Flanging die and forming method for titanium alloy serrated frame parts for aircraft

Abstract

The present invention provides a flanging mold and a forming method for titanium alloy serrated frame parts for aircraft. The flanging mold includes a lower template, an upper template and extrusion bolts; the upper surface of the lower template is provided with an irregular polygonal extrusion groove, and the lower template is provided with multiple groups of first positioning bolt holes at opposite ends along the length direction; the lower surface of the upper template is provided with an irregular polygonal extrusion boss matching the extrusion groove, and the upper template is provided with multiple groups of second positioning bolt holes that match the multiple groups of first positioning bolt holes one by one and penetrate the upper template along the thickness direction at opposite ends along the length direction; there are multiple groups of extrusion bolts, and the multiple groups of extrusion bolts are correspondingly arranged in the multiple groups of first positioning bolt holes and the multiple groups of second positioning bolt holes; the multiple groups of extrusion bolts are used to push the upper template toward the lower template to extrude the flange of the plate-type part placed between the extrusion groove and the extrusion boss.

Description

Technical Field

[0001] The present invention relates to the technical field of titanium alloy parts processing templates for aircraft, and in particular to a flanging die and a forming method for titanium alloy sawtooth frame parts 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] Currently, the manufacturing process of engine nacelles requires a large number of titanium alloy sheet step parts to manufacture the engine nacelle shell. Titanium alloy zigzag frame parts for aircraft are U-shaped flange parts, which need to be extruded into a U-shaped structure. The casting of titanium alloy sheet step parts is mainly based on stamping. Titanium alloy sheet step parts have the defects of being difficult to bend and shape, which places high demands on processing technology and template equipment. Existing processing templates make it difficult to process titanium alloy zigzag frame parts for aircraft that meet the requirements, so special dedicated templates are needed. Summary of the Invention

[0004] The main purpose of the present invention is to provide a flanging die and forming method for titanium alloy serrated frame parts for aircraft, so as to at least solve the problem that traditional templates in the prior art cannot process titanium alloy serrated frame parts for aircraft that meet the requirements.

[0005] In order to achieve the above-mentioned object, the present invention provides a flanging die and a forming method for titanium alloy sawtooth frame parts for aircraft.

[0006] In order to achieve the above-mentioned purpose, according to one aspect of the present invention, a flanging die for titanium alloy zigzag frame parts for aircraft is provided, comprising: a lower template, an upper template and an extrusion bolt; an irregular polygonal extrusion groove is provided on the upper surface of the lower template, and a positioning ridge extending along the symmetry axis in the length direction of the upper surface of the lower template is provided at the center of the bottom surface of the extrusion groove to divide the bottom surface of the extrusion groove into a first concave surface and a second concave surface, the first concave surface and the second concave surface are symmetrically distributed with the central ridge, and a plurality of groups of first positioning bolt holes are provided at opposite ends along the length direction; an irregular polygonal extrusion boss matching the extrusion groove is provided on the lower surface of the upper template, and a positioning ridge extending along the symmetry axis in the length direction of the upper surface of the lower template is provided at the center of the bottom surface of the extrusion groove to divide the bottom surface of the extrusion groove into a first concave surface and a second concave surface, the first concave surface and the second concave surface are symmetrically distributed with the central ridge, and a plurality of groups of first positioning bolt holes are provided at opposite ends along the length direction; An extrusion ridge is provided at the opposite ends of the upper template along the length direction, and the extrusion ridge matches the first ridge and extends along the axis of symmetry in the length direction of the lower surface of the upper template to divide the lower surface of the extrusion boss into a first convex surface matching the first concave surface and a second convex surface matching the second concave surface. The first convex surface and the second convex surface are symmetrically distributed along the extrusion ridge. The upper template is provided with multiple groups of second positioning bolt holes that match the multiple groups of first positioning bolt holes one by one and penetrate the upper template along the thickness direction at opposite ends along the length direction; there are multiple groups of extrusion bolts, and the multiple groups of extrusion bolts are correspondingly arranged in the multiple groups of first positioning bolt holes and the multiple groups of second positioning bolt holes; the multiple groups of extrusion bolts are used to push the upper template toward the lower template to extrude the flange of the plate part placed between the extrusion groove and the extrusion boss.

