Aero-engine anti-disassembly tooling

Abstract

The application discloses an aero-engine anti-disassembly tool, which comprises a base, a rotating frame, a driving mechanism and a clamping mechanism. The rotating frame is rotatably arranged on the base. The driving mechanism is used for driving the rotating frame to rotate relative to the base to adjust the angle. The clamping mechanism comprises a fixed plate, a clamping plate, a rotary screw, a limiting block and a pressing nut. The clamping plate is used for turning to the state of covering the fixed plate or separating from the fixed plate. A first limiting groove is formed on the side of the clamping plate away from the fixed plate. The first end of the rotary screw is hinged to the fixed plate. The second end of the rotary screw is used for rotating to the first limiting groove when the clamping plate covers the fixed plate. The limiting block is axially movably sleeved on the rotary screw and is used for being embedded in the first limiting groove. The pressing nut is threadedly connected with the rotary screw and is used for pressing the limiting block in the first limiting groove. The aero-engine anti-disassembly tool provided by the application has the advantages of simple and efficient structure, good anti-loosening effect and the ability of realizing quick clamping operation.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aero-engine assembly, in particular to an aero-engine anti-disassembly assembly tool. BACKGROUND

[0002] Due to the large size, complex structure and numerous parts of the aero-engine, the aero-engine needs to be rotated to multiple angles for assembly during the assembly process of each part. Therefore, a rotating assembly tool is usually configured to clamp and rotate the aero-engine to adjust the angle. However, in order to improve the disassembly efficiency, a quick release structure is generally used to clamp the aero-engine. The quick release structure may be loose during the multiple turning process of the aero-engine, which may even cause the aero-engine to fall and pose a safety hazard. Although using multiple sets of clamping structures in different directions can better fix the aero-engine, it may also make the clamping process too complicated, requiring the aero-engine to be fixed from different angles and positions. The overly complex clamping structure may also interfere with the assembly of the aero-engine, which is not suitable. SUMMARY

[0003] The present application provides an aero-engine anti-disassembly assembly tool to solve the technical problem that the existing aero-engine assembly tool is prone to looseness during the turning of the aero-engine.

[0004] An aero-engine anti-disassembly assembly tool, comprising a base, a rotating frame, a driving mechanism and a clamping mechanism;

[0005] The rotating frame is rotatably arranged on the base;

[0006] The driving mechanism is connected with the rotating frame and is used to drive the rotating frame to rotate relative to the base to adjust the angle;

[0007] The clamping mechanism comprises a fixed plate, a clamping plate, a rotary screw, a limiting block and a compression nut. The fixed plate is installed on the rotating frame. The first end of the clamping plate is hinged to the fixed plate. The second end of the clamping plate is used to turn to cover or separate from the fixed plate. The clamping plate is used to clamp a preset positioning shaft on the aero-engine on the fixed plate. One side of the clamping plate away from the fixed plate is provided with a first limiting groove. The first end of the rotary screw is hinged to the fixed plate. The second end of the rotary screw is used to rotate into the first limiting groove when the clamping plate covers the fixed plate. The limiting block is axially movably sleeved on the rotary screw and is used to be embedded in the first limiting groove. The compression nut is threadedly connected with the rotary screw and is used to compress the limiting block in the first limiting groove, thereby compressing and fixing the clamping plate relative to the fixed plate.

[0008] Preferably, a limiting pin is arranged on the side wall of the limiting block, and a second limiting groove matched with the limiting pin is further arranged on the side of the clamping plate away from the fixed plate, and the limiting pin is used to be embedded in the second limiting groove to limit the limiting block in the circumferential direction relative to the rotary screw.

[0009] Preferably, the second limiting groove is arranged along the width direction of the clamping plate and extends to the side surface of the clamping plate, and the length of the second limiting pin is greater than the length of the second limiting groove, so that the second limiting pin protrudes from the side surface of the clamping plate when embedded in the second limiting groove.

[0010] Preferably, the limiting pins are arranged on the opposite sides of the limiting block.

[0011] Preferably, the limiting block is arranged in a multi-prism structure, and the shape of the first limiting groove is matched with the limiting block, and the first limiting groove is further used to limit the limiting block in the circumferential direction.

