2A50 Aircraft Pipe Joint Forging Device
Through the forging technology of the 2A50 aircraft pipe joint forging device, the problems of high production cost and difficult manufacturing in the prior art are solved, and the effect of reducing production costs and improving mechanical properties and uniformity is achieved.
Patent Information
- Application Number
- CN202211411002.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- Filing Date
- 2022-11-11
- Publication Date
- 2025-06-03
- Estimated Expiration
- 2042-11-11
AI Technical Summary
The existing aircraft pipe joints are costly and difficult to manufacture, especially when preparing special-shaped multi-pass joints, multiple cast molds are required, resulting in increased cost and difficulty.
The 2A50 aircraft pipe joint forging device is used to generate two sets of joint pipe walls by casting, and then the pipe plug and the main pipe plug are forged to make the half-pipe wall under three-way compressive stress, increasing the density of the component structure, thereby improving the mechanical properties and uniformity.
Through forging technology, the dependence on high-precision casting molds is reduced, production costs are reduced, and the mechanical properties and uniformity of aircraft pipe joints are improved.
Smart Images
Figure CN115921758B_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to the technical field of general aviation auxiliary equipment, and particularly to a forging device for 2A50 aircraft pipe joints. Background Art
[0002] Multiple pipe fittings need to be provided on the aircraft skin for connecting with the static and dynamic pressure systems, ventilation systems, and sewage systems on the aircraft respectively;
[0003] When manufacturing 2A50 aircraft pipe joints, the casting method is usually adopted for preparation. Due to the particularity of aviation, the aircraft pipe joints have many production requirements in the production process. Therefore, a specific casting mold needs to be used to produce this type of joint. However, this type of casting mold needs to consume a large cost to produce to ensure its accuracy. Therefore, the current production cost of aircraft pipe joints is relatively high;
[0004] When manufacturing aircraft pipe joints with special-shaped multi-way joints, this type of aircraft pipe joint has a variety of specifications, complex shapes, and great processing difficulties. When the casting process is used for production, a large number of casting molds are needed, and its production cost is high;
[0005] Therefore, it is very necessary to invent a forging device for 2A50 aircraft pipe joints. Summary of the Invention
[0006] For this purpose, the present invention provides a forging device for 2A50 aircraft pipe joints. By adopting the casting method to produce two groups of joint pipe walls, and then using the branch pipe plugs and main pipe plugs with different target shape sizes to forge the produced joint pipe walls, the two groups of semi-pipe walls are always under triaxial compressive stress, increasing the density of the component structure, helping to form a fine and uniform microstructure, and further improving the mechanical properties and uniformity of the component, so as to form an aircraft pipe joint that meets the production requirements, and solve the problems of high production cost and great manufacturing difficulty of the existing forging equipment.
[0007] To achieve the above object, the present invention provides the following technical solution: A forging device for 2A50 aircraft pipe joints, including a casting device and a chassis. The casting device is located on one side of the top of the chassis and is connected to the chassis. The casting device includes a cover plate. It further includes: a pouring-receiving component connected to the cover plate;
[0008] The component to be poured includes a pouring rack. On both sides of the bottom of the pouring rack, two groups of limiting rods are fixedly installed. At the four corners of the bottom of the pouring rack, fastening columns are fixedly installed. On both sides of the bottom of the pouring rack, a pouring block is slidably connected. At the four corners of the bottom of the pouring block, fastening holes are opened. The four fastening columns are respectively fixedly connected to the four fastening holes. At the center of the top of the pouring block, a pouring area is opened. At the bottom of the pouring area, a lower stepped block is fixedly installed. On the lower stepped block, two forming grooves are opened. On both inner walls of the two forming grooves, blocking blocks are fixedly installed. On the upper walls of the two blocking blocks, flow-through grooves are opened. The two flow-through grooves are respectively communicated with the two forming grooves;
[0009] The component to be poured further includes a pressing plate. On both sides of the bottom of the pressing plate and the pouring block, limiting holes are opened. The limiting holes on the pressing plate and the pouring block are respectively slidably connected to the four limiting rods. At the four corners of the top of the pressing plate, positioning pins are fixedly installed. On the top of the pressing plate, two pouring pipes are fixedly installed. At the center of the bottom of the pressing plate, an upper stepped block is fixedly installed. On the bottom of the upper stepped block, two pressing grooves are opened. The two pressing grooves are respectively engaged with the two forming grooves. The bottom parts of the two pouring pipes are respectively located in the middle of the two pressing grooves and are communicated with the inside of the pressing grooves. On both sides of the pressing plate and the pouring block, two through holes are opened;
[0010] The component to be poured further includes a force-applying plate. At the four corners of the top of the force-applying plate, positioning holes are opened. The four positioning holes are respectively slidably connected to the four positioning pins. At the four corners of the bottom of the force-applying plate, inserting rods are fixedly installed. On the outer walls of the four inserting rods, return springs are sleeved. The tops of the four return springs are fixedly connected to the bottom of the force-applying plate. The four inserting rods are respectively inserted into the through holes on the pressing plate and the pouring block. The bottoms of the four return springs are respectively in contact with the top of the pressing plate. The tops of the two pouring pipes respectively penetrate through the force-applying plate.
