CN216324883U - Forging die for nozzle of aircraft engine - Google Patents
Forging die for nozzle of aircraft engine Download PDFInfo
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- CN216324883U CN216324883U CN202122823656.1U CN202122823656U CN216324883U CN 216324883 U CN216324883 U CN 216324883U CN 202122823656 U CN202122823656 U CN 202122823656U CN 216324883 U CN216324883 U CN 216324883U
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Abstract
The utility model relates to an aeroengine nozzle forging die which comprises an upper backing plate and a lower die holder which correspond up and down, wherein a circular plate is fixedly arranged at the center of the top surface of the upper backing plate, and an upper die is fixedly arranged at the center of the bottom of the circular plate; the center of the top of the lower die holder is fixedly provided with the lower die holder, and the center of the top of the lower die holder is provided with a die cavity with an upward opening; the die cavity consists of a circular plate limiting cavity, a flat plate die limiting cavity and a forming cavity which are communicated up and down; the bottom of the forming cavity is provided with a top head connecting hole which is vertically communicated with the bottom surface of the lower die, and a material returning device is sleeved in the top head connecting hole; and the lower die base is provided with a top rod joint hole which is communicated with the top head joint hole from top to bottom and is convenient for the jointing of the material returning device. The aero-engine nozzle forging die is simple in structure, easy to operate, low in product processing difficulty, capable of effectively reducing material consumption, low in processing cost, capable of effectively improving product processing efficiency and capable of effectively guaranteeing product performance.
Description
Technical Field
The utility model relates to the field of machining of aircraft engine nozzles, in particular to a forging die for an aircraft engine nozzle.
Background
At present, the production and processing mode of the nozzle of the aero-engine mainly comprises two modes of casting and machining; however, defects such as air holes, sand holes, insufficient pouring, shrinkage cavities, shrinkage porosity, slag inclusion and the like are easily generated during casting processing, the product quality is influenced, the structure control difficulty of the product formed by casting is high, the performance is not stable enough, and for the special application environment of an aircraft engine, the aircraft engine nozzle formed by casting has great potential performance hazards during application.
The machining mode usually uses a metal bar as an original blank main body, the metal bar with a corresponding size is clamped on a machine tool during machining, and the bar is machined by the milling mode of the machine tool. For the aircraft engine nozzle products with special structures, the machining mode is extremely low in material utilization rate, the aircraft engine nozzle with a large size is inconvenient to clamp by a machine tool, high in machining difficulty and limited, and the internal structure of the aircraft engine nozzle machined by the machining mode is discontinuous due to cutting, so that the performance of the product is unstable, and the quality of the product is influenced.
Disclosure of Invention
The utility model aims to solve the technical problem of providing an aircraft engine nozzle forging die which is low in material consumption and can effectively ensure the product performance.
In order to solve the technical problems, the utility model is realized by the following technical scheme: a nozzle forging die for an aero-engine comprises an upper backing plate and a lower die holder which correspond up and down, wherein a circular plate is fixedly arranged at the center of the top surface of the upper backing plate, and an upper die is fixedly arranged at the center of the bottom of the circular plate; the center of the top of the lower die holder is fixedly provided with the lower die holder, and the center of the top of the lower die holder is provided with a die cavity with an upward opening; the die cavity consists of a circular plate limiting cavity, a flat plate die limiting cavity and a forming cavity which are communicated up and down, the flat plate die limiting cavity is arranged at the top of the forming cavity, and the circular plate limiting cavity is arranged at the top of the flat plate die limiting cavity; the horizontal end surfaces of the forming cavity, the flat plate die limiting cavity and the circular plate limiting cavity are all in circular structures, wherein the diameter of the flat plate die limiting cavity is larger than the diameter of the top of the forming cavity and smaller than the diameter of the circular plate limiting cavity; the circular plate and the circular plate limiting cavity are in up-and-down correspondence and embedded fit, the upper die and the forming cavity are in up-and-down correspondence, the outline shape of the upper die is the same as that of the forming cavity, and the vertical cutting surfaces of the upper die and the forming cavity are in inverted trapezoidal structures; the bottom of the forming cavity is provided with a top head connecting hole which is vertically communicated with the bottom surface of the lower die, and a material returning device is sleeved in the top head connecting hole; and the lower die base is provided with a top rod joint hole which is communicated with the top head joint hole from top to bottom and is convenient for the jointing of the material returning device.
