of mounting holes, the linear drive components 2 drive the linear drive component 1 to move, the linear drive component 1 drives the clamping mechanism to adjust the position of the mold relative to the rotating axis of the rotary workbench, and each group of mounting holes is used to fix the clamping mechanism.

[0018] Optionally, the driving directions of the linear drive member 1 and the linear drive member 2 are perpendicular to each other, the linear drive member 2 is fixedly mounted on the rotating workbench, and the bottom of the linear drive member 1 is embedded and slidably connected to the rotating workbench.

[0019] Optionally, the forming mechanism further includes a three-axis truss and a manipulator disposed on the three-axis truss, and the tool head is replaceably mounted on the manipulator.

[0020] Optionally, the tool head is a rotary wheel.

[0021] A method for integrally forming an aircraft engine lip, using the aircraft engine lip integrally forming device as described above, comprises the following steps:

[0022] Fix the slab on the clamping assembly 1, start the rotary table and tool head, perform moldless pre-rotation on the slab, process the outer lip and lip tip, increase the contact area between the slab and the subsequent mold, and then stop the rotary table and tool head;

[0023] Replace the clamping component 1 with the clamping component 2, fix the mold on the clamping component 2, turn the pre-rotated slab over first and then clamp and fix it with the pressing ring 2 and the mold, the pressing ring 2 is located on one side of the outer lip and fits with the lip tip, start the rotary table and the tool head to pre-rotate the inner lip, and stop the rotary table and the tool head after completion;

[0024] After the inner lip is pre-spun, the tool head is replaced with a tool to cut off the plate core;

[0025] After the cutting is completed, the tool head is replaced, and the rotary table and tool head are started to perform inner lip film spinning on the cut workpiece. After the spinning is completed, the rotary table and the spinning wheel are stopped;

[0026] Remove the second pressing ring and install the third pressing ring, which is located on one side of the inner lip and fits with the lip tip. Start the rotary table and the tool head to spin the outer lip film to complete the overall forming of the lip.

[0027] The formed lip is annealed to eliminate internal stress.

[0028] The beneficial effects of the present invention are as follows: the aircraft engine lip integral forming device provided by the present invention, after the outer lip and lip tip of the lip are pre-spun out by opening the rotary table and the tool head, the clamping component 1 is removed and replaced with the clamping component 2, the pre-spun slab is turned over, and the slab is clamped and fixed by the cooperation of the pressure ring 2 and the mold, the tool head is on the inner side of the mold, and the inner lip of the lip is pre-spun out by opening the rotary table and the tool head, the tool head can be replaced with a cutting tool, the excess part of the inner circle of the slab is cut off, and then the inner lip is spun to gradually form the inner circle, the pressure ring 2 is removed, the pressure ring 3 is installed on the inner side of the mold, the tool head is adjusted to the outer side of the mold, and the outer lip is gradually formed, and the overall forming of the lip is finally completed, because the pressure ring 2 and the pressure ring 3 respectively clamp the lip tip, so when processing the inner lip, the slab and the lip tip located on the outer side of the mold are not easily driven to deform, and when processing the outer lip, the inner lip and the lip tip are not easily driven to deform, so multiple processing of the lip tip is avoided, and the contour accuracy of the lip is also improved.

[0029] By means of the aircraft engine lip integral forming method, a lip in a circular shape or composed of a plurality of arc segments of different radii can be integrally formed and manufactured, thereby improving the accuracy of the lip contour, the uniformity of the wall thickness, the mechanical strength and the assembly accuracy, while simplifying the processing technology and improving the production efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 A schematic diagram of the integral forming device provided in an embodiment of the present invention pre-spinning out the outer lip and the lip tip;

[0031] Figure 2 A schematic diagram of the integral forming device provided by an embodiment of the present invention pre-spinning out the inner lip;

[0032] Figure 3 A schematic diagram of the integral forming device provided in an embodiment of the present invention performing die-spinning on the inner lip;

[0033] Figure 4 A schematic diagram of the integral forming device provided by an embodiment of the present invention spinning the outer lip mold;

[0034] Figure 5 A schematic diagram of one structure of the integral forming device provided in an embodiment of the present invention;

[0035] Figure 6 A schematic diagram of the top view of the rotary table provided in an embodiment of the present invention;

[0036] Figure 7 A schematic structural diagram of a circular ring-shaped mold provided by an embodiment of the present invention;

[0037] Figure 8 A schematic structural diagram of a mold composed of multiple arc segments provided in an embodiment of the present invention;

[0038] Fig. 9 A schematic diagram of the position of the center of a circle of a mold with multiple arcs provided in an embodiment of the present invention.

