An auxiliary tool for forming a high temperature alloy layer on a blade of an aeroengine
Patent Information
- Application Number
- CN202522252353.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-10-24
- Publication Date
- 2026-09-22
- Estimated Expiration
- 2035-10-24
AI Technical Summary
I、在步骤S3中，工人需要先在螺纹杆7上套压板8，而后在螺纹杆7上螺纹连接锁紧螺母9，从而才能实现对叶片固定，当固定后，工人才能利用激光覆熔设备在叶片的叶身2上成型出高温合金层；而固定叶片的操作总共需要两个工序，这无疑是增加了固定叶片所用时间，从而降低了叶片的固定效率
[0017]本实用新型具有以下优点：极大提高叶片固定效率、提高在叶片叶身上成型出高温合金层效率。
Smart Images
Figure CN224780346U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the technical field of fixing blades before laser cladding, and in particular to an auxiliary tooling for forming a high-temperature alloy layer on aero-engine blades. Background Technology
[0002] The aircraft engine of a civil aircraft is equipped with a turbine, and multiple blades are installed on the turbine along its circumference. The core function of the blades is to convert the energy of the high-temperature and high-pressure gas into the rotational mechanical energy of the turbine, thereby providing rotational power for the aircraft engine.
[0003] There are many types of aircraft engines, and the corresponding types of blades also vary. For example, the structure of a certain type of blade... Figures 1-3 As shown, it includes a tenon 1 and a blade 2 that is connected to the tenon 1. The tenon 1 is rectangular and has grooves 3 on both the front and rear ends. The grooves 3 are used to cooperate with the turbine components to install the tenon 1 on the turbine, and then install the entire blade on the turbine.
[0004] After the blade is initially shaped by the machine tool, the process requires the use of an auxiliary fixture in conjunction with two laser cladding machines to form a high-temperature alloy layer on both the top and bottom surfaces of the blade body 2. The purpose of the formed high-temperature alloy layer is: 1. to make the blade body 2 more resistant to high temperatures. 2. to give the blade body 2 higher mechanical properties.
[0005] The structure of the auxiliary fixture is as follows: Figure 4 As shown, the auxiliary clamp is used to position and fix the two blades. The auxiliary clamp includes a pad 4. A positioning seat 5 is fixed on the top surface of the pad 4 and at its left and right ends. A positioning stop 6 that matches the outer contour of the tenon 1 of the blade is opened on the inner end face of the two positioning seats 5. A threaded rod 7 is fixed on the top surface of the two positioning seats 5.
[0006] The method by which workers use this auxiliary fixture in conjunction with two laser cladding machines to form a high-temperature alloy layer on both the top and bottom surfaces of the blade body 2 is as follows: S1, the worker took out two such... Figures 1-3 The blade shown; S2. Insert the tenon 1 of one blade from top to bottom into the positioning stop 6 of the positioning seat 5 on the left side, thereby achieving the positioning of the left blade. Figure 5 As shown, at this time, the blade body 2 of the left blade is directly below the laser head of the first laser cladding equipment; The worker inserts the tenon 1 of the other blade from top to bottom into the positioning stop 6 of the positioning seat 5 on the right side, thus achieving the positioning of the right blade. Figure 6As shown, at this time, the blade body 2 of the right-hand blade is directly below the laser head of the second laser cladding equipment; S3. The worker takes out two pressure plates 8 and places them onto the two threaded rods 7 respectively. Figure 7 As shown, at this time, the two pressure plates 8 are in contact with the top surfaces of the two tenons 1 respectively; then, the worker threads a locking nut 9 onto each of the two threaded rods 7, and presses the locking nut 9 onto the top surface of the pressure plate 8. Under the threaded connection force between the locking nut 9 and the threaded rod 7, the tenon 1 is fixed between the pressure plate 8 and the positioning seat 5, thereby achieving the fixation of the two blades, as shown. Figure 8 As shown; S4. The worker starts the first laser cladding equipment. The laser head of the first laser cladding equipment forms a high-temperature alloy layer on the top surface of the blade body 2 of the left blade. At the same time, the second laser cladding equipment is started. The laser head of the second laser cladding equipment forms a high-temperature alloy layer on the top surface of the blade body 2 of the right blade, thus achieving the formation of a high-temperature alloy layer on the top surface of the blade body 2 of both blades. S5. The worker unscrews the locking nut 9 from the threaded rod 7, then removes the pressure plate 8 from the threaded rod 7, and then removes the blade from the positioning stop 6 of the positioning seat 5. After removal, the worker rotates the blade 180°. Finally, the worker repeats steps S2 to S4 once to form a high-temperature alloy layer on the bottom surface of both blade bodies 2, thus ultimately achieving the formation of a high-temperature alloy layer on both the top and bottom surfaces of the two blades. S6. Workers can repeat steps S1 to S5 multiple times to form a high-temperature alloy layer on the top and bottom surfaces of multiple blades.