Furthermore, an extension cavity is arranged between the circular plate limiting cavity and the flat plate die limiting cavity, the extension cavity is communicated with the circular plate limiting cavity and the flat plate die limiting cavity from top to bottom, and the diameter of the extension cavity is larger than that of the flat plate die limiting cavity and smaller than that of the circular plate die limiting cavity.
Furthermore, the material returning device is formed by connecting an integrally formed top head and a top rod up and down and is of a T-shaped structure, the top head is sleeved in the top head connecting hole and is matched with the structure of the top head connecting hole, and the top rod penetrates through the bottom of the top head connecting hole and extends downwards into the corresponding top rod connecting hole.
Further, the ejector rod is in clearance fit with the ejector rod engagement hole, and a distance H is formed between the bottom surface of the ejector rod engagement hole and the bottom surface of the ejector rod engagement hole.
Further, the distance of the spacing H is 72 mm.
Furthermore, the center of the bottom surface of the circular plate is provided with an upper die connecting hole which is concave upwards and the structure of which is matched with that of the upper end of the upper die, and the top of the upper die is sleeved in the upper die connecting hole.
Furthermore, an assembly cavity which is concave downwards is arranged in the center of the top of the lower die holder, the outline shape and size of the assembly cavity are matched with those of the outer outline of the upper die, and the upper die is sleeved in the assembly cavity.
Furthermore, the vertical section of the assembly cavity is of an inverted trapezoidal structure, and the top surface of the upper die is higher than that of the lower die seat.
Furthermore, a flat plate die is arranged in the die cavity, and the flat plate die is in sleeve joint fit with the flat plate die limiting cavity.
Furthermore, the upper backing plate and the circular plate, the circular plate and the upper die and the lower die base are fixedly connected together through T-shaped inner hexagon bolts.
Compared with the prior art, the utility model has the advantages that: the aero-engine nozzle forging die is simple in structure, easy to operate, low in product processing difficulty, capable of effectively reducing material consumption, low in processing cost, capable of effectively improving product processing efficiency and capable of effectively guaranteeing product performance.
Drawings
The utility model is further described below with reference to the accompanying drawings.
FIG. 1 is a schematic structural view of the front face of an aircraft engine nozzle forging die of the present invention;
FIG. 2 is a cross-sectional view of the structure A-A of FIG. 1;
FIG. 3 is a cross-sectional view of a circular plate structure in the aero-engine nozzle forging die of the present invention;
FIG. 4 is a sectional view of the structure of the lower die of the aeroengine nozzle forging die.
In the figure: 1. an upper base plate; 2. a circular plate; 21. an upper die engagement hole; 3. a lower die; 31. a mold cavity; 311. a circular plate limiting cavity; 312. an extension cavity; 313. a flat plate die limiting cavity; 314. a molding cavity; 32. the top head is connected with the hole; 4. a lower die holder; 41. an assembly chamber; 42. the ejector rod is connected with the hole; 5. an upper die; 6. a material returning device.
