Flanging Die and Forming Method for Titanium Alloy Multi-curved Multi-layer Step Structure Parts for Aircraft

Abstract

The present invention provides a flanging die and a forming method for a titanium alloy multi-curved multi-layer stepped structure part for an aircraft. The flanging die includes a lower template, a blank holder, positioning bolts, an upper template, and extrusion bolts. The upper surface of the lower template is a curved surface structure, provided with irregularly shaped extrusion grooves and two groups of first extrusion bolt holes. The outer shapes of the two blank holders respectively match the outer shapes of the two material placement surfaces, and the blank holders are provided with two groups of positioning bolt holes. Two groups of positioning bolts are matched and inserted into the two groups of first extrusion bolt holes and the two groups of positioning bolt holes. The lower surface of the upper template is provided with extrusion bosses and two groups of second extrusion bolt holes. The two groups of extrusion bolts are used to push the upper template to move downward toward the lower template so that the extrusion bosses extrude the part blank placed between the lower template and the blank holder for flanging. It solves the problem that the traditional templates in the prior art cannot process titanium alloy multi-curved multi-layer stepped structure parts for aircraft that meet the requirements.

Description

Technical Field

[0001] The present invention relates to the technical field of titanium alloy part processing templates for aircraft, and in particular, to a flanging die and forming method for a titanium alloy multi-curved multi-layer stepped structure part for an aircraft. Background Technique

[0002] An aircraft engine is a highly complex and precise thermal machine. As the heart of an aircraft, it is not only the power for the aircraft to fly but also an important driving force for the development of the aviation industry. Every important change in the history of human aviation is inseparable from the technological progress of aircraft engines. And the engine nacelle, as the compartment for installing the aircraft engine, is also one of the most important core components in the aircraft propulsion system. The cost required for the engine nacelle accounts for about one-fourth of the total engine. At present, there is still a large gap between China and foreign advanced manufacturing technologies in the field of engine nacelles.

[0003] At present, during the manufacturing process of engine nacelles, a large number of titanium alloy plate stepped parts are required to manufacture the outer shell of the engine nacelle. The titanium alloy multi-curved multi-layer stepped structure part for an aircraft is a flanging part with a stepped structure and an arc structure. This flanging part needs to be pressed out with an arc structure. The casting of titanium alloy parts is mainly by stamping forming. However, titanium alloy parts have the defects of difficult bending and difficult shaping, and have high requirements for processing technology and template equipment. Existing processing templates are difficult to process titanium alloy multi-curved multi-layer stepped structure parts that meet the requirements for aircraft, so special dedicated templates need to be used. Summary of the Invention

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

[0005] To achieve the above object, the present invention provides a flanging die and forming method for a titanium alloy multi-curved multi-layer stepped structure part for an aircraft.

[0006] To achieve the above object, according to one aspect of the present invention, there is provided a flanging die for a titanium alloy multi-curved multi-layer stepped structure part for an aircraft, including a lower template, a blank holder, positioning bolts, an upper template, and extrusion bolts; the upper surface of the lower template is a curved surface structure, and an irregularly shaped extrusion groove is provided at the center of the upper surface of the lower template. A first stepped mechanism and a second stepped mechanism are respectively provided at one end of the bottom surface of the extrusion groove along the length direction and on both side walls of the extrusion groove along the thickness direction of the lower template. A positioning ridge extending along the symmetry axis of 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, and the first concave surface and the second concave surface are symmetrically distributed with respect to the center ridge; two material placement surfaces are formed in two regions adjacent to the extrusion groove along the width direction of the upper surface of the lower template, and two sets of first extrusion bolt holes are correspondingly provided on the two material placement surfaces; there are two blank holders, and the outer shapes of the two blank holders respectively match the outer shapes of the two material placement surfaces. Two sets of positioning bolt holes are provided on the blank holders, which correspond to and match some of the first extrusion bolt holes in the two sets of first extrusion bolt holes one by one; the positioning bolts are two sets, and the two sets of positioning bolts are matched and inserted into some of the first extrusion bolt holes in the two sets of first extrusion bolt holes and some of the positioning bolt holes in the two sets of positioning bolt holes; the two sets of positioning bolts are used to push the blank holder plate towards the lower template to fix the part blank placed between the extrusion groove and the blank holder; the lower surface of the upper template is a planar structure matching the upper surface of the blank holder, and an extrusion boss matching the extrusion groove is provided on the lower surface of the upper template. A third stepped structure matching the first stepped mechanism is provided at one end of the lower surface of the extrusion boss along the length direction, and fourth stepped structures 3 matching the second stepped mechanism are provided on both side walls of the extrusion boss; an extrusion ridge matching the positioning ridge and extending along the symmetry axis of the length direction of the lower surface of the upper template is provided at the center of the lower surface of the extrusion boss 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, and the first convex surface and the second convex surface are symmetrically distributed with respect to the extrusion ridge; two pressing surfaces matching the material placement surfaces are formed in two regions adjacent to the extrusion boss along the width direction of the lower surface of the upper template, and two sets of second extrusion bolt holes corresponding to and matching the other part of the first extrusion bolt holes in the two sets of first extrusion bolt holes are provided on the two pressing surfaces; the extrusion bolts are two sets, and the two sets of extrusion bolts are matched and inserted into the other part of the first extrusion bolt holes in the two sets of first extrusion bolt holes, the other part of the positioning bolt holes in the positioning bolt holes, and the two sets of second extrusion bolt holes; the two sets of extrusion bolts are used to push the upper template towards the lower template so that the extrusion boss extrudes the part blank placed between the lower template and the blank holder to be flanged.

