Double-blank flanging die and forming method for multi-step titanium alloy part of aircraft

Abstract

The application provides a double-billet flanging die and forming method for a titanium alloy multi-step ladder part for an aircraft. The flanging die comprises a lower die plate, a pressing plate, positioning bolts, an upper die plate and extruding bolts. The upper surface of the lower die plate is provided with a positioning boss, a plurality of first positioning bolt holes and a plurality of first extruding bolt holes. The shape of the pressing plate matches the shape of the positioning boss, and the pressing plate is provided with a plurality of second positioning bolt holes. The plurality of positioning bolts push the pressing plate to move towards the lower die plate to fix the part billet placed between the positioning boss and the pressing plate. The lower surface of the upper die plate is provided with an extruding groove matching the positioning boss and the pressing plate, and the upper die plate is further provided with a plurality of second extruding bolt holes. The plurality of extruding bolts push the upper die plate to move towards the lower die plate to make the extruding groove extrude the part billet placed between the positioning boss and the pressing plate to be flanged. The problem that the conventional die plate in the prior art cannot process the titanium alloy multi-step ladder part for an aircraft in accordance with requirements is solved.

Description

Technical Field

[0001] This invention relates to the field of processing template technology for titanium alloy parts for aircraft, and more specifically, to a double-blank flanging mold and forming method for titanium alloy multi-step parts for aircraft. Background Technology

[0002] Aircraft engines are highly complex and precise thermodynamic machines. As the heart of an aircraft, they not only power flight but also serve as a crucial driving force for the development of aviation. Every significant revolution in human aviation history is inextricably linked to advancements in aero-engine technology. The engine nacelle, as the compartment housing the aero-engine, is also one of the most critical core components of the aviation propulsion system. The cost of an engine nacelle accounts for approximately one-quarter of the total engine cost. Currently, my country lags significantly behind advanced foreign countries in the field of engine nacelle manufacturing technology.

[0003] Currently, the manufacturing process of engine nacelles requires the extensive use of titanium alloy sheet metal stepped parts to fabricate the nacelle's outer shell. The titanium alloy serrated frame-like parts used in aircraft are curved flanged structures that need to be pressed into an arc shape. The casting of titanium alloy sheet metal stepped parts is primarily done through stamping, but these parts suffer from difficulties in bending and shaping, placing high demands on processing technology and mold equipment. Existing processing molds are insufficient to produce the required titanium alloy serrated frame-like parts for aircraft; therefore, specialized molds are necessary. Summary of the Invention

[0004] The main objective of this invention is to provide a double-blank flanging mold and forming method for titanium alloy multi-step parts for aircraft, so as to at least solve the problem that traditional molds in the prior art cannot process titanium alloy multi-step parts for aircraft that meet the requirements.

[0005] To achieve the above objectives, the present invention provides a double-blank flanging mold and forming method for titanium alloy multi-step parts for aircraft.

[0006] To achieve the above objectives, according to one aspect of the present invention, a double-bulk flanging die for a titanium alloy multi-step part used in aircraft is provided, comprising: a lower template, a pressure plate, positioning bolts, an upper template, and extrusion bolts; a positioning boss is provided on the upper surface of the lower template, the positioning boss comprising an elliptical platform in the middle and two rectangular platforms extending to both sides from the two ends of the elliptical platform along the length direction of the lower template; the positioning boss is provided with a plurality of first positioning bolt holes, and a plurality of first extrusion bolt holes are provided on the upper surface of the lower template along the edge of the positioning boss; the shape of the pressure plate matches the shape of the positioning boss, and the pressure plate is provided with a plurality of second positioning bolt holes corresponding one-to-one with and matching the plurality of first positioning bolt holes; the positioning bolts are multiple Multiple positioning bolts are correspondingly inserted into multiple first positioning bolt holes and multiple second positioning bolt holes; the multiple positioning bolts are used to push the pressure plate towards the lower template to fix the part blank placed between the positioning boss and the pressure plate; the lower surface of the upper template has extrusion grooves that match both the positioning boss and the pressure plate, and the lower surface of the upper template has multiple second extrusion bolt holes that correspond one-to-one with and match the multiple first extrusion bolt holes along the edge of the extrusion grooves; there are multiple extrusion bolts, which are correspondingly inserted into the multiple first extrusion bolt holes and multiple second extrusion bolt holes; the multiple extrusion bolts are used to push the upper template towards the lower template so that the extrusion grooves extrude the part blank placed between the positioning boss and the pressure plate to turn the edge.

