Titanium alloy multi-curved step flanging part die and flanging method for aircraft

Abstract

The present invention provides a titanium alloy multi-curved step flanging part mold for aircraft and a flanging method. The titanium alloy multi-curved step flanging part mold for aircraft comprises: a lower template, an extrusion block and an extrusion bolt; a positioning groove is provided on the upper surface of the lower template, the inner side wall of the positioning groove is a first arc-shaped step structure, and the outer side wall of the positioning groove is a plurality of first plane structures perpendicular to each other; a plurality of groups of positioning bolt holes are provided on the outer side wall of the lower template; a plurality of extrusion blocks are adjustably arranged in the positioning groove along a horizontal straight line direction; the inner side walls of the plurality of extrusion blocks form a second arc-shaped step structure, and the outer side walls of the plurality of extrusion blocks are a plurality of second plane structures perpendicular to each other; a plurality of groups of extrusion bolts are correspondingly arranged in the plurality of groups of positioning bolt holes; the plurality of groups of extrusion bolts are used to push the plurality of extrusion blocks to move toward the first arc-shaped step structure to extrude the arc-shaped flanging parts; the problem that traditional molds cannot process titanium alloy multi-curved step flanging parts is solved.

Description

Technical Field

[0001] The present invention relates to the field of titanium alloy part processing dies for aircraft, and in particular to a titanium alloy multi-curved stepped flanging part die and a flanging method for aircraft. Background Art

[0002] Aircraft engines are highly complex and sophisticated thermal machines. As the heart of an aircraft, they not only power its flight but also serve as a vital driving force for the development of aviation. Every significant revolution in human aviation history is closely linked to technological advancements in aircraft engines. The nacelle, the compartment housing the aircraft engine, is also one of the most critical core components in aviation propulsion systems. The nacelle accounts for approximately a quarter of the total engine cost. Currently, my country's manufacturing technology in this area lags far behind advanced international technology.

[0003] At present, in the manufacturing process of the engine nacelle, a large number of titanium alloy multi-curved step flanging parts are needed to manufacture the outer shell of the engine nacelle. The titanium alloy multi-curved step flanging parts are arc-shaped flanging parts, which are circular arc-shaped step structures. The arc-shaped flanging parts have a circular arc-shaped tread, and two kick surfaces are formed by extending a certain distance vertically upward and vertically downward along the two edges of the tread. The lower folding edge and the upper folding edge of the arc-shaped flanging part both need to be processed into a stamping negative angle structure. The casting of titanium alloy multi-curved step flanging parts is mainly based on stamping. Titanium alloy multi-curved step flanging parts have the defects of being difficult to bend and difficult to shape, and have very high requirements for processing technology and mold equipment. It is difficult to process titanium alloy multi-curved step flanging parts that meet the requirements with existing processing molds, which requires the use of special dedicated molds. Summary of the Invention

[0004] The main purpose of the present invention is to provide a titanium alloy multi-curved stepped flanging part mold for aircraft, so as to at least solve the problem that traditional molds cannot process titanium alloy multi-curved stepped flanging parts.