[0007] Specifically, during implementation, the extrusion groove is a fish-shaped through groove extending along the length direction of the lower template; both ends of the extrusion boss extend along the length direction of the upper template to be flush with both ends of the upper template.

[0008] Further, the second stepped structure extends towards both sides along the thickness direction of the extrusion groove to the bottom surface of the extrusion groove and the upper surface of the lower template, and the fourth stepped structure extends towards both sides along the thickness direction of the extrusion boss to the lower surface of the extrusion boss and the lower surface of the upper template.

[0009] Further, the height of the positioning ridge at one end where the first stepped structure is located is lower than the height of the upper surface of the lower template, and the height of the other end of the positioning ridge is higher than the height of the upper surface of the lower template.

[0010] Further, a triangular positioning platform is provided at the other end of the positioning ridge; an extrusion platform matching the positioning platform is provided on the extrusion ridge.

[0011] Further, first inner fillet transition structures are respectively provided at the corners of the bottom surface of the extrusion groove and the two side walls of the extrusion groove, and first outer fillet transition structures are respectively provided at the corners of the two side walls of the extrusion groove and the upper surface of the lower template; second outer fillet structures matching the first inner fillet transition structures are respectively provided at the corners of the lower bottom surface of the extrusion boss and the two side walls of the extrusion boss, and second inner fillet transition structures matching the first outer fillet transition structures are respectively provided at the corners of the two side walls of the extrusion boss and the lower surface of the extrusion boss.

[0012] During specific implementation, a positioning cutting surface extending along the width direction is provided at one end of the upper surface of the lower template opposite to the first stepped structure; an extrusion cutting surface matching the positioning cutting surface is provided on the lower surface of the upper template.

[0013] Further, two groups of first extrusion bolt holes are correspondingly provided along the edge of the extrusion groove on two material placement surfaces; two groups of second extrusion bolt holes are correspondingly provided along the edge of the extrusion boss on two material pressing surfaces.

[0014] Further, both groups of first extrusion bolt holes are blind holes, both groups of positioning bolt holes and both groups of second extrusion bolt holes are through holes, and two groups of positioning bolts correspondingly pass through a part of the positioning bolt holes of the two groups of positioning bolt holes and are tightened in a part of the first extrusion bolt holes of the two groups of first extrusion bolt holes; two groups of extrusion bolts correspondingly pass through the other part of the positioning bolt holes of the two groups of second extrusion bolt holes and the positioning bolt holes and are tightened in the other part of the first extrusion bolt holes of the two groups of first extrusion bolt holes.

