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CN-121988855-A - High-temperature alloy diffusion welding device and welding process for aviation turbine disk

CN121988855ACN 121988855 ACN121988855 ACN 121988855ACN-121988855-A

Abstract

The invention relates to the technical field of diffusion welding devices, and discloses an aviation turbine disk high-temperature alloy diffusion welding device and a welding process thereof, wherein the aviation turbine disk high-temperature alloy diffusion welding device comprises mounting seats, positioning grooves are respectively formed in the two mounting seats, a mounting plate is arranged in the positioning grooves of the mounting seats, a pressing plate is arranged on one side of the mounting plate, limiting holes are uniformly formed in the two sides of the mounting plate and the mounting seat, the two sides of the limiting rod are fixedly connected with a connecting plate, a spring is uniformly and fixedly connected to one side of the connecting plate, a rotating shaft is rotatably connected to the inside of one end of the mounting seat, and racks are symmetrically meshed and connected to the tooth ends of the gears through central shafts. When the pressing plate is replaced, the connecting plate is pulled to enable the limit rods on two sides to be moved out synchronously through the linkage of the racks and the gears, the mounting plate and the pressing plate are taken out, a new mounting plate is put in and the holes are formed in Ji Xianwei, the mounting of the connecting plate is finished, and the rapid mounting and dismounting of the pressing plate are realized.

Inventors

  • LIU CHUAN
  • TANG BIN
  • LI JINSHAN

Assignees

  • 重庆三航新材料技术研究院有限公司

Dates

Publication Date
20260508
Application Date
20260318

Claims (10)

