Die forging die for turbine disc of aero-engine

Abstract

The utility model relates to an aero-engine turbine disc die forging die which comprises an upper die base and a lower die base which correspond to each other up and down, a turbine disc upper die is arranged at the center of the bottom of the upper die base, a turbine disc lower die is arranged at the center of the top of the lower die base, and the turbine disc upper die and the turbine disc lower die correspond to each other up and down; an upper die punch is arranged in the center of the bottom of the turbine disc upper die, the bottom of the upper die punch partially protrudes out of the lower portion of the bottom face of the turbine disc upper die, and an upper die cavity is formed in the bottom face of the portion, protruding out of the lower portion of the bottom face of the turbine disc upper die, of the bottom of the upper die punch. A lower die cavity is formed in the top face of the turbine disc lower die, and the lower die cavity corresponds to a protruding part at the bottom of the upper die punch in an up-down mode and is matched with the protruding part in an up-down embedded mode. According to the aero-engine turbine disc die forging die, closed die forging machining of an aero-engine turbine disc is achieved, the size of a machined semi-finished product is more similar to the structural size of a product, the follow-up machining allowance is small, material consumption is reduced, the production cost is reduced, and the machining efficiency is improved.

Description

Technical Field

[0001] The utility model relates to the processing of an aero-engine turbine disk, in particular to a forging die for an aero-engine turbine disk. Background Art

[0002] Aircraft engine turbine discs are the core components of engines in modern aviation equipment; they are large in size and have high strength requirements.

[0003] At present, the processing method of aircraft engine turbine discs is mainly through forging and machine tool rough and fine processing. The main process is to heat the metal bar material for manufacturing aircraft engine turbine discs and make it into a cake-shaped blank by upsetting, and then heat the cake-shaped blank and place it on a hydraulic press of about 30,000 tons for die forging, and finally load the semi-finished product after die forging on the machine tool for rough processing and processing. Among them, the die forging method is mainly processed by open die forging process. The heated cake-shaped blank is placed on the open die, and then the hydraulic press is turned on for processing. The semi-finished blank of the aircraft engine turbine disc made by this open die forging process has a relatively large processing allowance, is not close to the processing size of the product, has low precision, and requires more time for subsequent machine tool rough and fine processing, which affects the processing efficiency and wastes more materials, resulting in an increase in processing costs. Summary of the invention

[0004] The technical problem to be solved by the utility model is to provide an aero-engine turbine disc forging die which can improve the forging precision and processing efficiency of the aero-engine turbine disc.

[0005] In order to solve the above technical problems, the utility model is realized through the following technical solutions: an aircraft engine turbine disk forging die, comprising an upper die seat and a lower die seat corresponding to each other, the bottom center of the upper die seat is provided with a turbine disk upper die fixedly connected thereto, and the top center of the lower die seat is provided with a turbine disk lower die fixedly connected thereto, the turbine disk upper die and the turbine disk lower die correspond to each other up and down; the bottom center of the turbine disk upper die is provided with an upper die punch fixedly connected thereto, the bottom part of the upper die punch protrudes below the bottom surface of the turbine disk upper die, and the bottom surface of the part of the upper die punch protruding below the bottom surface of the turbine disk upper die is provided with an upwardly concave upper die cavity; the top surface of the turbine disk lower die is provided with a downwardly concave lower die cavity, the lower die cavity corresponds to the protruding part of the bottom of the upper die punch up and down, and the protruding part of the bottom of the upper die punch is embedded with the lower die cavity up and down; the bottom center of the upper die seat is provided with an upper die groove, and the top center of the lower die seat is provided with a lower die groove, The upper die of the turbine disk is embedded in the upper die groove and fixedly connected by bolts, and the lower die of the turbine disk is embedded in the lower die groove and fixedly connected by bolts; the outer side of the lower die of the turbine disk is inclined from bottom to top to form a lower engaging surface with an outward camber angle of 2 to 5°; the outer side of the upper die of the turbine disk is inclined from top to bottom to form an upper engaging surface with an outward camber angle of 2 to 5°; the side wall of the upper die groove is structurally consistent with the upper engaging surface, and the side wall of the lower die groove is structurally consistent with the lower engaging surface; the top of the lower die of the turbine disk is higher than the top of the lower die seat, and the height between the top surface of the lower die of the turbine disk and the top surface of the lower die seat is higher than the height between the bottom surface of the upper die punch and the bottom surface of the upper die seat; the center of the bottom surface of the upper die of the turbine disk is provided with an upwardly concave centering hole, the upper end of the upper die punch is embedded in the centering hole, and the two are fixedly connected by bolts; the bottom surface of the upper die punch is located outside the protruding part and is flush with the bottom surface of the upper die of the turbine disk.

