Anti-fatigue aero-engine blade machining device and process

Abstract

The invention discloses an anti-fatigue aero-engine blade machining device and technology, and relates to the technical field of engine blade machining. The device comprises a device outer frame and an aero-engine blade body, a first mesh plate and a second mesh plate which are matched for use are fixedly mounted at the lower end of an inner cavity of the device outer frame, and a shot blasting mechanism which is matched for use is fixedly mounted at the lower end of the side, close to the first mesh plate, of the inner cavity of the device outer frame; through cooperative use of the transferring mechanism and the limiting mechanism, the transferring support can be conveniently moved towards the outer side of the device outer frame, limiting rotating discs and limiting pressing blocks at the upper end and the lower end can be driven to rotate correspondingly, and then the butt joint and dislocation relation between the limiting pressing blocks at the upper end and the lower end and limiting inserting grooves can be adjusted correspondingly; therefore, the upper end of the aero-engine blade body can be clamped and mounted and the lower end of the aero-engine blade body can be detached and separated, convenience is provided for detaching and mounting of the aero-engine blade body, and a user can operate and use the aero-engine blade conveniently.

Description

Technical Field

[0001] The present invention relates to the technical field of engine blade processing, and specifically to an anti-fatigue aero-engine blade processing device and process. Background Technique

[0002] An aero-engine is a highly complex and precise thermal machine. To improve the anti-fatigue property of aero-engine blades, shot peening treatment is required. Shot peening is a surface strengthening process widely used in factories, that is, a cold working process in which shot particles bombard the surface of a workpiece and implant residual compressive stress to improve the fatigue strength of the workpiece.

[0003] However, there are still certain deficiencies in the existing anti-fatigue aero-engine blade processing devices during use: 1. There are defects in the disassembly and assembly of aero-engine blades, which are not convenient for users to operate. 2. It is not convenient to push and concentrate the shot particles generated by shot peening, so it is not convenient for later centralized treatment.

[0004] In view of the above problems, the present application proposes an anti-fatigue aero-engine blade processing device and process to solve the above problems. Summary of the Invention

[0005] In order to solve the problems that there are defects in the disassembly and assembly of aero-engine blades during the use of the existing technology and it is not convenient to push and concentrate the shot particles generated by shot peening; the purpose of the present invention is to provide an anti-fatigue aero-engine blade processing device and process.

[0006] To solve the above technical problems, the present invention adopts the following technical solutions: An anti-fatigue aero-engine blade processing device includes a device outer frame and an aero-engine blade body. A first mesh plate and a second mesh plate for cooperative use are fixedly installed at the lower end of the inner cavity of the device outer frame, and a shot peening mechanism for cooperative use is fixedly installed at the lower end of one side of the inner cavity of the device outer frame close to the first mesh plate. A transfer mechanism and a limiting mechanism for cooperative use with the shot peening mechanism and the aero-engine blade body are provided at the top end of the inner cavity of the device outer frame, and a boosting mechanism for cooperative use with the limiting mechanism is provided on one side of the device outer frame. An aggregate mechanism for cooperative use with the shot peening mechanism is provided at the bottom end of the inner cavity of the device outer frame. The cooperative use of the transfer mechanism and the limiting mechanism facilitates the disassembly and assembly of the aero-engine blade body. The setting and use of the boosting mechanism realize the convenient blanking of the aero-engine blade body after shot peening. The setting and use of the aggregate mechanism can push and concentrate the shot particles generated by shot peening.

[0007] Preferably, the transfer mechanism includes an electric cylinder body fixedly installed at the top end of the inner cavity of the device outer frame. An electric cylinder slider is slidably arranged on the electric cylinder body. The bottom end of the electric cylinder slider is fixedly installed with a transfer bracket, and the transfer bracket is slidably connected to the device outer frame. A transverse guide rod is fixedly inserted into the upper end of the device outer frame, and the transfer bracket is slidably sleeved on the transverse guide rod. A transverse guide hole is formed through the upper end of the transfer bracket, and the transverse guide rod slidably penetrates through the transverse guide hole. One end of the transfer bracket away from the electric cylinder slider can be slidably inserted into the device outer frame, and the bottom end of the transfer bracket is slidably inserted between the first mesh plate and the second mesh plate. The limiting mechanism includes an installation cylinder fixedly inserted on the transfer bracket. A driving motor is fixedly installed at the top end of the inner cavity of the installation cylinder. The output end of the driving motor rotates through the installation cylinder and a rotating bracket is fixedly sleeved at its end. The top end of the rotating bracket is fixedly sleeved with an installation cylinder column. A limiting outer ring is fixedly sleeved on the outside of the installation cylinder column. A plurality of limiting slots are arranged in an array on the outer wall of the limiting outer ring. One end of the aeroengine blade body can be slidably inserted into the limiting slot. Limiting turntables are rotatably installed at the top and bottom ends of the limiting outer ring. A plurality of limiting pressing blocks are integrally formed on the limiting turntables. The limiting pressing blocks are used in cooperation with the limiting slots. A driven gear ring is fixedly installed on the inner side of the limiting turntable. A first double-shaft motor is fixedly installed in the middle of the inner cavity of the installation cylinder column. The output ends on both sides of the first double-shaft motor rotate through the installation cylinder column and driving gears are fixedly sleeved at their ends. Symmetrically distributed electric push rods are fixedly inserted into the installation cylinder column. The end of the output end of the electric push rod is fixedly connected with a lifting support rod. A connecting gear is rotatably sleeved on the lifting support rod. The connecting gear can be meshed with the driving gear and the driven gear ring. A limiting gear is fixedly sleeved at the end of the lifting support rod. The limiting gear can be meshed with the driven gear ring. The outer wall of the lifting support rod and the inner wall of the middle part of the connecting gear are both damping structures. The connecting gear and the limiting gear are distributed in a staggered manner in the vertical plane.