[0012] Preferably, the side of the compression nut facing the limiting block is arranged as a compression surface, and the diameter of the compression surface is greater than the width of the limiting block.

[0013] Preferably, the rotating frame comprises two rotating shafts coaxially and spacedly arranged on the base, a curved arm arranged on the rotating shafts and extending along the radial direction of the rotating shafts, a support frame arranged at the end of the curved arm away from the rotating shafts and connecting the curved arms on the two rotating shafts into a whole, and a plurality of support columns arranged on the support frame and in the direction towards the rotating shafts, the clamping mechanism is arranged at the end of the support column away from the support frame, and a plurality of clamping mechanisms are arranged, and the plurality of clamping mechanisms and the plurality of support columns are arranged one-to-one, and the plurality of clamping mechanisms are respectively used to clamp different positioning shafts on the aero-engine and make the center of gravity of the aero-engine on the axis of the rotating shafts.

[0014] Preferably, the aero-engine anti-disassembly tool further comprises a positioning mechanism, the positioning mechanism comprises a positioning base, a positioning turntable, a positioning pin, a pin sleeve and a spring, the positioning base is fixedly installed on the base, the positioning turntable is arranged on the rotating frame and is provided with a plurality of positioning holes arranged at intervals in the circumferential direction, the positioning pin is installed on the positioning base through the pin sleeve, a guide groove extending in the direction towards the positioning turntable is formed on the end face of the pin sleeve away from the positioning turntable, the positioning pin is provided with a guide pin matched with the guide groove, and the spring is pressed in the pin sleeve and abuts against the positioning pin.

[0015] Preferably, a central hole is formed in the positioning base, one side of the positioning turntable is connected with the rotating frame, and the other side of the positioning turntable is provided with a central shaft penetrating through the central hole and used for rotating relative to the central hole.

[0016] Preferably, a plurality of universal wheels are arranged on the bottom of the base.

[0017] The aero-engine anti-disassembly tool has the following beneficial effects:

[0018] In the clamping mechanism of the aero-engine anti-disassembly tool, the clamping plate can be quickly pressed and fixed relative to the fixed plate or loosened through cooperation of the rotating screw and the pressing nut, so that the positioning shafts pre-set on the aero-engine are quickly clamped or loosened, the aero-engine is quickly clamped and positioned, and the aero-engine is conveniently and quickly disassembled and assembled. The clamping mechanism is arranged away from the aero-engine and does not interfere with the assembly operation of the aero-engine, so that the clamping mechanism is conveniently and flexibly rotated to different angles to complete the assembly operation of the aero-engine. More importantly, the limiting block is sleeved on the rotating screw, the radial fixation of the rotating screw is realized by embedding the limiting block in the first limiting groove of the clamping plate, the rotating action of the rotating screw is limited, when the rotating frame is rotated to the downward state in the loosening direction of the rotating screw, the loosening of the rotating screw is avoided through cooperation of the limiting block and the first limiting groove, the pressing nut is not easily loosened when being rotated to different angles, the state of pressing the clamping plate is maintained, the clamping and limiting structure is simple and efficient, the anti-disassembly effect is good, and no additional clamping process is needed, which is beneficial to realize the quick clamping operation.

[0019] In addition to the purposes, features and advantages described above, the present application has other purposes, features and advantages. The present application will be further described below with reference to the drawings. BRIEF DESCRIPTION OF DRAWINGS

[0020] The accompanying drawings, which form a part of this application, are intended to provide further understanding of the application and are incorporated herein in their entirety, and together with the general description of the application and

[0021] Figure 1 The structural schematic diagram of the engine anti-disassembly tooling provided by the present application, wherein the dashed box represents an aero-engine;

[0022] Figure 2 The structural schematic diagram of the engine anti-disassembly tooling provided by the present application, wherein the dashed box represents an aero-engine; Figure 1 The structural schematic diagram of the engine anti-disassembly tooling provided by the present application, wherein the dashed box represents an aero-engine;

[0023] Figure 3 The structural schematic diagram of the engine anti-disassembly tooling provided by the present application, wherein the dashed box represents an aero-engine; Figure 1 The structural schematic diagram of the engine anti-disassembly tooling provided by the present application, wherein the dashed box represents an aero-engine;