Detailed Description
The utility model is described in detail below with reference to the following figures and embodiments:
the forging die for the nozzle of the aero-engine shown in fig. 1 and 2 comprises an upper backing plate 1 and a lower die holder 4 which correspond to each other up and down, wherein a circular plate 2 is fixedly arranged at the center of the top surface of the upper backing plate 1, and an upper die 5 is fixedly arranged at the center of the bottom of the circular plate 2; the center of the top of the lower die holder 4 is fixedly provided with the lower die holder 4, and the center of the top of the lower die holder 4 is provided with a die cavity 31 with an upward opening; as shown in fig. 4, the mold cavity 31 is composed of a circular plate mold limiting cavity 311, a flat plate mold limiting cavity 313 and a molding cavity 314 which are communicated up and down, the flat plate mold limiting cavity 313 is arranged at the top of the molding cavity 314, and the circular plate mold limiting cavity 311 is arranged at the top of the flat plate mold limiting cavity 313; the horizontal end surfaces of the forming cavity 314, the flat plate die limiting cavity 313 and the circular plate limiting cavity 311 are all in circular structures, wherein the diameter of the flat plate die limiting cavity 313 is larger than the diameter of the top of the forming cavity 314 and smaller than the diameter of the circular plate limiting cavity 311; the circular plate 2 corresponds to the circular plate limiting cavity 311 up and down and is matched with the circular plate limiting cavity 311 in an embedded mode, the upper die 5 corresponds to the forming cavity 314 up and down, the outline shape of the upper die 5 is the same as that of the forming cavity 314, and the vertical section surfaces of the upper die 5 are in inverted trapezoid structures; a top head joint hole 32 which is vertically communicated with the bottom surface of the lower die 3 is formed in the bottom of the forming cavity 314, and a material returning device 6 is sleeved in the top head joint hole 32; and a top rod joint hole 42 which is communicated up and down and is convenient for the jointing of the material returning device 6 is arranged at the position, corresponding to the top head joint hole 32, on the lower die base 4.
In order to prevent the insufficient deformation of the blank during forging, an extension cavity 312 is arranged between the circular plate limiting cavity 311 and the flat plate die limiting cavity 313, the extension cavity 312 is communicated with the circular plate limiting cavity 31 and the flat plate die limiting cavity 313 up and down, and the diameter of the extension cavity 312 is larger than that of the flat plate die limiting cavity 313 and smaller than that of the circular plate die limiting cavity 31; the elongation rate of the blank during forging and processing can be effectively improved through the extension cavity 312, and then the forging has better performance.
In order to facilitate the forged piece to be withdrawn from the die cavity 31, the material returning device 6 is formed by connecting an integrally formed top head and a top rod up and down, and is in a T-shaped structure, the top head is sleeved in the top head engagement hole 32 and is matched with the structure of the top head engagement hole 32, and the top rod passes through the bottom of the top head engagement hole 32 and extends downwards in the corresponding top rod engagement hole 42; the ejector rod is convenient to be connected with a material returning structure on the forging press, the area of the ejector head is larger than that of the ejector rod, and the forging is not pressed and deformed due to the fact that the contact surface of the forging is too small when the ejector rod is convenient to lift and return materials.
In order to facilitate the connection of the ejector rod with the forging press at the later stage and not to influence the movement of the lower die holder 4, the ejector rod is in clearance fit with the ejector rod joint hole, a distance H is formed between the bottom surface of the ejector rod joint hole and the bottom surface of the ejector rod joint hole, and the distance H is 72 mm.
As shown in fig. 3, in order to prevent the upper die 5 from being biased radially in the horizontal direction on the circular plate 2 due to a force, an upper die coupling hole 21 which is concave upwards and has a structure matched with the upper end structure of the upper die 5 is formed in the center of the bottom surface of the circular plate 2, and the top of the upper die 5 is coupled in the upper die coupling hole 21.
In order to prevent the lower die 3 from radially deviating in the horizontal direction on the lower die holder 4 due to stress, the center of the top of the lower die holder 4 is provided with an assembly cavity 41 which is concave downwards, the contour shape and size of the assembly cavity 41 are matched with the contour shape and size of the upper die 5, and the upper die 5 is sleeved in the assembly cavity 41.
In order to facilitate the installation and the disassembly of the lower die 3 on the lower die holder 4, the vertical section of the assembly cavity 41 is in an inverted trapezoidal structure, and the top surface of the upper die 5 is higher than the top surface of the lower die holder 4.
In order to facilitate the radial upsetting of the cylindrical blank placed in the die cavity 31, a flat plate die is arranged in the die cavity 31, and the flat plate die is in sleeved fit with the flat plate die limiting cavity 313.
In order to facilitate installation and disassembly and improve the flexibility of the parts during use, the upper backing plate 1 and the circular plate 2, the circular plate 2 and the upper die 5 and the lower die 3 and the lower die base 4 are fixedly connected together through T-shaped inner hexagonal bolts.