[0008] Preferably, the boosting mechanism includes a side connection support plate fixedly connected to the device outer frame. An electric telescopic rod is fixedly installed at the top end of one side of the side connection support plate. The output end of the electric telescopic rod slides through the side connection support plate and a boosting cross plate is fixedly sleeved at its end. A boosting frame body is integrally formed at one end of the boosting cross plate. A vertical guide rod is fixedly inserted at the end of the boosting cross plate away from the boosting frame body. The vertical guide rod slides through the side connection support plate. A vertical guide hole is formed through the end of the side connection support plate close to the device outer frame. The vertical guide rod slides through the vertical guide hole. An arc-shaped rubber pad is fixedly connected to the bottom end of the boosting frame body. The arc-shaped rubber pad can be in contact with the aeroengine blade body.

[0009] Preferably, the aggregate mechanism includes a second double-shaft motor, a first rotating rod and a second rotating rod. The second double-shaft motor is fixedly installed at the bottom end of the inner cavity on the side of the device outer frame close to the shot peening mechanism. The end of the output end on one side of the second double-shaft motor is fixedly connected with a driving lead screw. The driving lead screw is rotatably inserted on the device outer frame, and an aggregate pushing plate is sleeved on the outer side of the driving lead screw in a threaded manner. The aggregate pushing plate is slidably clamped at the bottom end of the inner cavity of the device outer frame. The end of the output end on the other side of the second double-shaft motor is fixedly sleeved with a first bevel gear. The first rotating rod and the second rotating rod are both rotatably inserted at the bottom end of the inner cavity on the side of the device outer frame close to the second double-shaft motor. A second bevel gear is fixedly sleeved on the first rotating rod. The second bevel gear meshes with the first bevel gear. First discs are fixedly sleeved at both ends of the first rotating rod. Second discs are fixedly sleeved at both ends of the second rotating rod. A transmission belt is sleeved on the outer sides of the adjacent second discs and the first discs in a transmission manner. A baffle tarpaulin is wound around the second rotating rod. The leading end of the baffle tarpaulin slidably penetrates through the device outer frame and is fixedly connected with the aggregate pushing plate.

[0010] A processing technology of an anti-fatigue aero-engine blade processing device includes the following steps: Step 1: The electric cylinder body drives the electric cylinder slider to move towards the side close to the boosting mechanism, so as to drive the transfer bracket to move synchronously, and further drive the limiting mechanism to move synchronously and gradually move the transfer bracket to the outside of the device outer frame. When the electric cylinder slider moves to the other end of the electric cylinder body, the electric cylinder body is paused. Step 2: Start the two electric push rods synchronously, so as to drive the two lifting support rods to move downward synchronously, and further separate the lower connecting gear from the corresponding driving gear and the driven gear ring and make the lower limiting gear mesh with the corresponding driven gear ring, and make the upper connecting gear mesh with the corresponding driving gear and the driven gear ring and separate the upper limiting gear from the corresponding driven gear ring. Then turn off the electric push rods and start the first double-shaft motor, so as to drive the two driving gears to rotate synchronously, and further drive the upper connecting gear to rotate, and further drive the upper driven gear ring to rotate, so as to drive the upper limiting turntable and the limiting pressing block to rotate synchronously. When the limiting pressing block and the limiting slot are completely misaligned, pause the first double-shaft motor and insert a plurality of aero-engine blade bodies to be shot peened into the limiting slots in sequence. Then drive the first double-shaft motor to reverse, so as to drive the upper limiting pressing block to reverse and reset, and further fix the corresponding aero-engine blade body to be shot peened stably and conveniently in the corresponding limiting slot. Then start the upper electric push rod, so as to drive the corresponding connecting gear and the limiting gear to move upward. When the upper connecting gear is separated from the corresponding driving gear and the driven gear ring and the limiting gear meshes with the corresponding driven gear ring, turn off the corresponding electric push rod. Step 3: Reset the transfer bracket and start the shot peening mechanism. At this time, the shot peening mechanism can perform shot peening on the corresponding aero-engine blade body to be shot peened. During this period, the drive motor can drive the rotating bracket to rotate, thereby driving the mounting cylinder column to rotate, further driving the limiting outer ring to rotate, and further driving the fixed aero-engine blade body to rotate and adjust its position, so as to fully perform shot peening on all the fixed aero-engine blade bodies; Step 4: Transfer the shot peened aero-engine blade body to the outside of the device frame through the transfer bracket and start the electric push rod at the lower end, so that the connecting gear at the lower end can mesh with the corresponding driving gear and driven gear ring, and when the limiting gear is separated from the corresponding driven gear ring, the corresponding electric push rod is closed. Then start the electric telescopic rod, which can drive the boosting cross plate to lift conveniently, further drive the boosting frame to lift conveniently, and further drive the arc-shaped rubber pad to lift conveniently. During this period, the drive motor will drive the limiting outer ring to rotate and adjust again, so that the shot peened aero-engine blade body can be pushed out of the corresponding limiting slot through the arc-shaped rubber pad in turn, thus realizing the convenient blanking of the shot peened aero-engine blade body; Step 5: At the same time, the second double-shaft motor will drive the drive screw rod and the first bevel gear to rotate forward and backward alternately, so that the aggregate pushing plate can make a reciprocating motion, and drive the first rotating rod to rotate forward and backward alternately through the second bevel gear. Further, the second rotating rod can be driven to rotate forward and backward alternately through the first disc, transmission belt and second disc, and further drive the baffle tarpaulin to perform an alternating motion of unwinding and winding, so as to push and concentrate the pellets generated by shot peening. During the pushing process, the baffle tarpaulin can intercept the remaining pellets falling from above to prevent them from accumulating between the aggregate pushing plate and the second double-shaft motor, thus ensuring the full and normal development of the subsequent pellet pushing and concentrating operation. In addition, the intercepted pellets will fall on the side of the aggregate pushing plate far from the second double-shaft motor when the baffle tarpaulin is wound up.