[0015] According to another aspect of the present invention, a forming method for a titanium alloy multi-curved multi-layer stepped structure part for an aircraft is provided, and the forming method includes:

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

[0017] Place two pre-heated plate-shaped blanks in the extrusion groove respectively, so that one side surface of each of the two plate-shaped blanks is respectively placed on the first concave surface and the second concave surface of the extrusion groove;

[0018] Place two blank holding blocks correspondingly on two material placing surfaces;

[0019] Pass positioning bolts through some of the positioning bolt holes of the blank holding blocks and screw them tightly into the extrusion bolt holes of the lower template to push the blank holding blocks towards the lower template to fix the plate-shaped blank;

[0020] Place the upper template correspondingly on the lower template and the blank holding blocks;

[0021] Pass extrusion bolts through the extrusion bolt holes of the upper template and the other part of the positioning bolt holes of the blank holding blocks and screw them tightly into the extrusion bolt holes of the lower template to push the upper template towards the lower template to flang the plate-shaped blank;

[0022] After fixing and cooling for a period of time, loosen the extrusion bolts and positioning bolts outwards from the lower template in sequence, and take out the parts that have been flanged;

[0023] Use a cutting machine to cut out the required parts from the flanged and formed parts

[0024] The flanging die for the titanium alloy multi-curved multi-layer stepped structure part for aircraft of the technical solution of the present invention includes: a lower template, a blank holder, positioning bolts, an upper template, and extrusion bolts; the upper surface of the lower template is a curved surface structure, and an irregularly shaped extrusion groove is provided at the center of the upper surface of the lower template. At one end of the bottom surface of the extrusion groove along the length direction and on both side walls of the extrusion groove along the thickness direction of the lower template, a first stepped mechanism and a second stepped mechanism are respectively provided. A positioning ridge extending along the symmetry axis of 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, and the first concave surface and the second concave surface are symmetrically distributed with respect to the central ridge; two material placement surfaces are formed in two regions adjacent to the extrusion groove along the width direction of the upper surface of the lower template, and two groups of first extrusion bolt holes are correspondingly provided on the two material placement surfaces; there are two blank holders, and the outer shapes of the two blank holders respectively match the outer shapes of the two material placement surfaces. Two groups of positioning bolt holes corresponding to and matching with some of the first extrusion bolt holes in the two groups of first extrusion bolt holes are provided on the blank holders; there are two groups of positioning bolts, and the two groups of positioning bolts are matched and inserted into the two groups of first extrusion bolt holes and the two groups of positioning bolt holes; the two groups of positioning bolts are used to push the blank holder plate towards the lower template to fix the part blank placed between the extrusion groove and the blank holder; the lower surface of the upper template is a planar structure matching the upper surface of the blank holder, and an extrusion boss matching the extrusion groove is provided on the lower surface of the upper template. At one end of the lower surface of the extrusion boss along the length direction, a third stepped structure matching the first stepped mechanism is provided, and fourth stepped structures matching the second stepped mechanism are provided on both side walls of the extrusion boss. A pressing ridge extending along the symmetry axis of the length direction of the lower surface of the upper template and matching the positioning ridge is provided at the center of the lower surface of the extrusion boss 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, and the first convex surface and the second convex surface are symmetrically distributed with respect to the pressing ridge; two pressing surfaces matching the material placement surfaces are formed in two regions adjacent to the extrusion boss along the width direction of the lower surface of the upper template, and two groups of second extrusion bolt holes corresponding to and matching with the other part of the first extrusion bolt holes in the two groups of first extrusion bolt holes are provided on the two pressing surfaces; there are two groups of extrusion bolts, and the two groups of extrusion bolts are matched and inserted into the two groups of first extrusion bolt holes and the two groups of second extrusion bolt holes; the two groups of extrusion bolts are used to push the upper template towards the lower template so that the extrusion boss extrudes the part blank placed between the lower template and the blank holder to be flanged. It solves the problem that the traditional template in the prior art cannot process the titanium alloy multi-curved multi-layer stepped structure part for aircraft that meets the requirements. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] The specification drawings forming a part of this application are used to provide a further understanding of the present invention. The schematic embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation to the present invention. In the drawings:

[0026] Figure 1 It is a schematic structural diagram of a flanging die for a titanium alloy multi-curved multi-layer stepped structure part for an aircraft according to an embodiment of the present invention;

[0027] Figure 2 It is a front view of the lower die of a flanging die for a titanium alloy multi-curved multi-layer stepped structure part for an aircraft according to an embodiment of the present invention;

[0028] Figure 3 It is a left view of the lower die of a flanging die for a titanium alloy multi-curved multi-layer stepped structure part for an aircraft according to an embodiment of the present invention;

[0029] Figure 4 It is a front view of the lower die of a flanging die for a titanium alloy multi-curved multi-layer stepped structure part for an aircraft according to an embodiment of the present invention;

[0030] Figure 5 It is an axonometric view of the lower die of a flanging die for a titanium alloy multi-curved multi-layer stepped structure part for an aircraft according to an embodiment of the present invention;