[0011] Preferably, both sides of the cover plate are fixedly connected to both sides of the top of the pouring rack. The four limiting rods are fixedly connected to the bottom of the cover plate through bolts. At the center of the bottom of the cover plate, a cylinder is fixedly installed. At the output end of the cylinder, a bridge-shaped pressing plate is fixedly installed. The bottom of the bridge-shaped pressing plate is in movable contact with the top wall of the force-applying plate.
[0012] Preferably, the bottom of the pouring frame is fixedly connected to the top of the left side of the chassis. A stamping assembly is provided at the top of the right side of the chassis. The stamping assembly includes a support frame. The bottom of the support frame is fixedly connected to the side wall of the chassis. Three groups of first connecting rods are rotatably connected to both sides of the top of the support frame. The ends of the six first connecting rods are all rotatably connected to branch pipe plugs. The center of the front top of the support frame is rotatably connected to a second connecting rod. The end of the second connecting rod is rotatably connected to a main pipe plug. Three groups of receiving holes are symmetrically arranged on both sides of the main pipe plug. The six branch pipe plugs are respectively inserted into the six receiving holes. A lower forming block is fixedly installed on the top of the support frame. A lower installation groove is formed in the lower forming block. An upper installation block is provided on the top of the lower forming block. An upper installation groove is formed in the bottom of the upper installation block. The lower forming block is engaged with the upper installation block. A stamping machine is fixedly installed on the chassis. The output shaft of the stamping machine is fixedly connected to the top of the upper installation block.
[0013] The beneficial effects of the present invention are as follows:
[0014] 1. Pouring liquid is introduced into the two pouring pipes. The pouring liquid enters the flow grooves on the blocking blocks through the pouring pipes and flows into the forming grooves from the flow grooves. Under the action of the two blocking blocks, semi-tube walls are formed in the two forming grooves. The two semi-tube walls can be spliced to form a complete aircraft pipe joint. The semi-tube walls of the two aircraft pipe joints are respectively placed into the lower installation groove and the upper installation groove. At the same time, the six branch pipe plugs and the main pipe plug are rotated so that the six branch pipe plugs and the main pipe plug are all located inside the semi-tube wall in the lower installation groove, and the receiving holes on the six branch pipe plugs and the main pipe plug are inserted. Then, the semi-tube walls in the lower installation groove and the upper installation groove are heated to control their temperature to about 320 °C. The stamping machine is started to drive the upper installation block to press down by the output end of the stamping machine, so that the semi-tube walls in the upper installation groove and the lower installation groove are both forged by the branch pipe plugs and the receiving holes, and the two semi-tube walls are bonded together to form a complete aircraft pipe joint. This production method does not require a pouring mold with high precision;