[0005] In order to achieve the above-mentioned purpose, the present invention provides, on the one hand, a titanium alloy multi-curved step flanging part mold for aircraft, comprising: a lower template, an extrusion block and an extrusion bolt; a positioning groove is provided on the upper surface of the lower template, the inner side wall of the positioning groove is a first arc-shaped step structure, and the outer side wall of the positioning groove is a plurality of first plane structures perpendicular to each other; a plurality of positioning bolt holes are provided on the outer side wall of the lower template that are horizontally connected to the positioning groove; there are a plurality of extrusion blocks, and the positions of the plurality of extrusion blocks are adjustably arranged in the positioning groove along the horizontal straight line direction; the inner side walls of the plurality of extrusion blocks form a second arc-shaped step structure, and the outer side walls of the plurality of extrusion blocks are a plurality of second plane structures perpendicular to each other, and the plurality of second plane structures are connected to the plurality of first The planar structures correspond one to one; there are multiple groups of extrusion bolts, and the multiple groups of extrusion bolts are correspondingly arranged in the multiple groups of positioning bolt holes; the multiple groups of extrusion bolts are used to push the multiple extrusion blocks toward the first arc-shaped step structure to extrude the arc-shaped flange part placed between the first arc-shaped step structure and the second arc-shaped step structure; wherein, the angle between the lower step edge of the first arc-shaped step structure and the bottom surface of the positioning groove is less than 90°, and the angle between the upper step edge of the first arc-shaped step structure and its step surface is less than 90°; the outer shape of the second arc-shaped step structure matches the outer shape of the first arc-shaped step structure, and the multiple extrusion blocks move toward the first arc-shaped step structure to bend the lower folding edge and the upper folding edge of the arc-shaped flange part into a closed angle structure.

[0006] Furthermore, multiple groups of positioning pins are provided in the positioning groove, and the multiple groups of positioning pins are perpendicular to the bottom surface of the positioning groove; each extrusion block is provided with a group of strip positioning holes along its thickness direction, and the length direction of each group of strip positioning holes is consistent with the moving direction of the corresponding extrusion block; wherein, the multiple groups of positioning pins are correspondingly inserted into the multiple groups of strip positioning holes of the multiple extrusion blocks to limit the moving direction of the multiple extrusion blocks.

[0007] Furthermore, each group of positioning pins has two pieces, and each extrusion block has two strip-shaped positioning holes.

[0008] Furthermore, both ends of the positioning groove are open structures.

[0009] Furthermore, the transition portions between the multiple first planar structures are rounded structures; and the two top corner positions formed by the multiple extrusion blocks are rounded structures.

[0010] Furthermore, the dividing lines between the multiple extrusion blocks are opposite to the two vertex angles formed between the multiple extrusion blocks, and the dividing lines between the multiple extrusion blocks are not parallel to any of the second planar structures.

[0011] Furthermore, the first arc-shaped step structure and the second arc-shaped step structure are both semicircular step structures.

[0012] Furthermore, each group of positioning bolt holes and each group of extrusion bolts are four, and each group of positioning bolt holes is evenly spaced along the extension direction of the outer side wall of the lower template.

[0013] On the other hand, the present invention provides a flanging method, which is applied to a titanium alloy multi-curved step flanging part mold for aircraft. The flanging method includes: placing an arc-shaped flanging piece on a first arc-shaped step structure along the circumference; placing a plurality of extrusion blocks one by one in the positioning groove along the circumference of the first arc-shaped step structure; respectively placing a plurality of second plane structures on the outer side walls of the plurality of extrusion blocks opposite to a plurality of first plane structures on the outer side walls of the positioning groove; tightening a plurality of groups of extrusion bolts provided in a plurality of groups of positioning bolt holes into the interior of the lower template in turn to abut the plurality of groups of extrusion bolts against the plurality of second plane structures; pushing a plurality of extrusion blocks toward the first arc-shaped step structure by the plurality of groups of extrusion bolts to extrude the arc-shaped flanging piece placed between the first arc-shaped step structure and the second arc-shaped step structure, and bending the lower flanging edge and the upper flanging edge of the arc-shaped flanging piece into a closed angle structure.