[0011] Compared with the prior art, the beneficial effects of the present invention are as follows: 1. By the combined use of the transfer mechanism and the limiting mechanism, the transfer bracket can be conveniently moved to the outside of the device frame, and it provides convenience for the meshing and separation of the connecting gear at the lower end with the corresponding driving gear and driven gear ring, the meshing and separation of the limiting gear at the lower end with the corresponding driven gear ring, the meshing and separation of the connecting gear at the upper end with the corresponding driving gear and driven gear ring, and the meshing and separation of the limiting gear at the upper end with the corresponding driven gear ring. Thereby, the limiting turntable and limiting block at the upper and lower ends can be driven to rotate respectively, and then the docking and misalignment relationship between the upper and lower limiting blocks and the limiting slots can be adjusted respectively, so as to realize the upper-end clamping installation and lower-end disassembly separation of the aero-engine blade body, thus providing convenience for the disassembly and assembly of the aero-engine blade body and facilitating the user to operate and use; 2. By setting up and using the boosting mechanism, the boosting cross plate can be driven to lift conveniently, so that the boosting frame can be driven to lift conveniently, and then the arc-shaped rubber pad can be driven to lift conveniently. Thus, the arc-shaped rubber pad can be used to push the aviation engine blade body after shot peening out of the corresponding limiting slots in sequence, and then the convenient blanking of the aviation engine blade body after shot peening is realized, which further provides convenience for the operation and use of the user. 3. By setting up and using the aggregate mechanism, the aggregate pushing plate can be driven to make a reciprocating motion, and the first rotating rod can be driven to rotate forward and backward alternately through the second bevel gear. Thus, the second rotating rod can be driven to rotate forward and backward alternately through the first round plate, the transmission belt and the second round plate, and then the baffle tarpaulin can be driven to perform the alternate motion of unwinding and rewinding. Therefore, the pellets generated by shot peening can be pushed and concentrated, which is convenient for subsequent centralized treatment. During the pushing process, the baffle tarpaulin can intercept the residual pellets falling from above to prevent them from accumulating between the aggregate pushing plate and the second double-shaft motor, thus ensuring the full and normal development of the subsequent pellet pushing and concentrating operation. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the following drawings are only some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0013] Figure 1 It is a schematic structural diagram of the present invention.

[0014] Figure 2 It is a schematic installation diagram of the aggregate mechanism in the present invention.

[0015] Figure 3 For the present invention Figure 2 The enlarged schematic diagram of the structure at A in it.

[0016] Figure 4 For the present invention Figure 2 The enlarged schematic diagram of the structure at B in it.

[0017] Figure 5 For the present invention Figure 2 The enlarged schematic diagram of the structure at C in it.

[0018] Figure 6 For the present invention Figure 2 The enlarged schematic diagram of the structure at D in it.

[0019] Figure 7 It is a schematic installation diagram of the limiting mechanism in the present invention.

[0020] Figure 8For the present invention Figure 7 Schematic enlarged view of the structure at position E in the present invention.

[0021] Figure 9 For the present invention Figure 7 Schematic enlarged view of the structure at position F in the present invention.

[0022] In the figure: 1. Outer frame of the device; 11. First mesh plate; 12. Second mesh plate; 2. Aeroengine blade body; 3. Transfer mechanism; 31. Electric cylinder body; 32. Electric cylinder slider; 33. Transfer bracket; 34. Horizontal guide rod; 35. Horizontal guide hole; 4. Limiting mechanism; 41. Installation cylinder; 42. Driving motor; 43. Rotating bracket; 44. Installation cylinder column; 45. Limiting outer ring; 46. Limiting slot; 47. Limiting turntable; 48. Limiting pressure block; 49. Driven gear ring; 410. First double-shaft motor; 411. Driving gear; 412. Electric push rod; 413. Lifting support rod; 414. Connecting gear; 415. Limiting gear; 5. Boosting mechanism; 51. Side connection support plate; 52. Electric telescopic rod; 53. Boosting cross plate; 54. Boosting frame; 55. Arc-shaped rubber pad; 56. Vertical guide rod; 57. Vertical guide hole; 6. Aggregating mechanism; 61. Second double-shaft motor; 62. First rotating rod; 63. Second rotating rod; 64. Driving lead screw; 65. Aggregating push plate; 66. First bevel gear; 67. Second bevel gear; 68. First round plate; 69. Second round plate; 610. Transmission belt; 611. Material-blocking tarpaulin. Specific embodiments

[0023] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0024] Embodiment: As Figures 1-9As shown in the figure, the present invention provides a processing device for an anti-fatigue aeroengine blade, which includes a device outer frame 1 and an aeroengine blade body 2. A first mesh plate 11 and a second mesh plate 12 used in cooperation are fixedly installed at the lower end of the inner cavity of the device outer frame 1. And a shot peening mechanism used in cooperation is fixedly installed at the lower end of one side of the inner cavity of the device outer frame 1 close to the first mesh plate 11. The shot peening mechanism includes a manipulator and a shot peening device used in cooperation, so as to realize the shot peening treatment of the aeroengine blade body 2. This is the prior art and will not be elaborated here. A transfer mechanism 3 and a limiting mechanism 4 used in cooperation with the shot peening mechanism and the aeroengine blade body 2 are provided at the top end of the inner cavity of the device outer frame 1. And a boosting mechanism 5 used in cooperation with the limiting mechanism 4 is provided on one side of the device outer frame 1. An aggregate mechanism 6 used in cooperation with the shot peening mechanism is provided at the bottom end of the inner cavity of the device outer frame 1. The cooperation of the transfer mechanism 3 and the limiting mechanism 4 provides convenience for the disassembly and assembly of the aeroengine blade body 2. The setting and use of the boosting mechanism 5 realize the convenient blanking of the aeroengine blade body 2 after shot peening. The setting and use of the aggregate mechanism 6 can push and concentrate the pellets generated by shot peening.