[0015] 2. By utilizing the limiting and guiding effects of the six branch pipe plugs and the main pipe plug, the movement of the stamping machine is converted into the axial movement of each pipe on the aircraft pipe joint along the branch pipe plugs and the main pipe plug, realizing the coordinated extension of multiple pipes, so as to realize the overall forging and forming of each pipe of the aircraft pipe joint. By utilizing the connection positions and inner diameter shape dimensions of the six branch pipe plugs and the main pipe plug, flexible forging and forming of aircraft pipe joints with different target shape dimensions can be realized. During the stamping process of the stamping machine, the two semi-tube walls are always under triaxial compressive stress, suppressing the appearance of cracks on the surface of the semi-tube wall during stamping due to uneven pressure, avoiding different axial wall thicknesses of the formed component after compression due to uneven distribution of the pouring liquid during the pouring process, increasing the density of the component tissue, contributing to the formation of fine and uniform microstructures, and thus improving the mechanical properties and uniformity of the aircraft pipe joint component. Brief Description of the Drawings
[0016] Figure 1 It is a schematic structural diagram of the forging device provided by the present invention;
[0017] Figure 2 It is a schematic structural diagram of the pouring device provided by the present invention;
[0018] Figure 3 It is an exploded view of the pouring device provided by the present invention;
[0019] Figure 4 It is a schematic structural diagram of the component to be poured provided by the present invention;
[0020] Figure 5 It is an exploded view of the component to be poured provided by the present invention;
[0021] Figure 6 It is a schematic structural diagram of the poured block provided by the present invention;
[0022] Figure 7 It is a schematic structural diagram of two groups of barrier blocks provided by the present invention;
[0023] Figure 8 It is a schematic structural diagram of the pressing plate provided by the present invention;
[0024] Figure 9 It is a schematic structural diagram of the stamping component provided by the present invention;
[0025] Figure 10 It is an internal structural diagram of the stamping component provided by the present invention;
[0026] Figure 11 It is an internal exploded view of the stamping component provided by the present invention;
[0027] Figure 12 It is a schematic structural diagram of the upper mounting block provided by the present invention;
[0028] Figure 13 It is an assembly diagram of the upper mounting block and the lower mounting block provided by the present invention.
[0029] In the figure: pouring device 100, poured component 110, poured rack 111, limit rod 112, set screw column 113, poured block 114, limit hole 115, through hole 116, set screw hole 117, poured area 118, lower stepped block 119, forming groove 120, blocking block 121, flow groove 122, pressing plate 130, positioning pin 131, pouring pipe 132, upper stepped block 133, pressing groove 134, force - applying plate 140, positioning hole 141, inserting rod 142, return spring 143, cover plate 150, air cylinder 151, bridge - type pressing plate 152, chassis 200, stamping component 210, support frame 211, first connecting rod 212, branch pipe plug 213, second connecting rod 214, main pipe plug 215, receiving hole 216, lower forming block 217, lower installation groove 218, upper installation block 219, upper installation groove 220, stamping machine 230. Detailed implementation mode
[0030] The preferred embodiments of the present invention will be described below with reference to the accompanying drawings. It should be understood that the preferred embodiments described herein are only for the purpose of illustration and explanation of the present invention, and are not used to limit the present invention.