[0031] Figure 6 It is a front view of the blank holder of a flanging die for a titanium alloy multi-curved multi-layer stepped structure part for an aircraft according to an embodiment of the present invention;

[0032] Figure 7 It is a left view of the blank holder of a flanging die for a titanium alloy multi-curved multi-layer stepped structure part for an aircraft according to an embodiment of the present invention;

[0033] Figure 8 It is a top view of the blank holder of a flanging die for a titanium alloy multi-curved multi-layer stepped structure part for an aircraft according to an embodiment of the present invention;

[0034] Figure 9 It is an axonometric view of the blank holder of a flanging die for a titanium alloy multi-curved multi-layer stepped structure part for an aircraft according to an embodiment of the present invention;

[0035] Figure 10 It is a front view of the upper die of a flanging die for a titanium alloy multi-curved multi-layer stepped structure part for an aircraft according to an embodiment of the present invention;

[0036] Figure 11 It is a left view of the upper die of a flanging die for a titanium alloy multi-curved multi-layer stepped structure part for an aircraft according to an embodiment of the present invention;

[0037] Figure 12 It is a top view of the upper die of a flanging die for a titanium alloy multi-curved multi-layer stepped structure part for an aircraft according to an embodiment of the present invention;

[0038] Figure 13 An axonometric view of the upper die of a flanging die for a titanium alloy multi-curved multi-layer stepped structure part for an aircraft according to an embodiment of the present invention.

[0039] Among them, the above-mentioned drawings include the following reference numerals:

[0040] 10. Lower template; 11. Extrusion groove; 12. First stepped mechanism; 13. Second stepped mechanism; 14. Positioning ridge; 15. Material placement surface; 16. First extrusion bolt hole; 17. Positioning platform; 18. Positioning cutting surface; 20. Pressure block; 21. Positioning bolt hole; 30. Positioning bolt; 40. Upper template; 41. Extrusion boss; 42. Third stepped structure; 43. Fourth stepped structure; 44. Extrusion ridge; 45. Pressure material surface; 46. Second extrusion bolt hole; 47. Extrusion platform; 48. Extrusion cutting surface; 50. Extrusion bolt. Specific embodiments

[0041] It should be noted that, without conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the drawings and in conjunction with the embodiments.