[0025] The transfer mechanism 3 includes an electric cylinder body 31, which is fixedly installed at the top end of the inner cavity of the device outer frame 1. A slider 32 of the electric cylinder is slidably arranged on the electric cylinder body 31. The bottom end of the slider 32 of the electric cylinder is fixedly installed with a transfer bracket 33, and the transfer bracket 33 is slidably connected to the device outer frame 1. A transverse guide rod 34 is fixedly inserted at the upper end of the device outer frame 1, and the transfer bracket 33 is slidably sleeved on the transverse guide rod 34. A transverse guide hole 35 is formed through the upper end of the transfer bracket 33, and the transverse guide rod 34 slidably penetrates through the transverse guide hole 35. The cooperation between the transverse guide rod 34 and the transverse guide hole 35 plays a role in limiting and guiding the movement adjustment of the transfer bracket 33. One end of the transfer bracket 33 away from the slider 32 of the electric cylinder can be slidably inserted into the device outer frame 1, and the bottom end of the transfer bracket 33 is slidably inserted between the first mesh plate 11 and the second mesh plate 12. The limiting mechanism 4 includes an installation cylinder body 41, which is fixedly inserted on the transfer bracket 33. A driving motor 42 is fixedly installed at the top end of the inner cavity of the installation cylinder body 41. The output end of the driving motor 42 rotates through the installation cylinder body 41 and a rotating bracket 43 is fixedly sleeved at its end. An installation cylinder column 44 is fixedly sleeved at the top end of the rotating bracket 43. A limiting outer ring 45 is fixedly sleeved on the outer side of the installation cylinder column 44. A plurality of limiting slots 46 are formed in an array on the outer wall of the limiting outer ring 45. One end of the aeroengine blade body 2 can be slidably inserted into the limiting slots 46. Limiting turntables 47 are rotatably installed at the top and bottom ends of the limiting outer ring 45, and a plurality of limiting blocks 48 are integrally formed on the limiting turntables 47. The limiting blocks 48 cooperate with the limiting slots 46. A driven gear ring 49 is fixedly installed inside the limiting turntable 47. A first double-shaft motor 410 is fixedly installed in the middle of the inner cavity of the installation cylinder column 44. The output ends on both sides of the first double-shaft motor 410 rotate through the installation cylinder column 44 and driving gears 411 are fixedly sleeved at their ends. Symmetrically distributed electric push rods 412 are fixedly inserted on the installation cylinder column 44. The end of the output end of the electric push rod 412 is fixedly connected with a lifting support rod 413. A connecting gear 414 is rotatably sleeved on the lifting support rod 413, and the connecting gear 414 can mesh with the driving gear 411 and the driven gear ring 49. A limiting gear 415 is fixedly sleeved at the end of the lifting support rod 413, and the limiting gear 415 can mesh with the driven gear ring 49. The outer wall of the lifting support rod 413 and the inner wall of the middle part of the connecting gear 414 are both of damping structure, and the connecting gear 414 and the limiting gear 415 are distributed in a staggered manner in the vertical plane, so that the connecting gear 414 and the limiting gear 415 can alternately mesh with the driving gear 411.

[0026] By adopting the above technical solution, the cylinder body 31 will drive the cylinder slider 32 to move towards the side close to the boosting mechanism 5, so as to drive the transfer bracket 33 to move synchronously, and further drive the limiting mechanism 4 to move synchronously and gradually move the transfer bracket 33 to the outside of the device outer frame 1. When the cylinder slider 32 moves to the other end of the cylinder body 31, the cylinder body 31 is paused, and two electric push rods 412 are started synchronously, so as to drive the two lifting support rods 413 to move downward synchronously, and further enable the lower connecting gear 414 to be separated from the corresponding driving gear 411 and the driven gear ring 49, and enable the lower limiting gear 415 to be engaged with the corresponding driven gear ring 49, and enable the upper connecting gear 414 to be engaged with the corresponding driving gear 411 and the driven gear ring 49 and enable the upper limiting gear 415 to be separated from the corresponding driven gear ring 49. Then, the electric push rod 412 is closed and the first double-shaft motor 410 is started, so as to drive the two driving gears 411 to rotate synchronously, and further drive the upper connecting gear 414 to rotate, and further drive the upper driven gear ring 49 to rotate, so as to drive the upper limiting turntable 47 and the limiting pressure block 48 to rotate synchronously. When the limiting pressure block 48 is completely misaligned with the limiting slot 46, the first double-shaft motor 410 is paused and a plurality of aeroengine blade bodies 2 to be shot-peened are inserted into the limiting slot 46 in sequence. Then, the first double-shaft motor 410 is driven to reverse, so as to drive the upper limiting pressure block 48 to reverse and reset, and further fix the corresponding aeroengine blade body 2 to be shot-peened stably and conveniently in the corresponding limiting slot 46. Subsequently, the upper electric push rod 412 is started, so as to drive the corresponding connecting gear 414 and the limiting gear 415 to move upward, and when the upper connecting gear 414 is separated from the corresponding driving gear 411 and the driven gear ring 49 and the limiting gear 415 is engaged with the corresponding driven gear ring 49, the corresponding electric push rod 412 is closed. The transfer bracket 33 is reset and the shot-peening mechanism is started. At this time, the shot-peening mechanism can perform shot-peening treatment on the corresponding aeroengine blade body 2 to be shot-peened. During this period, the driving motor 42 can drive the rotating bracket 43 to rotate, so as to drive the mounting cylinder column 44 to rotate, and further drive the limiting outer ring 45 to rotate, and further drive the fixed aeroengine blade body 2 to rotate and adjust the position, so as to fully perform shot-peening treatment on all the fixed aeroengine blade bodies 2.

