An assembly system and method for an aeroengine locking element

Abstract

The application discloses an assembly system and method for an aero-engine locking element, and relates to the technical field of automatic assembly and precision control of threaded parts. The assembly system reproduces the geometric characteristics of the rotor and the nut through the first simulation structure and the second simulation structure of the pre-learning tool, and converts the complex blind angle positioning into a calculable digital process. The endoscope at the second end of the inner stop outer rotation tool guides the initial alignment of the inner stop boss and the rotor positioning groove in the contracted state, and observes the outer stop lug and the inner stop lug of the stop washer in real time in the elongated state, so that the installation device can accurately guide the outer stop lug into the nut positioning groove and the inner stop lug into the rotor positioning groove. The inner stop ring tool is driven by the booster arm to slide axially along the inner wall of the outer stop ring tool, and the elastic stop piece is used to stably push the axially stop ring and the stop washer surrounded by the clamping into the installation position. The assembly success rate and the locking reliability are improved, and the high-quality assembly of the key connection part of the aero-engine is ensured.

Description

Technical Field

[0001] This invention relates to the field of automated assembly and precision control technology for threaded parts, and in particular to an assembly system and method for locking components of aero engines. Background Technology

[0002] In the manufacturing and maintenance of aero engines, the connection between the shaft rotor and the nut is a crucial step in ensuring the stable operation of this core component. Due to the compact internal structure of the engine, the nut is often located in a narrow space within a deep cavity, limiting the operating environment and obstructing visibility.

[0003] Chinese patent application CN202511627792.X discloses a "tightening device and method for a low-pressure turbine shaft end nut of an aero-engine," comprising: a robotic arm, an electric tightener connected thereto, and an inner-stop, outer-rotation fixture. The inner-stop, outer-rotation fixture includes: an inner-stop fixture and an outer-rotation fixture, an outer-rotation drive device, and a vision inspection device. The outer-rotation drive device is connected to the electric tightener, and the second end of the outer-rotation fixture is connected to the shaft end nut to drive the outer-rotation fixture to rotate and tighten the shaft end nut. The first end of the inner-stop fixture is fixed to the outer-rotation drive device, and its second end is connected to the low-pressure turbine shaft to prevent the low-pressure turbine shaft from rotating under force during the insertion of the shaft end nut. The vision inspection device is used to guide the inner-stop fixture to align and connect with the low-pressure turbine shaft, and to guide the shaft end nut to align with the low-pressure turbine shaft.

[0004] However, the aforementioned patent can only determine whether the nut connecting groove and the rotor positioning groove are aligned through a visual inspection device. The alignment accuracy and stability are not good, and the locking washers and axial retaining rings need to be installed manually, resulting in low assembly efficiency and insufficient locking reliability. Summary of the Invention

[0005] Based on this, the present invention provides an assembly system for locking components of aero-engines. By setting up pre-worked fixtures, installation devices and endoscopes, a main inner stop boss is set within the field of view of the endoscope, which improves the installation accuracy of the stop washer and axial retaining ring, and improves the connection stability of the nut and rotor.

[0006] This invention provides an assembly system for locking components in aero engines, used to install an axial retaining ring and a locking washer at the connection between the rotor and the nut on the aero engine shaft end, comprising: Assist arm; An inner stop and outer rotation tooling, the first end of which is connected to the assist arm; The pre-training fixture has a first end that is detachably connected to the second end of the inner stop and outer rotation fixture; the first end of the pre-training fixture is provided with a first simulation structure and a second simulation structure, the first simulation structure being the same as the first end structure of the rotor, and the second simulation structure being the same as the first end structure of the nut. The mounting device has a first end that is detachably connected to the second end of the inner stop and outer rotation tooling; the second end of the mounting device is provided with a plurality of elastic baffles along the axial direction, and the plurality of elastic baffles surround and clamp the mounting axial retaining ring and the stop washer; the outer peripheral surface of the first end of the stop washer is provided with a plurality of outer stop ears, and the second end of the stop washer is provided with a plurality of inner stop ears; An endoscope is provided at the second end of the inner stop and outer rotation tooling. The endoscope is used to guide the outer stop ear to connect with the nut positioning groove, and the inner stop ear to connect with the rotor positioning groove.

[0007] In some embodiments, the first end of the pre-training fixture is provided with an inner ring and an outer ring. The first simulation structure includes a plurality of inner ring grooves provided on the inner ring, and the inner ring grooves correspond one-to-one with the rotor positioning grooves on the rotor. The second simulation structure includes a plurality of outer ring grooves provided on the outer ring, and the outer ring grooves correspond one-to-one with the nut positioning grooves on the nut.