[0042] A flanging die for a titanium alloy multi-curved multi-layer stepped structure part for an aircraft according to an embodiment of the present invention, such as Figure 1 、 Figure 10 、 Figure 11 、 Figure 12 and Figure 13As shown in the figure, it includes a lower template 10, a blank holding block 20, a positioning bolt 30, an upper template 40, and an extrusion bolt 50; the upper surface of the lower template 10 is a curved surface structure, and an irregularly shaped extrusion groove 11 is provided at the center of the upper surface of the lower template 10. At one end of the bottom surface of the extrusion groove 11 along the length direction and on both side walls of the extrusion groove 11 along the thickness direction of the lower template 10, a first step mechanism 12 and a second step mechanism 13 are respectively provided. A positioning ridge 14 extending along the symmetry axis of the length direction of the upper surface of the lower template 10 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 and a second concave surface, and the first concave surface and the second concave surface are symmetrically distributed with respect to the central ridge; two feeding surfaces 15 are formed in two regions adjacent to the extrusion groove 11 along the width direction of the upper surface of the lower template 10, and two groups of first extrusion bolt holes 16 are correspondingly provided on the two feeding surfaces 15; there are two blank holding blocks 20, and the outer shapes of the two blank holding blocks 20 respectively match the outer shapes of the two feeding surfaces 15. Two groups of positioning bolt holes 21 that correspond to and match some of the first extrusion bolt holes 16 in the two groups of first extrusion bolt holes 16 are provided on the blank holding blocks 20; the positioning bolts 30, there are two groups of positioning bolts 30, and the two groups of positioning bolts 30 are matched and inserted into a part of the first extrusion bolt holes 16 in the two groups of first extrusion bolt holes 16 and a part of the positioning bolt holes 21 in the two groups of positioning bolt holes 21; the two groups of positioning bolts 30 are used to push the two blank holding blocks towards the lower template 10 to fix the part blank placed between the extrusion groove 11 and the blank holding blocks 20; the lower surface of the upper template 40 is a planar structure that matches the upper surface of the blank holding block 20, and an extrusion boss 41 that matches the extrusion groove 11 is provided on the lower surface of the upper template 40. At one end of the lower surface of the extrusion boss 41 along the length direction, a third step structure 42 that matches the first step mechanism 12 is provided, and fourth step structures 43 that match the second step mechanism 13 are provided on both side walls of the extrusion boss 41. A pressing ridge 44 that matches the positioning ridge 14 and extends along the symmetry axis of the length direction of the lower surface of the upper template 40 is provided at the center of the lower surface of the extrusion boss 41 to divide the lower surface of the extrusion boss 41 into a first convex surface that matches the first concave surface and a second convex surface that matches the second concave surface, and the first convex surface and the second convex surface are symmetrically distributed with respect to the pressing ridge 44; two pressing surfaces 45 that match the feeding surfaces 15 are formed in two regions adjacent to the extrusion boss 41 along the width direction of the lower surface of the upper template 40, and two groups of second extrusion bolt holes 46 that correspond to and match the other part of the first extrusion bolt holes 16 in the two groups of first extrusion bolt holes 16 are provided on the two pressing surfaces 45; there are two groups of extrusion bolts 50, and the two groups of extrusion bolts 50 are matched and inserted into the other part of the first extrusion bolt holes 16 in the two groups of first extrusion bolt holes 16, the other part of the positioning bolt holes 21 in the positioning bolt holes 21, and the two groups of second extrusion bolt holes 46; the two groups of extrusion bolts 50 are used to push the upper template 40 towards the lower template 10 so that the extrusion boss 41 extrudes the part blank placed between the lower template 10 and the blank holding blocks 20 to turn the edge.When the flanging die for the titanium alloy multi-curved multi-layer stepped structure part for the aircraft in this embodiment is specifically used, first fix the lower template 10 on the placement platform of the stamping machine, place the two pre-heated plate-shaped blanks to be flanged in the extrusion grooves 11 respectively, and then place the two pressure blocks 20 on the two material placement surfaces 15 respectively. Fix the blanks in the extrusion grooves 11 by screwing the multiple positioning bolts 30 arranged in the positioning bolt holes 21 into the first extrusion bolt holes 16 in sequence. Then place the upper template 40 corresponding to the lower template 10 and the two pressure blocks 20, and screw the multiple extrusion bolts 50 arranged in the multiple second extrusion bolt holes 46 into the multiple first extrusion bolt holes 16 in sequence. The multiple extrusion bolts 50 push the upper template 40 to move downward toward the lower template 10 so that the extrusion bosses 41 extrude the part blank placed between the extrusion grooves 11 and the two pressure blocks 20 to be flanged. After fixing and cooling for a period of time, unscrew the multiple extrusion bolts 50 and the multiple positioning bolts 30 out of the lower template 10 in sequence, take out the parts that have been flanged, and then use a cutting machine to cut out the required parts from the two flanged parts. The template of the present invention is ingeniously designed and simple and convenient to operate, can effectively process the difficult-to-machine titanium alloy plate blanks, has high working efficiency, and solves the problem that the traditional templates in the prior art cannot process the titanium alloy multi-curved multi-layer stepped structure parts for aircraft that meet the requirements.

[0043] During specific implementation, as Figure 2 , Figure 3 , Figure 4 and Figure 5 shown, the extrusion groove 11 is a fish-shaped through groove extending along the length direction of the lower template 10; both ends of the extrusion boss 41 extend along the length direction of the upper template 40 to be flush with both ends of the upper template 40.

[0044] Furthermore, the second stepped structure extends to both sides along the thickness direction of the extrusion groove 11 to the bottom surface of the extrusion groove 11 and the upper surface of the lower template 10, and the fourth stepped structure 43 extends to both sides along the thickness direction of the extrusion boss 41 to the lower surface of the extrusion boss 41 and the lower surface of the upper template 40.

[0045] Furthermore, the height of the positioning ridge 14 at one end where the first stepped structure is located is lower than the height of the upper surface of the lower template 10, and the height of the other end of the positioning ridge 14 is higher than the height of the upper surface of the lower template 10.

[0046] Furthermore, as Figure 6 , Figure 7 , Figure 8 and Figure 9 shown, a triangular positioning platform 17 is provided at the other end of the positioning ridge 14; an extrusion platform 47 matching the positioning platform 17 is provided on the extrusion ridge 44.