[0014] The technical solution of the present invention is a mold for a titanium alloy multi-curved step flanging part for aircraft, comprising: a lower template, an extrusion block and an extrusion bolt; a positioning groove is provided on the upper surface of the lower template, the inner side wall of the positioning groove is a first arc-shaped step structure, and the outer side wall of the positioning groove is a plurality of first plane structures perpendicular to each other; a plurality of groups of positioning bolt holes are provided on the outer side wall of the lower template that pass through the positioning groove in a horizontal direction; there are a plurality of extrusion blocks, and the positions of the plurality of extrusion blocks are adjustably arranged in the positioning groove along a horizontal straight line direction; the inner side walls of the plurality of extrusion blocks are a second arc-shaped step structure, and the outer side walls of the plurality of extrusion blocks are a plurality of second plane structures perpendicular to each other, and the plurality of second plane structures are aligned with the plurality of first plane structures. One corresponds to another; there are multiple groups of extrusion bolts, and the multiple groups of extrusion bolts are correspondingly arranged in the multiple groups of positioning bolt holes; the multiple groups of extrusion bolts are used to push the multiple extrusion blocks toward the first arc-shaped step structure to extrude the arc-shaped flanging part placed between the first arc-shaped step structure and the second arc-shaped step structure; wherein the angle between the lower step edge of the first arc-shaped step structure and the bottom surface of the positioning groove is less than 90°, and the angle between the upper step edge of the first arc-shaped step structure and its step surface is less than 90°; the second arc-shaped step structure matches the shape of the first arc-shaped step structure, and the multiple extrusion blocks move toward the first arc-shaped step structure to bend the lower and upper folding edges of the arc-shaped flanging part into a closed-angle structure. The present invention solves the problem that traditional molds cannot process titanium alloy multi-curved step flanging parts. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] The accompanying drawings, which constitute part of this application, are intended to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are intended to explain the present invention and do not constitute an undue limitation of the present invention. In the accompanying drawings:

[0016] Figure 1 This is a schematic structural diagram of a titanium alloy multi-curved stepped flanging part mold for aircraft, which may be selected according to an embodiment of the present invention;

[0017] Figure 2 This is a schematic diagram of the lower template structure of a titanium alloy multi-curved stepped flanging part mold for aircraft, which can be selected according to an embodiment of the present invention;

[0018] Figure 3 The present invention is a schematic diagram of an extrusion block structure of a titanium alloy multi-curved stepped flanging part die for aircraft according to an embodiment of the present invention.

[0019] The above drawings include the following reference numerals:

[0020] 10. Lower template; 11. Positioning groove; 12. First arc-shaped step structure; 13. First plane structure; 14. Positioning bolt hole; 20. Extrusion block; 21. Second arc-shaped step structure; 22. Second plane structure; 23. Strip-shaped positioning hole; 30. Extrusion bolt; 40. Positioning pin. DETAILED DESCRIPTION