[0007] Furthermore, the intersections of the elliptical frustum and the two rectangular frustums are all provided with inner rounded corner transition structures.

[0008] Furthermore, multiple first positioning bolt holes are respectively arranged along the circumference on the upper surface of the elliptical platform and along the length direction of the lower template on the upper surface of the rectangular platform.

[0009] Furthermore, all of the first positioning bolt holes are blind holes, and all of the second positioning bolt holes are through holes. The multiple positioning bolts pass through the multiple second positioning bolt holes and are tightened into the multiple first positioning bolt holes.

[0010] Furthermore, the extrusion groove includes an elliptical groove in the middle and two rectangular grooves extending to both sides from both ends of the elliptical groove along the length direction of the upper template.

[0011] Furthermore, the intersection of the elliptical groove and the two rectangular grooves is provided with an outer rounded corner transition structure that matches the inner rounded corner transition structure.

[0012] Furthermore, multiple first extrusion bolt holes are respectively provided on the lower surface of the upper template along the circumference of the elliptical groove and along the circumference of the rectangular groove.

[0013] Furthermore, the multiple first extrusion bolt holes are all blind holes, the multiple second extrusion bolt holes are all through holes, and the multiple extrusion bolts pass through the multiple second extrusion bolt holes and are tightened in the multiple first extrusion bolt holes.

[0014] According to another aspect of the present invention, a method for forming a multi-step titanium alloy part for aircraft is provided, the forming method comprising:

[0015] Fix the lower template onto the platform of the stamping machine;

[0016] Two preheated plate blanks are placed on the extrusion boss;

[0017] Place the pressure plate on the extrusion boss accordingly;

[0018] Tighten the positioning bolts through the positioning bolt holes of the pressure plate and into the extrusion bolt holes of the lower template to push the pressure plate toward the lower template to fix the plate-shaped blank.

[0019] Place the upper template through the pressure plate onto the lower template;

[0020] Tighten the extrusion bolts through the extrusion bolt holes of the upper template and into the extrusion bolt holes of the lower template to push the upper template toward the lower template so that the plate blank is turned over;

[0021] After the parts have cooled for a period of time, loosen the extrusion bolts and positioning bolts one by one by unscrewing them to the outside of the template, and take out the parts that have been flanged.

[0022] Use a cutting machine to cut out the required parts from the flanged parts.

[0023] The present invention relates to a double-bulk flanging die for a titanium alloy multi-step part used in aircraft, comprising: a lower die plate, a pressure plate, positioning bolts, an upper die plate, and extrusion bolts; the upper surface of the lower die plate is provided with a positioning boss, which includes an elliptical platform in the middle and two rectangular platforms extending to both sides from the two ends of the elliptical platform along the length of the lower die plate; the positioning boss is provided with multiple first positioning bolt holes, and the upper surface of the lower die plate is provided with multiple first extrusion bolt holes along the edge of the positioning boss; the shape of the pressure plate matches the shape of the positioning boss, and the pressure plate is provided with multiple second positioning bolt holes that correspond one-to-one with and match the multiple first positioning bolt holes; there are multiple positioning bolts, and the multiple positioning bolts correspond to... The upper template has multiple first and second positioning bolt holes. These positioning bolts push the pressure plate towards the lower template to secure the part blank placed between the positioning boss and the pressure plate. The lower surface of the upper template has extrusion grooves that match both the positioning boss and the pressure plate. Along the edge of these extrusion grooves, the lower surface of the upper template has multiple second extrusion bolt holes that correspond one-to-one with and match the first extrusion bolt holes. Multiple extrusion bolts are inserted into the first and second extrusion bolt holes. These bolts push the upper template towards the lower template to cause the extrusion grooves to press and fold the part blank placed between the positioning boss and the pressure plate. This solves the problem that traditional templates in the prior art cannot process multi-step titanium alloy parts for aircraft that meet the requirements. Attached Figure Description

[0024] The accompanying drawings, which form part of this application, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings:

[0025] Figure 1 This is a schematic diagram of the structure of a double-blank flanging mold for a titanium alloy multi-step part for aircraft, which is optional according to an embodiment of the present invention;

[0026] Figure 2 This is a front view of the lower template of a double-blank flanging die for a titanium alloy multi-step part for aircraft, which is optional according to an embodiment of the present invention;

[0027] Figure 3 This is a left view of the lower template of a double-blank flanging die for a titanium alloy multi-step part for aircraft, which is optional according to an embodiment of the present invention.