[0027] The boosting mechanism 5 includes a side connection support plate 51. The side connection support plate 51 is fixedly connected to the outer frame 1 of the device. And at the top end of one side of the side connection support plate 51, an electric telescopic rod 52 is fixedly installed. The output end of the electric telescopic rod 52 slidably penetrates through the side connection support plate 51 and a boosting cross plate 53 is fixedly sleeved at its end. And at one end of the boosting cross plate 53, a boosting frame body 54 is integrally formed. At the end of the boosting cross plate 53 away from the boosting frame body 54, a vertical guide rod 56 is fixedly inserted. And the vertical guide rod 56 slidably penetrates through the side connection support plate 51. A vertical guide hole 57 is penetrated and opened at one end of the side connection support plate 51 close to the outer frame 1 of the device. And the vertical guide rod 56 slidably penetrates through the vertical guide hole 57. The cooperation of the vertical guide rod 56 and the vertical guide hole 57 plays a role in limiting and guiding the movement adjustment of the boosting cross plate 53. At the bottom end of the boosting frame body 54, an arc-shaped rubber pad 55 is fixedly connected. And the arc-shaped rubber pad 55 can be in contact with the aero-engine blade body 2.

[0028] By adopting the above technical solution, the aero-engine blade body 2 after shot peening is transferred to the outside of the outer frame 1 of the device through the transfer bracket 33 and the electric push rod 412 at the lower end is started. Thus, the connecting gear 414 at the lower end can be engaged with the corresponding driving gear 411 and the driven gear ring 49, and when the limiting gear 415 is separated from the corresponding driven gear ring 49, the corresponding electric push rod 412 is closed. Subsequently, the electric telescopic rod 52 is started, so that the boosting cross plate 53 can be driven to lift conveniently. Furthermore, the boosting frame body 54 can be driven to lift conveniently. Further, the arc-shaped rubber pad 55 can be driven to lift conveniently. During this period, the driving motor 42 will drive the limiting outer ring 45 to rotate and adjust again. Thus, the aero-engine blade body 2 after shot peening can be pushed out of the corresponding limiting slot 46 in turn through the arc-shaped rubber pad 55.

[0029] The aggregate mechanism 6 includes a second double-shaft motor 61, a first rotating rod 62 and a second rotating rod 63. The second double-shaft motor 61 is fixedly installed at the bottom end of the inner cavity of the outer frame 1 of the device close to the shot peening mechanism. And at the end of the output end on one side of the second double-shaft motor 61, a driving lead screw 64 is fixedly connected. The driving lead screw 64 is rotatably inserted on the outer frame 1 of the device. And an aggregate pushing plate 65 is threadedly sleeved on the outer side of the driving lead screw 64. The aggregate pushing plate 65 is slidably clamped at the bottom end of the inner cavity of the outer frame 1 of the device. At the end of the output end on the other side of the second double-shaft motor 61, a first bevel gear 66 is fixedly sleeved. The first rotating rod 62 and the second rotating rod 63 are both rotatably inserted at the bottom end of the inner cavity of the outer frame 1 of the device close to the second double-shaft motor 61. And a second bevel gear 67 is fixedly sleeved on the first rotating rod 62. The second bevel gear 67 is meshed with the first bevel gear 66. At both ends of the first rotating rod 62, first disc wheels 68 are fixedly sleeved. At both ends of the second rotating rod 63, second disc wheels 69 are fixedly sleeved. And a transmission belt 610 is sleeved on the outer sides of the adjacent second disc wheels 69 and the first disc wheels 68 in a transmission manner. A material blocking tarpaulin 611 is wound around the second rotating rod 63. And the leading end of the material blocking tarpaulin 611 slidably penetrates through the outer frame 1 of the device and is fixedly connected to the aggregate pushing plate 65.

[0030] By adopting the above technical solution, the second double-shaft motor 61 will drive the driving lead screw 64 and the first bevel gear 66 to rotate forward and backward alternately, so as to drive the aggregate pushing plate 65 to make a reciprocating motion, and can drive the first rotating rod 62 to rotate forward and backward alternately through the second bevel gear 67. Furthermore, the second rotating rod 63 can be driven to rotate forward and backward alternately through the first disc 68, the transmission belt 610 and the second disc 69, and further, the baffle tarpaulin 611 can be driven to perform an alternating motion of unwinding and winding, so as to push and concentrate the pellets generated by shot peening. During the pushing process, the baffle tarpaulin 611 can intercept the residual pellets falling from above, preventing them from accumulating between the aggregate pushing plate 65 and the second double-shaft motor 61, thus ensuring the full and normal development of the subsequent pellet pushing and concentrating operation. In addition, the intercepted pellets will fall on the side of the aggregate pushing plate 65 away from the second double-shaft motor 61 when the baffle tarpaulin 611 is wound up.