[0008] In some embodiments, the mounting device includes: An outer retaining ring fixture is connected to the second end of the inner stop outer rotation fixture. The second end of the outer retaining ring fixture is provided with a plurality of outer retaining bosses. The outer retaining bosses correspond one-to-one with the bosses of the nut. At least one of the outer retaining bosses is provided with a shim at its second end. At least two of the outer retaining bosses are provided with elastic baffles on their inner circumferential surfaces. The inner retaining ring fixture is connected to the second end of the inner stop outer rotation fixture, and the outer retaining ring fixture surrounds the inner retaining ring fixture in an annular shape. The inner retaining ring fixture can slide axially along the inner wall of the outer retaining ring fixture.

[0009] In some embodiments, the plurality of outer stop bosses include mounting bosses and reserved bosses, wherein the mounting boss is provided with the shim block and the elastic baffle, and the reserved boss is provided with the outer stop ear.

[0010] In some embodiments, the outer retaining ring fixture is connected to the second end of the inner stop external rotation fixture by an outer retaining screw, the inner retaining ring fixture is connected to the second end of the inner stop external rotation fixture by an inner retaining screw, and the elastic baffle is fixed to the inner circumferential surface of the outer retaining boss by a baffle screw.

[0011] In some embodiments, the inner retaining ring tooling is provided with a through clearance groove, the endoscope is inserted into the clearance groove, and the endoscope includes a light source.

[0012] In some embodiments, the endoscope has a retracted state and an extended state; The second end of the inner stop and outer rotation tooling is provided with a plurality of inner stop bosses along the circumferential direction, and the inner stop bosses correspond one-to-one with the rotor positioning grooves; In the retracted state, the endoscope guides the inner stop boss to align and connect with the rotor positioning groove; in the extended state, the endoscope guides the outer stop ear to connect with the nut positioning groove, and the inner stop ear to connect with the rotor positioning groove.

[0013] In some embodiments, the axial retaining ring is provided with a notch, and both ends of the notch are provided with through holes.

[0014] In some embodiments, the system includes a gearbox connected to the assist arm, the input end of the gearbox being connected to a servo tightening shaft, and the output end of the gearbox being provided with the inner stop and outer rotation fixture.

[0015] Accordingly, the present invention also provides an assembly method for a locking element of an aero-engine, employing the assembly system for a locking element of an aero-engine as described above, for installing an axial retaining ring and a locking washer at the connection between the rotor and the nut at the shaft end of the aero-engine. The assembly method includes: Align and connect the inner groove of the pre-training fixture with the inner stop boss of the inner stop outer rotation fixture. Adjust the position of the outer rotation boss of the inner stop outer rotation fixture by means of the servo tightening shaft until the outer rotation boss is engaged in the outer groove of the pre-training fixture. The minimum division angle is obtained based on the number of times the rotor positioning slot and the nut positioning slot are aligned at all angles; from any alignment position of the rotor positioning slot and the nut positioning slot to the next alignment position, the minimum division angle is the minimum angle at which the nut needs to be tightened. The servo tightening shaft is manipulated to apply a preset rated torque, and the first angle corresponding to the angle alignment position of the pre-training fixture is recorded; Disassemble the pre-training fixture and install the nut onto the second end of the inner stop-out-rotation fixture; Adjust the endoscope to the retracted position, and use the assist arm to insert the nut into the blind cavity and make it fit against the rotor; The servo tightening shaft is manipulated to apply a preset minimum torque, and the second angle corresponding to the angular alignment position of the nut at this time is recorded; Based on the minimum division angle, the first angle, and the second angle, the minimum tightening angle is obtained; The servo tightening shaft is manipulated to continue tightening the nut to the minimum tightening angle, completing the angular positioning of the nut and connecting the nut to the rotor; The inner stop and outer rotation tooling is moved out of the blind cavity by the assisting arm, the first end of the installation device is connected to the second end of the inner stop and outer rotation tooling, and the axial retaining ring and the stop washer are sequentially inserted radially into the annular space inside the elastic baffle. The endoscope is adjusted to the extended state, and the installation device is sent into the blind cavity by the assist arm, so that the outer stop ear is aligned with the nut positioning groove and the inner stop ear is aligned with the rotor positioning groove. The control arm feeds axially, pushing the stop washer and the axial retaining ring to be installed sequentially at the first end of the nut.

