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CN-122007335-A - High-temperature alloy casting device for spaceflight

CN122007335ACN 122007335 ACN122007335 ACN 122007335ACN-122007335-A

Abstract

The invention relates to the technical field of alloy casting, in particular to a high-temperature alloy casting device for spaceflight, which comprises a bracket, wherein a die frame is arranged in the bracket, the wax mould is characterized in that a plurality of wax moulds are fixedly connected to the mould frame, and clamping assemblies and driving assemblies are respectively arranged on two sides of the mould frame. The clamping assembly is matched with the driving assembly to realize stable clamping and accurate rotation of the die frame and ensure that all parts of the wax die are heated uniformly, the inserted rod is accurately corresponding to ports of the wax die, the heating assembly is used for heating the wax layer on the inner wall in a targeted manner, the reciprocating mechanism is combined to drive the inserted rod to rotate forward for half cycles and then rotate backward for half cycles, the wax layer is enabled to melt completely without dead angles, the high-precision requirement of space casting on wax die treatment is met, the collecting mechanism is linked with the driving assembly to realize efficient recovery of heated wax liquid, raw material waste is reduced, production cost of space high-temperature alloy casting is reduced, the integration degree of the whole structure is high, manual intervention is reduced by automatic operation, and the operation efficiency and stability are improved.

Inventors

  • QIAN ZHENJIE
  • QIAN DONGFANG
  • Guo Jingou
  • WANG HONGTAO
  • HU NINGNING
  • KANG FEI

Assignees

  • 东亚科技(苏州)有限公司

Dates

Publication Date
20260512
Application Date
20260303

Claims (10)