[0031] A processing technology for a fatigue-resistant aero-engine blade processing device includes the following steps: Step 1: The cylinder body 31 of the electric cylinder will drive the cylinder slider 32 to move towards the side close to the boosting mechanism 5, so as to drive the transfer bracket 33 to move synchronously, and further drive the limiting mechanism 4 to move synchronously and gradually move the transfer bracket 33 to the outside of the device outer frame 1. When the cylinder slider 32 moves to the other end of the cylinder body 31, the cylinder body 31 is paused. Step 2: Simultaneously start two electric push rods 412, so as to drive the two lifting support rods 413 to move downward synchronously, and further enable the connecting gears 414 at the lower end to separate from the corresponding driving gears 411 and the driven gear rings 49, and enable the limiting gears 415 at the lower end to mesh with the corresponding driven gear rings 49. Also, enable the connecting gears 414 at the upper end to mesh with the corresponding driving gears 411 and the driven gear rings 49, and enable the limiting gears 415 at the upper end to separate from the corresponding driven gear rings 49. Then, turn off the electric push rods 412 and start the first double-shaft motor 410, so as to drive the two driving gears 411 to rotate synchronously, and further drive the connecting gears 414 at the upper end to rotate, and further drive the driven gear rings 49 at the upper end to rotate, so as to drive the limiting turntables 47 and the limiting pressing blocks 48 at the upper end to rotate synchronously. When the limiting pressing blocks 48 and the limiting slots 46 are completely misaligned, pause the first double-shaft motor 410 and sequentially insert a plurality of aeroengine blade bodies 2 to be shot-peened into the limiting slots 46. Then, drive the first double-shaft motor 410 to reverse, so as to drive the limiting pressing blocks 48 at the upper end to reverse and reset, and further can conveniently and stably fix the corresponding aeroengine blade bodies 2 to be shot-peened in the corresponding limiting slots 46. Subsequently, start the electric push rod 412 at the upper end, so as to drive the corresponding connecting gears 414 and the limiting gears 415 to move upward, and turn off the corresponding electric push rod 412 when the connecting gears 414 at the upper end separate from the corresponding driving gears 411 and the driven gear rings 49 and the limiting gears 415 mesh with the corresponding driven gear rings 49; Step 3: Reset the transfer bracket 33 and start the shot-peening mechanism. At this time, the shot-peening mechanism can perform shot-peening treatment on the corresponding aeroengine blade bodies 2 to be shot-peened. During this period, the drive motor 42 can drive the rotating bracket 43 to rotate, so as to drive the mounting cylinder column 44 to rotate, and further drive the limiting outer ring 45 to rotate, and further drive the fixed aeroengine blade bodies 2 to rotate and adjust the position, so as to fully perform shot-peening treatment on all the fixed aeroengine blade bodies 2; Step 4: Transfer the shot-peened aeroengine blade bodies 2 to the outside of the device frame 1 through the transfer bracket 33 and start the electric push rod 412 at the lower end, so as to turn off the corresponding electric push rod 412 when the connecting gears 414 at the lower end mesh with the corresponding driving gears 411 and the driven gear rings 49 and the limiting gears 415 separate from the corresponding driven gear rings 49. Subsequently, start the electric telescopic rod 52, so as to drive the boosting cross plate 53 to lift conveniently, and further drive the boosting frame 54 to lift conveniently, and further drive the arc-shaped rubber pad 55 to lift conveniently. During this period, the drive motor 42 will drive the limiting outer ring 45 to rotate and adjust again, so as to sequentially push the shot-peened aeroengine blade bodies 2 out of the corresponding limiting slots 46 through the arc-shaped rubber pad 55, and further realize the convenient blanking of the shot-peened aeroengine blade bodies 2; Step 5. Meanwhile, the second dual-axis motor 61 will drive the driving lead screw 64 and the first bevel gear 66 to rotate in forward and reverse directions alternately, so as to drive the aggregate pushing plate 65 to make a reciprocating motion, and can drive the first rotating rod 62 to rotate in forward and reverse directions alternately through the second bevel gear 67. Furthermore, it can drive the second rotating rod 63 to rotate in forward and reverse directions alternately through the first disc 68, the transmission belt 610 and the second disc 69, and further drive the baffle tarpaulin 611 to perform an alternating motion of unwinding and winding, so as to push and concentrate the pellets generated by shot peening. During the pushing process, the baffle tarpaulin 611 can intercept the residual pellets falling from above to prevent them from accumulating between the aggregate pushing plate 65 and the second dual-axis motor 61, thus ensuring the full and normal development of the subsequent pellet pushing and concentrating operation. In addition, the intercepted pellets will fall on the side of the aggregate pushing plate 65 away from the second dual-axis motor 61 when the baffle tarpaulin 611 is wound up.

[0032] Obviously, those skilled in the art can make various changes and modifications to the present invention without departing from the spirit and scope of the present invention. Thus, if these modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalent technologies, the present invention also intends to include these modifications and variations.

Claims

1. An anti-fatigue machining device for aero-engine blades, comprising an outer frame of the device (1) and aero-engine blade body (2), characterized in that: At the lower end of the inner cavity of the outer frame (1) of the device, a first mesh plate (11) and a second mesh plate (12) which are used in cooperation are fixedly installed, and a shot peening mechanism which is used in cooperation is fixedly installed at the lower end of one side of the inner cavity of the outer frame (1) close to the first mesh plate (11). At the top end of the inner cavity of the outer frame (1), a transfer mechanism (3) and a limiting mechanism (4) which are used in cooperation with the shot peening mechanism and the aeroengine blade body (2) are provided. And on one side of the outer frame (1) of the device, a boosting mechanism (5) which is used in cooperation with the limiting mechanism (4) is provided. At the bottom end of the inner cavity of the outer frame (1), an aggregate mechanism (6) which is used in cooperation with the shot peening mechanism is provided. The cooperation of the transfer mechanism (3) and the limiting mechanism (4) facilitates the disassembly and assembly of the aeroengine blade body (2). The setting and use of the boosting mechanism (5) realize the convenient blanking of the aeroengine blade body (2) after shot peening. The setting and use of the aggregate mechanism (6) can push and concentrate the pellets generated by shot peening.