[0016] Compared with the prior art, the technical solution provided by this invention has the following advantages: The assembly system for locking components of aero-engines provided by this invention reproduces the geometric features of the rotor and nut through the first and second simulation structures of the pre-learning fixture, transforming the complex blind angular positioning into a calculable digital process. This digital process allows the final tightening angle to be automatically calculated and output in real time when the tightening reaches the lower torque limit, making the tightening to the lower torque limit and angle alignment an automatic and continuous process. This effectively solves the problem of the nut facing greater input torque requirements and easy runout when restarting after a pause under high torque conditions (dynamic friction is converted into static friction, and static friction has abrupt changes). Based on this, the endoscope at the second end of the inner stop and outer rotation fixture guides the inner stop boss to initially align with the rotor positioning groove in the retracted state, and observes the outer and inner stop ears of the stop washer in real time in the extended state, enabling the installation device to accurately guide the outer stop ear into the nut positioning groove and the inner stop ear into the rotor positioning groove. Then, the inner retaining ring fixture is axially slid along the inner wall of the outer retaining ring fixture by the assist arm. The axial retaining ring and the stop washer, which are held by elastic baffles, are smoothly pushed into the installation position. This effectively solves the problems of difficult angular positioning of the nut in the narrow space of the deep cavity due to obstructed vision, easy misalignment and fall-off of locking elements during manual installation, and inability to visually confirm the alignment status in real time. It eliminates the risk of over-tightening and safety hazards caused by repeated manual adjustments, improves the first-time success rate of assembly and locking reliability, and ensures high-quality assembly of critical connection parts of aero-engines.

[0017] It is understood that, compared with the prior art, the assembly method for locking elements of aero-engines provided in this embodiment of the invention includes all the technical features and effects of the assembly system for locking elements of aero-engines described above, and will not be repeated here. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the assembly system for locking elements in aero engines provided by the present invention; Figure 2 A schematic diagram of the pre-assembly tooling in the assembly system for locking elements of aero-engines provided by the present invention; Figure 3A cross-sectional spatial structure diagram of the rotor and nut in the assembled position in the assembly system for the locking element of an aero-engine provided by the present invention. Figure 4 This is a schematic diagram of the installation device in the assembly system for locking elements of an aero-engine provided by the present invention. Figure 5 A schematic diagram of the structure of the locking washer in the assembly system of the locking element for aero-engine provided by the present invention; Figure 6 A schematic diagram of the structure of the axial retaining ring in the assembly system for locking elements of aero engines provided by the present invention; Figure 7 A schematic diagram showing the placement of the retaining washer and axial retaining ring in the mounting device in the assembly system for the locking element of an aero-engine provided by the present invention; Figure 8 This is a partial sectional front view structural schematic diagram of the internal stop external rotation tooling, gearbox, and intelligent servo tightening shaft in the assembly system for locking elements of aero engines provided by the present invention. Figure 9 for Figure 8 A partial sectional view of the spatial structure of the second end of the inner stop tooling; Figure 10 yes Figure 8 Schematic diagram of the cross-sectional spatial structure of the inner and outer rotating sleeve; Figure 11 yes Figure 8 A partial sectional view of the spatial structure of the intermediate gearbox; Figure 12 A horizontal attitude diagram of the assembly system for locking elements of aero engines provided by the present invention; Figure 13 This is a diagram showing the alignment of the outer sleeve and nut in the assembly system for locking components of an aero-engine provided by the present invention. Figure 14 This is a diagram showing the alignment of the inner stop tooling and the rotor in the assembly system for locking components of an aero-engine provided by the present invention. Figure 15 This is a schematic diagram showing the assembly positions of the rotor and nut; Figure 16 A schematic diagram of the alignment detector in the assembly system for locking components of an aero-engine provided by the present invention; Figure 17 Comparison diagrams before and after adjustment of the inner stop boss and outer rotating boss in the assembly system for locking components of aero-engines provided by the present invention.

[0019] Explanation of reference numerals in the attached figures: 1. Internal stop and external rotation tooling; 11. Internal stop fixture; 111. Internal stop fixture shaft; 112. Internal stop fixture chuck; 113. Detector retaining ring; 114. Endoscope holder; 115. Main internal stop boss; 116. Internal stop boss; 117. Observation boss; 118. Alignment detector; 119. Sliding spline; 1110. Internal stop spring; 12. Outer sleeve; 121. Tightening sleeve; 122. Tightening shaft; 123. Outer spring; 124. Rubber ring; 125. Outer boss; 126. Triangular spline; 127. Outer support bearing; 128. Sleeve retaining ring; 129. Spring retaining ring; 1210. Inner support bearing; 1211. Outer removable screw; 13. Endoscope; 2. Gearbox; 21. Drive wheel; 22. Driven wheel; 23. Tooling connection part; 24. Operating handle; 25. Attitude switching slide; 26. Lifting module; 261. Lifting rod; 262. Display screen; 27. Internal stop removable screw; 3. Servo tightening shaft; 4. Assistive arm; 5. Threaded connection structure; 51. Rotor; 52. Nut; 53. Connected part; 54. Rotor positioning groove; 55. Nut positioning groove; 6. Preview the tooling; 61. Inner ring; 611. Inner ring groove; 62. Outer ring; 621. Outer ring groove; 7. Install the device; 71. Outer retaining ring fixture; 72. Inner retaining ring fixture; 721. Clearance groove; 73. Elastic baffle; 74. Ballast block; 75. Outer retaining screw; 76. Inner retaining screw; 77. Baffle screw; 78. Outer retaining boss; 781. Assembly boss; 782. Reserved boss; 8. Locking washer; 81. Outer locking lug; 82. Inner locking lug; 9. Axial retaining ring; 91. Notch; 92. Through hole. Detailed Implementation