[0028] Figure 4 This is a top view of the lower template of a double-blank flanging die for a titanium alloy multi-step part for aircraft, which is optional according to an embodiment of the present invention.

[0029] Figure 5This is an axial view of the lower template of a double-blank flanging die for a titanium alloy multi-step part for aircraft, which is optional according to an embodiment of the present invention.

[0030] Figure 6 This is a front view of the pressure plate of a double-blank flanging die for a titanium alloy multi-step part for an aircraft, which is optional according to an embodiment of the present invention;

[0031] Figure 7 This is a left view of the pressure plate of a double-blank flanging die for a titanium alloy multi-step part for an aircraft, which is optional according to an embodiment of the present invention.

[0032] Figure 8 This is a top view of the pressure plate of a double-blank flanging die for a titanium alloy multi-step part for an aircraft, which is optional according to an embodiment of the present invention.

[0033] Figure 9 This is an axial view of the blanking plate of a double-blank flanging die for a titanium alloy multi-step part for an aircraft, which is optional according to an embodiment of the present invention.

[0034] Figure 10 This is a front view of the upper template of a double-blank flanging mold for a titanium alloy multi-step part for aircraft, which is optional according to an embodiment of the present invention;

[0035] Figure 11 This is a front view of the upper template of a double-blank flanging mold for a titanium alloy multi-step part for aircraft, which is optional according to an embodiment of the present invention;

[0036] Figure 12 This is a top view of the upper template of a double-blank flanging mold for a titanium alloy multi-step part for aircraft, which is optional according to an embodiment of the present invention.

[0037] Figure 13 This is an axial view of the upper template of a double-blank flanging mold for a titanium alloy multi-step part for aircraft, which is optional according to an embodiment of the present invention.

[0038] The above figures include the following reference numerals:

[0039] 10. Lower template; 11. Positioning boss; 12. First positioning bolt hole; 13. First extrusion bolt hole; 20. Pressure plate; 21. Second positioning bolt hole; 30. Positioning bolt; 40. Upper template; 41. Extrusion groove; 42. Second extrusion bolt hole; 50. Extrusion bolt; 60. Lifting hole. Detailed Implementation

[0040] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0041] According to an embodiment of the present invention, a double-bulk flanging die for multi-step titanium alloy parts for aircraft is provided, such as... Figure 1As shown, the assembly includes a lower template 10, a pressure plate 20, positioning bolts 30, an upper template 40, and extrusion bolts 50. The upper surface of the lower template 10 is provided with a positioning boss 11, which includes an elliptical platform in the middle and two rectangular platforms extending from both ends of the elliptical platform along the length of the lower template 10 towards both sides. The positioning boss 11 has multiple first positioning bolt holes 12, and the upper surface of the lower template 10 has multiple first extrusion bolt holes 13 along the edge of the positioning boss 11. The shape of the pressure plate 20 matches the shape of the positioning boss 11, and the pressure plate 20 has multiple second positioning bolt holes 21 that correspond one-to-one with and match the multiple first positioning bolt holes 12. Multiple positioning bolts 30 are provided, and these multiple positioning bolts 30 are correspondingly inserted into the multiple first positioning bolts 30 and the multiple first extrusion bolt holes 50. The upper template 40 has a set of extrusion grooves 41 that match both the positioning boss 11 and the pressure plate 20. The lower surface of the upper template 40 has a set of second extrusion bolt holes 42 that correspond one-to-one with and match the first extrusion bolt holes 13. Multiple extrusion bolts 50 are inserted into the first extrusion bolt holes 13 and the second extrusion bolt holes 42. The multiple extrusion bolts 50 are inserted into the first extrusion bolt holes 13 and the second extrusion bolt holes 42. The multiple extrusion bolts 50 are used to push the upper template 40 towards the lower template 10 so that the extrusion grooves 41 extrude and fold the part blank placed between the positioning boss 11 and the pressure plate 20. In this embodiment, the double-blank flanging die for titanium alloy multi-step parts for aircraft is used as follows: First, the lower template 10 is fixed on the placement platform of the stamping machine. The two preheated plate blanks to be flanged are placed on the positioning bosses 11. Then, the pressure plate 20 is placed on the blanks. The blanks are fixed to the positioning bosses 11 by sequentially screwing the multiple positioning bolts 30 (located in the second positioning bolt hole 21) into the first positioning bolt hole 12. Finally, the upper template 40 is placed on the lower template 10 through the pressure plate 20. Multiple extrusion bolts 50, positioned within multiple second extrusion bolt holes 42, are sequentially tightened into multiple first extrusion bolt holes 13. These bolts push the upper template 40 towards the lower template 10, causing the extrusion groove 41 to press and fold the part blank placed between the positioning boss 11 and the pressure plate 20. After a period of cooling and fixing, the multiple extrusion bolts 50 and multiple positioning bolts 30 are sequentially loosened from the outside of the lower template 10. The folded part is then removed, and a cutting machine is used to cut the required portions from the two folded parts. This invention features a cleverly designed template that is simple and convenient to operate. It can effectively process difficult-to-machine titanium alloy plate blanks and can process two part blanks simultaneously, resulting in high work efficiency. This solves the problem that traditional templates in the prior art cannot process multi-step titanium alloy parts for aircraft that meet the requirements.