[0007] Furthermore, the extrusion groove is a through groove extending to both sides along the width direction of the lower template with the positioning ridge as the center, and the extrusion boss is extended to both sides along the width direction of the upper template with the extrusion ridge as the center until it is flush with both sides of the upper template.

[0008] Furthermore, the heights of the intersection points of the positioning ridge and the upper surface of the lower template at both ends are equal. The positioning ridge is an arc-shaped structure with equal heights at both ends and a depression in the middle. The intersection lines of the first concave surface and the second concave surface with the upper surface of the lower template and the intersection points at both ends are equal in height. The heights of the first concave surface and the second concave surface at the corners with the side walls of the extrusion groove are lower than the heights of the intersection points at both ends.

[0009] Furthermore, a first cut surface and a second cut surface are respectively provided at the intersection of the first concave surface and the second concave surface with the upper surface of the lower template, a first inner rounded corner transition structure and a second inner rounded corner transition structure are respectively provided at the corners of the first concave surface and the second concave surface with the side wall of the extrusion groove, and a first outer rounded corner transition structure is provided at the corner of the side wall of the extrusion groove with the upper surface of the lower template.

[0010] Furthermore, the intersection points of both ends of the positioning ridge are respectively provided with a triangular first concave block arranged along the thickness direction of the lower template and a first convex block arranged along the length direction of the lower template.

[0011] Furthermore, the heights of the intersection points of the extrusion ridge and the lower surface of the upper template at both ends are equal, and the extrusion ridge is an arc-shaped structure with equal heights at both ends and a depression in the middle. The intersection lines of the first convex surface and the second convex surface with the lower surface of the upper template and the intersection points at both ends are equal in height, and the heights of the first convex surface and the second convex surface at the corners with the side walls of the extrusion boss are lower than the heights of the intersection points at both ends.

[0012] Furthermore, a third section matching the first section and a fourth section matching the second section are respectively provided at the intersections of the first convex surface and the second convex surface with the lower surface of the upper template, and a second outer rounded corner structure matching the first inner rounded corner transition structure and a third outer rounded corner structure matching the second inner rounded corner transition structure are respectively provided at the corners of the first convex surface and the second convex surface with the side wall of the extrusion boss, and a third inner rounded corner structure matching the first outer rounded corner transition structure is provided at the corner of the side wall of the extrusion boss with the lower surface of the upper template.

[0013] Furthermore, the intersection points of both ends of the extrusion ridge are respectively provided with a triangular second convex block matched with the first concave block and arranged along the thickness direction of the lower template, and a second concave block matched with the first convex block and arranged along the length direction of the lower template.

[0014] Furthermore, the multiple groups of first positioning bolt holes, the multiple groups of second positioning bolt holes and the multiple groups of extrusion bolts are all two groups, the two groups of first positioning bolt holes are blind holes, the two groups of second positioning bolt holes are through holes, the two groups of first positioning bolt holes are relatively arranged at the two ends of the upper surface of the lower template of the extrusion groove; the two groups of second positioning bolt holes are relatively arranged at the two ends of the lower surface of the extrusion boss, and the two groups of extrusion bolts pass through the two groups of second positioning bolt holes and are tightened in the two groups of first positioning bolt holes.