[0024] Figure 4 The structural schematic diagram of the engine anti-disassembly tooling provided by the present application, wherein the dashed box represents an aero-engine; Figure 3 The structural schematic diagram of the engine anti-disassembly tooling provided by the present application, wherein the dashed box represents an aero-engine

[0025] Figure 5 The structural schematic diagram of the engine anti-disassembly tooling provided by the present application, wherein the dashed box represents an aero-engine; Figure 3 The structural schematic diagram of the engine anti-disassembly tooling provided by the present application, wherein the dashed box represents an aero-engine;

[0026] Figure 6 The structural schematic diagram of the engine anti-disassembly tooling provided by the present application, wherein the dashed box represents an aero-engine; Figure 1 The structural schematic diagram of the engine anti-disassembly tooling provided by the present application, wherein the dashed box represents an aero-engine;

[0027] Figure 7 The structural schematic diagram of the engine anti-disassembly tooling provided by the present application, wherein the dashed box represents an aero-engine; Figure 6 The structural schematic diagram of the engine anti-disassembly tooling provided by the present application, wherein the dashed box represents an aero-engine;

[0028] Figure 8 The structural schematic diagram of the engine anti-disassembly tooling provided by the present application, wherein the dashed box represents an aero-engine; Figure 6 The structural schematic diagram of the engine anti-disassembly tooling provided by the present application, wherein the dashed box represents an aero-engine;

[0029] Figure 9 The structural schematic diagram of the engine anti-disassembly tooling provided by the present application, wherein the dashed box represents an aero-engine; Figure 8 The structural schematic diagram of the engine anti-disassembly tooling provided by the present application, wherein the dashed box represents an aero-engine;

[0030] Figure 10 The structural schematic diagram of the engine anti-disassembly tooling provided by the present application, wherein the dashed box represents an aero-engine; Figure 6 The structural schematic diagram of the engine anti-disassembly tooling provided by the present application, wherein the dashed box represents an aero-engine;

[0031] LEGEND:

[0032] 1000, an aero-engine anti-disassembly tool; 1, a base; 11, a universal wheel; 2, a rotating frame; 21, a rotating shaft; 22, a curved arm; 23, a support frame; 24, a support column; 3, a driving mechanism; 31, a motor; 32, a speed reducer; 4, a clamping mechanism; 41, a fixed plate; 42, a clamping plate; 421, a first limiting groove; 422, a second limiting groove; 423, an avoiding groove; 43, a rotary screw; 44, a limiting block; 441, a limiting pin; 442, a through hole; 45, a compression nut; 5, a positioning mechanism; 51, a positioning seat; 511, a mounting hole; 512, a center hole; 52, a positioning turntable; 521, a positioning hole; 522, a center shaft; 53, a positioning pin; 54, a pin sleeve; 541, a pin hole; 542, a guide groove; 55, a spring; 56, a guide pin; 2000, an aero-engine; 2001, a positioning shaft. DETAILED DESCRIPTION

[0033] The embodiments of the present application are described in detail below with reference to the accompanying drawings, but the present application can be implemented in various different ways as defined and covered by the following.

[0034] Figures 1 to 10 The aero-engine anti-disassembly tool provided by the embodiments of the present application is shown together, which is used for clamping an aero-engine and driving the aero-engine to rotate to adjust an angle, thereby assisting to complete the assembly work of parts of the aero-engine at different angles and different positions, the clamping limiting structure is simple and efficient, and the aero-engine is effectively prevented from loosening.

[0035] Please combine Figure 1 and Figure 2 , the aero-engine anti-disassembly tool 1000 comprises a base 1, a rotating frame 2, a driving mechanism 3 and a clamping mechanism 4, the rotating frame 2 is rotatably arranged on the base 1, the driving mechanism 3 is connected with the rotating frame 2 and is used for driving the rotating frame 2 to rotate relative to the base 1 to adjust an angle, and the clamping mechanism 4 is arranged on the rotating frame 2 and is used for clamping and fixing an aero-engine 2000, so that the rotating frame 2 can drive the aero-engine 2000 to rotate to adjust an assembly angle.