[0042] Furthermore, such as Figure 2 , Figure 3 , Figure 4 and Figure 5 As shown, the intersection of the elliptical platform and the two rectangular platforms is provided with an inner rounded corner transition structure, which effectively avoids the problems of cracking and breakage of the mold and blank during the stamping process.

[0043] Furthermore, multiple first positioning bolt holes 12 are respectively arranged along the circumference on the upper surface of the elliptical platform and along the length direction of the lower template 10 on the upper surface of the rectangular platform.

[0044] Furthermore, such as Figure 6 , Figure 7 , Figure 8 and Figure 9 As shown, the multiple first positioning bolt holes 12 are all blind holes, the multiple second positioning bolt holes 21 are all through holes, and the multiple positioning bolts 30 pass through the multiple second positioning bolt holes 21 and are tightened in the multiple first positioning bolt holes 12.

[0045] In specific implementation, such as Figure 10 , Figure 11 , Figure 12 and Figure 13 As shown, the extrusion groove 41 includes an elliptical groove in the middle and two rectangular grooves extending to both sides along the length of the upper template 40 from both ends of the elliptical groove.

[0046] Furthermore, the intersection of the elliptical groove and the two rectangular grooves is provided with an outer rounded corner transition structure that matches the inner rounded corner transition structure, effectively avoiding the problems of cracking and breakage of the mold and blank during the stamping process.

[0047] Furthermore, multiple first extrusion bolt holes 13 are respectively provided on the lower surface of the upper template 40 along the circumference of the elliptical groove and along the circumference of the rectangular groove.

[0048] Furthermore, the plurality of first extrusion bolt holes 13 are all blind holes, the plurality of second extrusion bolt holes 42 are all through holes, and the plurality of extrusion bolts 50 pass through the plurality of second extrusion bolt holes 42 and are tightened in the plurality of first extrusion bolt holes 13.

[0049] In specific implementation, such as Figure 1 As shown, multiple lifting holes 60 are provided on the outer side wall of the lower mold and the outer side wall of the upper mold. By screwing bolts with hooks into the lifting holes 60, the lower template 10 and the upper template 40 can be lifted and transported by a crane respectively.

[0050] According to another aspect of the present invention, a method for forming a multi-step titanium alloy part for aircraft is provided, the forming method comprising:

[0051] Fix the lower template onto the platform of the stamping machine;

[0052] Two preheated plate blanks are placed on the extrusion boss;

[0053] Place the pressure plate on the extrusion boss accordingly;

[0054] Tighten the positioning bolts through the positioning bolt holes of the pressure plate and into the extrusion bolt holes of the lower template to push the pressure plate toward the lower template to fix the plate-shaped blank.

[0055] Place the upper template through the pressure plate onto the lower template;

[0056] Tighten the extrusion bolts through the extrusion bolt holes of the upper template and into the extrusion bolt holes of the lower template to push the upper template toward the lower template so that the plate blank is turned over;

[0057] After the parts have cooled for a period of time, loosen the extrusion bolts and positioning bolts one by one by unscrewing them to the outside of the template, and take out the parts that have been flanged.