[0015] According to another aspect of the present invention, a method for forming titanium alloy sawtooth frame parts for aircraft is provided, the forming method comprising:

[0016] Fix the lower template on the placement platform of the punching machine;

[0017] Placing two preheated plate-shaped blanks in the extrusion grooves respectively, with one side of the two plate-shaped blanks placed on the first concave surface and the second concave surface of the extrusion groove respectively;

[0018] Placing the upper template on the lower template accordingly;

[0019] Pass the extrusion bolts through the positioning bolt holes of the upper template and tighten them into the positioning bolt holes of the lower template to push the upper template toward the lower template to flanging the plate blank;

[0020] After cooling for a period of time, loosen the extrusion bolts on the outside of the lower template and take out the parts that have been flanging;

[0021] Use a cutting machine to cut the flanged parts into the required serrated shape.

[0022] The flanging die of titanium alloy serrated frame parts for aircraft of the technical solution of the present invention comprises: a lower template, an upper template and an extrusion bolt; an irregular polygonal extrusion groove is provided on the upper surface of the lower template, and a positioning ridge is provided at the center of the bottom surface of the extrusion groove along the symmetry axis in the length direction of the upper surface of the lower template to divide the bottom surface of the extrusion groove into a first concave surface and a second concave surface, and the first concave surface and the second concave surface are symmetrically distributed with the central ridge, and a plurality of groups of first positioning bolt holes are provided at opposite ends along the length direction; an irregular polygonal extrusion boss is provided on the lower surface of the upper template to match the extrusion groove, and a positioning ridge is provided at the center of the lower surface of the extrusion boss to match the positioning ridge and to extend along the upper surface An extrusion ridge extending along the longitudinal axis of symmetry on the lower surface of the template divides the lower surface of the extrusion boss into a first convex surface matching the first concave surface and a second convex surface matching the second concave surface. The first and second convex surfaces are symmetrically distributed along the extrusion ridge. Multiple sets of second positioning bolt holes are formed at opposite ends of the upper template along its length, matching the multiple sets of first positioning bolt holes and extending through the thickness of the upper template. Multiple sets of extrusion bolts are correspondingly positioned within the multiple sets of first positioning bolt holes and the multiple sets of second positioning bolt holes. The multiple sets of extrusion bolts are used to push the upper template toward the lower template to compress the flange of the plate-shaped part placed between the extrusion groove and the extrusion boss. This solves the problem that conventional templates in the prior art cannot produce titanium alloy zigzag frame parts that meet the requirements. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] 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:

[0024] Figure 1 This is a schematic structural diagram of a titanium alloy sawtooth frame part flanging die for aircraft, which may be selected according to an embodiment of the present invention;

[0025] Figure 2 This is a front view of a lower template of a titanium alloy sawtooth frame part flanging die for aircraft, which can be selected according to an embodiment of the present invention;

[0026] Figure 3 This is a top view of a lower template of a flanging die for titanium alloy serrated frame parts for aircraft, which may be selected according to an embodiment of the present invention;

[0027] Figure 4 This is an axonometric view of an upper template of a flanging die for titanium alloy sawtooth frame parts for aircraft, which may be selected according to an embodiment of the present invention;

[0028] Figure 5This is a front view of an upper template of a flanging die for a titanium alloy sawtooth frame part for aircraft, which may be selected according to an embodiment of the present invention;

[0029] Figure 6 This is a top view of an upper template of a flanging die for titanium alloy serrated frame parts for aircraft, which may be selected according to an embodiment of the present invention;

[0030] Figure 7 The present invention is an axial view of an upper template of a flanging die for titanium alloy serrated frame parts for aircraft, which can be selected according to an embodiment of the present invention.

[0031] The above drawings include the following reference numerals:

[0032] 10. Lower template; 11. Extrusion groove; 12. Positioning ridge; 13. First concave surface; 14. Second concave surface; 15. First positioning bolt hole; 20. Upper template; 21. Extrusion boss; 22. Extrusion ridge; 23. First convex surface; 24. Second convex surface; 25. Second positioning bolt hole; 30. Extrusion bolt. DETAILED DESCRIPTION

[0033] 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.