[0021] It should be noted that, in the absence of conflict, the embodiments and features of the embodiments in this application can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0022] like Figure 1As shown, a titanium alloy multi-curved step flanging part mold for aircraft includes: a lower template 10, an extrusion block 20 and an extrusion bolt 30; a positioning groove 11 is provided on the upper surface of the lower template 10, the inner side wall of the positioning groove 11 is a first arc-shaped step structure 12, and the outer side wall of the positioning groove 11 is a plurality of first plane structures 13 perpendicular to each other; the outer side wall of the lower template 10 is provided with a plurality of groups of positioning bolt holes 14 that pass through the positioning groove 11 in the horizontal direction; there are a plurality of extrusion blocks 20, and the positions of the plurality of extrusion blocks 20 are adjustably arranged in the positioning groove 11 along the horizontal straight line direction; the inner side walls of the plurality of extrusion blocks 20 form a second arc-shaped step structure 21, and the outer side walls of the plurality of extrusion blocks 20 are a plurality of second plane structures 22 perpendicular to each other, and the plurality of second plane structures 22 are connected to the plurality of first plane structures The structures 13 correspond one to one; there are multiple groups of extrusion bolts 30, and the multiple groups of extrusion bolts 30 are correspondingly arranged in the multiple groups of positioning bolt holes 14; the multiple groups of extrusion bolts 30 are used to push the multiple extrusion blocks 20 to move toward the first arc-shaped step structure 12 to extrude the arc-shaped flanging part placed between the first arc-shaped step structure 12 and the second arc-shaped step structure 21; wherein, the angle between the lower step edge of the first arc-shaped step structure 12 and the groove bottom surface of the positioning groove 11 is less than 90°, and the angle between the upper step edge of the first arc-shaped step structure 12 and its step surface is less than 90°; the outer shape of the second arc-shaped step structure 21 matches the outer shape of the first arc-shaped step structure 12, and the multiple extrusion blocks 20 move toward the first arc-shaped step structure 12 to bend the lower folding edge and the upper folding edge of the arc-shaped flanging part into a closed angle structure. When the present invention is used, the lower template 10 is first fixed on the placement platform of the punching machine, and the arc-shaped flanging piece that needs to be folded and closed is placed on the first arc-shaped step structure 12 along the circumference. The multiple extrusion blocks 20 are placed one by one in the positioning groove 11 along the circumference of the first arc-shaped step structure 12, so that the multiple second plane structures 22 of the outer side walls of the multiple extrusion blocks 20 are respectively opposite to the multiple first plane structures 13 of the outer side walls of the positioning groove 11. The multiple groups of extrusion bolts 30 set in the multiple groups of positioning bolt holes 14 are sequentially inserted into the positioning groove 11. The lower template 10 is tightened internally so that the multiple groups of extrusion bolts 30 abut against the multiple second planar structures 22. When all the extrusion bolts 30 are tightened, the multiple groups of extrusion bolts 30 push the multiple extrusion blocks 20 toward the first arc-shaped step structure 12 to extrude the arc-shaped flanging part placed between the first arc-shaped step structure 12 and the second arc-shaped step structure 21. After being fixed and cooled for a period of time, the multiple groups of extrusion bolts 30 are loosened toward the outside of the lower template 10, and the multiple extrusion blocks 20 are taken out one by one, and the arc-shaped flanging part with a stamped closed angle on both sides is taken out. The mold of the present invention is cleverly designed and simple and convenient to operate. It can simultaneously stamp a closed angle on both sides of the arc-shaped flanging part. The present invention solves the problem that existing processing molds cannot process titanium alloy multi-curved step flanging parts.

[0023] As an optimization solution of the present invention, Figure 1 and Figure 2 As shown, the outer side wall of the positioning groove 11 is three first planar structures 13 perpendicular to each other, and the transition portion formed between the three first planar structures 13 is a rounded structure.

[0024] As an optimization solution of the present invention, Figure 1 、 Figure 2 and Figure 3 As shown, the angle between the upper step edge of the first arc-shaped step structure 12 and its step surface ranges from 70° to 85°.

[0025] As an optimization solution of the present invention, Figure 1 、 Figure 2 and Figure 3 As shown, the angle between the lower step edge of the first arc-shaped step structure 12 and the bottom surface of the positioning groove 11 ranges from 70° to 85°.

[0026] As an optimization solution of the present invention, Figure 1 and Figure 2 As shown, multiple sets of positioning pins 40 are disposed within the positioning groove 11, with the multiple sets of positioning pins 40 being perpendicular to the bottom surface of the positioning groove 11. Each extrusion block 20 has a set of strip-shaped positioning holes 23 formed along its thickness, with the length of each set of strip-shaped positioning holes 23 aligning with the movement direction of the corresponding extrusion block 20. The multiple sets of positioning pins 40 are inserted into the multiple sets of strip-shaped positioning holes 23 of the multiple extrusion blocks 20 to limit the movement direction of the multiple extrusion blocks 20. Each set of positioning pins 40 consists of two, and each extrusion block 20 has two strip-shaped positioning holes 23. The two positioning pins 40 in each set are disposed in front of the corresponding first planar structure 13 at a predetermined interval. Preferably, the positioning pin 40 can be replaced by a bolt. A corresponding bolt hole is opened at the position where the positioning pin 40 was originally installed in the positioning groove 11. After the extrusion block 20 is placed in the positioning groove 11, the bolts are correspondingly inserted into the multiple groups of strip positioning holes 23 of the multiple extrusion blocks 20 and connected and tightened through the bolt holes. The bolt cap should be slightly higher than the height of the strip positioning hole 23, and the diameter of the bolt should match the width of the strip positioning hole 23. This can not only limit the movement direction of the extrusion block 20, but also, because of the presence of the bolt cap, when the extrusion block 20 abuts against the first arc-shaped step structure 12, it can prevent the extrusion block 20 from tilting up, thereby affecting the flanging closed angle effect of the arc flanging part. The two strip positioning holes 23 on each extrusion block 20 are set at a preset interval in the middle part of the extrusion block 20.