[0047] Further, first inner fillet transition structures are respectively provided at the corners between the bottom surface of the extrusion groove 11 and the two side walls of the extrusion groove 11, and first outer fillet transition structures are respectively provided at the corners between the two side walls of the extrusion groove 11 and the upper surface of the lower template 10; second outer fillet structures matching the first inner fillet transition structures are respectively provided at the corners between the lower bottom surface of the extrusion boss 41 and the two side walls of the extrusion boss 41, and second inner fillet transition structures matching the first outer fillet transition structures are respectively provided at the corners between the two side walls of the extrusion boss 41 and the lower surface of the extrusion boss 41, effectively avoiding the problems of cracking and breaking of the mold and the blank during the stamping process.

[0048] During specific implementation, a positioning section 18 extending in the width direction is provided at one end of the upper surface of the lower template 10 opposite to the first step structure; an extrusion section 48 matching the positioning section 18 is provided on the lower surface of the upper template 40.

[0049] Further, two groups of first extrusion bolt holes 16 are correspondingly arranged on the two material placing surfaces 15 along the edge of the extrusion groove 11; two groups of second extrusion bolt holes 46 are correspondingly arranged on the two material pressing surfaces 45 along the edge of the extrusion boss 41.

[0050] Further, both groups of first extrusion bolt holes 16 are blind holes, both groups of positioning bolt holes 21 and both groups of second extrusion bolt holes 46 are through holes, and two groups of positioning bolts 30 correspondingly pass through a part of the positioning bolt holes 21 of the two groups of positioning bolt holes 21 and are tightened in a part of the first extrusion bolt holes 16 of the two groups of first extrusion bolt holes 16; two groups of extrusion bolts 50 correspondingly pass through the other part of the positioning bolt holes 21 of the two groups of second extrusion bolt holes 46 and the positioning bolt holes 21 and are tightened in the other part of the first extrusion bolt holes 16 of the two groups of first extrusion bolt holes 16.

[0051] According to a forming method of a titanium alloy multi-curved multi-layer stepped structure part for an aircraft according to another embodiment of the present invention, the forming method includes:

[0052] Fix the lower template on the placement platform of the stamping machine;

[0053] Place two pre-heated plate-shaped blanks in the extrusion groove respectively, so that one side surface of each of the two plate-shaped blanks is placed on the first concave surface and the second concave surface of the extrusion groove respectively;

[0054] Place two pressing blocks correspondingly on the two material placing surfaces;

[0055] Pass the positioning bolts through part of the positioning bolt holes of the pressing blocks and screw them into the extrusion bolt holes of the lower template to push the pressing blocks to move towards the lower template to fix the plate-shaped blanks;

[0056] Place the upper template correspondingly on the lower template and the pressing blocks;

[0057] Pass the extrusion bolt through the extrusion bolt hole of the upper template and the other positioning bolt hole of the blank holder, and screw it tightly into the extrusion bolt hole of the lower template to push the upper template towards the lower template to cause the flanging of the plate-shaped blank;

[0058] After fixing and cooling for a period of time, loosen the extrusion bolt and the positioning bolt outwards from the lower template in sequence, and take out the part that has been flanged;

[0059] Use a cutting machine to cut out the required part of the flanged and formed part

[0060] When the flanging die for the titanium alloy multi-curved multi-layer stepped structure part of the aircraft in this embodiment is specifically used, first fix the lower template 10 on the placement platform of the stamping machine, place the two pre-heated plate-shaped blanks to be flanged in the extrusion grooves 11 respectively, and then place the two blank holders 20 correspondingly on the two material placement surfaces 15. By screwing the multiple positioning bolts 30 arranged in the positioning bolt holes 21 into the first extrusion bolt holes 16 in sequence, the blanks are fixed in the extrusion grooves 11. Then place the upper template 40 correspondingly on the lower template 10 and the two blank holders 20, and screw the multiple extrusion bolts 50 arranged in the multiple second extrusion bolt holes 46 into the positioning bolt holes 21 and the multiple first extrusion bolt holes 16 in sequence. The multiple extrusion bolts 50 push the upper template 40 towards the lower template 10 to cause the extrusion boss 41 to extrude the part blank placed between the extrusion groove 11 and the two blank holders 20 for flanging. After fixing and cooling for a period of time, loosen the multiple extrusion bolts 50 and the multiple positioning bolts 30 outwards from the lower template 10 in sequence, take out the part that has been flanged, and then use a cutting machine to cut out the required part of the two flanged and formed parts. The template design of the present invention is ingenious, the operation is simple and convenient, it can effectively process the difficult-to-process titanium alloy plate blanks, the work efficiency is high, and it solves the problem that the traditional template in the prior art cannot process the titanium alloy multi-curved multi-layer stepped structure parts that meet the requirements for the aircraft.