[0034] According to an embodiment of the present invention, a titanium alloy sawtooth frame part flanging die for aircraft is provided. Figure 1As shown, it includes a lower template 10, an upper template 20 and an extrusion bolt 30; an irregular polygonal extrusion groove 11 is provided on the upper surface of the lower template 10, and a positioning ridge 12 is provided at the center of the bottom surface of the extrusion groove 11 along the longitudinal axis of the upper surface of the lower template 10 to divide the bottom surface of the extrusion groove 11 into a first concave surface 13 and a second concave surface 14. The first concave surface 13 and the second concave surface 14 are symmetrically distributed with the central ridge. The lower template 10 is provided with multiple groups of first positioning bolt holes 15 at opposite ends along the longitudinal direction; an irregular polygonal extrusion boss 21 is provided on the lower surface of the upper template 20 to match the extrusion groove 11, and a positioning ridge 12 is provided at the center of the lower surface of the extrusion boss 21 to match the positioning ridge 12 and along the longitudinal axis of the lower surface of the upper template 20. The extended extrusion ridge 22 divides the lower surface of the extrusion boss 21 into a first convex surface 23 matching the first concave surface 13 and a second convex surface 24 matching the second concave surface 14. The first convex surface 23 and the second convex surface 24 are symmetrically distributed with the extrusion ridge 22. The upper template 20 is provided with multiple groups of second positioning bolt holes 25 at opposite ends along the length direction, which match the multiple groups of first positioning bolt holes 15 one by one and penetrate the upper template 20 along the thickness direction; there are multiple groups of extrusion bolts 30, and the multiple groups of extrusion bolts 30 are correspondingly arranged in the multiple groups of first positioning bolt holes 15 and the multiple groups of second positioning bolt holes 25; the multiple groups of extrusion bolts 30 are used to push the upper template 20 toward the lower template 10 to extrude the flange of the plate-type part placed between the extrusion groove 11 and the extrusion boss 21. When the flanging die of titanium alloy serrated frame parts for aircraft of this embodiment is used, the lower template 10 is first fixed on the placement platform of the punching machine, the pre-heated plate blank to be flanging is placed in the extrusion groove 11, and then the upper template 20 is placed on the plate blank accordingly. Thereafter, the multiple groups of extrusion bolts 30 arranged in the multiple groups of second positioning bolt holes 25 are tightened into the multiple groups of first positioning bolt holes 14 in sequence. The multiple groups of extrusion bolts 30 push the upper template 20 toward the lower template 10 to extrude the plate blank placed between the extrusion groove 11 and the extrusion boss 21 to flange. After fixing and cooling for a period of time, the multiple groups of extrusion bolts 30 are loosened to the outside of the lower template 10, the parts that have been flanging are taken out, and then a cutting machine is used to cut the flanging-formed parts into the required serrated shape. The template of the present invention is cleverly designed, simple and convenient to operate, highly efficient, and easy to transport. It can effectively process difficult-to-process titanium alloy plates and further press out a step structure on the plates, solving the problem in the prior art that traditional templates cannot process titanium alloy serrated frame parts for aircraft that meet the requirements.

[0035] In specific implementation, the extrusion groove 11 is a through groove extending to both sides along the width direction of the lower template 10 with the positioning ridge 12 as the center, and the extrusion boss 21 is extended to both sides along the width direction of the upper template 20 with the extrusion ridge 22 as the center until it is flush with both sides of the upper template 20.

[0036] Further, if Figure 2 、 Figure 3 and Figure 4 As shown, the height of the intersection points of the positioning ridge 12 and the upper surface of the lower template 10 at both ends are equal, the positioning ridge 12 is an arc-shaped structure with equal heights at both ends and a depression in the middle, the intersection line of the first concave surface 13 and the second concave surface 14 with the upper surface of the lower template 10 and the height of the intersection points at both ends are equal, and the height of the corners of the first concave surface 13 and the second concave surface 14 and the side walls of the extrusion groove 11 are lower than the height of the intersection points at both ends.