[0058] The required parts of the flanged parts are cut using a cutting machine. In this embodiment, the double-blank flanging mold for multi-step titanium alloy parts for aircraft is used as follows: First, the lower template 10 is fixed on the placement platform of the stamping machine. The two preheated plate blanks to be flanged are placed on the positioning bosses 11. Then, the pressure plate 20 is placed on the blanks. The blanks are fixed to the positioning bosses 11 by sequentially screwing the multiple positioning bolts 30 (located in the second positioning bolt hole 21) into the first positioning bolt hole 12. Finally, the upper template 40 is placed on the lower template 10 through the pressure plate 20. Multiple extrusion bolts 50, positioned within multiple second extrusion bolt holes 42, are sequentially tightened into multiple first extrusion bolt holes 13. These bolts push the upper template 40 towards the lower template 10, causing the extrusion groove 41 to press and fold the part blank placed between the positioning boss 11 and the pressure plate 20. After a period of cooling and fixing, the multiple extrusion bolts 50 and multiple positioning bolts 30 are sequentially loosened from the outside of the lower template 10. The folded part is then removed, and a cutting machine is used to cut the required portions from the two folded parts. This invention features a cleverly designed template that is simple and convenient to operate. It can effectively process difficult-to-machine titanium alloy plate blanks and can process two part blanks simultaneously, resulting in high work efficiency. This solves the problem that traditional templates in the prior art cannot process multi-step titanium alloy parts for aircraft that meet the requirements.

[0059] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A dual billet flanging die for a multi-step titanium alloy aircraft part, comprising: The utility model relates to a kind of moulding die for flanging, including: Lower die plate (10), the upper surface of the lower die plate (10) is provided with positioning boss (11), the positioning boss (11) includes oval table body in middle part and two rectangular table bodies extended towards two sides along the length direction of the lower die plate (10) by two ends of the oval table body;The positioning boss (11) is equipped with a plurality of first locating bolt holes (12), and the upper surface of the lower die plate (10) is provided with a plurality of first extrusion bolt holes (13) along the edge of the positioning boss (11); Pressing plate (20), the shape of the pressing plate (20) is matched with the shape of the positioning boss (11), and the pressing plate (20) is provided with a plurality of second locating bolt holes (21) corresponding to and matched with a plurality of the first locating bolt holes (12) one by one; Locating bolt (30), the locating bolt (30) is a plurality of, and a plurality of the locating bolt (30) is correspondingly arranged in a plurality of the first locating bolt (30) and a plurality of the second locating bolt hole (21);A plurality of locating bolts (30) are used to push the pressing plate (20) towards the lower die plate (10) to move to fix the part blank placed between the positioning boss (11) and the pressing plate (20); Upper die plate (40), the lower surface of the upper die plate (40) is provided with extrusion groove (41) matched with the positioning boss (11) and the pressing plate (20), and the lower surface of the upper die plate (40) is provided with a plurality of second extrusion bolt holes (42) corresponding to and matched with a plurality of the first extrusion bolt holes (13) along the edge of the extrusion groove (41); Extrusion bolt (50), the extrusion bolt (50) is a plurality of, and a plurality of the extrusion bolt (50) is correspondingly arranged in a plurality of the first extrusion bolt hole (13) and a plurality of the second extrusion bolt hole (42);A plurality of the extrusion bolt (50) is used to push the upper die plate (40) towards the lower die plate (10) to move to make the extrusion groove (41) extrude the part blank placed between the positioning boss (11) and the pressing plate (20) flanging.

2. The dual billet flanging die for a multi-step titanium alloy aircraft part of claim 1, wherein, The intersection of the oval table body and the two rectangular table bodies is provided with an inner fillet transition structure.

3. The dual billet flanging die for a multi-step titanium alloy aircraft part of claim 2, wherein, A plurality of the first locating bolt holes (12) are respectively arranged on the upper surface of the oval table body along the circumference and on the upper surface of the rectangular table body along the length direction of the lower die plate (10).