[0036] Please combine Figure 3 and Figure 4 , the clamping mechanism 4 comprises a fixed plate 41, a clamping plate 42, a rotary screw 43, a limiting block 44 and a compression nut 45, the fixed plate 41 is fixedly installed on the rotating frame 2, a first end (for example, the left end in the direction shown by the arrow of Figure 3 the clamping plate 42 is hinged to the fixed plate 41, and a second end (for example, the right end in the direction shown by the arrow of Figure 3The second end of the clamping plate 42 is the right end) for turning to the state of covering or separating from the fixed plate 41, the clamping plate 42 is used for clamping the preset positioning shaft 2001 on the aero-engine 2000 to the fixed plate 41, and a first limiting groove 421 is formed on the side of the clamping plate 42 away from the fixed plate 41. Figure 4 The first end of the rotary screw 43 is the bottom end) and is hinged to the fixed plate 41, and the second end of the rotary screw 43 is the top end) for rotating to the first limiting groove 421 when the clamping plate 42 covers the fixed plate 41. Figure 4 The first end of the rotary screw 43 is the bottom end) and is hinged to the fixed plate 41, and the second end of the rotary screw 43 is the top end) for rotating to the first limiting groove 421 when the clamping plate 42 covers the fixed plate 41.

[0037] In the clamping mechanism 4 of the aero-engine anti-separation assembly tool 1000, the clamping plate 42 can be quickly pressed and fixed or loosened relative to the fixed plate 41 through the cooperation of the rotary screw 43 and the compression nut 45, so that the preset positioning shaft 2001 on the aero-engine 2000 is quickly clamped or loosened, the aero-engine 2000 is quickly clamped and positioned, and the assembly and disassembly are convenient and fast. By adding the positioning shaft 2001 to the aero-engine 2000, the clamping mechanism 4 can be arranged away from the aero-engine 2000, which does not interfere with the assembly operation of the aero-engine 2000, and is convenient and flexible to rotate to different angles to complete the assembly operation of the aero-engine 2000. More importantly, the limiting block 44 is sleeved on the rotary screw 43, and the radial fixation of the rotary screw 43 can be realized by embedding the limiting block 44 in the first limiting groove 421 of the clamping plate 42, which limits the rotary action of the rotary screw 43. When the rotary frame 2 rotates to the downward state in the loosening direction of the rotary screw 43, the rotary screw 43 can be prevented from loosening through the cooperation of the limiting block 44 and the first limiting groove 421, so that the compression nut 45 is not easily loosened when rotating to different angles, and the state of pressing the clamping plate 42 can be maintained. The clamping and limiting structure is simple and efficient, the anti-separation effect is good, and additional clamping processes are not needed, which is conducive to realizing quick clamping operation.

[0038] Please refer to Figure 3 and Figure 5The side wall of the limiting block 44 is provided with a limiting pin 441, and the side of the clamping plate 42 away from the fixed plate 41 is also provided with a second limiting groove 422 matched with the limiting pin 441. The limiting pin 441 is used to be embedded in the second limiting groove 422 to limit the limiting block 44 circumferentially relative to the rotary screw 43. By circumferentially limiting the limiting block 44 through the limiting pin 441, the loosening of the compression nut 45 caused by the rotation of the limiting block 44 relative to the rotary screw 43 after being embedded in the first limiting groove 421 is avoided, the fastening effect of the compression nut 45 is improved, and the rotary screw 43 is further fixed through the limiting pin 441, so that the rotary screw 43 is limited and fixed in more directions.

[0039] Preferably, the second limiting groove 422 is arranged along the width direction of the clamping plate 42 and extends to the side surface of the clamping plate 42, and the length of the second limiting pin 441 is greater than the length of the second limiting groove 422, so that the second limiting pin 441 protrudes from the side surface of the clamping plate 42 when embedded in the second limiting groove 422. Therefore, the limiting block 44 can be pressed or taken out through the second limiting pin 441 from the side surface of the clamping plate 42, so that the limiting block 44 is not difficult to be taken out after being tightly embedded in the first limiting groove 421, and the clamping convenience is further improved.