[0020] To make the above-mentioned objects, features, and advantages of the present invention more apparent and understandable, specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings. Many specific details are set forth in the following description to provide a thorough understanding of the present invention. However, the present invention can be practiced in many other ways different from those described herein, and those skilled in the art can make similar modifications without departing from the spirit of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed below.

[0021] This invention provides an assembly system for locking components in aircraft engines, see below. Figures 1 to 7 . Figure 1 This is a schematic diagram of the assembly system for locking elements in aero engines provided by the present invention; Figure 2 A schematic diagram of the pre-assembly tooling in the assembly system for locking elements of aero-engines provided by the present invention; Figure 3 A cross-sectional spatial structure diagram of the rotor and nut in the assembled position in the assembly system for the locking element of an aero-engine provided by the present invention. Figure 4 This is a schematic diagram of the installation device in the assembly system for locking elements of an aero-engine provided by the present invention. Figure 5 A schematic diagram of the structure of the locking washer in the assembly system of the locking element for aero-engine provided by the present invention; Figure 6 A schematic diagram of the structure of the axial retaining ring in the assembly system for locking elements of aero engines provided by the present invention; Figure 7 This is a schematic diagram showing the placement of the locking washer and axial retaining ring in the mounting device of the assembly system for the locking element of an aero-engine provided by the present invention.

[0022] This invention provides an assembly system for locking components of an aero-engine, used to install an axial retaining ring 9 and a locking washer 8 at the connection between the rotor 51 and the nut 52 at the shaft end of the aero-engine. The system includes: an assist arm 4; an inner stop-outward rotation fixture 1, the first end of which is connected to the assist arm 4; a pre-installation fixture 6, the first end of which is detachably connected to the second end of the inner stop-outward rotation fixture 1; the first end of the pre-installation fixture 6 is provided with a first simulated structure and a second simulated structure, the first simulated structure being the same as the first end structure of the rotor 51, and the second simulated structure being the same as the first end structure of the nut 52; installation... The device 7 has a first end that is detachably connected to the second end of the inner stop and outer rotation fixture 1. The second end of the device 7 is provided with a plurality of elastic baffles 73 along the axial direction. The plurality of elastic baffles 73 surround and clamp the axial retaining ring 9 and the stop washer 8. The outer circumferential surface of the first end of the stop washer 8 is provided with a plurality of outer stop ears 81, and the second end of the stop washer 8 is provided with a plurality of inner stop ears 82. The second end of the inner stop and outer rotation fixture 1 is provided with an endoscope 13, which is used to guide the outer stop ears 81 to connect with the nut positioning groove 55 and the inner stop ears 82 to connect with the rotor positioning groove 54.

[0023] Specifically, before the actual installation of nut 52, the pre-training fixture 6 pre-determines the target position for angular alignment of nut 52 by simulating the geometric features of nut 52 and rotor 51. The shape, size, and distribution of the first simulated structure are exactly the same as the first end structure of rotor 51, and the shape, size, and distribution of the second simulated structure are exactly the same as the first end structure of nut 52. In other words, the pre-training fixture 6 can allow the inner stop and outer rotation fixture 1 to be practiced in an external or shallow cavity environment without consuming real parts, and provides preset parameters for the actual nut tightening angular alignment process.

[0024] The mounting device 7 is used to carry and push the axial retaining ring 9 and the stop washer 8 into the installation position after the nut 52 and the rotor 51 are connected. A plurality of elastic baffles 73 are axially arranged at the second end of the mounting device 7. These elastic baffles 73 are arranged in a ring to form a certain elasticity. The axial retaining ring 9 and the stop washer 8 can be pressed radially into this ring space and tightly held by the elastic restoring force of the elastic baffles 73, preventing them from falling or shifting during insertion into the deep cavity. The number, thickness, and material of the elastic baffles 73 can be adaptively adjusted according to the weight and size of the axial retaining ring 9 and the stop washer 8; this embodiment of the invention does not impose any special limitations on this.