[0027] As an optimization solution of the present invention, Figure 2 As shown, both ends of the positioning groove 11 are open structures. The opening structure at both ends of the positioning groove 11 allows the staff to better directly observe the flanging closed angle effect of the arc-shaped flanging part during the stamping operation.

[0028] As an optimization solution of the present invention, Figure 1 、 Figure 2 and Figure 3 As shown, the transition portion between the multiple first planar structures 13 is a rounded structure; the two vertex positions formed by the multiple extrusion blocks 20 are rounded structures. The dividing line between the multiple extrusion blocks 20 is opposite to the two vertex positions formed by the multiple extrusion blocks 20, and the dividing line between the multiple extrusion blocks 20 is not parallel to any of the second planar structures 22. There are three extrusion blocks 20, and the overall upper surface formed by the three extrusion blocks 20 is an arched structure with two rounded corners. The first arc-shaped step structure 12 is a semicircular arc. The extending direction of the dividing line between the extrusion blocks 20 corresponds to the maximum curvature of the first arc-shaped step structure 12. The dividing line divides the extrusion block 20 into two equal parts from the center of the rounded corner outward to avoid wrinkles and cracks in the arc-shaped flanging piece at the maximum curvature when the flanging is closed.

[0029] As an optimization solution of the present invention, Figure 1 and Figure 3 As shown, both the first curved step structure 12 and the second curved step structure 21 are semicircular step structures. The second curved step structure 21 matches the first curved step structure 12 in shape so that the second curved step structure 21 and the first curved step structure 12 can be closely abutted.

[0030] As an optimization solution of the present invention, the present invention can further set up an integral upper template, which matches the lower template 10. When all the extrusion bolts 30 are tightened, the upper template is fastened to the lower template 10, which can ensure that the first arc-shaped step structure 12 and the second arc-shaped step structure 21 fit more tightly, and the part molding effect is better.

[0031] As an optimization solution of the present invention, Figure 2 As shown, each group of positioning bolt holes 14 and each group of extrusion bolts 30 are four, and each group of positioning bolt holes 14 is evenly spaced along the extension direction of the outer side wall of the lower template 10. The extrusion bolts 30 are M12 bolts.