4. The dual billet flanging die for a multi-step titanium alloy aircraft part of claim 3, wherein, A plurality of the first locating bolt holes (12) are blind holes, a plurality of the second locating bolt holes (21) are through holes, and a plurality of the locating bolts (30) are correspondingly arranged through a plurality of the second locating bolt holes (21) and screwed in a plurality of the first locating bolt holes (12).

5. The dual billet flanging die for a multi-step titanium alloy aircraft part of claim 4, wherein, The extrusion groove (41) includes oval groove in middle part and two rectangular grooves extended towards two sides along the length direction of the upper die plate (40) by two ends of the oval groove.

6. The dual billet flanging die for a multi-step titanium alloy aircraft part of claim 5 wherein, The intersection of the oval groove and the two rectangular grooves is provided with an outer fillet transition structure matched with the inner fillet transition structure.

7. The dual billet flanging die for a multi-step titanium alloy aircraft part of claim 6 wherein, A plurality of the second extrusion bolt holes (42) are respectively arranged along the oval groove and the rectangular groove in the circumferential direction of the lower surface of the upper die plate (40).

8. The dual billet flanging die for a multi-step titanium alloy aircraft part of claim 7, wherein, A plurality of the first extrusion bolt holes (13) are blind holes, a plurality of the second extrusion bolt holes (42) are through holes, and a plurality of the extrusion bolts (50) pass through the second extrusion bolt holes (42) and are screwed in the first extrusion bolt holes (13).

9. The dual billet flanging die for a multi-step titanium alloy aircraft part of claim 8, wherein, A plurality of hoisting holes (60) are arranged on the outer side wall of the lower die plate (10) and the outer side wall of the upper die plate (40).

10. A method of forming a multiple stepped titanium alloy part for an aircraft, the method comprising: providing a titanium alloy material; forming a first step in the titanium alloy material; forming a second step in the titanium alloy material; and forming a third step in the titanium alloy material. The forming method is applied to the double-billet flanging die for the titanium alloy multi-step ladder part of the aircraft according to any one of claims 1-9, and the forming method comprises: Fixing the lower die plate on the placement platform of the stamping machine; Placing two preheated plate-shaped billets on the positioning bosses respectively; Placing the pressing plate on the positioning bosses correspondingly; Tightening the positioning bolts through the positioning bolt holes of the pressing plate into the positioning bolt holes of the lower die plate to push the pressing plate towards the lower die plate to fix the plate-shaped billets; Placing the upper die plate on the lower die plate through the pressing plate; Tightening the extrusion bolts through the extrusion bolt holes of the upper die plate into the extrusion bolt holes of the lower die plate to push the upper die plate towards the lower die plate to make the plate-shaped billets flange; After fixing and cooling for a period of time, sequentially unscrewing the extrusion bolts and the positioning bolts from the outside of the lower die plate, and taking out the parts that have been flanged; Using a cutting machine to cut the flanged parts into the required parts. A plurality of the second extrusion bolt holes (42) are respectively arranged along the oval groove and the rectangular groove in the circumferential direction of the lower surface of the upper die plate (40). A plurality of the first extrusion bolt holes (13) are blind holes, a plurality of the second extrusion bolt holes (42) are through holes, and a plurality of the extrusion bolts (50) pass through the second extrusion bolt holes (42) and are screwed in the first extrusion bolt holes (13). A plurality of hoisting holes (60) are arranged on the outer side wall of the lower die plate (10) and the outer side wall of the upper die plate (40). The forming method is applied to the double-billet flanging die for the titanium alloy multi-step ladder part of the aircraft according to any one of claims 1-9, and the forming method comprises: Fixing the lower die plate on the placement platform of the stamping machine; Placing two preheated plate-shaped billets on the positioning bosses respectively; Placing the pressing plate on the positioning bosses correspondingly; Tightening the positioning bolts through the positioning bolt holes of the pressing plate into the positioning bolt holes of the lower die plate to push the pressing plate towards the lower die plate to fix the plate-shaped billets; Placing the upper die plate on the lower die plate through the pressing plate; Tightening the extrusion bolts through the extrusion bolt holes of the upper die plate into the extrusion bolt holes of the lower die plate to push the upper die plate towards the lower die plate to make the plate-shaped billets flange; After fixing and cooling for a period of time, sequentially unscrewing the extrusion bolts and the positioning bolts from the outside of the lower die plate, and taking out the parts that have been flanged; Using a cutting machine to cut the flanged parts into the required parts.

Images