[0061] The above are only the preferred embodiments of the present invention and are not used to limit the present invention. For those skilled in the art, the present invention can have various changes and modifications. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A flanging die for a titanium alloy multi-curved multi-layer stepped structure part used in an aircraft, characterized in that, Comprising: A lower template (10), the upper surface of the lower template (10) being a curved surface structure. An irregularly shaped extrusion groove (11) is provided at the center of the upper surface of the lower template (10). At one end of the bottom surface of the extrusion groove (11) along the length direction and on both side walls of the extrusion groove (11) along the thickness direction of the lower template (10), a first step mechanism (12) and a second step mechanism (13) are respectively provided. A positioning ridge (14) extending along the symmetry axis of the length direction of the upper surface of the lower template (10) 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 and a second concave surface, and the first concave surface and the second concave surface are symmetrically distributed with respect to the central ridge. Two material placement surfaces (15) are formed in two regions adjacent to the extrusion groove (11) along the width direction of the upper surface of the lower template (10). Two groups of first extrusion bolt holes (16) are correspondingly provided on the two material placement surfaces (15); Pressure blocks (20), there are two pressure blocks (20), and the outer shapes of the two pressure blocks (20) respectively match the outer shapes of the two material placement surfaces (15). Two groups of positioning bolt holes (21) that correspond to and match the two groups of first extrusion bolt holes (16) one by one are provided on the pressure blocks (20); Positioning bolts (30), there are two groups of positioning bolts (30), and the two groups of positioning bolts (30) are respectively inserted into a part of the two groups of first extrusion bolt holes (16) and a part of the two groups of positioning bolt holes (21) in a matching manner. The two groups of positioning bolts (30) are used to push the pressure plate towards the lower template (10) to fix the part blank placed between the extrusion groove (11) and the pressure blocks (20); The upper template (40), the lower surface of the upper template (40) is a planar structure matching the upper surface of the blank holder (20), the lower surface of the upper template (40) is provided with an extrusion boss (41) matching the extrusion groove (11), one end of the lower surface of the extrusion boss (41) along the length direction is provided with a third step structure (42) matching the first step mechanism (12), both side walls of the extrusion boss (41) are provided with a fourth step structure (43) matching the second step mechanism (13), the center of the lower surface of the extrusion boss (41) is provided with an extrusion ridge (44) matching the positioning ridge (14) and extending along the symmetry axis of the length direction of the lower surface of the upper template (40) to divide the lower surface of the extrusion boss (41) 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 with respect to the extrusion ridge (44); two regions adjacent to the extrusion boss (41) along the width direction of the lower surface of the upper template (40) form two blank holding surfaces (45) matching the blank placing surface (15), and two sets of second extrusion bolt holes (46) corresponding to and matching the other part of the first extrusion bolt holes (16) of the two sets of the first extrusion bolt holes (16) are provided on the two blank holding surfaces (45); Extrusion bolts (50), there are two sets of the extrusion bolts (50), and the two sets of the extrusion bolts (50) are respectively inserted through the other part of the first extrusion bolt holes (16) of the two sets of the first extrusion bolt holes (16), the other part of the positioning bolt holes (21) of the positioning bolt holes (21), and the two sets of the second extrusion bolt holes (46); the two sets of the extrusion bolts (50) are used to push the upper template (40) to move towards the lower template (10) so that the extrusion boss (41) extrudes the flanging of the part blank placed between the lower template (10) and the blank holder (20).

2. The flanging die for the titanium alloy multi-curved multi-layer stepped structure part for aircraft according to claim 1, characterized in that, The extrusion groove (11) is a fish-shaped through groove extending along the length direction of the lower template (10); both ends of the extrusion boss (41) extend along the length direction of the upper template (40) to be flush with both ends of the upper template (40).

3. The flanging die for the titanium alloy multi-curved multi-layer stepped structure part for aircraft according to claim 1, characterized in that, The second step structure extends to the bottom surface of the extrusion groove (11) and the upper surface of the lower template (10) respectively towards both sides along the thickness direction of the extrusion groove (11), and the fourth step structure (43) extends to the lower surface of the extrusion boss (41) and the lower surface of the upper template (40) respectively towards both sides along the thickness direction of the extrusion boss (41).