[0040] Preferably, the opposite sides of the limiting block 44 are both provided with the limiting pin 441, the second limiting groove 422 is arranged one by one corresponding to the limiting pin 441, and the two limiting pins 441 protrude from the opposite sides of the clamping plate 42, so that the limiting block 44 is taken and placed more labor-saving and handily, the force of the limiting block 44 is balanced, and because of the two limiting pins 441 and the two second limiting grooves 422, only a small angle of rotation of the limiting block 44 is needed to align the limiting pin 441 with the second limiting groove 422 during embedding the limiting block 44 in the first limiting groove 421, without rotating more than 90 degrees, so that the clamping is more convenient.

[0041] Preferably, the limiting block 44 is provided with a multi-prism structure, specifically a three-prism, a four-prism, a five-prism, etc., and the shape of the first limiting groove 421 is matched with the limiting block 44, and the first limiting groove 421 is also used to limit the limiting block 44 circumferentially. By providing the limiting block 44 with a multi-prism structure and the first limiting groove 421 with a matched multi-prism groove, the limiting block 44 can be circumferentially limited after being embedded in the first limiting groove 421, so that the limiting block 44 is prevented from rotating, the fixing effect is further improved, and the compression nut 45 is prevented from loosening.

[0042] Further, a through hole 442 is formed in the center of the limiting block 44, and the rotating screw 43 is arranged in the through hole 442, so that the limiting block 44 can move axially relative to the rotating screw 43 through the through hole 442.

[0043] As shown in Figure 4 Further, an avoiding groove 423 is arranged on the end face of the second end of the clamping plate 42 away from the first end, and the avoiding groove 423 is used for allowing the rotating screw 43 to rotate to the inside of the clamping plate 42 and allowing the second end of the rotating screw 43 to be located on the first limiting groove 421, so that the rotating screw 43 can be arranged vertically relative to the outer surface of the clamping plate 42, and the limiting block 44 and the compression nut 45 can be arranged vertically on the clamping plate 42, thereby improving the compression effect.

[0044] Preferably, one side of the compression nut 45 facing the limiting block 44 is arranged as a compression surface, and the diameter of the compression surface is greater than the width of the limiting block 44, that is, the vertical projection of the compression surface on the limiting block 44 exceeds the surface of the limiting block 44, so that the compression surface can sufficiently compress the limiting block 44, thereby improving the compression effect. In addition, the part of the compression surface exceeding the limiting block 44 can abut against the surface of the clamping plate 42, thereby strengthening the compression and fixation of the clamping plate 42.

[0045] Further, the compression nut 45 comprises a first segment and a second segment arranged coaxially, the first segment is used for abutting against the limiting block 44, and the second segment is arranged at the end of the first segment away from the limiting block 44, the diameter of the second segment is greater than the diameter of the first segment, and the second segment is provided with a driving part, which is used for holding by hand or clamping by a tool, so as to drive the compression nut 45 to rotate more conveniently and labor-savingly.

[0046] As shown in Figure 1 and Figure 2As shown, the rotating frame 2 comprises rotating shafts 21, curved arms 22, a support frame 23 and support columns 24. The rotating shafts 21 are coaxial and spaced apart on the base 1, i.e. the rotating shafts 21 are arranged on opposite sides of the base 1 along the same axis, and one of the rotating shafts 21 is connected with the driving mechanism 3. The curved arms 22 are arranged on the rotating shafts 21 and extend radially along the rotating shafts 21. The support frame 23 is arranged at one end of the curved arms 22 away from the rotating shafts 21 and connects the curved arms 22 on the rotating shafts 21 as a whole. The support frame 23 can be made of profiled sections, which is low in cost and convenient to process. Different sizes of support frames 23 can be quickly processed according to the size of the aero-engine 2000. The support columns 24 are arranged on the support frame 23 and face the rotating shafts 21.

[0047] Further, the clamping mechanisms 4 are arranged at one end of the support columns 24 away from the support frame 23. The clamping mechanisms 4 are arranged in one-to-one correspondence with the support columns 24. The clamping mechanisms 4 are respectively used to clamp different positioning shafts 2001 of the aero-engine 2000 and make the center of gravity of the aero-engine 2000 on the axis of the rotating shafts 21.

[0048] Specifically, by adjusting the positions and lengths of the support columns 24, the clamping positions of the clamping mechanisms 4 can be adjusted, so that the center of gravity of the aero-engine 2000 is controlled on the axis of the rotating shafts 21, which is more conducive to smoothly driving the aero-engine 2000 to rotate and adjust the angle, avoids shaking due to the deviation of the center of gravity, and has higher stability.