[0031] Referring to the attached Figures 1-13 , the 2A50 aircraft pipe joint forging device provided by the present invention includes a pouring device 100 and a chassis 200. The pouring device 100 is located on one side of the top of the chassis 200 and is connected to the chassis 200. The pouring device 100 includes a cover plate 150. It further includes: a poured component 110 connected to the cover plate 150;
[0032] The poured component 110 includes a poured rack 111. On both sides of the bottom of the poured rack 111, two groups of limit rods 112 are fixedly installed. At the four corners of the bottom of the poured rack 111, set screw columns 113 are fixedly installed. On both sides of the bottom of the poured rack 111, a poured block 114 is slidably connected. At the four corners of the bottom of the poured block 114, set screw holes 117 are opened. The four set screw columns 113 are respectively fixedly connected to the four set screw holes 117. At the center of the top of the poured block 114, a poured area 118 is opened. At the bottom of the poured area 118, a lower stepped block 119 is fixedly installed. On the lower stepped block 119, two groups of forming grooves 120 are opened. On the inner walls of both sides of the two groups of forming grooves 120, blocking blocks 121 are fixedly installed. On the upper walls of the two groups of blocking blocks 121, flow grooves 122 are opened. The two groups of flow grooves 122 are respectively communicated with the two groups of forming grooves 120;
[0033] The component 110 to be poured further includes a pressing plate 130. Limit holes 115 are respectively formed on both sides of the bottom of the pressing plate 130 and the block 114 to be poured. The limit holes 115 on the pressing plate 130 and the block 114 to be poured are respectively slidably connected with four groups of limit rods 112. Positioning pins 131 are fixedly installed at the four corners of the top of the pressing plate 130. Two groups of pouring pipes 132 are fixedly installed at the top of the pressing plate 130. An upper stepped block 133 is fixedly installed at the center of the bottom of the pressing plate 130. Two pressing grooves 134 are formed at the bottom of the upper stepped block 133. The two pressing grooves 134 are respectively engaged with the two forming grooves 120. The bottoms of the two groups of pouring pipes 132 are respectively located in the middle of the two pressing grooves 134 and are internally communicated with the pressing grooves 134. Two groups of through holes 116 are respectively formed on both sides of the pressing plate 130 and the block 114 to be poured;
[0034] The component 110 to be poured further includes a force - applying plate 140. Positioning holes 141 are respectively formed at the four corners of the top of the force - applying plate 140. The four positioning holes 141 are respectively slidably connected with the four positioning pins 131. Plug rods 142 are fixedly installed at the four corners of the bottom of the force - applying plate 140. Return springs 143 are sleeved on the outer side walls of the four plug rods 142. The tops of the four return springs 143 are fixedly connected with the bottom of the force - applying plate 140. The four plug rods 142 are respectively inserted into the through holes 116 on the pressing plate 130 and the block 114 to be poured. The bottoms of the four return springs 143 are in contact with the top of the pressing plate 130. The tops of the two groups of pouring pipes 132 respectively penetrate through the force - applying plate 140. Specifically, the block 114 to be poured and the pressing plate 130 are installed on the pouring frame 111 through the limit rods 112. At the same time, the positioning pins 131 are engaged with the positioning holes 141 to install the force - applying plate 140 on the pressing plate 130. Then, the cover plate 150 is covered, and the bridge - shaped pressing plate 152 is engaged with the force - applying plate 140. At this time, the driving cylinder 151 is driven. The output shaft of the cylinder 151 drives the bridge - shaped pressing plate 152 to press down the force - applying plate 140. The plug rods 142 on the force - applying plate 140 are slidably connected with the through holes 116 on the pressing plate 130 and the block 114 to be poured, so that the return springs 143 are compressed by the force. At the same time, under the action of the elastic force, the pressing plate 130 is extruded, so that the upper stepped block 133 at the bottom of the pressing plate 130 is closely attached to the lower stepped block 119 on the block 114 to be poured, and the pressing grooves 134 on the upper stepped block 133 are closely attached to the side walls of the forming grooves 120 on the lower stepped block 119. Then, pouring liquid is introduced through the two groups of pouring pipes 132. The pouring liquid enters the flow grooves 122 on the blocking block 121 through the pouring pipes 132 and flows into the forming grooves 120 from the flow grooves 122. Under the action of the two blocking blocks 121, semi - pipe walls are formed in the two forming grooves 120. The two semi - pipe walls can be spliced to form a complete aircraft pipe joint.
[0035] Further, both sides of the cover plate 150 are fixedly connected to both sides of the top of the pouring frame 111. Four groups of limiting rods 112 are fixedly connected to the bottom of the cover plate 150 by bolts. A cylinder 151 is fixedly installed at the center of the bottom of the cover plate 150. The output end of the cylinder 151 is fixedly installed with a bridge-shaped pressing plate 152. The bottom of the bridge-shaped pressing plate 152 is in movable contact with the top wall of the force-applying plate 140.