[0039] In the figure: 10, rotating worktable; 11, mounting hole; 20, clamping mechanism; 21, clamping component 1; 211, bracket 1; 212, pressure ring 1; 22, clamping component 2; 221, mold; 222, pressure ring 2; 223, pressure ring 3; 224, bracket 2; 23, clamping claw; 31, tool head; 32, three-axis truss; 33, manipulator; 40, slab; 50, linear drive component 1; 60, linear drive component 2. DETAILED DESCRIPTION

[0040] In order to make the objectives, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with specific embodiments and with reference to the accompanying drawings.

[0041] like Figure 1-4 As shown, the present invention provides an aircraft engine lip integral forming device, comprising: a rotating worktable 10, a clamping mechanism 20 arranged on the rotating worktable 10 and a forming mechanism, the clamping mechanism 20 comprises a replaceable clamping component 1 21 and a clamping component 2 22, the clamping component 1 21 is used to clamp the edge of a plate blank 40, the clamping component 22 comprises a mold 221, a detachable pressing ring 222 and a detachable pressing ring 3 223 which are respectively arranged on the inner and outer sides of the mold 221, the pressing ring 222 and the pressing ring 3 223 are used to respectively clamp the lip tip and fix it to the mold 221; the forming mechanism comprises a plurality of tool heads 31 whose positions can be adjusted in a three-dimensional coordinate system.

[0042] Compared with the prior art, the aircraft engine lip integral forming device provided by the embodiment of the present invention is to open the rotary table 10 and the tool head 31 to pre-spin the outer lip and the lip tip of the lip, remove the clamping component 1 21, replace it with the clamping component 2 22, turn over the pre-spinned slab 40, and press and fix the slab 40 by the cooperation of the pressure ring 222 and the mold 221. The tool head 31 is on the inner side of the mold 221. The inner lip of the lip is pre-spinned by opening the rotary table 10 and the tool head 31. The tool head 31 can be replaced with a tool to cut off the excess part of the inner circle of the slab 40. The inner lip is then spun to gradually form an inner ring, and the second press ring 222 is removed. The third press ring 223 is installed on the inner side of the mold 221, and the tool head 31 is adjusted to the outer side of the mold 221 to gradually shape the outer lip, and finally the overall forming of the lip is completed. Since the second press ring 222 and the third press ring 223 respectively press the lip tip, when processing the inner lip, the slab 40 located on the outer side of the mold 221 and the lip tip are not easily caused to deform. When processing the outer lip, the inner lip and the lip tip are not easily caused to deform, so multiple processing of the lip tip is avoided, and the contour accuracy of the lip is also improved.

[0043] It should be noted that the attached Figure 1-5 The other half of the structure is omitted symmetrically, and the dotted line is the symmetry line, which is also the rotation axis of the rotating workbench 10.

[0044] In this embodiment, the clamping assembly 21 includes a plurality of brackets 211 and a pressure ring 212 , and the pressure ring 212 is rigidly disposed on the bracket 211 .

[0045] Specifically, if the bracket 211 is an annular bracket, the number of the bracket 211 is one, which is installed on the rotating table 10 through a fastening component, and the pressure ring 212 is fixed on the top of the bracket 211 and close to the outside. Usually, the pressure ring 212 is a circular ring structure and is coaxially arranged with the rotation axis of the rotating table 10. When the slab 40 is pressed, it is ensured that the rotation axis of the slab 40 is coaxial with the rotation axis of the rotating table 10; if the bracket 211 is an arc bracket, the number of the bracket 211 is at least two, and the two brackets 211 can be combined into a complete arc structure. There can also be a gap between the two brackets 211. Preferably, the two brackets 211 are symmetrically arranged on both sides of the rotation axis of the rotating table 10, which is convenient for installation and ensures a more balanced force. The pressure ring 212 can move up and down on the bracket 211 to loosen or press the slab 40. The pressure ring 212 has a hydraulic cylinder or an electric cylinder.