  1. 1. A high-temperature alloy casting device for spaceflight is characterized by comprising, The device comprises a bracket (1), wherein a die frame (17) is arranged in the bracket (1), a plurality of wax dies (18) are fixedly connected to the die frame (17), clamping assemblies and driving assemblies are respectively arranged on two sides of the die frame (17), the clamping assemblies are used for clamping the die frame (17), and the driving assemblies are used for driving the die frame (17) to rotate; The bottom of the inner side of the bracket (1) is fixedly connected with a workbench (2), a bottom box (23) is arranged above the workbench (2) through a lifting assembly, a plurality of inserting rods (25) are arranged at the top of the bottom box (23), heating assemblies are arranged on the inserting rods (25), the inserting rods (25) correspond to ports of a wax mould (18) in a vertical state, and the heating assemblies are used for heating and melting wax on the inner wall of the wax mould (18); the reciprocating mechanism is arranged in the bottom box (23), can drive the inserted rod (25) to reciprocate positively and negatively, and can firstly carry the inserted rod (25) to rotate positively and negatively for half a cycle and then rotate reversely for half a cycle; The collecting mechanism is arranged at one side of the workbench (2) and is used for collecting the heated wax liquid; the driving assembly is arranged on one side of the collecting mechanism and is used for driving the collecting mechanism.
  2. 2. The aerospace superalloy casting device according to claim 1, wherein the clamping assembly comprises a first electric push rod (15) fixedly arranged at one end of the side wall of the bracket (1), a push plate (16) is rotatably arranged at the driving end of the first electric push rod (15), and the outer wall of the push plate (16) corresponds to one end of the die frame (17).
  3. 3. The aerospace superalloy casting device according to claim 2, wherein the driving assembly comprises a propping frame (11) rotatably arranged on one side of the top of the support (1), a first gear (12) is fixedly arranged at one end of the propping frame (11), a second gear (13) is arranged in a meshed manner on the first gear (12), a first motor (14) is fixedly arranged on the top of the outer side of the support (1), a driving output end of the first motor (14) is in transmission connection with a transmission shaft, and the support (1) penetrated by the transmission shaft is fixedly connected with a central shaft of the second gear (13).
  4. 4. The aerospace superalloy casting device according to claim 3, wherein the lifting assembly comprises a second electric push rod (21) fixedly arranged in the middle of the bottom of the workbench (2), through grooves are formed in two sides of the workbench (2), a limiting rod (22) is slidably arranged in the through grooves, and the top of the limiting rod (22) is fixedly connected with the bottom of the bottom box (23).
  5. 5. The aerospace superalloy casting device according to claim 4, wherein the heating component comprises a protruding block (26) fixedly connected to the top of the inserted rod (25), a heating strip (27) is fixedly arranged on one side of the protruding block (26) and the outer wall of the inserted rod (25), one end of the heating strip (27) is fixedly connected with a conducting wire, and the conducting wire penetrates through the side wall of the inserted rod (25) and is connected with an external power supply.
  6. 6. The aerospace superalloy casting device according to claim 4 or 5 wherein the top of the bottom box (23) is detachably provided with a top cover (24), the outer side of the bottom of the insert rod (25) is provided with a collecting cover (28), and the collecting cover (28) is fixedly arranged on the top of the top cover (24).
  7. 7. The aerospace superalloy casting device according to claim 6, wherein the reciprocating mechanism comprises a plurality of inner rings (3) rotatably mounted at the bottom of the top cover (24), a connecting frame (31) is fixedly mounted on the outer wall of each inner ring (3), an outer ring (32) is fixedly mounted at the other end of each connecting frame (31), a plurality of transmission teeth (33) are fixedly mounted on the outer wall of each outer ring (32), the transmission teeth (33) on the outer sides of two adjacent outer rings (32) are meshed, a plurality of outer teeth (34) are fixedly mounted on the inner wall of each outer ring (32), a plurality of inner teeth (35) are fixedly mounted on the outer wall of each inner ring (3), a third gear (36) is arranged between each outer ring (32) and each inner ring (3), and each third gear (36) penetrates through the bottom of the top cover (24) and is fixedly connected with the bottom of the corresponding inserted rod (25).
  8. 8. The aerospace superalloy casting device according to claim 7 wherein the inner teeth (35) extend from an axial top end to an axial bottom end in the axial direction of the inner ring (3) and the outer teeth (34) extend from an axial bottom end to an axial top end in the axial direction of the outer ring (32).
  9. 9. The aerospace superalloy casting device according to claim 8, wherein the collecting mechanism comprises a sealing cylinder (46) fixedly arranged on one side of the workbench (2), a sealing plug (45) is movably arranged in an inner cavity of the sealing cylinder (46), an extrusion rod (44) is fixedly connected to the middle of one side of the sealing plug (45), a feed pipe (47) is arranged at two ends of one side of the sealing cylinder (46) in a communicated mode, the other end of the feed pipe (47) is communicated with the inner cavity of a corresponding collecting cover (28), two adjacent collecting covers (28) are communicated through a guide pipe, a discharge pipe (48) is arranged at two ends of the other side of the sealing cylinder (46) in a communicated mode, a one-way valve (49) is arranged on each of the discharge pipe (48) and the feed pipe (47), the one-way valve (49) of the discharge pipe (48) flows to the outside, and the one-way valve (49) of the feed pipe (47) flows to the outside through the collecting cover (28) to the sealing cylinder (46).
  10. 10. The aerospace superalloy casting device according to claim 9, wherein the driving assembly comprises a second motor (38) fixedly arranged on one side of the inner wall of the bottom box (23), a driving output end of the second motor (38) is in transmission connection with a transmission shaft, the other end of the transmission shaft and the other end of the inner wall of the bottom box (23) are respectively provided with a shaft coupling (4), a transmission belt (41) is correspondingly arranged on the two shafts (4) in transmission, one shaft coupling (4) is fixedly connected with a central shaft of a fourth gear (37), the middle part of the other shaft coupling (4) penetrates through the bottom of the bottom box (23) and is fixedly connected with an eccentric disc (42), a driving arm (43) is rotatably arranged on the outer wall of the eccentric disc (42), and the other end of the driving arm (43) is rotatably connected with the other end of the extrusion rod (44).