[0049] In this embodiment, the support columns 24 are four in number and are arranged at four corner ends of the support frame 23, so as to stably support the aero-engine 2000 and avoid the assembly surfaces of the aero-engine 2000. In other embodiments, the number and positions of the support columns 24 can be adjusted according to the specific parameters of the aero-engine 1000. For example, when the aero-engine 2000 is larger and heavier, more support columns 24 and clamping mechanisms 4 can be configured, and the support columns 24 and the clamping mechanisms 4 are arranged to avoid the assembly positions of the aero-engine 2000, so as to avoid interference with the assembly operation.

[0050] As shown in FIG. 4, the aero-engine 2000 is clamped by the clamping mechanisms 4, and the center of gravity of the aero-engine 2000 is on the axis of the rotating shafts 21. The driving mechanism 3 drives the rotating frame 2 to rotate, so that the aero-engine 2000 rotates and adjusts the angle. Figure 6As shown, the aero-engine anti-disassembly tool 1000 further comprises a positioning mechanism 5, which comprises a positioning base 51 fixedly installed on the base 1, a positioning turntable 52 provided on the rotating frame 2 and circumferentially spaced apart with a plurality of positioning holes 521 (shown in Figure 8 ), a positioning pin 53 installed on the positioning base 51 through a pin sleeve 54, the pin sleeve 54 being provided with a guide groove 542 (shown in Figure 10 ) extending towards the positioning turntable 52 at an end face thereof away from the positioning turntable 52, a guide pin 56 provided on the positioning pin 53 and matched with the guide groove 542, and a spring 55 abutting against the positioning pin 53 and installed in the pin sleeve 54.

[0051] Specifically, when the guide pin 56 is aligned with the guide groove 542, the positioning pin 53 can be driven by the spring 55 to move towards the positioning turntable 52 and be inserted into the positioning hole 521, thereby achieving positioning and fixation of the positioning turntable 52 relative to the positioning base 51, positioning and fixation of the rotating frame 2 relative to the base 1, and stable fixation of the aero-engine 2000 on the rotating frame 2, facilitating assembly operation. When the aero-engine 2000 needs to be flipped, the positioning pin 53 is only needed to be pulled out of the positioning hole 521, the guide pin 56 is then disengaged from the guide groove 542, and the positioning pin 53 is rotated by a certain angle, so that the guide pin 56 abuts against the end face of the pin sleeve 54 to axially limit the positioning pin 53, thereby keeping the positioning pin 53 disengaged from the positioning turntable 52. At this time, the rotating frame 2 can be driven by the driving mechanism 3 to rotate and adjust the assembly angle of the aero-engine 2000. Similarly, after rotation adjustment, the positioning pin 53 can be rotated by a certain angle to align the guide pin 56 with the guide groove 542, so that the positioning pin 53 can be automatically inserted into the corresponding positioning hole 521 to achieve positioning and fixation of the rotating frame 2. The positioning and unpositioning operations are convenient and fast.

[0052] It is worth noting that when the positioning hole 521 on the positioning turntable 52 is misaligned with the positioning pin 53, the positioning pin 53 cannot be inserted into the positioning hole 521. Therefore, the conventional manual latch structure is easily stuck and cannot be inserted and positioned. In this embodiment, since the spring 55 can drive the positioning pin 53 to automatically move in the direction toward the positioning turntable 52, when the aircraft engine 2000 is rotated to an approximate angle that meets the assembly requirements, the guide pin 56 can be rotated and inserted into the guide groove 542, and then the driving mechanism 3 drives the rotating frame 2 to slowly rotate and finely adjust the angle of the positioning turntable 52. When the positioning hole 521 on the positioning turntable 52 is rotated to a state facing the positioning pin 53, the positioning pin 53 can be automatically inserted into the positioning hole 521 under the elastic force of the spring 55, achieving automatic positioning and fixation to ensure that it is fixed in place.