4. The flanging die for the titanium alloy multi-curved multi-layer stepped structure part for aircraft according to claim 1, characterized in that, The height of the positioning ridge (14) at one end where the first step structure is located is lower than the height of the upper surface of the lower template (10), and the height of the other end of the positioning ridge (14) is higher than the height of the upper surface of the lower template (10).

5. The flanging die for the titanium alloy multi-curved multi-layer stepped structure part for aircraft according to claim 4, characterized in that, A triangular positioning platform (17) is provided at the other end of the positioning ridge (14); the extrusion ridge (44) is provided with an extrusion platform (47) matching the positioning platform (17).

6. The flanging die for the titanium alloy multi-curved multi-layer stepped structure part for aircraft according to claim 1, characterized in that, At the corners of the bottom surface of the extrusion groove (11) and the two side walls of the extrusion groove (11), first inner fillet transition structures are respectively provided. At the corners of the two side walls of the extrusion groove (11) and the upper surface of the lower template (10), first outer fillet transition structures are respectively provided. At the corners of the lower bottom surface of the extrusion boss (41) and the two side walls of the extrusion boss (41), second outer fillet structures matching the first inner fillet transition structures are respectively provided. At the corners of the two side walls of the extrusion boss (41) and the lower surface of the extrusion boss (41), second inner fillet transition structures matching the first outer fillet transition structures are respectively provided.

7. The flanging die for the titanium alloy multi-curved multi-layer stepped structure part for aircraft according to claim 1, characterized in that, At one end of the upper surface of the lower template (10) opposite to the first step structure, a positioning cut surface (18) extending in the width direction is provided. On the lower surface of the upper template (40), an extrusion cut surface (48) matching the positioning cut surface (18) is provided.

8. The flanging die for the titanium alloy multi-curved multi-layer stepped structure part for aircraft according to claim 1, characterized in that, Two groups of the first extrusion bolt holes (16) are correspondingly arranged on the two placing surfaces (15) along the edge of the extrusion groove (11). Two groups of the second extrusion bolt holes (46) are correspondingly arranged on the two pressing surfaces (45) along the edge of the extrusion boss (41).

9. The flanging die for the titanium alloy multi-curved multi-layer stepped structure part for aircraft according to claim 8, characterized in that, Both groups of the first extrusion bolt holes (16) are blind holes. Both groups of the positioning bolt holes (21) and both groups of the second extrusion bolt holes (46) are through holes. Two groups of positioning bolts (30) correspondingly pass through a part of the positioning bolt holes (21) of the two groups of positioning bolt holes (21) and are tightened in a part of the first extrusion bolt holes (16) of the two groups of the first extrusion bolt holes (16). Two groups of extrusion bolts (50) correspondingly pass through the other part of the positioning bolt holes (21) of the two groups of the second extrusion bolt holes (46) and the positioning bolt holes (21) and are tightened in the other part of the first extrusion bolt holes (16) of the two groups of the first extrusion bolt holes (16).

10. A forming method for a titanium alloy multi-curved multi-layer stepped structure part for an aircraft, characterized in that The forming method is applied to the flanging die for the titanium alloy multi-curved multi-layer stepped structure part for an aircraft as described in any one of claims 1-9. The forming method includes: Fix the lower template on the placing platform of the stamping machine. Place two pre-heated plate-shaped blanks in the extrusion groove respectively, so that one side surface of each of the two plate-shaped blanks is placed on the first concave surface and the second concave surface of the extrusion groove respectively. Place two pressing blocks correspondingly on the two placing surfaces. Pass the positioning bolts through part of the positioning bolt holes of the pressing blocks and screw them into the extrusion bolt holes of the lower template to push the pressing blocks towards the lower template to fix the plate-shaped blanks. Place the upper template correspondingly on the lower template and the pressing blocks. Pass the extrusion bolts through the extrusion bolt holes of the upper template and the other part of the positioning bolt holes of the pressing blocks and screw them into the extrusion bolt holes of the lower template to push the upper template towards the lower template to flang the two plate-shaped blanks. After fixing and cooling for a period of time, unscrew the extrusion bolts and the positioning bolts outwards from the lower template in sequence, and take out the parts that have been flanged. Use a cutting machine to cut out the required part from the flanged and formed part.

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