[0006] Furthermore, hanging holes are arranged around the outer sides of the upper die base and the outer sides of the lower die base.

[0007] Furthermore, a material withdrawal hole is provided at the bottom center of the lower mold cavity and passes through the bottom of the turbine disc lower mold vertically, and a push rod is movably provided in the material withdrawal hole; a material ejection hole is provided at a position on the top surface of the lower mold base corresponding to the material withdrawal hole and passing through its bottom, and the material ejection hole corresponds to the material withdrawal hole vertically and is connected to each other.

[0008] Compared with the prior art, the advantages of the utility model are: this aircraft engine turbine disc forging die realizes the closed die forging processing of the aircraft engine turbine disc, the size of the processed semi-finished product is closer to the product structure size of the aircraft engine turbine disc, the subsequent processing allowance is small, the material consumption is saved, the production cost is reduced, and the processing efficiency is improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0009] In order to more clearly illustrate the technical solutions of the embodiments of the utility model, the drawings required for use in the embodiments will be briefly introduced below. It should be understood that the following drawings only show certain embodiments of the utility model and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other relevant drawings can be obtained based on these drawings without paying creative work.

[0010] Figure 1 It is a schematic diagram of the side structure of a die forging die for an aircraft engine turbine disc in a closed die state of the utility model;

[0011] Figure 2 yes Figure 1 Structural cross-section view of AA in the middle;

[0012] Figure 3 The utility model discloses a side structural sectional view of a turbine disc upper die and a turbine disc lower die in an aircraft engine turbine disc forging die in a die opening state.

[0013] In the figure: 1. upper die seat; 11. upper die groove; 2. lower die seat; 21. lower die groove; 22. ejector hole; 3. turbine disc lower die; 31. lower die cavity; 32. ejector hole; 33. lower mating surface; 4. lifting hole; 5. turbine disc upper die; 51. centering hole; 52. upper mating surface; 6. upper die punch; 61. upper die cavity; 7. ejector pin. DETAILED DESCRIPTION

[0014] In order to make the purpose, technical scheme and advantages of the embodiments of the utility model clearer, the technical scheme in the embodiments of the utility model will be clearly and completely described below in conjunction with the drawings in the embodiments of the utility model. Obviously, the described embodiments are part of the embodiments of the utility model, not all of the embodiments. Generally, the components of the embodiments of the utility model described and shown in the drawings here can be arranged and designed in various different configurations.

[0015] Therefore, the following detailed description of the embodiments of the utility model provided in the accompanying drawings is not intended to limit the scope of the utility model claimed for protection, but only represents the selected embodiments of the utility model. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in the field without making creative work are within the scope of protection of the utility model. It should be noted that similar reference numerals and letters represent similar items in the following drawings, so once an item is defined in one drawing, it is not necessary to further define and explain it in the subsequent drawings. In the description of the embodiments of the utility model, it should be noted that if the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inside", "outside" and the like indicate the orientation or position relationship based on the orientation or position relationship shown in the drawings, or the orientation or position relationship of the utility model product when used, it is only for the convenience of describing the utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation of the utility model. Furthermore, the terms “first”, “second”, etc. are merely used for distinguishing descriptions and should not be understood as indicating or implying relative importance.

[0016] In addition, the terms "horizontal" and "vertical" do not mean that the components must be absolutely horizontal or vertical, but can be slightly tilted. For example, "horizontal" only means that its direction is more horizontal than "vertical", and does not mean that the structure or component must be completely horizontal, but can be slightly tilted.