[0036] Further, the bottom of the pouring rack 111 is fixedly connected to the left top of the chassis 200. A stamping assembly 210 is provided at the right top of the chassis 200. The stamping assembly 210 includes a support frame 211. The bottom of the support frame 211 is fixedly connected to the side wall of the chassis 200. Three groups of first connecting rods 212 are rotatably connected to both sides of the top of the support frame 211. The ends of the six first connecting rods 212 are rotatably connected to branch pipe plugs 213. The center of the front top of the support frame 211 is rotatably connected to a second connecting rod 214. The end of the second connecting rod 214 is rotatably connected to a main pipe plug 215. Three groups of receiving holes 216 are symmetrically arranged on both sides of the main pipe plug 215. The six branch pipe plugs 213 are respectively inserted into the six receiving holes 216. A lower forming block 217 is fixedly installed on the top of the support frame 211. A lower installation groove 218 is formed in the lower forming block 217. An upper installation block 219 is provided on the top of the lower forming block 217. An upper installation groove 220 is formed in the bottom of the upper installation block 219. The lower forming block 217 is engaged with the upper installation block 219. A stamping machine 230 is fixedly installed on the chassis 200. The output shaft of the stamping machine 230 is fixedly connected to the top of the upper installation block 219. Specifically, the half pipe walls of two aircraft pipe joints are respectively placed into the lower installation groove 218 and the upper installation groove 220. At the same time, the six branch pipe plugs 213 and the main pipe plug 215 are rotated so that the six branch pipe plugs 213 and the main pipe plug 215 are all located inside the half pipe wall in the lower installation groove 218, and the receiving holes 216 on the six branch pipe plugs 213 and the main pipe plug 215 are inserted. Then, the half pipe walls in the lower installation groove 218 and the upper installation groove 220 are heated to control their temperature to about 320 °C. The stamping machine 230 is started to drive the upper installation block 219 to press down by the output end of the stamping machine 230, so that the half pipe walls in the upper installation groove 220 and the lower installation groove 218 are both forged by the branch pipe plugs 213 and the receiving holes 216, and the two half pipe walls are attached and connected, thus forming a complete 2A50 aircraft pipe joint. Particularly, by utilizing the limiting and guiding effects of the six branch pipe plugs 213 and the main pipe plug 215, the movement of the stamping machine 230 is converted into the axial movement of each pipeline on the 2A50 aircraft pipe joint along the branch pipe plugs 213 and the main pipe plug 215, realizing the coordinated extension of multiple pipelines, so as to realize the overall forging and forming of each pipeline of the 2A50 aircraft pipe joint. By utilizing the connection positions and inner diameter shape dimensions of the six branch pipe plugs 213 and the main pipe plug 215, the flexible forging and forming of 2A50 aircraft pipe joints with different target shape dimensions can be realized. During the stamping process of the stamping machine 230, the two half pipe walls are always under triaxial compressive stress, suppressing the appearance of cracks on the surface of the half pipe wall during stamping due to uneven pressure, avoiding different axial wall thicknesses of the components formed after pressing due to uneven distribution of the pouring liquid during the pouring process, increasing the density of the component structure, contributing to the formation of fine and uniform microstructures, and further improving the mechanical properties and uniformity of the 2A50 aircraft pipe joint components.