[0025] It should be noted that in this embodiment of the invention, the ultimate goal is to install the retaining washer 8 and the axial retaining ring 9 into place. Throughout the process, the preparatory fixture 6 completes the preparatory work before installing the retaining washer 8 and the axial retaining ring 9, focusing on aligning the angles and transforming blind operation within the deep cavity into visual data control, eliminating the risk of over-tightening and angle errors caused by manual adjustment by feel. The installation device 7 completes the placement and execution work; installation can only be performed using the installation device 7 after the preparatory fixture 6 has completed its preparatory work. Therefore, the preparatory fixture 6 and the installation fixture are sequential processes. Based on this, the endoscope 13 is integrated into the end of the inner stop and outer rotation fixture 1 and provides dual-state visual guidance, thus enabling real-time confirmation of the alignment status of the inner and outer retaining ears 81 with the positioning groove during the installation of the locking elements, avoiding misinstallation. Furthermore, since the installation device 7 is equipped with a surrounding elastic baffle 73, it can effectively clamp the axial retaining ring 9 and the retaining washer 8 during transport, preventing them from falling off or shifting within the deep cavity, significantly improving the first-time success rate of assembly and operational safety.

[0026] Please refer to it again. Figure 2 In some embodiments, the first end of the pre-training fixture 6 is provided with an inner ring 61 and an outer ring 62. The first simulation structure includes a plurality of inner ring grooves 611 provided on the inner ring 61, and the inner ring grooves 611 correspond one-to-one with the rotor positioning grooves 54 on the rotor 51. The second simulation structure includes a plurality of outer ring grooves 621 provided on the outer ring 62, and the outer ring grooves 621 correspond one-to-one with the nut positioning grooves 55 on the nut 52.

[0027] Specifically, the first end of the pre-training fixture 6 has an inner ring 61 and an outer ring 62, meaning that the end of the first end of the pre-training fixture 6 has a concentrically arranged double-layer annular structure area. The inner ring 61 is located in the central area, and the outer ring 62 surrounds the outer periphery of the inner ring 61, together simulating the rotor 51 and the nut 52. The first simulation structure includes multiple inner ring grooves 611 provided on the inner ring 61. The number, shape, distribution angle, and depth of the inner ring grooves 611 are configured to be completely consistent with the rotor positioning groove 54 on the rotor 51. The function of the inner ring grooves 611 is to physically engage with the inner stop boss 116 on the inner stop outer rotation fixture 1, thereby simulating the locking state when the inner stop outer rotation fixture 1 is connected to the real rotor 51 during the pre-training stage. The second simulation structure includes multiple outer ring grooves 621 provided on the outer ring 62. The number, shape, distribution angle, and depth of the outer ring grooves 621 are configured to be completely consistent with the nut positioning groove 55 on the nut 52. The function of the outer ring groove 621 is to physically engage with the outer rotating boss 125 on the inner stop outer rotating tool 1, thereby simulating the driving state when the inner stop outer rotating tool 1 drives the real nut 52 to rotate during the pre-training stage.

[0028] It should be noted that the inner ring 61 and outer ring 62 of the pre-training fixture 6 are an integral structure. That is, the relative positions of the first and second simulated structures are fixed and cannot rotate relative to each other. The reason is that although the rotor 51 has multiple rotor positioning slots 54 and the nut 52 has multiple nut positioning slots 55, the number of rotor positioning slots 54 and nut positioning slots 55 are coprime. Therefore, when the rotor 51 and nut 52 are connected, there is only one alignment situation, that is, only one rotor positioning slot 54 and one nut positioning slot 55 are aligned. The pre-training fixture 6 only needs to simulate this one situation.

[0029] Thus, since the pre-training fixture 6 adopts a double-layer simulation structure of inner ring 61 and outer ring 62, and the inner ring groove 611 and outer ring groove 621 correspond one-to-one with the positioning grooves of the real rotor 51 and nut 52, it can quantitatively reproduce the angular coupling relationship between the rotor 51 and nut 52 in the deep cavity under non-working conditions. This solves the technical problems in the prior art caused by the inability to directly observe the relative positions of parts in the deep cavity, which leads to angular positioning that relies on manual experience, has low adjustment efficiency, and is prone to over-tightening. It achieves the technical effect of transforming the complex blind cavity angular alignment problem into a calculable digital angle control process, which significantly improves the assembly accuracy and consistency.