[0017] In the description of the embodiments of the present invention, "multiple" means at least 2.

[0018] In the description of the embodiments of the present utility model, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "set", "install", "connect", and "connect" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present utility model can be understood according to specific circumstances. Example

[0019] Please refer to the instruction manual Figure 1 and 2 As shown, the instruction manual is attached Figure 1 and 2The utility model is shown as a die forging die for an aircraft engine turbine disc, which is used in conjunction with a 30,000-ton hydraulic press, and includes an upper die seat 1 and a lower die seat 2 corresponding to each other. The upper die seat 1 is installed at the bottom of a movable crossbeam of the hydraulic press by T-bolts, and the lower die seat 2 is installed on the workbench of the hydraulic press by T-bolts, and the top of the upper die seat 1 and the bottom of the lower die seat 2 are both provided with T-slots for convenient connection of the T-bolts to the hydraulic press, wherein the T-slots on the upper die seat 1 are inverted, and the top surface of the lower die seat 2 is provided with a ejection hole 22 that passes through the bottom thereof, and the ejection hole 22 corresponds to the ejector on the hydraulic press that can pass through the workbench up and down, and the ejector can extend upward into The ejection hole 22; due to the relatively large volume of the aircraft engine turbine disk, the corresponding volumes of the upper die base 1 and the lower die base 2 are relatively large. In order to facilitate their installation and disassembly on the hydraulic press, the outer sides of the upper die base 1 and the outer sides of the lower die base 2 are provided with lifting holes 4. The upper die base 1 has a plurality of lifting holes 4 on the side surface, which are evenly distributed horizontally along the outer periphery with the end face center of the upper die base 1 as the axis. Similarly, the lower die base 2 has a plurality of lifting holes 4 on the side surface, which are evenly distributed horizontally along the outer periphery with the end face center of the lower die base 2 as the axis. The lifting holes 4 are threaded holes, and the lifting bolts matched with the threads thereof are installed in the lifting holes 4, which can be hoisted on the hydraulic press by a crane; refer to the attached manual. Figure 2As shown, the bottom center of the upper die seat 1 is provided with a turbine disk upper die 5 fixedly connected thereto, and the top center of the lower die seat 2 is provided with a turbine disk lower die 3 fixedly connected thereto, and the turbine disk upper die 5 and the turbine disk lower die 3 correspond to each other up and down; in order to facilitate the installation of the turbine disk upper die 5 and the turbine disk lower die 3 on the upper die seat 1 and the lower die seat 2 respectively, to ensure the installation position accuracy and the stability of the horizontal position after installation, and not to easily cause horizontal offset due to external force, thereby affecting the die forging, an upper die groove 11 is provided at the bottom center of the upper die seat 1, and a lower die groove 21 is provided at the top center of the lower die seat 2, the turbine disk upper die 5 is embedded in cooperation with the upper die groove 11, and they are fixedly connected together by bolts, which is convenient for disassembly and assembly, the turbine disk lower die 3 is embedded in cooperation with the lower die groove 21, and they are fixedly connected together by bolts, which is convenient for disassembly and assembly, and the upper die groove 11 and the lower die groove 21 of the matching turbine disk upper die 5 and the turbine disk lower die 3 are provided. The installation of the turbine disc upper die 5 and the turbine disc lower die 3 can be realized effectively, conveniently and quickly, and the embedded matching mode effectively limits the horizontal position of the turbine disc upper die 5 and the turbine disc lower die 3, ensuring the reliability and stability of