[0032] The present invention provides a flanging method, which is applied to a titanium alloy multi-curved step flanging part mold for aircraft. The flanging method includes: placing an arc-shaped flanging piece on a first arc-step structure 12 along the circumference; placing a plurality of extrusion blocks 20 one by one in the circumference of the first arc-step structure 12 in sequence in a positioning groove 11; respectively aligning a plurality of second plane structures 22 on the outer side walls of the plurality of extrusion blocks 20 with a plurality of first plane structures 13 on the outer side walls of the positioning groove 11; tightening a plurality of groups of extrusion bolts 30 provided in a plurality of groups of positioning bolt holes 14 into the interior of a lower template 10 in sequence to abut the plurality of groups of extrusion bolts 30 against the plurality of second plane structures 22; pushing the plurality of extrusion blocks 20 toward the first arc-step structure 12 by the plurality of groups of extrusion bolts 30 to extrude the arc-shaped flanging piece placed between the first arc-step structure 12 and the second arc-step structure 21, and bending the lower flanging edge and the upper flanging edge of the arc-shaped flanging piece into a closed angle structure. The flanging method is specifically as follows: first, use other molds to pre-press out an arc-shaped flanging piece, and the arc-shaped flanging piece is a circular arc-shaped step structure. The arc-shaped flanging piece has an arc-shaped tread, and the two edges of the tread extend vertically upward and vertically downward for a certain distance to form two kick surfaces. When the present invention is used, first fix the lower template 10 on the placement platform of the punching machine, and place the arc-shaped flanging piece that needs to be folded and closed angled on the first arc-shaped step structure 12 along the circumference, and place the three extrusion blocks 20 one by one in the positioning groove 11 along the circumference of the first arc-shaped step structure 12. The three groups of positioning pins 40 are correspondingly inserted into the three groups of strip positioning holes 23 of the three extrusion blocks 20 to limit the moving direction of the three extrusion blocks 20. The three second planar structures 22 of the outer walls of the three extrusion blocks 20 are respectively aligned with the three first planar structures 13 of the outer walls of the positioning groove 11, and the three groups of extrusion bolts 30 set in the three groups of positioning bolt holes 14 are tightened in sequence toward the interior of the lower template 10 so that the extrusion bolts 30 abut against the three second planar structures 22. When all the extrusion bolts 30 are tightened, the three groups of extrusion bolts 30 push the three extrusion blocks 20 toward the first arc-shaped step structure 12 to extrude the arc-shaped flanging piece placed between the first arc-shaped step structure 12 and the second arc-shaped step structure 21. After being fixed and cooled for a period of time, the three groups of extrusion bolts 30 are loosened outside the lower template 10, and the positioning pins 40 are pulled out of the strip-shaped positioning holes 23 of the three extrusion blocks 20. The three extrusion blocks 20 are taken out one by one, and the arc-shaped flanging piece with a stamped closed angle on both sides is taken out. The method of the present invention is easy to operate, simple in process, and highly efficient.

[0033] The mold of the present invention has a simple structure and is easy to use. It can accurately press out the required double-sided stamping closed angle structure, solving the problem that existing processing molds cannot process titanium alloy multi-curved stepped flanging parts.

[0034] The foregoing description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Those skilled in the art will readily appreciate that various modifications and variations of the present invention are possible. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention are intended to be within the scope of protection of the present invention.

Claims

1. A titanium alloy multi-curved stepped flanging part die for aircraft, characterized in that: include: A lower template (10), wherein the upper surface of the lower template (10) is provided with a positioning groove (11), the inner side wall of the positioning groove (11) is a first arc-shaped step structure (12), and the outer side wall of the positioning groove (11) is a plurality of first plane structures (13) perpendicular to each other; the outer side wall of the lower template (10) is provided with a plurality of groups of positioning bolt holes (14) that pass through the positioning groove (11) in a horizontal direction; An extrusion block (20), wherein the extrusion blocks (20) are multiple, and the multiple extrusion blocks (20) are arranged in the positioning groove (11) in an adjustable manner along a horizontal straight line direction; the inner side walls of the multiple extrusion blocks (20) form a second arc-shaped step structure (21), and the outer side walls of the multiple extrusion blocks (20) are multiple second planar structures (22) perpendicular to each other, and the multiple second planar structures (22) correspond one to one to the multiple first planar structures (13); Extrusion bolts (30), the extrusion bolts (30) are multiple groups, and the multiple groups of extrusion bolts (30) are correspondingly arranged in the multiple groups of positioning bolt holes (14); the multiple groups of extrusion bolts (30) are used to push the multiple extrusion blocks (20) toward the first arc-shaped step structure (12) to squeeze the arc-shaped flange member placed between the first arc-shaped step structure (12) and the second arc-shaped step structure (21); wherein the angle between the lower step edge of the first arc-shaped step structure (12) and the bottom surface of the positioning groove (11) is less than 90°, and the angle between the upper step edge of the first arc-shaped step structure (12) and its step surface is less than 90°; the shape of the second arc-shaped step structure (21) matches the shape of the first arc-shaped step structure (12), and the plurality of extrusion blocks (20) move toward the first arc-shaped step structure (12) to bend the lower folding edge and the upper folding edge of the arc-shaped flanging member into a closed-angle structure; The dividing lines between the plurality of extrusion blocks (20) are relative to the vertex angles formed between the plurality of extrusion blocks (20), and the dividing lines between the plurality of extrusion blocks (20) are not parallel to any of the second plane structures (22); the extending direction of the dividing lines between the extrusion blocks (20) corresponds to the point where the curvature of the first arc-shaped step structure (12) is maximum, and the dividing lines divide the extrusion blocks (20) into two parts from the center of the fillet outward.