The specific working principle is as follows: fixedly connecting an upper padding plate 1 and a lower die holder 4 on a hydraulic press in a vertically corresponding manner, placing a preheated metal bar blank into a die cavity 31 of a lower die 3, centering the bottom surface of the metal bar blank in the center of a forming cavity 314, then placing a flat die on the top surface of the metal bar blank, setting the pressure of the hydraulic press, driving a circular plate 2 fixedly connected to the bottom surface of the hydraulic press and an upper die 5 to synchronously move downwards by the hydraulic press through the upper padding plate 1, contacting the bottom surface of the upper die 5 with the top surface of the flat die and gradually applying pressure downwards to the flat die, radially upsetting the metal bar blank positioned below the bottom of the flat die by the flat die until the flat die is matched with a flat die limiting cavity 313, and forging the metal bar blank into a shape matched with the forming cavity 314 in structure; controlling the upper backing plate 1 to move upwards through a hydraulic press, driving the circular plate 2 and the upper die 5 to synchronously move upwards and reset, so that the upper die 5 is separated from the die cavity 31, then taking out the flat die positioned in the die cavity 31, controlling the upper die 5 to move downwards through the hydraulic press again after the flat die is taken out of the die cavity 31, carrying out reverse extrusion forming on the blank positioned in the forming cavity 314 by the upper die 5, extending the blank positioned in the forming cavity 314 in the peripheral direction under the extrusion action of the upper die 5, ensuring the deformation amount of the blank during reverse extrusion through the extending cavity 312, and finishing forging and pressing when the circular plate 2 is matched with the circular plate limiting cavity 311 to form an aircraft engine nozzle forging; and then the upper backing plate 1 is controlled by the hydraulic press to return upwards, the upper backing plate 1 drives the circular plate 2 and the upper die 5 to synchronously return upwards, after the upper die 5 is completely separated from the lower die 3, the lower die base 4 arranged on the worktable of the hydraulic press moves outwards, the material returning device 6 penetrates through the ejector rod joint hole 42 to lift upwards through the material returning machine, the nozzle forging of the aircraft engine positioned in the die cavity 31 is pushed upwards out of the die cavity 31, and the forging and pressing work of the nozzle of the aircraft engine is completed.
The aero-engine nozzle forging die is simple in structure, easy to operate, low in product processing difficulty, capable of effectively reducing material consumption, low in processing cost, capable of effectively improving product processing efficiency and capable of effectively guaranteeing product performance.
It is to be emphasized that: the above embodiments are only preferred embodiments of the present invention, and are not intended to limit the present invention in any way, and all simple modifications, equivalent changes and modifications made to the above embodiments according to the technical spirit of the present invention are within the scope of the technical solution of the present invention.
Claims (10)
1. The utility model provides an aeroengine nozzle forges mould which characterized in that: the die comprises an upper backing plate (1) and a lower die holder (4) which correspond up and down, wherein a circular plate (2) is fixedly arranged at the center of the top surface of the upper backing plate (1), and an upper die (5) is fixedly arranged at the center of the bottom of the circular plate (2); the center of the top of the lower die holder (4) is fixedly provided with the lower die holder (4), and the center of the top of the lower die holder (4) is provided with a die cavity (31) with an upward opening; the die cavity (31) consists of a circular plate die limiting cavity (311), a flat plate die limiting cavity (313) and a forming cavity (314) which are communicated up and down, the flat plate die limiting cavity (313) is arranged at the top of the forming cavity (314), and the circular plate die limiting cavity (311) is arranged at the top of the flat plate die limiting cavity (313); the horizontal end faces of the forming cavity (314), the flat plate die limiting cavity (313) and the circular plate limiting cavity (311) are all in a circular structure, wherein the diameter of the flat plate die limiting cavity (313) is larger than the diameter of the top of the forming cavity (314) and smaller than the diameter of the circular plate limiting cavity (311); the circular plate (2) and the circular plate limiting cavity (311) are vertically corresponding and matched in an embedded mode, the upper die (5) and the forming cavity (314) are vertically corresponding, the outline shape of the upper die (5) is the same as that of the forming cavity (314), and the vertical section surfaces of the upper die and the forming cavity are of inverted trapezoid structures; a top head joint hole (32) which is vertically communicated with the bottom surface of the lower die (3) is formed in the bottom of the forming cavity (314), and a material returning device (6) is sleeved in the top head joint hole (32); and a mandril joint hole (42) which is communicated from top to bottom and is convenient for the jointing of the material returning device (6) is arranged at the position, corresponding to the mandril joint hole (32), on the lower die base (4).