[0053] like Figure 10 As shown, the pin sleeve 54 further has a pin hole 541 along its axial direction. The positioning pin 53 is inserted into the pin hole 541 and is configured to move axially along the pin hole 541. The pin hole 541 radially limits the positioning pin 53, thereby improving the stability of the positioning pin 53. The guide groove 542 radially penetrates the pin hole 541 on opposite sides thereof, so that the guide pin 56 can be inserted into the guide groove 542 by rotating a small angle.

[0054] like Figure 7 As shown, a mounting hole 511 is provided on the positioning seat 51, and the pin sleeve 54 is detachably embedded in the mounting hole 511. The pin sleeve 54 is installed through the mounting hole 511, which is convenient for assembly. When problems occur with the pin sleeve 54, the spring 55 or the positioning pin 53, they can be quickly removed and replaced, thereby improving the convenience of repair and maintenance.

[0055] Please combine Figure 9 Furthermore, a center hole 512 is also provided on the positioning seat 51, one side of the positioning turntable 52 is connected to the rotating frame 2, and the other side of the positioning turntable 52 is provided with a center shaft 522 that passes through the center hole 512 and is used to rotate relative to the center hole 512. The positioning turntable 52 is rotatably connected to the positioning seat 51 through the cooperation between the center shaft 522 and the center hole 512. The connection structure is simple and efficient, and can enable any positioning hole 521 on the positioning turntable 52 to be rotated to a state facing the positioning pin 53.

[0056] Further, in the two rotating shafts 21 of the rotating frame 2, one rotating shaft 21 is connected with the driving mechanism 3, the central shaft 522 can be used as the other rotating shaft 21, the rotating frame 2 is supported by the central shaft 522, the structure can be simplified, and the positioning mechanism 5 is arranged on the side of the rotating frame 2 away from the driving mechanism 3, so that the positioning mechanism 5 and the driving mechanism 3 do not interfere with each other.

[0057] As shown in Figure 1 Further, the driving mechanism 3 comprises a motor 31 and a speed reducer 32 connected with the output shaft of the motor 31, the speed reducer 32 is connected with the rotating shaft 21 and is used to drive the rotating shaft 21 to rotate under the driving of the motor 31, the torque of the motor 31 is enhanced through the speed reducer 32, and it is ensured that the aero-engine 2000 can be stably driven to rotate.

[0058] Further, the motor 31 is a servo motor, so that the motor 31 can accurately control the rotation angle of the rotating shaft 21, thereby accurately controlling the overturning angle of the aero-engine 2000.

[0059] Further, the bottom of the base 1 is provided with a plurality of universal wheels 11, the universal wheels 11 are provided with self-locking structures, the base 1 can be moved and adjusted in position through the universal wheels 11, thereby driving the aero-engine 2000 to move and adjust the assembly position, more assembly requirements can be met, and the applicability is improved.

[0060] The above only describes the preferred embodiments of the present application and is not used to limit the present application. For those skilled in the art, the present application can have various modifications and changes. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. An anti-slip assembly tool for an aircraft engine, characterized in that: The base (1), the rotating frame (2), the driving mechanism (3) and the clamping mechanism (4) are included. The rotating frame (2) is rotatably arranged on the base (1). The driving mechanism (3) is connected with the rotating frame (2) and is used for driving the rotating frame (2) to rotate and adjust the angle relative to the base (1). The clamping mechanism (4) includes a fixed plate (41), a clamping plate (42), a rotary screw (43), a limiting block (44) and a pressing nut (45). The fixed plate (41) is installed on the rotating frame (2). The first end of the clamping plate (42) is hinged to the fixed plate (41). The second end of the clamping plate (42) is used to turn to the state of covering or separating from the fixed plate (41). The clamping plate (42) is used to clamp the preset positioning shaft (2001) on the aero-engine (2000) on the fixed plate (41). One side of the clamping plate (42) away from the fixed plate (41) is provided with a first limiting groove (421). The first end of the rotary screw (43) is hinged to the fixed plate (41). The second end of the rotary screw (43) is used to rotate into the first limiting groove (421) when the clamping plate (42) covers the fixed plate (41). The limiting block (44) is axially movably sleeved on the rotary screw (43) and is used to be embedded in the first limiting groove (421). The pressing nut (45) is threadedly connected with the rotary screw (43) and is used to press the limiting block (44) in the first limiting groove (421), so as to press and fix the clamping plate (42) relative to the fixed plate (41).