the horizontal position; in order to prevent the turbine disc upper die 5 and the turbine disc lower die 3 from being easily deformed in the lateral direction due to pressure during long-term use, affecting the removal of the turbine disc upper die 5 and the turbine disc lower die 3 from the upper die seat 1 and the lower die seat 2, the outer side of the turbine disc lower die 3 is inclined from bottom to top to form a lower engaging surface 33 with an outward camber angle of 2 to 5°; the outer side of the turbine disc upper die 5 is inclined from top to bottom to form an upper engaging surface 52 with an outward camber angle of 2 to 5°; the side wall of the upper die groove 11 is structurally consistent with the upper engaging surface 52, and the side wall of the lower die groove 21 is structurally consistent with the lower engaging surface 33, forming an inclined surface match, which is convenient for the removal and installation of the turbine disc upper die 5 and the turbine disc lower die 3; refer to the attached manual Figure 3 As shown, the bottom center of the turbine disc upper die 5 is provided with an upper die punch 6 fixedly connected thereto. In order to facilitate the accuracy of the installation position of the upper die punch 6 at the bottom of the turbine disc upper die 5 and ensure that it can be installed quickly, an upwardly concave centering hole 51 is provided at the bottom center of the turbine disc upper die 5. The size of the centering hole 51 is consistent with the size of the upper end of the upper die punch 6. The upper end of the upper die punch 6 can be embedded in the centering hole 51 and they are fixed together by bolts; refer to the appendix of the specification. Figure 3As shown, the bottom part of the upper die punch 6 protrudes below the bottom surface of the turbine disk upper die 5, and the protruding part protrudes downward with the bottom center of the turbine disk upper die 5 as the center. The bottom surface of the part where the bottom of the upper die punch 6 protrudes below the bottom surface of the turbine disk upper die 5 is provided with an upper die cavity 61 which is concave upward. The protruding part and the upper die cavity 61 at the center of the bottom surface constitute the upper forming part of the forging processing of the semi-finished blank of the aircraft engine turbine disk; in order to facilitate the lower part of the semi-finished blank of the aircraft engine turbine disk The top surface of the turbine disk lower die 3 is provided with a downwardly concave lower die cavity 31, and the lower die cavity 31 corresponds to the protruding portion at the bottom of the upper die punch 6, and the protruding portion at the bottom of the upper die punch 6 is embedded with the lower die cavity 31. After the upper die base 1 and the lower die base 2 are molded, the upper die cavity 61 at the bottom of the upper die punch 6 and the corresponding lower die cavity 31 constitute the die forging cavity of the semi-finished blank of the aircraft engine turbine disk; in order to realize closed die forging, refer to the attached manual Figure 2 and 3 As shown, the top of the turbine disk lower die 3 is higher than the top of the lower die seat 2, and the height between the top surface of the turbine disk lower die 3 and the top surface of the lower die seat 2 is higher than the height between the bottom surface of the upper die punch 6 and the bottom surface of the upper die seat 1; the bottom surface of the upper die punch 6 is located outside the protruding part and is flush with the bottom surface of the turbine disk upper die 5. When the mold is closed, the protruding part of the bottom of the upper die punch 6 is embedded in the lower die cavity 31, and the bottom surface of the upper die punch 6 is located outside the protruding part and the bottom surface of the turbine disk upper die 5 is completely fitted together with the top surface of the turbine disk lower die 3. No flash will be generated during the die forging process, and the size of the die forging cavity formed between the upper die cavity 61 and the lower die cavity 31 is closer to the precision size of the aircraft engine turbine disk.