[0046] In one embodiment, if the second bracket 224 is an annular bracket, the number of the second bracket 224 is one, which is sufficient to support the mold 221 to ensure that the mold 221 does not undergo excessive bending and deformation. It is installed on the rotating workbench 10 through a fastening component, and the second pressure ring 222 is fixed on the top of the second bracket 224 and close to the outside, and the third pressure ring 223 is fixed on the top of the second bracket 224 and close to the inside. The second pressure ring 222 and the third pressure ring 223 are not used at the same time. Usually, the second pressure ring 222 and the third pressure ring 223 are circular ring structures and are aligned with the rotating axis of the rotating workbench 10. Coaxial arrangement, when pressing the slab 40, ensure that the rotation axis of the slab 40 is coaxial with the rotation axis of the rotary table 10; if the bracket 224 is an arc-shaped bracket, the number of the bracket 224 is at least two, and two or more brackets 224 can be combined to form a complete arc-shaped structure. Of course, if the rigidity of the mold 221 is large enough, there can also be a gap between the brackets 224. Preferably, the two brackets 224 are symmetrically arranged on both sides of the rotation axis of the rotary table 10, which is convenient for installation, ensuring a more balanced force, and also conducive to the later adjustment of the position of the mold 221. The pressure ring 222 and the pressure ring 3 223 can move up and down on the bracket 224 to loosen or press the slab 40. The pressure ring 222 or the pressure ring 3 223 has a hydraulic cylinder or an electric cylinder.

[0047] In this embodiment, the clamping mechanism 20 further includes a plurality of claws, which are used to clamp and fix the clamping assembly 1 21 and the clamping assembly 2 22 respectively.

[0048] Specifically, the clamping claw is a fastener commonly used in machine tools, and is used here to fix the bracket 1 211 and the bracket 2 224, so that the bracket 1 211 and the bracket 2 224 can be quickly disassembled and installed. The clamping claw can be adjusted in position after being separated from the rotary table 10.

[0049] In this embodiment, in order to reduce the influence of the second pressing ring 222 and the third pressing ring 223 on the contour of the lip tip when in use, the second pressing ring 222 and the third pressing ring 223 are provided with an arc surface that fits the lip tip.

[0050] In this embodiment, please refer to Figure 7-Figure 9 The mold 221 is a circular ring-shaped part or a closed-loop part composed of multiple arc segments.

[0051] It should be noted that the side and top contours of the mold 221 are consistent with the contour of the lip. Most of the lips are in the shape of a ring, and the corresponding mold 221 is a ring-shaped part; there are also a few lips that are composed of arc segments of different radii. This type of lip usually requires the separate manufacture of multiple arc segments, and then welding them together. It is achieved through a split-welding process and is usually difficult to form as a whole. The aircraft engine lip integral forming device is equipped with a specially designed mold 221, so that this lip integral forming can be achieved. The mold 221 has two symmetrically arranged arc segments L1, arc segments L2 and arc segment L3 located at both ends of the two arc segments L1 and tangent to the arc segment L1, and the arc segment L3 is a semicircular arc segment. The centers of the arc segments L1, L2 and L3 are O', O" and O"' respectively; the radii of the arc segments L1, L3 and L2 increase successively.

[0052] In this embodiment, please refer to Figure 5 and Figure 6 The rotary worktable 10 is provided with a plurality of linear drive members 50, a plurality of linear drive members 60 and a plurality of groups of mounting holes 11. The linear drive members 60 drive the linear drive members 50 to move. The linear drive members 50 drive the clamping mechanism 20 to adjust the position of the mold 221 relative to the rotating axis of the rotary worktable 10. Each group of mounting holes 11 is used to fix the clamping mechanism 20.

[0053] Specifically, the driving directions of the linear drive member 1 50 and the linear drive member 2 60 are perpendicular to each other, the linear drive member 2 60 is fixedly mounted on the rotary table 10, and the bottom of the linear drive member 1 50 is embedded and slidably connected to the rotary table 10; preferably, the two linear drive members 1 50 are symmetrically arranged, and each linear drive member 1 50 is connected to the output end of a linear drive member 2 60; when the two linear drive members 1 50 are opposite to each other and facing the rotation axis of the rotary table 10, the control unit couples the two linear drive members 1 50 to synchronously drive the bracket 2 224 in the same direction, so that the two centers O' of the mold 221 composed of multiple arc segments coincide with the rotation axis of the rotary table 10 respectively, and the rotary table 10 and the tool head 31 are started, and the reciprocating rotation angle of the rotary table 10 does not exceed the radian of the arc segment L1, that is, The outer lip at the arc segment L1 can be spun; the linear drive member 2 60 drives the linear drive member 1 50, which drives the clamp 23 and the bracket 2 224 to translate, so that the center O" of the mold 221 composed of multiple arc segments coincides with the rotation axis of the rotary table 10, the rotary table 10 and the tool head 31 are started, and the reciprocating rotation angle of the rotary table 10 does not exceed the radian of the arc segment L2, and the outer lip at the arc segment L2 can be spun; similarly, through the action of the linear drive member 1 50 and the linear drive member 2 60, the two center O"'s of the mold 221 composed of multiple arc segments coincide with the rotation axis of the rotary table 10, the rotary table 10 and the tool head 31 are started, and the reciprocating rotation angle of the rotary table 10 does not exceed the radian of the arc segment L3, and the outer lip at the arc segment L3 can be spun.