2. The machining device for an anti-fatigue aero-engine blade according to claim 1, characterized in that, The transfer mechanism (3) includes an electric cylinder body (31). The electric cylinder body (31) is fixedly installed at the top end of the inner cavity of the outer frame (1), and an electric cylinder slider (32) is slidably arranged on the electric cylinder body (31). The bottom end of the electric cylinder slider (32) is fixedly installed with a transfer bracket (33), and the transfer bracket (33) is slidably connected with the outer frame (1) of the device. One end of the transfer bracket (33) away from the electric cylinder slider (32) can be slidably inserted into the outer frame (1) of the device, and the bottom end of the transfer bracket (33) is slidably inserted between the first mesh plate (11) and the second mesh plate (12).

3. An anti-fatigue aero-engine blade processing device according to claim 2, characterized in that, A transverse guide rod (34) is fixedly inserted at the upper end of the outer frame (1) of the device, and the transfer bracket (33) is slidably sleeved on the transverse guide rod (34).

4. An anti-fatigue aeroengine blade processing device according to claim 3, characterized in that, A transverse guide hole (35) is formed through the upper end of the transfer bracket (33), and the transverse guide rod (34) slidably penetrates through the transverse guide hole (35).

5. The machining device for an anti-fatigue aero-engine blade according to claim 2, characterized in that, The limiting mechanism (4) includes a mounting cylinder body (41). The mounting cylinder body (41) is fixedly inserted on the transfer bracket (33), and a driving motor (42) is fixedly installed at the top end of the inner cavity of the mounting cylinder body (41). The output end of the driving motor (42) rotates through the mounting cylinder body (41) and a rotating bracket (43) is fixedly sleeved at the end thereof. And a mounting cylinder column (44) is fixedly sleeved at the top end of the rotating bracket (43). A limiting outer ring (45) is fixedly sleeved on the outer side of the mounting cylinder column (44), and a plurality of limiting slots (46) which are distributed in an array are formed on the outer wall of the limiting outer ring (45). One end of the aeroengine blade body (2) can be slidably inserted into the limiting slots (46). Limiting turntables (47) are rotatably installed at the top end and the bottom end of the limiting outer ring (45), and a plurality of limiting pressing blocks (48) which are distributed in an array are integrally formed on the limiting turntables (47). The limiting pressing blocks (48) are used in cooperation with the limiting slots (46). A driven gear ring (49) is fixedly installed on the inner side of the limiting turntable (47); In the middle of the inner cavity of the installation cylinder column (44), a first dual-shaft motor (410) is fixedly installed. The output ends on both sides of the first dual-shaft motor (410) rotate through the installation cylinder column (44) and are fixedly sleeved with driving gears (411) at their ends. Symmetrically distributed electric push rods (412) are fixedly inserted into the installation cylinder column (44). The end of the output end of the electric push rod (412) is fixedly connected with a lifting support rod (413). A connecting gear (414) is rotatably sleeved on the lifting support rod (413), and the connecting gear (414) can mesh with the driving gear (411) and the driven gear ring (49). A limiting gear (415) is fixedly sleeved at the end of the lifting support rod (413), and the limiting gear (415) can mesh with the driven gear ring (49). The outer wall of the lifting support rod (413) and the inner wall of the middle part of the connecting gear (414) are both damping structures, and the connecting gear (414) and the limiting gear (415) are arranged in a staggered manner in the vertical plane.

6. The machining device for an anti-fatigue aero-engine blade according to claim 1, characterized in that, The boosting mechanism (5) includes a side connection support plate (51). The side connection support plate (51) is fixedly connected to the device outer frame (1). At the top end of one side of the side connection support plate (51), an electric telescopic rod (52) is fixedly installed. The output end of the electric telescopic rod (52) slides through the side connection support plate (51) and is fixedly sleeved with a boosting cross plate (53) at its end. One end of the boosting cross plate (53) is integrally formed with a boosting frame body (54). The bottom end of the boosting frame body (54) is fixedly connected with an arc-shaped rubber pad (55), and the arc-shaped rubber pad (55) can contact the aero-engine blade body (2).

7. An anti-fatigue aeroengine blade processing device according to claim 6, characterized in that, A vertical guide rod (56) is fixedly inserted into the end of the boosting cross plate (53) away from the boosting frame body (54), and the vertical guide rod (56) slides through the side connection support plate (51).

8. The machining device for an anti-fatigue aero-engine blade according to claim 7, wherein, A vertical guide hole (57) is formed through one end of the side connection support plate (51) close to the device outer frame (1), and the vertical guide rod (56) slides through the vertical guide hole (57).