[0030] Please refer to it again. Figure 4 and Figure 7In some embodiments, the mounting device 7 includes: an outer retaining ring fixture 71 connected to the second end of the inner stop-outward rotation fixture 1, the second end of the outer retaining ring fixture 71 being provided with a plurality of outer retaining bosses 78, the outer retaining bosses 78 corresponding one-to-one with the bosses of the nut 52, at least one outer retaining boss 78 being provided with a shim block 74 at its second end, and at least two outer retaining bosses 78 being provided with elastic baffles 73 on their inner circumferential surfaces; an inner retaining ring fixture 72 connected to the second end of the inner stop-outward rotation fixture 1, and the outer retaining ring fixture 71 annularly surrounding the inner retaining ring fixture 72, the inner retaining ring fixture 72 being able to slide axially along the inner wall of the outer retaining ring fixture 71.

[0031] The boss of nut 52 refers to the boss between two adjacent nut positioning grooves 55. The outer stop boss 78 corresponds one-to-one with the boss of nut 52, meaning that the position and number of the outer stop boss 78 and the boss of nut 52 are the same.

[0032] Specifically, the outer retaining ring fixture 71 is an annular component used to support the locking element and provide a radial positioning reference. The first end of the outer retaining ring fixture 71 is detachably connected to the second end of the inner stop-outer rotation fixture 1, and its second end has multiple outer retaining bosses 78 evenly distributed circumferentially. The number, shape, and spacing of the outer retaining bosses 78 are set according to the actual structure of the nut 52, and are equal in number and position to the bosses at the end of the nut 52. Through the physical coupling between the outer retaining bosses 78 and the bosses of the nut 52, the outer retaining ring fixture 71 plays a radial positioning role during installation, ensuring that the axis of the mounting device 7 remains coaxial with the axes of the aero-engine rotor 51 and the nut 52.

[0033] In the outer retaining boss 78, at least one outer retaining boss 78 has a shim block 74 at its second end. The height of the shim block 74 can be set according to the installation gap depth between the nut 52 and the rotor 51, and it is used as a limit stop during axial feeding. When the shim block 74 contacts the end face of the nut 52 or the bottom of the positioning groove, the outer retaining ring fixture 71 stops axial movement, thereby providing a reaction force support for the relative sliding of the inner retaining ring fixture 72.

[0034] In addition, at least two outer retaining bosses 78 have elastic retaining plates 73 on their inner circumferential surfaces. The elastic retaining plates 73 are radially elastic sheet-like clamping members, and their material can be spring steel or other metal materials with a high modulus of elasticity. The elastic retaining plates 73 are fixed to the inner side of the outer retaining bosses 78 by interference fit or screw fastening, and their inner ring 61 forms an annular space for accommodating the axial retaining ring 9 and the stop washer 8. The elastic retaining plates 73 cooperate with the outer retaining ring fixture 71, using their radial elastic force to prevent the axial retaining ring 9 and the stop washer 8 from falling out during insertion into the deep cavity, while allowing the inner retaining ring fixture 72 to generate necessary radial clearance when pushing the locking element.

[0035] The inner retaining ring fixture 72 is an annular push rod assembly used to transmit axial thrust for installing locking elements. The inner retaining ring fixture 72 is connected to the second end of the inner stop-outer-rotation fixture 1 and is annularly surrounded by the outer retaining ring fixture 71. A sliding fit is formed between the outer diameter of the inner retaining ring fixture 72 and the inner diameter of the outer retaining ring fixture 71, allowing the inner retaining ring fixture 72 to slide axially along the inner wall of the outer retaining ring fixture 71. When the outer retaining ring fixture 71 stops moving due to the shim 74 pressing against the nut 52, the assist arm 4 can still continue to drive the inner retaining ring fixture 72 forward. The front end face of the inner retaining ring fixture 72 can directly contact and push the axial retaining ring 9 and the stop washer 8 located within the elastic baffle 73, pushing them out of the annular space and pressing them into the designated installation positions of the nut 52 and rotor 51.

[0036] Please refer to it again. Figure 4 In some embodiments, the plurality of outer bosses 78 include mounting bosses 781 and reserved bosses 782. Mounting bosses 781 are provided with shims 74 and elastic baffles 73, and reserved bosses 782 are provided with outer stop ears 81.