[0037] The usage process of the present invention is as follows: Those skilled in the art install the pouring block 114 and the pressing plate 130 onto the pouring frame 111 through the limiting rod 112. At the same time, the positioning pin 131 is engaged with the positioning hole 141, and the force - applying plate 140 is installed onto the pressing plate 130. Then, the cover plate 150 is covered, and the bridge - type pressing plate 152 is engaged with the force - applying plate 140. At this time, the driving cylinder 151 is driven. The output shaft of the cylinder 151 drives the bridge - type pressing plate 152 to press down the force - applying plate 140. The insertion rod 142 on the force - applying plate 140 is in sliding connection with the through - hole 116 on the pressing plate 130 and the pouring block 114, causing the return spring 143 to be compressed under force. At the same time, under the action of the elastic force, it squeezes the pressing plate 130, making the upper stepped block 133 at the bottom of the pressing plate 130 fit tightly with the lower stepped block 119 on the pouring block 114, and making the pressing groove 134 on the upper stepped block 133 fit tightly with the side wall of the forming groove 120 on the lower stepped block 119. Then, the pouring liquid is introduced through two groups of pouring pipes 132. The pouring liquid enters the flow - through groove 122 on the blocking block 121 through the pouring pipes 132 and flows from the flow - through groove 122 into the forming groove 120. Under the action of the two groups of blocking blocks 121, semi - pipe walls are formed in the two groups of forming grooves 120, and the two groups of semi - pipe walls can be spliced to form a complete aircraft pipe joint;
[0038] Place the semi-wall tubes of two sets of aircraft pipe joints into the lower installation groove 218 and the upper installation groove 220 respectively. At the same time, rotate the six sets of branch pipe plugs 213 and the main pipe plug 215 so that the six sets of branch pipe plugs 213 and the main pipe plug 215 are all located within the semi-wall tubes in the lower installation groove 218, and make the receiving holes 216 on the six sets of branch pipe plugs 213 and the main pipe plug 215 inserted. Then heat the semi-wall tubes in the lower installation groove 218 and the upper installation groove 220 to control their temperature at about 320 °C. Start the stamping machine 230 so that the output end of the stamping machine 230 drives the upper installation block 219 to press down, so that the semi-wall tubes in the upper installation groove 220 and the semi-wall tubes in the lower installation groove 218 are both forged by the branch pipe plugs 213 and the receiving holes 216, and the two sets of semi-wall tubes are bonded and connected to form a complete 2A50 aircraft pipe joint. By utilizing the limiting and guiding effects of the six sets of branch pipe plugs 213 and the main pipe plug 215, the movement of the stamping machine 230 is converted into the axial movement of each pipe on the 2A50 aircraft pipe joint along the branch pipe plugs 213 and the main pipe plug 215, realizing the coordinated extension of multiple pipes, so as to realize the integral forging and forming of each pipe of the 2A50 aircraft pipe joint. By utilizing the connection positions and inner diameter shape dimensions of the six sets of branch pipe plugs 213 and the main pipe plug 215, the flexible forging and forming of 2A50 aircraft pipe joints with different target shape dimensions can be realized. During the stamping process of the stamping machine 230, the two sets of semi-wall tubes are always under triaxial compressive stress, which inhibits the appearance of cracks on the surface of the semi-wall tubes during the stamping process due to uneven pressure, and avoids the different axial wall thicknesses of the components formed after compression due to uneven distribution of the pouring liquid during the pouring process, increasing the density of the component structure, contributing to the formation of fine and uniform microstructures, and thus improving the mechanical properties and uniformity of the 2A50 aircraft pipe joint components.
[0039] The above are only the preferred embodiments of the present invention. Any person skilled in the art may modify the present invention by using the technical solutions described above or modify it into an equivalent technical solution. Therefore, any simple modification or equivalent replacement made according to the technical solutions of the present invention shall fall within the scope of protection required by the present invention.