9. The anti-fatigue aero-engine blade processing device according to claim 1, characterized in that, The aggregate mechanism (6) includes a second double-shaft motor (61), a first rotating rod (62) and a second rotating rod (63). The second double-shaft motor (61) is fixedly installed at the bottom end of the inner cavity of the device outer frame (1) close to the shot blasting mechanism. The end of one output end of the second double-shaft motor (61) is fixedly connected with a driving lead screw (64). The driving lead screw (64) is rotatably inserted into the device outer frame (1), and an aggregate pushing plate (65) is sleeved on the outer side of the driving lead screw (64). The aggregate pushing plate (65) is slidably clamped at the bottom end of the inner cavity of the device outer frame (1). The end of the other output end of the second double-shaft motor (61) is fixedly sleeved with a first bevel gear (66). The first rotating rod (62) and the second rotating rod (63) are both rotatably inserted into the bottom end of the inner cavity of the device outer frame (1) close to the second double-shaft motor (61). A second bevel gear (67) is fixedly sleeved on the first rotating rod (62). The second bevel gear (67) meshes with the first bevel gear (66). The two ends of the first rotating rod (62) are both fixedly sleeved with first round disks (68). The two ends of the second rotating rod (63) are both fixedly sleeved with second round disks (69). A transmission belt (610) is sleeved on the outer sides of the adjacent second round disks (69) and the first round disks (68). A baffle tarpaulin (611) is wound around the second rotating rod (63). The leading end of the baffle tarpaulin (611) slidably penetrates through the device outer frame (1) and is fixedly connected with the aggregate pushing plate (65).

10. The processing technology of a processing device for an anti-fatigue aero-engine blade, characterized in that, Using a fatigue-resistant aero-engine blade processing device according to claim 9, comprising the following steps: Step 1, the cylinder body (31) will drive the cylinder slider (32) to move towards the side close to the boosting mechanism (5), so as to drive the transfer bracket (33) to move synchronously, and further drive the limiting mechanism (4) to move synchronously and make the transfer bracket (33) gradually move to the outside of the device outer frame (1). When the cylinder slider (32) moves to the other end of the cylinder body (31), the cylinder body (31) is paused; Step 2: Simultaneously start two electric push rods (412), so as to drive two lifting support rods (413) to move downward synchronously, and further enable the connecting gears (414) at the lower end to be separated from the corresponding driving gears (411) and the driven gear ring (49), and enable the limiting gears (415) at the lower end to mesh with the corresponding driven gear ring (49). At the same time, enable the connecting gears (414) at the upper end to mesh with the corresponding driving gears (411) and the driven gear ring (49), and enable the limiting gears (415) at the upper end to be separated from the corresponding driven gear ring (49). Then, turn off the electric push rods (412) and start the first double-shaft motor (410), so as to drive two driving gears (411) to rotate synchronously, and further drive the connecting gears (414) at the upper end to rotate, and further drive the driven gear ring (49) at the upper end to rotate, so as to drive the upper limiting turntable (47) and the limiting pressure block (48) to rotate synchronously. When the limiting pressure block (48) is completely misaligned with the limiting slot (46), pause the first double-shaft motor (410) and sequentially insert a plurality of aero-engine blade bodies (2) to be shot-peened into the limiting slot (46). Then, drive the first double-shaft motor (410) to reverse, so as to drive the upper limiting pressure block (48) to reverse and reset, and further stably and conveniently fix the corresponding aero-engine blade body (2) to be shot-peened in the corresponding limiting slot (46). Subsequently, start the electric push rod (412) at the upper end, so as to drive the corresponding connecting gear (414) and the limiting gear (415) to move upward, and turn off the corresponding electric push rod (412) when the connecting gear (414) at the upper end is separated from the corresponding driving gear (411) and the driven gear ring (49), and the limiting gear (415) meshes with the corresponding driven gear ring (49); Step 3: Reset the transfer bracket (33) and start the shot-peening mechanism. At this time, the shot-peening mechanism can perform shot-peening treatment on the corresponding aero-engine blade body (2) to be shot-peened. During this period, the drive motor (42) can drive the rotating bracket (43) to rotate, so as to drive the mounting cylinder column (44) to rotate, and further drive the limiting outer ring (45) to rotate, and further drive the fixed aero-engine blade body (2) to rotate and adjust the position, so as to fully perform shot-peening treatment on all the fixed aero-engine blade bodies (2); Step 4: Transfer the shot-peened aeroengine blade body (2) to the outside of the device frame (1) through the transfer bracket (33) and start the electric push rod (412) at the lower end, so that the connecting gear (414) at the lower end can mesh with the corresponding driving gear (411) and the driven gear ring (49), and close the corresponding electric push rod (412) when the limiting gear (415) is separated from the corresponding driven gear ring (49). Then start the electric telescopic rod (52), which can drive the boosting cross plate (53) to lift conveniently, and then drive the boosting frame (54) to lift conveniently, and further drive the arc-shaped rubber pad (55) to lift conveniently. During this period, the driving motor (42) will drive the limiting outer ring (45) to rotate and adjust again, so that the shot-peened aeroengine blade body (2) can be pushed out of the corresponding limiting slot (46) through the arc-shaped rubber pad (55) in turn, thus realizing the convenient blanking of the shot-peened aeroengine blade body (2). Step 5: At the same time, the second double-shaft motor (61) will drive the driving screw rod (64) and the first bevel gear (66) to rotate in positive and negative directions alternately, so that the aggregate pushing plate (65) can make a reciprocating motion, and drive the first rotating rod (62) to rotate in positive and negative directions alternately through the second bevel gear (67). Furthermore, the second rotating rod (63) can be driven to rotate in positive and negative directions alternately through the first disc (68), the transmission belt (610) and the second disc (69), and further drive the baffle tarpaulin (611) to make an alternating motion of unwinding and winding, so that the pellets generated by shot peening can be pushed and concentrated. During the pushing process, the baffle tarpaulin (611) can intercept the residual pellets falling from above to prevent them from accumulating between the aggregate pushing plate (65) and the second double-shaft motor (61), thus ensuring the full and normal development of the subsequent pellet pushing and concentrating operation. In addition, the intercepted pellets will fall on the side of the aggregate pushing plate (65) away from the second double-shaft motor (61) when the baffle tarpaulin (611) is wound up.

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