[0037] Furthermore, the intersections of the first and second concave surfaces 13, 14 with the upper surface of the lower template 10 are respectively provided with first and second tangent surfaces. The corners between the first and second concave surfaces 13, 14 and the sidewalls of the extrusion groove 11 are respectively provided with first and second inner fillet transition structures. The corners between the sidewalls of the extrusion groove 11 and the upper surface of the lower template 10 are provided with first outer fillet transition structures. This effectively avoids the problem of cracking and breaking of the mold and blank during the stamping process.

[0038] Furthermore, at the intersection points of both ends of the positioning ridge 12 , a triangular first concave block arranged along the thickness direction of the lower template 10 and a first convex block arranged along the length direction of the lower template 10 are respectively provided.

[0039] When implementing it specifically, Figure 5 、 Figure 6 and Figure 7 As shown, the heights of the intersection points of the extrusion ridge 22 and the lower surface of the upper template 20 at both ends are equal. The extrusion ridge 22 is an arc-shaped structure with equal heights at both ends and a depression in the middle. The intersection lines of the first convex surface 23 and the second convex surface 24 with the lower surface of the upper template 20 and the intersection points at both ends are equal. The heights of the corners of the first convex surface 23 and the second convex surface 24 with the side walls of the extrusion boss 21 are lower than the heights of the intersection points at both ends.

[0040] Furthermore, the intersections of the first convex surface 23 and the second convex surface 24 with the lower surface of the upper template 20 are respectively provided with a third section matching the first section and a fourth section matching the second section. The corners of the first convex surface 23 and the second convex surface 24 with the side wall of the extrusion boss 21 are respectively provided with a second outer rounded corner structure matching the first inner rounded corner transition structure and a third outer rounded corner structure matching the second inner rounded corner transition structure. The corners of the side wall of the extrusion boss 21 with the lower surface of the upper template 20 are provided with a third inner rounded corner structure matching the first outer rounded corner transition structure. This effectively avoids the problem of cracking and breaking of the mold and blank during the stamping process.

[0041] Furthermore, the intersection points of both ends of the extrusion ridge 22 are respectively provided with a triangular second convex block matched with the first concave block and arranged along the thickness direction of the lower template 10 and a second concave block matched with the first convex block and arranged along the length direction of the lower template 10.

[0042] During specific implementation, there are two groups of multiple first positioning bolt holes 15, multiple groups of second positioning bolt holes 25 and multiple groups of extrusion bolts 30. The two groups of first positioning bolt holes 15 are blind holes, and the two groups of second positioning bolt holes 25 are through holes. The two groups of first positioning bolt holes 15 are relatively arranged at the two ends of the upper surface of the lower template 10 of the extrusion groove 11; the two groups of second positioning bolt holes 25 are relatively arranged at the two ends of the lower surface of the extrusion boss 21, and the two groups of extrusion bolts 30 pass through the two groups of second positioning bolt holes 25 and are tightened in the two groups of first positioning bolt holes 15.

[0043] According to another embodiment of the present invention, a method for forming a titanium alloy sawtooth frame part for aircraft includes:

[0044] Fix the lower template on the placement platform of the punching machine;

[0045] Placing two preheated plate-shaped blanks in the extrusion grooves respectively, with one side of the two plate-shaped blanks placed on the first concave surface and the second concave surface of the extrusion groove respectively;

[0046] Placing the upper template on the lower template accordingly;

[0047] Pass the extrusion bolts through the positioning bolt holes of the upper template and tighten them into the positioning bolt holes of the lower template to push the upper template toward the lower template to flanging the plate blank;

[0048] After cooling for a period of time, loosen the extrusion bolts on the outside of the lower template and take out the parts that have been flanging;

[0049] Use a cutting machine to cut the flanged parts into the required serrated shape.