[0054] It should be noted that the clamping jaws 23 are fixed to the mounting holes 11 by bolts. After the bolts are removed, the clamping jaws 23 can be driven by the linear drive member 1 50 and the linear drive member 2 60 to move to the next set of mounting holes 11 on the rotating work platform. In order to reduce friction, lubricating oil can be applied to the bottom of the clamping jaws 23.

[0055] In this embodiment, when forming a lip composed of multiple arc segments with different radii, the arc segment with a larger radius should be processed first to ensure a smooth transition at the junction; of course, the order can also be adjusted if necessary.

[0056] When spinning the inner lip and the lip tip, the vertical distance between the tool head 31 and the rotation axis of the rotating worktable 10 can be adjusted to achieve the forming of the lip tip of the lip composed of multiple arc segments of different radii. When spinning the inner lip, the relative position of the mold 221 and the rotation axis of the rotating worktable 10 is adjusted in the same way as when spinning the outer lip, so it will not be repeated.

[0057] In this embodiment, the forming mechanism further includes a three-axis truss 32 and a manipulator 33 disposed on the three-axis truss 32 , and the tool head 31 is replaceably mounted on the manipulator 33 , so that the position of the tool head 31 can be adjusted in three-dimensional coordinates.

[0058] Furthermore, the tool head 31 is a rotary wheel, which can roll on the surface of the slab 40. The high degree of freedom of the rotary wheel can improve the fitting accuracy in terms of the rotary wheel trajectory, meet the processing requirements of various products, and can also reduce the cracks and wrinkles on the workpiece surface caused by uneven wall thickness during large deformation processing; the wall thickness reduction during the strong spinning process can effectively crush the coarse, brittle and hard grains of the material, achieve the effect of refining the grains, and effectively improve the mechanical properties of the product, thereby improving the service life and product quality of the processed product. It has a variety of processing forms, and the rotary wheel can be replaced with various processing tools. It can realize one device, that is, spinning curved surface forming, and turning processing, reducing the number of clamping times while completing multiple processing steps, ensuring the processing accuracy of the workpiece.

[0059] The present invention also provides an aircraft engine lip integral forming method, using the aircraft engine lip integral forming device as described above, comprising the following steps:

[0060] Fix the slab 40 on the clamping assembly 21, start the rotary table 10 and the tool head 31, perform moldless pre-rotation on the slab 40, process the outer lip and the lip tip, increase the contact area between the slab 40 and the subsequent mold 221, and then stop the rotary table 10 and the tool head 31;

[0061] Replace the clamping assembly 1 21 with the clamping assembly 2 22, fix the mold 221 on the clamping assembly 2 22, turn the pre-rotated slab 40 over first and then clamp and fix it with the pressing ring 2 22 and the mold 221, the pressing ring 222 is located on one side of the outer lip and fits with the lip tip, start the rotating table 10 and the tool head 31 to pre-rotate the inner lip, and stop the rotating table 10 and the tool head 31 after completion;

[0062] After the inner lip is pre-rotated, the tool head 31 is replaced with a tool to cut off the plate core;

[0063] After the cutting is completed, the tool head 31 is replaced, the rotary table 10 and the tool head 31 are started, and the inner lip film is spun on the cut workpiece. After the spun is completed, the rotary table 10 and the spinning wheel are stopped;

[0064] Remove the second pressing ring 222 and install the third pressing ring 223, which is located on one side of the inner lip and fits with the lip tip. Start the rotating table 10 and the tool head 31 to spin the outer lip film to complete the overall forming of the lip.

[0065] The formed lip is annealed to eliminate internal stress.

[0066] By means of the aircraft engine lip integral forming method, a lip in a circular shape or composed of a plurality of arc segments of different radii can be integrally formed and manufactured, thereby improving the accuracy of the lip contour, the uniformity of the wall thickness, the mechanical strength and the assembly accuracy, while simplifying the processing technology and improving the production efficiency.