  1. 1. The utility model provides an aviation turbine disk superalloy diffusion welding device, includes workstation (1) and two mount pad (2), its characterized in that is two constant head tank (201) have all been seted up to the inside of mount pad (2), install mounting panel (202) in constant head tank (201) of mount pad (2), clamp plate (203) are installed to one side of mounting panel (202), spacing hole (204) have evenly been seted up to the inside both sides of mounting panel (202) and mount pad (2), both sides in spacing hole (204) of mounting panel (202) and mount pad (2) all sliding connection have gag lever post (205), both sides the one end of gag lever post (205) is fixedly connected with connecting plate (206), one side evenly fixedly connected with spring (207) of connecting plate (206), one end fixed connection of spring (207) is in one side of mount pad (2), one end inside rotation of mount pad (2) is connected with clamp plate (208), outer wall fixedly connected with gear (209) of axis of rotation (208), tooth end that gear (209) are center pin symmetry (210) is connected with rack (210), one side of the inside of the centre gripping subassembly (1) is connected with rack (210).
  2. 2. The high-temperature alloy diffusion welding device of an aviation turbine disk is characterized in that the outer wall of the rack (210) is slidably connected in the mounting seat (2), a sliding block (211) is fixedly connected to one side of the rack (210), sliding rails (212) are symmetrically arranged on one side of the mounting seat (2), and the outer wall of the sliding block (211) is slidably connected to the outer wall of the sliding rail (212).
  3. 3. The high-temperature alloy diffusion welding device of an aviation turbine disk is characterized in that a fixing frame (3) is fixedly connected to the top of a workbench (1), an air cylinder (301) is installed at the top of the fixing frame (3), the top of one mounting seat (2) is fixedly connected to the output end of the air cylinder (301), and the bottom of the other mounting seat (2) is fixedly connected to the top of the workbench (1).
  4. 4. The high-temperature alloy diffusion welding device of an aviation turbine disk is characterized in that the clamping assembly comprises a servo motor (4), the bottom of the servo motor (4) is installed inside a workbench (1), the output end of the servo motor (4) is fixedly connected with a rotating plate (401), two ends of the rotating plate (401) are rotationally connected with connecting rods (402), the tops of the connecting rods (402) are rotationally connected with sliding blocks (403), sliding grooves (404) are symmetrically formed in the tops of the workbench (1), and the outer walls of the sliding blocks (403) are slidably connected in the sliding grooves (404).
  5. 5. The high-temperature alloy diffusion welding device of an aviation turbine disk is characterized in that the tops of the sliding blocks (403) are fixedly connected with a supporting frame (5), a driving motor (501) is installed at the tops of the supporting frame (5), the output end of the driving motor (501) is fixedly connected with a threaded rod (502), one end of the threaded rod (502) is rotatably connected in the supporting frame (5), the outer wall of the threaded rod (502) is in threaded connection with a moving block (503), and the outer wall of the moving block (503) is in sliding connection with the supporting frame (5).
  6. 6. The high-temperature alloy diffusion welding device for aviation turbine discs according to claim 5, wherein one side of each of the two moving blocks (503) is fixedly connected with a supporting column (6), and one end of each supporting column (6) is fixedly connected with an arc clamping plate (601).
  7. 7. The high-temperature alloy diffusion welding device of an aviation turbine disk is characterized in that two sides of two mounting seats (2) are fixedly connected with connecting frames (7), one ends of a plurality of connecting frames (7) are fixedly connected with two annular pipes (701) in a matching mode, the inner walls of the two annular pipes (701) are respectively arranged on the outer walls of the two mounting seats (2), nozzles (702) are uniformly and fixedly connected to the inner walls of the annular pipes (701), one side of one annular pipe (701) is fixedly connected with a connecting pipe (703), one end of the connecting pipe (703) is fixedly connected with an air outlet pipe (704), and one end of the air outlet pipe (704) is fixedly connected in the other annular pipe (701).
  8. 8. The high-temperature alloy diffusion welding device of an aviation turbine disk is characterized in that a fixed rod (8) is fixedly connected to the top of the workbench (1), a connecting cylinder (801) is fixedly connected to the top of the fixed rod (8), the other end of the annular tube (701) is fixedly connected to the inside of the connecting cylinder (801), a sealing plug (802) is slidingly connected to the inner wall of the connecting cylinder (801), a movable rod (803) is fixedly connected to one side of the sealing plug (802), the outer wall of the movable rod (803) is slidingly connected to the inside of the connecting cylinder (801), a support (804) is fixedly connected to one end of the movable rod (803), one end of the support (804) is fixedly connected to one side of one support frame (5), and an air inlet pipe (805) is fixedly connected to the outer wall of the connecting cylinder (801).
  9. 9. The high-temperature alloy diffusion welding device of an aviation turbine disk according to claim 1, wherein a control panel (9) is fixedly connected to one side of the workbench (1), and the control panel (9) is electrically connected with electrical elements in the device.
  10. 10. An aviation turbine disk superalloy diffusion welding process is characterized by being applied to the aviation turbine disk superalloy diffusion welding device as claimed in any one of claims 1-9, and comprising the following steps: When the pressure plate (203) is replaced in use, an operator pulls one side of the connecting plate (206) to enable the limiting rod (205) to move out of the limiting hole (204) and the spring (207) to stretch, the connecting plate (206) drives the rack (210) to move, the driving gear (209) and the rotating shaft (208) rotate to drive the other side of the rack (210) and the connecting plate (206) to move, so that the limiting rods (205) on two sides are synchronously moved out, and the mounting plate (202) and the pressure plate (203) can be taken out; During installation, the installation plate (202) provided with the pressing plate (203) is placed in the positioning groove (201), the connecting plate (206) is loosened after the Ji Xianwei holes (204), and the reaction force of the spring (207) drives the limit rods (205) on two sides to be inserted into the limit holes (204) through the gear (209) and the rack (210) to complete installation; when welding operation is carried out, the upper section and the lower section of the turbine disk are aligned and placed on the lower pressing plate (203), a driving motor (501) is started to drive a threaded rod (502) to rotate, a moving block (503) and an arc clamping plate (601) are adjusted to be at proper heights up and down, a servo motor (4) is started to drive a rotating plate (401) to rotate, a sliding block (403) slides in a sliding groove (404) through a connecting rod (402), and a supporting frame (5) and the arc clamping plate (601) are driven to clamp the turbine disk; Meanwhile, the support frame (5) can drive the support frame (804), the movable rod (803) and the sealing plug (802) to block the air inlet pipe (805), the starting cylinder (301) can drive the upper mounting seat (2) and the pressing plate (203) to move downwards, the heating piece in the upper pressing plate (203) and the lower pressing plate (203) can heat the welding interface of the turbine disc at high temperature, and under the conditions of high temperature and high pressure, the welding interface atoms of the upper half section and the lower half section of the turbine disc are mutually diffused to form metallurgical bonding, so that diffusion welding operation is completed; after the welding operation is finished, the servo motor (4) reversely rotates to enable the arc clamping plate (601) to be loosened, the sealing plug (802) is far away from the air inlet pipe (805), argon enters the connecting cylinder (801) through the air inlet pipe (805), then enters the annular pipe (701) through the air outlet pipe (704) and the connecting pipe (703), is sprayed to the clamping plate (203) through the nozzle (702) to be cooled, and all electric elements are controlled through the control panel (9) in the whole process.