[0050] When the flanging die of titanium alloy serrated frame parts for aircraft of this embodiment is used, the lower template 10 is first fixed on the placement platform of the punching machine, the pre-heated plate blank to be flanging is placed in the extrusion groove 11, and then the upper template 20 is placed on the plate blank accordingly. Thereafter, the multiple groups of extrusion bolts 30 arranged in the multiple groups of second positioning bolt holes 25 are tightened into the multiple groups of first positioning bolt holes 14 in sequence. The multiple groups of extrusion bolts 30 push the upper template 20 toward the lower template 10 to extrude the plate blank placed between the extrusion groove 11 and the extrusion boss 21 to flange. After fixing and cooling for a period of time, the multiple groups of extrusion bolts 30 are loosened to the outside of the lower template 10, the parts that have been flanging are taken out, and then a cutting machine is used to cut the flanging-formed parts into the required serrated shape. The template of the present invention is cleverly designed, simple and convenient to operate, highly efficient, and easy to transport. It can effectively process difficult-to-process titanium alloy plates and further press out a step structure on the plates, solving the problem in the prior art that traditional templates cannot process titanium alloy serrated frame parts for aircraft that meet the requirements.

[0051] 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 sawtooth frame part flanging die for aircraft, characterized in that: include: A lower template (10), wherein the upper surface of the lower template (10) is provided with an irregular polygonal extrusion groove (11), a positioning ridge (12) extending along the symmetry axis of the upper surface of the lower template (10) in the longitudinal direction is provided at the center of the bottom surface of the extrusion groove (11) to divide the bottom surface of the extrusion groove (11) into a first concave surface (13) and a second concave surface (14), the first concave surface (13) and the second concave surface (14) are symmetrically distributed with respect to the positioning ridge (12), and a plurality of first positioning bolt holes (15) are provided at opposite ends of the lower template (10) in the longitudinal direction; An upper template (20), wherein the lower surface of the upper template (20) is provided with an irregular polygonal extrusion boss (21) matching the extrusion groove (11), an extrusion ridge (22) matching the positioning ridge (12) and extending along the symmetric axis of the lower surface of the upper template (20) in the length direction is provided at the center of the lower surface of the extrusion boss (21) to divide the lower surface of the extrusion boss (21) into a first convex surface (23) matching the first concave surface (13) and a second convex surface (24) matching the second concave surface (14), the first convex surface (23) and the second convex surface (24) being symmetrically distributed with the extrusion ridge (22), and a plurality of groups of second positioning bolt holes (25) matching the plurality of groups of first positioning bolt holes (15) and penetrating the upper template (20) in the thickness direction are provided at opposite ends of the upper template (20) in the length direction; 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 the first positioning bolt holes (15) and the multiple groups of the second positioning bolt holes (25); the multiple groups of extrusion bolts (30) are used to push the upper template (20) toward the lower template (10) to extrude the flange of the plate-shaped part placed between the extrusion groove (11) and the extrusion boss (21).

2. The titanium alloy sawtooth frame part flanging die for aircraft according to claim 1, characterized in that: The extrusion groove (11) is a through groove extending to both sides along the width direction of the lower template (10) with the positioning ridge (12) as the center, and the extrusion boss (21) is extended to both sides along the width direction of the upper template (20) with the extrusion ridge (22) as the center until it is flush with both sides of the upper template (20).

3. The titanium alloy sawtooth frame part flanging die for aircraft according to claim 2, characterized in that The positioning ridge (12) and the upper surface of the lower template (10) have the same height at their two ends of the intersection point. The positioning ridge (12) is an arc-shaped structure with equal heights at both ends and a depression in the middle. The intersection lines of the first concave surface (13) and the second concave surface (14) with the upper surface of the lower template (10) are equal in height to the intersection points at both ends. The heights of the first concave surface (13) and the second concave surface (14) at the corners of the side walls of the extrusion groove (11) are lower than the heights of the intersection points at both ends.