[0037] Specifically, this invention achieves differentiated processing of different parts of the locking element by functionally dividing the outer retaining boss 78 into an assembly boss 781 and a reserved boss 782. The assembly boss 781 is a protruding structure on the outer retaining ring tooling 71 that bears the main clamping and limiting functions. Its number can be set according to the size and distribution requirements of the stop washer 8 and the axial retaining ring 9. The assembly boss 781 is responsible for constraining the main body of the axial retaining ring 9 and the stop washer 8, preventing them from falling off during transportation and feeding. The assembly boss 781 integrates a shim block 74 and an elastic baffle 73, which together constitute the pre-assembly clamping unit of the locking element, ensuring that the element does not fall off or misalign during insertion into the deep cavity. The reserved boss 782 is a protruding structure on the outer retaining ring tooling 71 used to support the outer stop ear 81 of the stop washer 8. It does not have an elastic baffle 73 or a shim block 74. During the assembly preparation stage, the outer stop ear 81 of the stop washer 8 is placed directly on the top plane of the reserved boss 782.

[0038] Please refer to it again. Figure 4 In some embodiments, the outer retaining ring fixture 71 is connected to the second end of the inner stop outer rotation fixture 1 by the outer retaining screw 75, the inner retaining ring fixture 72 is connected to the second end of the inner stop outer rotation fixture 1 by the inner retaining screw 76, and the elastic baffle 73 is fixed to the inner circumferential surface of the outer retaining boss 78 by the baffle screw 77.

[0039] Specifically, the outer retaining ring fixture 71 is connected to the second end of the inner stop-outward rotation fixture 1 via an outer retaining screw 75. The outer retaining screw 75 passes through the mounting hole at the first end of the outer retaining ring fixture 71 and is screwed into the corresponding threaded hole at the second end of the inner stop-outward rotation fixture 1. The inner retaining ring fixture 72 is connected to the second end of the inner stop-outward rotation fixture 1 via an inner retaining screw 76. The inner retaining screw 76 fixes the inner retaining ring fixture 72 at a specific position on the inner stop-outward rotation fixture 1, while allowing the inner retaining ring fixture 72 to remain relatively stationary or slide axially when needed. The elastic baffle 73 is fixed to the inner circumferential surface of the outer stop boss 78 via a baffle screw 77. The root or fixed end of the elastic baffle 73 is installed inside the outer stop boss 78 of the outer retaining ring fixture 71 by screw clamping. The baffle screw 77 not only serves a fixing function, but also allows for fine adjustment of the initial clamping force of the elastic baffle 73 by adjusting the tightening torque, so that it can firmly hold the axial retaining ring 9 and the stop washer 8, and allow the locking element to be smoothly disengaged when subjected to sufficient axial thrust.

[0040] Please refer to it again. Figure 4 In some embodiments, the inner retaining ring tooling 72 is provided with a through clearance groove 721, and the endoscope 13 is inserted into the clearance groove 721. The endoscope 13 includes a light source.

[0041] Specifically, to ensure that the inner retaining ring fixture 72 does not interfere with the endoscope 13 during its advancement, a through clearance groove 721 is provided on the inner retaining ring fixture 72. During the process of the inner retaining ring fixture 72 sliding axially to push the locking element for installation, the endoscope 13 remains relatively stationary or only undergoes necessary extension and retraction adjustments, while the inner retaining ring fixture 72 slides relative to the endoscope 13, providing clearance space for the endoscope 13. The two achieve spatial coexistence and motion decoupling through the clearance groove 721, avoiding mechanical collisions or friction between the inner retaining ring fixture 72 and the endoscope 13.

[0042] Since the connection between the rotor 51 and the nut 52 at the end of the aero-engine shaft is usually located in a deep cavity blind area where natural light cannot reach and the ambient illumination is extremely low, the endoscope 13 includes a light source. The light source is integrated into the front end of the endoscope 13, or it can be a light-emitting unit inside the endoscope body. It is used to illuminate the area in front of the inner retaining ring fixture 72, and the reflected light enters the objective lens of the endoscope 13, thereby forming a clear image that is transmitted to an external display device. Through this cooperation, even when the inner retaining ring fixture 72 blocks some of the external light, the light source can still directly illuminate the work point, ensuring that the operator or control system can clearly identify the relative positions of the outer stop ear 81 and the nut positioning groove 55, and the inner stop ear 82 and the rotor positioning groove 54, thus achieving precise alignment.

[0043] Please refer to it again. Figure 7In some embodiments, the endoscope 13 has a retracted state and an extended state; the second end of the inner stop outer rotation tool 1 is provided with a plurality of inner stop bosses 116 along the circumferential direction, and the inner stop bosses 116 correspond one-to-one with the rotor positioning grooves 54; in the retracted state, the endoscope 13 is used to guide the inner stop bosses 116 to align and connect with the rotor positioning grooves 54; in the extended state, the endoscope 13 is used to guide the outer stop ear 81 to connect with the nut positioning groove 55, and the inner stop ear 82 to connect with the rotor positioning groove 54.