[0067] A person skilled in the art should understand that the discussion of any of the above embodiments is merely illustrative and is not intended to imply that the scope of protection of the present application is limited to these examples. In line with the concept of the present application, the technical features in the above embodiments or different embodiments may be combined, the steps may be implemented in any order, and there are many other variations of different aspects of one or more embodiments of the present application as described above, which are not provided in detail for the sake of simplicity.

[0068] One or more embodiments of the present application are intended to cover all such substitutions, modifications and variations that fall within the broad scope of the present application. Therefore, any omissions, modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of one or more embodiments of the present application should be included in the protection scope of the present application.

Claims

1. A method for integrally forming an aircraft engine lip, characterized in that: The steps include: The slab (40) is fixed on the clamping assembly (21), the rotary table (10) and the tool head (31) are started, and the slab (40) is pre-rotated without a mold to form an outer lip and a lip tip, thereby increasing the contact area between the slab (40) and the subsequent mold (221), and then the rotary table (10) and the tool head (31) are stopped; The clamping component 1 (21) is replaced with the clamping component 2 (22), and the mold (221) is fixed on the clamping component 2 (22). The pre-rotated slab (40) is first turned over and then clamped and fixed by the pressing ring 2 (222) and the mold (221). The pressing ring 2 (222) is located on the side of the outer lip and fits with the lip tip. The rotating table (10) and the tool head (31) are started to pre-rotate the inner lip. After completion, the rotating table (10) and the tool head (31) are stopped. After the inner lip is pre-rotated, the tool head (31) is replaced with a tool to remove the plate core; After the cutting is completed, the tool head (31) is replaced, the rotary table (10) and the tool head (31) are started, and the inner lip film is spun on the cut workpiece. After the spun is completed, the rotary table (10) and the spinning wheel are stopped; The second pressing ring (222) is removed, and the third pressing ring (223) is installed. The third pressing ring (223) is located on one side of the inner lip and fits with the lip tip. The rotary table (10) and the tool head (31) are started to spin the outer lip film to complete the overall forming of the lip. The formed lip is annealed to eliminate internal stress.

2. An aircraft engine lip integral forming device, characterized in that: For executing the method according to claim 1, the device comprises: Rotating table (10); a clamping mechanism (20) disposed on a rotating worktable (10), the clamping mechanism (20) comprising a replaceable clamping assembly (21) and a clamping assembly (22), the clamping assembly (21) being used to clamp the edge of the slab (40), the clamping assembly (22) comprising a mold (221), and a detachable pressing ring (222) and a detachable pressing ring (223) disposed on both sides of the mold (221), the pressing ring (222) and the detachable pressing ring (223) being used to clamp the lip tip and fix it to the mold (221); and A forming mechanism, the forming mechanism comprising a plurality of tool heads (31) whose positions can be adjusted in a three-dimensional coordinate system; The clamping assembly 1 (21) comprises a plurality of brackets 1 (211) and a pressure ring 1 (212), wherein the pressure ring 1 (212) is rigidly arranged on the bracket 1 (211); the clamping mechanism (20) further comprises a plurality of claws, wherein the claws are used to clamp and fix the clamping assembly 1 (21) and the clamping assembly 2 (22) respectively.

3. The aircraft engine lip integral forming device according to claim 2, characterized in that: The support frame 1 (211) is a ring frame or an arc frame.

4. The aircraft engine lip integral forming device according to claim 3, characterized in that: When the bracket one (211) is an arc-shaped bracket, two brackets one (211) are symmetrically arranged on both sides of the rotation axis of the rotating worktable (10).

5. The aircraft engine lip integral forming device according to claim 2, characterized in that: The second pressing ring (222) and the third pressing ring (223) are provided with arc-shaped surfaces that fit with the lip tip.

6. The aircraft engine lip integral forming device according to claim 2, characterized in that: The mold (221) is a circular ring-shaped member or a closed ring member composed of multiple circular arc segments.

7. The aircraft engine lip integral forming device according to claim 2, characterized in that: The clamping assembly 2 (22) further comprises a plurality of brackets 2 (224), and the pressing ring 2 (222) and the pressing ring 3 (223) are detachably mounted on the brackets 2 (224).

8. The aircraft engine lip integral forming device according to claim 2, characterized in that: The rotary worktable (10) is provided with a plurality of linear drive members 1 (50), a plurality of linear drive members 2 (60) and a plurality of groups of mounting holes (11); the linear drive members 2 (60) drive the linear drive member 1 (50) to move; the linear drive member 1 (50) drives the clamping mechanism (20) to adjust the position of the mold (221) relative to the rotation axis of the rotary worktable (10); and each group of mounting holes (11) is used to fix the clamping mechanism (20).

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