[0007] However, although this auxiliary fixture, in conjunction with two laser cladding machines, can form a high-temperature alloy layer on both the top and bottom surfaces of the blade body 2, it still has the following technical defects: I. In step S3, the worker needs to first put the pressure plate 8 on the threaded rod 7, and then thread the locking nut 9 on the threaded rod 7 to fix the blade. After fixing, the worker can use the laser cladding equipment to form a high-temperature alloy layer on the blade body 2. The operation of fixing the blade requires two steps, which undoubtedly increases the time used to fix the blade and reduces the blade fixing efficiency.
[0008] II. In step S5, the worker needs to manually unscrew the locking nut 9 from the threaded rod 7, and then remove the pressure plate 8 from the threaded rod 7. After removing it, the worker needs to rotate the blade 180° so that a high-temperature alloy layer can be formed on the bottom surface of the blade body. A total of three steps are required to form a high-temperature alloy layer on the bottom surface of the blade body, which undoubtedly prolongs the time for forming a high-temperature alloy layer on the bottom surface of the blade body 2, thereby further reducing the efficiency of forming a high-temperature alloy layer on the blade body 2.
[0009] Therefore, there is an urgent need for an auxiliary tooling that can greatly improve the blade fixing efficiency and the efficiency of forming a high-temperature alloy layer on the blade body. Utility Model Content
[0010] The purpose of this invention is to overcome the shortcomings of the prior art and provide an auxiliary tooling that greatly improves the blade fixing efficiency and the efficiency of forming a high-temperature alloy layer on the blade body.
[0011] The purpose of this utility model is achieved through the following technical solution: an auxiliary tooling for forming a high-temperature alloy layer on the blade of an aero-engine, which includes a base plate, and a left tooling assembly and a right tooling assembly are respectively arranged on the base plate and on its left and right sides. The left tooling assembly includes a vertical plate fixed on the base plate, and a rotating shaft is rotatably installed on the upper end of the vertical plate. A rotating seat is fixed on the inner end of the rotating shaft. The top surface of the rotating seat has a rectangular groove extending to the right through its right end face. The rectangular groove matches the outer contour of the blade tenon. The depth of the rectangular groove is equal to the thickness of the tenon. Limiting bosses are fixed inside the rectangular groove and on its front and rear walls. The two limiting bosses match the two slots of the tenon respectively. A guide seat is fixed on the top surface of the rotating seat, located on the left side of the rectangular groove. A stop block is slidably installed inside the guide seat and contacts the top surface of the rotating seat. The right end of the stop block extends directly above the rectangular groove. A lever is fixed on the left extension end of the stop block. A horizontal spring is fixed between the lever and the guide seat. A drive assembly for driving the two rotating seats to rotate simultaneously is provided between the left tooling assembly, the right tooling assembly and the base plate.
[0012] Multiple foot pads are fixed on the bottom surface of the base plate.
[0013] The left and right tooling components are arranged symmetrically.
[0014] The bottom end of the guide seat is provided with a guide groove, and the stop block is slidably engaged with the guide groove.
[0015] The drive assembly includes a drive motor fixed to the base plate, a drive shaft rotatably mounted between the vertical plate of the left tooling assembly and the vertical plate of the right tooling assembly, and belt drive mechanisms are installed between the rotating shaft of the left tooling assembly and the drive shaft, and between the rotating shaft of the right tooling assembly and the drive shaft. The belt drive mechanism located on the left side includes a driven pulley fixed on the outer end of the rotating shaft and a driving pulley fixed on the drive shaft, with a belt installed between the driving pulley and the driven pulley.
[0016] The auxiliary tooling also includes a controller, which is electrically connected to the drive motor via signal lines.