Claims
1. 2A50 aircraft pipe joint forging device, including a pouring device (100) and a chassis (200), the pouring device (100) is located on one side of the top of the chassis (200) and is connected to the chassis (200). It is characterized in that: The pouring device (100) includes a cover plate (150): It also includes: a pouring-receiving component (110) connected to the cover plate (150); The pouring-receiving component (110) includes a pouring-receiving frame (111). On both sides of the bottom of the pouring-receiving frame (111), two groups of limit rods (112) are fixedly installed. At the four corners of the bottom of the pouring-receiving frame (111), four sets of set screws (113) are fixedly installed. On both sides of the bottom of the pouring-receiving frame (111), a pouring-receiving block (114) is slidably connected. At the four corners of the bottom of the pouring-receiving block (114), set screw holes (117) are opened. The four sets of set screws (113) are respectively fixedly connected to the four sets of set screw holes (117). At the center of the top of the pouring-receiving block (114), a pouring-receiving area (118) is opened. At the bottom of the pouring-receiving area (118), a lower stepped block (119) is fixedly installed. On the lower stepped block (119), two sets of forming grooves (120) are opened. On the inner walls of both sides of the two sets of forming grooves (120), barrier blocks (121) are fixedly installed. On the upper walls of the two sets of barrier blocks (121), flow-through grooves (122) are opened. The two sets of flow-through grooves (122) are respectively communicated with the two sets of forming grooves (120); The pouring-receiving component (110) also includes a pressing plate (130). On both sides of the bottom of the pressing plate (130) and the pouring-receiving block (114), limit holes (115) are opened. The limit holes (115) on the pressing plate (130) and the pouring-receiving block (114) are respectively slidably connected to the four sets of limit rods (112). At the four corners of the top of the pressing plate (130), positioning pins (131) are fixedly installed. On the top of the pressing plate (130), two sets of pouring pipes (132) are fixedly installed. At the center of the bottom of the pressing plate (130), an upper stepped block (133) is fixedly installed. At the bottom of the upper stepped block (133), two sets of pressing grooves (134) are opened. The two sets of pressing grooves (134) are respectively engaged with the two sets of forming grooves (120). The bottoms of the two sets of pouring pipes (132) are respectively located in the middle of the two sets of pressing grooves (134) and are communicated with the inside of the pressing grooves (134). On both sides of the pressing plate (130) and the pouring-receiving block (114), two sets of through holes (116) are opened; The component to be poured (110) further includes a force - applying plate (140). Positioning holes (141) are provided at the four corners of the top of the force - applying plate (140). The four groups of positioning holes (141) are respectively slidably connected to four groups of positioning pins (131). Plug rods (142) are fixedly installed at the four corners of the bottom of the force - applying plate (140). The outer walls of the four groups of plug rods (142) are all sleeved with return springs (143). The tops of the four groups of return springs (143) are fixedly connected to the bottom of the force - applying plate (140). The four groups of plug rods (142) are respectively inserted into through - holes (116) located on the pressing plate (130) and the pouring - receiving block (114). The bottoms of the four groups of return springs (143) are all in contact with the top of the pressing plate (130). The tops of the two groups of pouring pipes (132) all penetrate through the force - applying plate (140); The bottom of the pouring - receiving frame (111) is fixedly connected to the top of the left side of the bottom frame (200). A stamping component (210) is provided at the top of the right side of the bottom frame (200). The stamping component (210) includes a support frame (211). The bottom of the support frame (211) is fixedly connected to the side wall of the bottom frame (200). Three groups of first connecting rods (212) are rotatably connected to both sides of the top of the support frame (211). The ends of the six groups of first connecting rods (212) are all rotatably connected to branch - pipe plugs (213). The center of the top of the front of the support frame (211) is rotatably connected to a second connecting rod (214). The end of the second connecting rod (214) is rotatably connected to a main - pipe plug (215). Three groups of receiving holes (216) are symmetrically arranged on both sides of the main - pipe plug (215). The six groups of branch - pipe plugs (213) are respectively inserted into the six groups of receiving holes (216). A lower forming block (217) is fixedly installed on the top of the support frame (211). A lower installation groove (218) is provided on the lower forming block (217). An upper installation block (219) is provided on the top of the lower forming block (217). An upper installation groove (220) is provided at the bottom of the upper installation block (219). The lower forming block (217) is engaged with the upper installation block (219). A stamping machine (230) is fixedly installed on the bottom frame (200). The output shaft of the stamping machine (230) is fixedly connected to the top of the upper installation block (219).
2. The forging device for 2A50 aircraft pipe joints according to claim 1, characterized in that: Both sides of the cover plate (150) are fixedly connected to both sides of the top of the pouring - receiving frame (111). The four groups of limiting rods (112) are fixedly connected to the bottom of the cover plate (150) by bolts. A cylinder (151) is fixedly installed at the center of the bottom of the cover plate (150). The output end of the cylinder (151) is fixedly installed with a bridge - shaped pressing plate (152). The bottom of the bridge - shaped pressing plate (152) is in movable contact with the top wall of the force - applying plate (140).
Citation Information
Patent Citations
Precise forging and pressing die for machined part
CN113172157A
Press for the forging of tubular elements
GB826338A