4. The titanium alloy sawtooth frame part flanging die for aircraft according to claim 3, characterized in that: A first cut surface and a second cut surface are respectively provided at the intersections of the first concave surface (13) and the second concave surface (14) with the upper surface of the lower template (10); a first inner rounded corner transition structure and a second inner rounded corner transition structure are respectively provided at the corners of the first concave surface (13) and the second concave surface (14) with the side wall of the extrusion groove (11); and a first outer rounded corner transition structure is provided at the corner of the side wall of the extrusion groove (11) with the upper surface of the lower template (10).

5. The titanium alloy sawtooth frame part flanging die for aircraft according to claim 4, characterized in that: The intersection points of both ends of the positioning ridge (12) are respectively provided with a triangular first concave block arranged along the thickness direction of the lower template (10) and a first convex block arranged along the length direction of the lower template (10).

6. The titanium alloy sawtooth frame part flanging die for aircraft according to claim 5, characterized in that: The heights of the intersection points of the extrusion ridge (22) and the lower surface of the upper template (20) at both ends are equal, and the extrusion ridge (22) is an arc-shaped structure with equal heights at both ends and a depression in the middle. The intersection lines of the first convex surface (23) and the second convex surface (24) with the lower surface of the upper template (20) are equal to the heights of the intersection points at both ends, and the heights of the corners of the first convex surface (23) and the second convex surface (24) with the side walls of the extrusion boss (21) are lower than the heights of the intersection points at both ends.

7. The titanium alloy sawtooth frame part flanging die for aircraft according to claim 6, characterized in that: A third section matching the first section and a fourth section matching the second section are respectively provided at the intersections of the first convex surface (23) and the second convex surface (24) with the lower surface of the upper template (20); a second outer rounded corner structure matching the first inner rounded corner transition structure and a third outer rounded corner structure matching the second inner rounded corner transition structure are respectively provided at the corners of the first convex surface (23) and the second convex surface (24) with the side wall of the extrusion boss (21); and a third inner rounded corner structure matching the first outer rounded corner transition structure is provided at the corner of the side wall of the extrusion boss (21) with the lower surface of the upper template (20).

8. The titanium alloy sawtooth frame part flanging die for aircraft according to claim 7, characterized in that: The intersection points of both ends of the extrusion ridge (22) are respectively provided with a triangular second convex block matched with the first concave block and arranged along the thickness direction of the lower template (10), and a second concave block matched with the first convex block and arranged along the length direction of the lower template (10).

9. The titanium alloy sawtooth frame part flanging die for aircraft according to claim 1, characterized in that: The plurality of groups of the first positioning bolt holes (15), the plurality of groups of the second positioning bolt holes (25) and the plurality of groups of the extrusion bolts (30) are all two groups, the two groups of the first positioning bolt holes (15) are all blind holes, the two groups of the second positioning bolt holes (25) are through holes, the two groups of the first positioning bolt holes (15) are relatively arranged at the two ends of the upper surface of the lower template (10) of the extrusion groove (11); the two groups of the second positioning bolt holes (25) are relatively arranged at the two ends of the lower surface of the extrusion boss (21), and the two groups of the extrusion bolts (30) pass through the two groups of the second positioning bolt holes (25) and are tightened in the two groups of the first positioning bolt holes (15).

10. A method for forming titanium alloy sawtooth frame parts for aircraft, characterized in that: The forming method is applied to a flanging die for titanium alloy serrated frame parts for aircraft according to any one of claims 1 to 9, and the forming method comprises: Fix the lower template on the placement platform of the punching machine; Placing two preheated plate-shaped blanks in the extrusion grooves respectively, so that one side of the two plate-shaped blanks is placed on the first concave surface and the second concave surface of the extrusion groove respectively; Placing the upper template on the lower template accordingly; Passing the extrusion bolts through the positioning bolt holes of the upper template and tightening them into the positioning bolt holes of the lower template to push the upper template toward the lower template to flanging the plate blank; After being fixed and cooled for a period of time, the extrusion bolts are loosened toward the outside of the lower template, and the parts with completed flanging are taken out; The flanging formed part is cut into the required serrated shape using a cutting machine.

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