Description

High-temperature alloy casting device for spaceflight Technical Field The invention relates to the technical field of alloy casting, in particular to a high-temperature alloy casting device for spaceflight. Background At present, in the field of aerospace high-temperature alloy casting, wax pattern preparation and treatment are key links for guaranteeing casting precision, and the follow-up alloy forming quality is directly influenced, however, the conventional wax pattern treatment device has a plurality of defects in practical application, and is difficult to meet the severe requirements of aerospace casting on high precision and high stability. The conventional heating assembly is of a fixed structure, only a local area of the inner wall of the wax mold can be heated, the whole area of the inner wall cannot be covered, obvious heating dead angles exist, insufficient wax layer melting and more residues are caused, additional manual cleaning is needed, and the operation flow and error risk are increased; the design of the wax liquid collecting system is unreasonable, molten wax liquid is easy to drop to the surface of equipment or a workbench, the collecting efficiency is low, the raw materials are seriously wasted, the production cost is increased, and equipment pollution and potential safety hazards can be caused by wax liquid leakage. There is a need for improvement, and we propose a superalloy casting device for aerospace use. Disclosure of Invention The present invention has been made in view of the above or the problem in the prior art that it is difficult to collect wax liquid. Accordingly, the invention aims to provide a high-temperature alloy casting device for aerospace. In order to solve the technical problems, the invention provides the following technical proposal that comprises, The device comprises a bracket, wherein a mold frame is arranged in the bracket, a plurality of wax molds are fixedly connected to the mold frame, clamping assemblies and driving assemblies are respectively arranged on two sides of the mold frame, the clamping assemblies are used for clamping the mold frame, and the driving assemblies are used for driving the mold frame to rotate; the bottom of the inner side of the bracket is fixedly connected with a workbench, a bottom box is arranged above the workbench through a lifting assembly, a plurality of inserted bars are arranged at the top of the bottom box, heating assemblies are arranged on the inserted bars, the inserted bars correspond to the ports of the wax mould in a vertical state, and the heating assemblies are used for heating and melting wax on the inner wall of the wax mould; The reciprocating mechanism is arranged in the bottom box and can drive the insert rod to reciprocate in the forward and reverse directions; The collecting mechanism is arranged at one side of the workbench and is used for collecting the heated wax liquid; the driving assembly is arranged on one side of the collecting mechanism and is used for driving the collecting mechanism. As a preferable scheme of the high-temperature alloy casting device for spaceflight, the clamping assembly comprises a first electric push rod fixedly arranged at one end of the side wall of the bracket, a push plate is rotatably arranged at the driving end of the first electric push rod, and the outer wall of the push plate corresponds to one end of the die frame. As a preferable scheme of the high-temperature alloy casting device for spaceflight, the driving assembly comprises a propping frame rotatably arranged on one side of the top of the support, one end of the propping frame is fixedly provided with a first gear, the first gear is meshed with and provided with a second gear, the top of the outer side of the support is fixedly provided with a first motor, the driving output end of the first motor is in transmission connection with a transmission shaft, and the support penetrated by the transmission shaft is fixedly connected with a middle shaft of the second gear. As a preferable scheme of the high-temperature alloy casting device for spaceflight, the lifting assembly comprises a second electric push rod fixedly arranged in the middle of the bottom of the workbench, through grooves are formed in two sides of the workbench in a penetrating mode, a limiting rod is slidably arranged in the through grooves, and the top of the limiting rod is fixedly connected with the bottom of the bottom box. As a preferable scheme of the high-temperature alloy casting device for spaceflight, the heating assembly comprises a protruding block fixedly connected to the top of the inserted link, a heating strip is fixedly arranged on one side of the protruding block and the outer wall of the inserted link, one end of the heating strip is fixedly connected with a conducting wire, and the conducting wire penetrates through the side wall of the inserted link and is connected with an external power supply. As a preferable scheme of the h