2. The titanium alloy multi-curved stepped flanging part mold for aircraft according to claim 1, characterized in that: A plurality of positioning pins (40) are provided in the positioning groove (11), and the plurality of positioning pins (40) are perpendicular to the bottom surface of the positioning groove (11); each of the extrusion blocks (20) is provided with a group of strip-shaped positioning holes (23) along its thickness direction, and the length direction of each group of the strip-shaped positioning holes (23) is consistent with the moving direction of the corresponding extrusion block (20); Wherein, a plurality of groups of positioning pins (40) are correspondingly inserted into a plurality of groups of the strip-shaped positioning holes (23) of a plurality of the extrusion blocks (20) to limit the movement directions of the plurality of the extrusion blocks (20).

3. The titanium alloy multi-curved stepped flanging part mold for aircraft according to claim 2, characterized in that: Each group of positioning pins (40) is composed of two, and each extrusion block (20) is composed of two strip-shaped positioning holes (23).

4. The titanium alloy multi-curved stepped flanging part mold for aircraft according to claim 1, characterized in that: Both ends of the positioning groove (11) are open structures.

5. The titanium alloy multi-curved stepped flanging part mold for aircraft according to claim 1, characterized in that: The transition portions between the plurality of first planar structures (13) are rounded structures; and the top corner positions formed by the plurality of extrusion blocks (20) are rounded structures.

6. The titanium alloy multi-curved stepped flanging part mold for aircraft according to claim 1, characterized in that: The first arc-shaped step structure (12) and the second arc-shaped step structure (21) are both semicircular step structures.

7. The titanium alloy multi-curved stepped flanging part mold for aircraft according to claim 1, characterized in that: Each group of the positioning bolt holes (14) and each group of the extrusion bolts (30) are four in number, and each group of the positioning bolt holes (14) are evenly spaced along the extension direction of the outer side wall of the lower template (10).

8. A flanging method, characterized in that: The flanging method is applied to a titanium alloy multi-curved stepped flanging part mold for aircraft according to any one of claims 1 to 7, and the flanging method comprises: Placing the arc-shaped flanging piece on the first arc-shaped step structure (12) along the circumferential direction; The plurality of extrusion blocks (20) are sequentially placed one by one in the positioning groove (11) along the circumference of the first arc-shaped step structure (12), and the plurality of second planar structures (22) on the outer side walls of the plurality of extrusion blocks (20) are respectively opposed to the plurality of first planar structures (13) on the outer side walls of the positioning groove (11); The plurality of extrusion bolts (30) provided in the plurality of positioning bolt holes (14) are sequentially tightened into the interior of the lower template (10) to abut the plurality of extrusion bolts (30) against the plurality of second planar structures (22), and the plurality of extrusion blocks (20) are pushed toward the first arc-shaped step structure (12) by the plurality of extrusion bolts (30) to extrude the arc-shaped flanging member placed between the first arc-shaped step structure (12) and the second arc-shaped step structure (21), and the lower flanging edge and the upper flanging edge of the arc-shaped flanging member are bent into a closed-angle structure.

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