[0017] This invention has the following advantages: it greatly improves the blade fixing efficiency and the efficiency of forming a high-temperature alloy layer on the blade body. Attached Figure Description
[0018] Figure 1 This is a schematic diagram of the structure of a certain type of blade; Figure 2 for Figure 1 Top view; Figure 3 for Figure 2 CC section view; Figure 4 This is a schematic diagram of the structure of an auxiliary fixture in the prior art; Figure 5 A schematic diagram illustrating the positioning of the left-side blade; Figure 6 A schematic diagram illustrating the positioning of the right-side blade; Figure 7 This is a schematic diagram showing the two pressure plates being fitted onto the two threaded rods respectively; Figure 8 A schematic diagram illustrating how to fix two blades; Figure 9 This is a schematic diagram of the structure of this utility model; Figure 10 for Figure 9 Top view; Figure 11 for Figure 10 DD sectional view; Figure 12 A schematic diagram showing the connection between the rotating seat and the two limiting bosses; Figure 13 for Figure 12 Top view; Figure 14 Axonometric drawing of the guide seat; Figure 15 for Figure 14 Main section diagram; Figure 16A schematic diagram showing how to manually pull the lever of the left tooling assembly to the left; Figure 17 This is a schematic diagram showing how the first blade is positioned using the left tooling assembly; Figure 18 for Figure 17 A schematic diagram of direction E; Figure 19 This is a schematic diagram showing how the first blade is fixed using the left tooling assembly; Figure 20 This is a schematic diagram showing how the second blade is fixed using the right tooling assembly. Figure 21 This is a schematic diagram showing both blades rotating exactly 180°. Figure 22 This is a schematic diagram of removing a blade with a high-temperature alloy layer. In the picture: 1-Tenon, 2-Blade body, 3-Slot, 4-Pad, 5-Positioning seat, 6-Positioning stop, 7-Threaded rod, 8-Pressure plate, 9-Locking nut; 10-Base plate, 11-Left tooling assembly, 12-Right tooling assembly, 13-Upright plate, 14-Rotating shaft, 15-Rotating seat, 16-Rectangular recess, 17-Limiting boss, 18-Guide seat, 19-Stop block, 20-Pulley, 21-Horizontal spring, 22-Guide groove, 23-Drive motor, 24-Drive shaft, 25-Driven pulley, 26-Driven pulley, 27-Belt. Detailed Implementation
[0019] The present invention will be further described below with reference to the accompanying drawings. The scope of protection of the present invention is not limited to the following description: like Figures 9-15 As shown, an auxiliary tooling for forming a high-temperature alloy layer on an aero-engine blade includes a base plate 10. A left tooling assembly 11 and a right tooling assembly 12 are respectively disposed on the left and right sides of the base plate 10, symmetrically arranged. The left tooling assembly 11 includes a vertical plate 13 fixed to the base plate 10. A rotating shaft 14 is rotatably mounted on the upper end of the vertical plate 13, and a rotating seat 15 is fixed to the inner end of the rotating shaft 14. Multiple foot pads are fixed to the bottom surface of the base plate 10.
[0020] A rectangular recess 16 extending to the right through the right end face is formed on the top surface of the rotating seat 15. The rectangular recess 16 matches the outer contour of the blade tenon 1. The depth of the rectangular recess 16 is equal to the thickness of the tenon 1. Limiting bosses 17 are fixedly provided inside the rectangular recess 16 and on its front and rear walls. The two limiting bosses 17 respectively match the two slots 3 of the tenon 1. A guide seat 18 located to the left of the rectangular recess 16 is fixedly provided on the top surface of the rotating seat 15. A stop block 19 that contacts the top surface of the rotating seat 15 is slidably installed in the guide seat 18. The right end of the stop block 19 extends directly above the rectangular recess 16. A lever plate 20 is fixedly provided on the left extension end of the stop block 19. A horizontal spring 21 is fixed between the lever plate 20 and the guide seat 18. A guide groove 22 is formed at the bottom end of the guide seat 18. The stop block 19 slides in cooperation with the guide groove 22.
[0021] A drive assembly for driving the two rotating seats 15 to rotate simultaneously is provided between the left tooling assembly 11, the right tooling assembly 12 and the base plate 10. The drive assembly includes a drive motor 23 fixed on the base plate 10 and a drive shaft 24 rotatably mounted between the upright plate 13 of the left tooling assembly 11 and the upright plate 13 of the right tooling assembly 12. Belt drive mechanisms are installed between the rotating shaft 14 of the left tooling assembly 11 and the drive shaft 24, and between the rotating shaft 14 of the right tooling assembly 12 and the drive shaft 24. The belt drive mechanism located on the left side includes a driven pulley 25 fixed on the outer end of the rotating shaft 14 and a driving pulley 26 fixed on the drive shaft 24. A belt 27 is installed between the driving pulley 26 and the driven pulley 25.
[0022] The auxiliary tooling also includes a controller, which is electrically connected to the drive motor 23 via a signal line. The worker can control the start or stop of the drive motor 23 through the controller, thus facilitating the worker's operation.