[0020] After die forging, when the upper die seat 1 drives the turbine disc upper die 5 and the upper die punch 6 to rise and open the die, in order to facilitate the ejection of the aircraft engine turbine disc semi-finished product in the lower die cavity 31 from the lower die cavity 31, it is convenient to remove it. Figure 2 and 3 As shown, a withdrawal hole 32 which passes through the bottom of the turbine disk lower mold 3 from top to bottom is provided at the bottom center of the lower mold cavity 31, and a push rod 7 is movably provided in the withdrawal hole 32; the push rod 7 is in a T-shaped structure, which is convenient for ejecting the semi-finished product of the aircraft engine turbine disk and increases the contact area with the bottom surface of the semi-finished product of the aircraft engine turbine disk, so as to avoid the aircraft engine turbine disk semi-finished product being easily deformed by force; the position of the ejection hole 22 on the lower mold base 2 corresponds to the position of the withdrawal hole 32 from top to bottom and is interconnected. When ejecting the material, the ejector of the hydraulic press can contact the bottom of the push rod 7 upward through the ejection hole 22, and the ejector pushes the push rod 7 upward to eject the semi-finished product of the aircraft engine in the lower mold cavity 31, so as to facilitate unloading.

[0021] This aircraft engine turbine disc forging die realizes the closed die forging processing of aircraft engine turbine discs. The size of the processed semi-finished products is closer to the product structure size of the aircraft engine turbine disc, and the subsequent processing allowance is small, which saves material consumption, reduces production costs, and improves processing efficiency.

[0022] It should be emphasized that the above are only preferred embodiments of the present invention and are not intended to limit the present invention. For those skilled in the art, the present invention may be subject to various modifications and changes. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A die forging die for an aircraft engine turbine disk, comprising an upper die seat (1) and a lower die seat (2) corresponding to each other, wherein a turbine disk upper die (5) fixedly connected thereto is disposed at the bottom center of the upper die seat (1), and a turbine disk lower die (3) fixedly connected thereto is disposed at the top center of the lower die seat (2), wherein the turbine disk upper die (5) and the turbine disk lower die (3) correspond to each other in the upper and lower directions; an upper die punch (6) fixedly connected thereto is disposed at the bottom center of the turbine disk upper die (5), and the bottom of the upper die punch (6) is The upper die punch (6) protrudes below the bottom surface of the turbine disc upper die (5); the bottom surface of the upper die punch (6) protruding below the bottom surface of the turbine disc upper die (5) is provided with an upwardly concave upper die cavity (61); the top surface of the turbine disc lower die (3) is provided with a downwardly concave lower die cavity (31), the lower die cavity (31) corresponds to the protruding portion of the bottom of the upper die punch (6) in the upper and lower directions, and the protruding portion of the bottom of the upper die punch (6) is embedded in the lower die cavity (31) in the upper and lower directions, characterized in that: An upper die groove (11) is provided at the bottom center of the upper die seat (1), and a lower die groove (21) is provided at the top center of the lower die seat (2); the turbine disc upper die (5) is embedded in the upper die groove (11) and fixedly connected together by bolts; the turbine disc lower die (3) is embedded in the lower die groove (21) and fixedly connected together by bolts; the outer periphery of the turbine disc lower die (3) is inclined from bottom to top to form a lower mating surface (33) with an outward camber angle of 2 to 5 degrees; the outer periphery of the turbine disc upper die (5) is inclined from top to bottom to form an upper mating surface (52) with an outward camber angle of 2 to 5 degrees; the side wall of the upper die groove (11) The structure of the lower die groove (21) is consistent with the structure of the upper mating surface (52), and the side wall of the lower die groove (21) is consistent with the structure of the lower mating surface (33); the top of the turbine disc lower die (3) is higher than the top of the lower die seat (2), and the height between the top surface of the turbine disc lower die (3) and the top surface of the lower die seat (2) is higher than the height between the bottom surface of the upper die punch (6) and the bottom surface of the upper die seat (1); the center of the bottom surface of the turbine disc upper die (5) is provided with an upwardly concave centering hole (51), the upper end of the upper die punch (6) is embedded in the centering hole (51), and the two are fixed together by bolts; the bottom surface of the upper die punch (6) is located outside the protruding part and is flush with the bottom surface of the turbine disc upper die (5).

2. The aero-engine turbine disk forging die according to claim 1, characterized in that: Lifting holes (4) are provided on the outer sides of the upper die base (1) and the outer sides of the lower die base (2).

3. The aero-engine turbine disk forging die according to claim 1, characterized in that: A material withdrawal hole (32) penetrating the bottom of the turbine disc lower die (3) from top to bottom is provided at the bottom center of the lower die cavity (31), and a push rod (7) is movably provided in the material withdrawal hole (32); a material ejection hole (22) penetrating the bottom is provided at a position of the top surface of the lower die base (2) corresponding to the material withdrawal hole (32), and the material ejection hole (22) and the material withdrawal hole (32) correspond to each other from top to bottom and are connected to each other.

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