Description

High-temperature alloy diffusion welding device and welding process for aviation turbine disk Technical Field The invention relates to the technical field of diffusion welding devices, in particular to an aero turbine disk high-temperature alloy diffusion welding device and a welding process thereof. Background The aviation turbine disk is a core key component of an aeroengine, is used as a core bearing component for connecting turbine blades and an engine main shaft, has the main effects of transmitting the output torque of the engine and bearing the huge centrifugal force generated by the high-speed rotation of the turbine blades, is widely applied to the field of military and civil aeroengines, and is generally divided into semi-finished products of an upper half turbine disk and a lower half turbine disk due to the large size of the aviation turbine disk, and diffusion welding is used as a solid-phase welding method, so that the welding interface atoms of the upper half turbine disk and the lower half turbine disk can be mutually diffused under the conditions of high temperature and high pressure to form metallurgical bonding, the mechanical property of a welded joint and the base metal tend to be consistent, and the defects of weld seam air holes, cracks, brittle phase precipitation and the like generated by the traditional fusion welding technology are avoided, so that the high-temperature alloy diffusion welding device of the aviation turbine disk is needed. Traditional diffusion welding device, the clamp plate adopts fixed mounting generally, does not possess quick assembly disassembly function, leads to the turbine dish of device only to adapt to single specification, when needs switch the turbine dish of different models and carry out diffusion welding operation, operating personnel need to wholly dismantle and reassemble the frock, not only adjust the cycle length, the dress inefficiency is changed to the commonality extremely poor moreover, can't satisfy the flexible production requirement that aeroengine field is multiple kinds, small batch, high-efficient switch, seriously restricted aviation turbine dish diffusion welding's production efficiency and adaptation ability. Disclosure of Invention Aiming at the defects of the prior art, the invention provides an aero turbine disc high-temperature alloy diffusion welding device and a welding process thereof, which solve the problems that the conventional diffusion welding device is usually fixedly installed, does not have a quick dismounting function, and can only adapt to a turbine disc with single specification, when the turbine disc with different types needs to be switched to carry out diffusion welding operation, operators need to integrally dismount and reassemble a tool, the adjustment period is long, the replacement efficiency is low, the universality is extremely poor, the flexible production requirements of multi-variety, small-batch and high-efficiency switching in the aero turbine disc field can not be met, and the production efficiency and the adaptation capability of the aero turbine disc diffusion welding are seriously restricted. The high-temperature alloy diffusion welding device for the aviation turbine disk comprises a workbench and two mounting seats, wherein positioning grooves are formed in the two mounting seats, a mounting plate is mounted in each positioning groove of each mounting seat, a pressing plate is mounted on one side of each mounting plate, limiting holes are uniformly formed in the two sides of each mounting plate and each mounting seat, limiting rods are slidably connected in the limiting holes of each mounting plate and each mounting seat, one end of each limiting rod is fixedly connected with a connecting plate, one side of each connecting plate is uniformly and fixedly connected with a spring, one end of each spring is fixedly connected to one side of each mounting seat, a rotating shaft is rotatably connected in one end of each mounting seat, a gear is fixedly connected to the outer wall of each rotating shaft, racks are symmetrically meshed with the tooth ends of the gears, one end of each rack is fixedly connected to one side of each connecting plate, and clamping assemblies are mounted in the workbench. Through adopting above-mentioned technical scheme, when needs change the clamp plate according to different turbine discs, the pulling connecting plate makes the spring tensile, the gag lever post shifts out from the spacing hole, one side connecting plate removes simultaneously and drives the rack and remove, and then drive gear and axis of rotation rotate, make opposite side rack synchronous movement, drive opposite side connecting plate and spring tensile, both sides gag lever post shift out in step, can follow the inside of constant head tank with mounting panel and clamp plate later and shift out, during the installation, put into the constant head tank with the mounting panel that is equipped with th