2. The aircraft engine nozzle forging die of claim 1, wherein: an extension cavity (312) is arranged between the circular plate limiting cavity (311) and the flat plate die limiting cavity (313), the extension cavity (312) is communicated with the circular plate limiting cavity (311) and the flat plate die limiting cavity (313) up and down, and the diameter of the extension cavity (312) is larger than that of the flat plate die limiting cavity (313) and smaller than that of the circular plate die limiting cavity (311).
3. The aircraft engine nozzle forging die of claim 1, wherein: the material returning device (6) is formed by connecting an integrally formed top head and a top rod up and down and is of a T-shaped structure, the top head is sleeved in the top head joint hole (32) and is matched with the structure of the top head joint hole (32), and the top rod penetrates through the bottom of the top head joint hole (32) and extends downwards in the corresponding top rod joint hole (42).
4. The aircraft engine nozzle forging die of claim 3, wherein: the ejector rod is in clearance fit with the ejector rod engagement hole, and a distance H is formed between the bottom surface of the ejector rod engagement hole and the bottom surface of the ejector rod engagement hole.
5. The aircraft engine nozzle forging die of claim 4, wherein: the distance of the spacing H is 72 mm.
6. The aircraft engine nozzle forging die of claim 1, wherein: the center of the bottom surface of the circular plate (2) is provided with an upper die joint hole (21) which is concave upwards and the structure of which is matched with that of the upper end of the upper die (5), and the top of the upper die (5) is sleeved in the upper die joint hole (21).
7. The aircraft engine nozzle forging die of claim 1, wherein: the center of the top of the lower die holder (4) is provided with an assembly cavity (41) which is concave downwards, the outline shape and size of the assembly cavity (41) are matched with the outline shape and size of the upper die (5), and the upper die (5) is sleeved in the assembly cavity (41).
8. The aircraft engine nozzle forging die of claim 7, wherein: the vertical section of the assembly cavity (41) is of an inverted trapezoidal structure, and the top surface of the upper die (5) is higher than that of the lower die holder (4).
9. The aircraft engine nozzle forging die of claim 1, wherein: and a flat plate die is arranged in the die cavity (31), and the flat plate die is in sleeve fit with the flat plate die limiting cavity (313).
10. The aircraft engine nozzle forging die of claim 1, wherein: the upper base plate (1) and the circular plate (2), the circular plate (2) and the upper die (5) and the lower die (3) and the lower die seat (4) are fixedly connected together through T-shaped inner hexagonal bolts.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122823656.1U CN216324883U (en) | 2021-11-17 | 2021-11-17 | Forging die for nozzle of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122823656.1U CN216324883U (en) | 2021-11-17 | 2021-11-17 | Forging die for nozzle of aircraft engine |
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| Publication Number | Publication Date |
|---|---|
| CN216324883U true CN216324883U (en) | 2022-04-19 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122823656.1U Active CN216324883U (en) | 2021-11-17 | 2021-11-17 | Forging die for nozzle of aircraft engine |
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| CN (1) | CN216324883U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115090760A (en) * | 2022-05-27 | 2022-09-23 | 遵义航天新力精密铸锻有限公司 | Aeroengine mounting support point bending tool |
| CN115283598A (en) * | 2022-08-25 | 2022-11-04 | 上海电气上重铸锻有限公司 | Forging device and forging method for 316LN stainless steel super-thick trapezoidal section forging |
-
2021
- 2021-11-17 CN CN202122823656.1U patent/CN216324883U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115090760A (en) * | 2022-05-27 | 2022-09-23 | 遵义航天新力精密铸锻有限公司 | Aeroengine mounting support point bending tool |
| CN115283598A (en) * | 2022-08-25 | 2022-11-04 | 上海电气上重铸锻有限公司 | Forging device and forging method for 316LN stainless steel super-thick trapezoidal section forging |
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