2. The aerospace engine anti-uninstallation tooling of claim 1, wherein, The side wall of the limiting block (44) is provided with a limiting pin (441). The side of the clamping plate (42) away from the fixed plate (41) is also provided with a second limiting groove (422) matched with the limiting pin (441). The limiting pin (441) is used to be embedded in the second limiting groove (422) to limit the limiting block (44) relative to the rotary screw (43) circumferentially.

3. The aerospace engine anti-uninstall tooling of claim 2, wherein, The second limiting groove (422) is arranged along the width direction of the clamping plate (42) and extends to the side surface of the clamping plate (42). The length of the limiting pin (441) is greater than the length of the second limiting groove (422), so that the limiting pin (441) protrudes from the side surface of the clamping plate (42) when embedded in the second limiting groove (422).

4. The aerospace engine anti-uninstall tooling of claim 2 or 3, wherein, The opposite sides of the limiting block (44) are both provided with the limiting pin (441).

5. The aerospace engine anti-uninstall tooling of claim 1, wherein, The limiting block (44) is provided as a polygonal structure. The shape of the first limiting groove (421) is matched with the limiting block (44). The first limiting groove (421) is also used to limit the limiting block (44) circumferentially.

6. The aerospace engine anti-uninstall tooling of claim 1, wherein, The side of the pressing nut (45) facing the limiting block (44) is provided as a pressing surface. The diameter of the pressing surface is greater than the width of the limiting block (44).

7. The aerospace engine anti-uninstall tooling of claim 1, wherein, The rotating frame (2) comprises two rotating shafts (21) coaxially and spacedly mounted on the base (1), curved arms (22) mounted on the rotating shafts (21) and arranged along the radial direction of the rotating shafts (21), a support frame (23) provided at one end of the curved arms (22) away from the rotating shafts (21) and connecting the curved arms (22) on the two rotating shafts (21) into a whole, and a plurality of support columns (24) separately provided on the support frame (23) and arranged in a direction towards the rotating shafts (21), the clamping mechanisms (4) being mounted at one end of the support columns (24) away from the support frame (23), the clamping mechanisms (4) being provided in plurality, the plurality of clamping mechanisms (4) being arranged in one-to-one correspondence with the plurality of support columns (24), and the plurality of clamping mechanisms (4) being respectively used for clamping different positioning shafts (2001) on the aero-engine (2000) and making the center of gravity of the aero-engine (2000) on the axis of the rotating shafts (21).

8. The aerospace engine anti-uninstall tooling of claim 1, wherein, The aero-engine anti-disassembly tool further comprises a positioning mechanism (5), the positioning mechanism (5) comprising a positioning seat (51), a positioning turntable (52), a positioning pin (53), a pin sleeve (54) and a spring (55), the positioning seat (51) being fixedly mounted on the base (1), the positioning turntable (52) being provided on the rotating frame (2) and being arranged with a plurality of positioning holes (521) in a circumferential direction, the positioning pin (53) being mounted on the positioning seat (51) through the pin sleeve (54), the pin sleeve (54) being provided with a guide groove (542) extending in a direction towards the positioning turntable (52) on an end face away from the positioning turntable (52), the positioning pin (53) being provided with a guide pin (56) matched with the guide groove (542), and the spring (55) being spring-loaded in the pin sleeve (54) and abutting against the positioning pin (53), the positioning pin (53) being used for moving in a direction towards the positioning turntable (52) and being inserted into the positioning hole (521) under the driving of the spring (55) when the guide pin (56) is aligned with the guide groove (542), and the positioning pin (53) being used for abutting against the end face of the pin sleeve (54) through the guide pin (56) when the guide pin (56) is misaligned with the guide groove (542), thereby keeping the state of being separated from the positioning turntable (52).

9. The aerospace engine anti-uninstall tooling of claim 8, wherein, The positioning seat (51) is provided with a central hole (512), one side of the positioning turntable (52) is connected with the rotating frame (2), and the other side of the positioning turntable (52) is provided with a central shaft (522) penetrating through the central hole (512) and being used for rotating relative to the central hole (512).

10. The aerospace engine anti-uninstall tooling of claim 1, wherein, The bottom of the base (1) is provided with a plurality of universal wheels (11).

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