[0023] The method by which workers use this auxiliary tooling in conjunction with two laser cladding machines to form a high-temperature alloy layer on both the top and bottom surfaces of the blade body 2 is as follows: S1, the worker took out two such... Figures 1-3 The blade shown; S2. The specific steps for positioning and fixing the first blade are as follows: S21. The worker pulls the lever 20 of the left tooling assembly 11 to the left by hand. The direction of movement of the lever 20 is as follows: Figure 16 As shown by the middle arrow, the lever 20 drives the stop block 19 to move to the left, the lever 20 stretches the horizontal spring 21 to the left, and the stop block 19 moves toward the rectangular sink 16 away from the rotating seat 15. When the worker observes that the stop block 19 no longer blocks the rectangular sink 16, the worker stops pulling the lever 20 and keeps the lever 20 stationary. S22. The worker inserts the tenon 1 of the blade from top to bottom into the rectangular countersunk 16 of the rotating seat 15 of the left tooling assembly 11. After insertion, the two slots 3 of the blade tenon 1 respectively fit onto the two limiting bosses 17 in the rectangular countersunk 16, so as to position the first blade through the left tooling assembly 11. Figures 17-18 As shown, at this time, the top surface of the blade tenon 1 is flush with the top surface of the rotating seat 15, and at the same time, the blade body 2 is directly below the laser head of the first laser cladding equipment. S23. The worker releases the lever 20. Under the elastic restoring force of the horizontal spring 21, the lever 20 moves to the right. The lever 20 drives the stop block 19 to move to the right synchronously. When the horizontal spring 21 returns to its initial state, the bottom surface of the stop block 19 contacts the top surface of the tenon 1, so as to fix the first blade through the left tooling assembly 11. Figure 19 As shown, the tenon 1 of the blade is fixed between the stop 19 and the two limiting bosses 17. As can be seen from step S2, the worker only needs to pull the lever 20 to the left first, and then insert the tenon 1 of the blade from top to bottom into the rectangular groove 16 of the rotating seat 15, so that the tenon 1 of the blade is restricted in the horizontal direction by the two limiting bosses 17. Finally, the lever 20 is released, so that the tenon 1 of the blade is restricted in the vertical direction by the stop block 19, thereby quickly fixing the blade.
[0024] Therefore, it can be seen that this auxiliary tooling is comparable to that in the workshop. Figures 4-8 The fixing method shown eliminates the need for workers to first put a pressure plate 8 on the threaded rod 7, or to thread a locking nut 9 onto the threaded rod 7 to fix the blade. Instead, it simplifies the blade fixing process, thereby enabling the blade to be fixed in a short time and greatly improving the blade fixing efficiency.
[0025] S3. The worker repeats steps S21-S22 once to position the first blade using the right tooling assembly 12. At this point, the blade body 2 is directly below the laser head of the second laser cladding equipment. Then, the worker repeats step S23 once to fix the second blade using the right tooling assembly 12. Figure 20 As shown; S4. The worker starts the first laser cladding equipment. The laser head of the first laser cladding equipment forms a high-temperature alloy layer on the top surface of the blade body 2 of the left blade. At the same time, the second laser cladding equipment is started. The laser head of the second laser cladding equipment forms a high-temperature alloy layer on the top surface of the blade body 2 of the right blade, thus achieving the formation of a high-temperature alloy layer on the top surface of the blade body 2 of both blades. S5. The drive motor 23 of the worker control drive component starts, the drive motor 23 drives the drive shaft 24 to rotate, the drive shaft 24 drives the active pulleys 26 of the two belt drive mechanisms to rotate synchronously, the active pulleys 26 drive the driven pulleys 25 to rotate via the belt 27, the driven pulleys 25 drive the rotating shaft 14 to rotate, the rotating shaft 14 drives the rotating seat 15 connected to it to rotate synchronously, and then drives the fixed blades to rotate synchronously. When the drive motor 23 has been running for the set time, the controller shuts off the drive motor 23. At this time, both blades have rotated exactly 180°. Figure 21 As shown, the bottom surfaces of the blades 2 are directly below the laser heads of the two laser cladding machines; S6. The worker repeats step S4 once to form a high-temperature alloy layer on the bottom surface of both blades 2, thus finally achieving the formation of a high-temperature alloy layer on both the top and bottom surfaces of both blades. S7. The specific steps for removing the two blades with the high-temperature alloy layer are as follows: S71. The worker controls the drive motor 23 to reverse through the controller, so that both rotating seats 15 rotate in the opposite direction. When the drive motor 23 has worked for a set time, the controller controls the drive motor 23 to turn off. At this time, both rotating seats 15 and two blades are reset. S72. The worker pulls the lever 20 outward to move the stop 19 away from the blade tenon 1. Then the worker removes the blade with the high-temperature alloy layer, in the following direction: Figure 22 As indicated by the middle arrow; S8. Workers can repeat steps S1 to S7 multiple times to form a high-temperature alloy layer on the top and bottom surfaces of multiple blades.
[0026] Furthermore, as can be seen from steps S5 to S6, the worker only needs to control the drive motor 23 of the drive assembly to start, which will cause the blades 2 of the two blades to rotate 180° simultaneously, so that the bottom surfaces of the blades 2 of the two blades are facing upwards. Then, a high-temperature alloy layer can be formed on the bottom surface of the blades by the laser head of the laser cladding equipment.
[0027] Therefore, it can be seen that this auxiliary tooling is comparable to that in the workshop. Figures 4-8 The operation method shown eliminates the need to unscrew the locking nut 9 from the threaded rod 7, remove the pressure plate 8 from the threaded rod 7, and require the worker to manually rotate the blade 180°. This reduces the number of steps, shortens the time required to form a high-temperature alloy layer on the bottom surface of the blade body 2, and thus improves the efficiency of forming a high-temperature alloy layer on the blade body 2.
Claims
1. An auxiliary tooling for forming a high-temperature alloy layer on the blades of an aero-engine, characterized in that: It includes a base plate (10), on which a left tooling assembly (11) and a right tooling assembly (12) are respectively provided on the left and right sides. The left tooling assembly (11) includes a vertical plate (13) fixed on the base plate (10). A rotating shaft (14) is rotatably mounted on the upper end of the vertical plate (13), and a rotating seat (15) is fixed on the inner end of the rotating shaft (14). The top surface of the rotating seat (15) is provided with a rectangular recess (16) extending to the right through its right end face. The rectangular recess (16) matches the outer contour of the blade tenon (1). The depth of the rectangular recess (16) is equal to the thickness of the tenon (1). Limiting bosses (17) are fixedly provided inside the rectangular recess (16) and on its front and rear walls. The two limiting bosses (17) match the two slots (3) of the tenon (1) respectively. A guide seat (18) located on the left side of the rectangular recess (16) is fixedly provided on the top surface of the rotating seat (15). A stop block (19) that contacts the top surface of the rotating seat (15) is slidably installed inside the guide seat (18). The right end of the stop block (19) extends directly above the rectangular recess (16). A lever plate (20) is fixedly provided on the left extension end of the stop block (19). A horizontal spring (21) is fixed between the lever plate (20) and the guide seat (18). A drive assembly for driving the two rotating seats (15) to rotate simultaneously is provided between the left tooling assembly (11), the right tooling assembly (12) and the base plate (10).
2. The auxiliary tooling for forming a high-temperature alloy layer on an aero-engine blade according to claim 1, characterized in that: Multiple foot pads are fixed on the bottom surface of the base plate (10).
3. The auxiliary tooling for forming a high-temperature alloy layer on an aero-engine blade according to claim 1, characterized in that: The left tooling assembly (11) and the right tooling assembly (12) are arranged symmetrically on the left and right sides.
4. The auxiliary tooling for forming a high-temperature alloy layer on an aero-engine blade according to claim 1, characterized in that: The bottom end of the guide seat (18) is provided with a guide groove (22), and the stop block (19) slides in cooperation with the guide groove (22).
5. The auxiliary tooling for forming a high-temperature alloy layer on an aero-engine blade according to claim 1, characterized in that: The drive assembly includes a drive motor (23) fixed on the base plate (10), a drive shaft (24) rotatably mounted between the vertical plate (13) of the left tooling assembly (11) and the vertical plate (13) of the right tooling assembly (12), and belt drive mechanisms are installed between the rotating shaft (14) of the left tooling assembly (11) and the drive shaft (24), and between the rotating shaft (14) of the right tooling assembly (12) and the drive shaft (24). The belt drive mechanism located on the left side includes a driven pulley (25) fixed on the outer end of the rotating shaft (14) and a driving pulley (26) fixed on the drive shaft (24). A belt (27) is installed between the driving pulley (26) and the driven pulley (25).
6. The auxiliary tooling for forming a high-temperature alloy layer on an aero-engine blade according to claim 1, characterized in that: The auxiliary tooling also includes a controller, which is electrically connected to the drive motor (23) via a signal line.