[0044] Specifically, the endoscope 13 can be a tubular endoscope 13, which has a retracted state and an extended state. In the retracted state, it is used to guide the inner stop boss 116 on the inner stop tool 11 to align and connect with the rotor positioning groove 54 on the rotor 51. In the extended state, it is used to guide the stop washer 8 assembled on the positioning tool to be smoothly installed into the groove of the tightened rotor 51 and nut 52.

[0045] This invention employs an endoscope 13 with both retracted and extended states, enabling the same vision system to meet both the high-precision alignment requirements of the inner stop boss 116 and the rotor positioning groove 54, and the alignment requirements of the outer stop ear 81, the inner stop ear 82, the nut positioning groove 55, and the rotor positioning groove 54. This solves the problem of alignment difficulties caused by changes in observation distance within a deep and narrow cavity, avoids spatial interference and cumbersome operation caused by frequent changes in observation tools or the addition of redundant equipment, and significantly improves assembly efficiency and the success rate of first-time alignment.

[0046] Please refer to it again. Figure 6 In some embodiments, the axial retaining ring 9 is provided with a notch 91, and both ends of the notch 91 are provided with through holes 92.

[0047] Specifically, the main structure of the axial retaining ring 9 has a certain degree of elasticity, and its outer diameter is usually slightly larger than the diameter of the accommodating space at the installation location. Therefore, a notch 91 is provided on the axial retaining ring 9, making the originally closed annular structure an open annular structure. Through holes 92 are provided at both ends of the notch 91. During installation, by inserting a tool into the through holes 92 and stretching it, the notch 91 of the axial retaining ring 9 is reduced, and the overall diameter becomes smaller, allowing it to fit into the outer retaining ring fixture 71. Afterwards, the tool is removed, the axial retaining ring 9 returns to its original position, and is secured in the outer retaining ring fixture 71.

[0048] Please refer to it again. Figure 1 Please refer to the following: Figure 8 and Figure 11 , Figure 8 This is a partial sectional front view structural schematic diagram of the internal stop external rotation tooling, gearbox, and intelligent servo tightening shaft in the assembly system for locking elements of aero engines provided by the present invention. Figure 11 yes Figure 8A partial cross-sectional spatial structure diagram of the gearbox. In some embodiments, the system includes a gearbox 2 connected to the assist arm 4, the input end of the gearbox 2 being connected to the servo tightening shaft 3, and the output end of the gearbox 2 being provided with an inner stop and outer rotation fixture 1.

[0049] Specifically, the gearbox 2 includes a tooling connection part 23, inside which a driving gear 21 and a driven gear 22 are meshed and connected. The gear shaft of the driving gear 21 is connected to the servo tightening shaft 3, and the driven gear 22 is connected to the outer rotating sleeve 12. The second end of the tooling connection part 23 is connected to the first end of the inner stop tool 11. The gearbox 2 has a hollow structure, with the driving gear 21 and the driven gear 22 installed inside. The tooling connection part 23 serves as the main support of the gearbox 2, not only supporting the internal gears but also acting as a connection interface for external components. The gear shaft of the driving gear 21 is fixedly connected to the servo tightening shaft 3, and the driven gear 22 is externally meshed with the driving gear 21. The driven gear 22 is fixedly connected to the outer rotating sleeve 12. During operation, the high-speed, low-torque power output by the servo tightening shaft 3 is transmitted to the driven gear 22 via the driving gear 21. Through the reasonable design of the gear transmission ratio, the effect of speed reduction and torque increase is achieved, thereby outputting a low-speed, high-torque output suitable for the assembly of the high-torque nut 52. It should be understood that the gear transmission ratio can be set according to specific assembly torque requirements, for example, it can be set to a transmission structure with a reduction ratio greater than 1. In addition, the tooling connection part 23 also serves to bear the reaction torque. During the tightening process, the reaction torque received by the inner stop tooling 11 is transmitted to the gearbox 2 housing through the tooling connection part 23, thereby preventing the reaction torque from affecting the normal operation of the servo tightening shaft 3 and ensuring the stability of the tightening process.

[0050] Preferably, the gear drive can be a helical gear drive, which can reduce the vibration caused by gear meshing during tightening and make the tightening process smoother.

[0051] Accordingly, the present invention also provides an assembly method for a locking element of an aero-engine, employing the above-described assembly system for a locking element of an aero-engine, for installing an axial retaining ring 9 and a stop washer 8 at the connection between the rotor 51 and the nut 52 at the shaft end of the aero-engine. The assembly method includes: aligning and connecting the inner ring groove 611 of the pre-training fixture 6 with the inner stop boss 116 of the inner stop outer rotation fixture 1; adjusting the position of the outer rotation boss 125 of the inner stop outer rotation fixture 1 using the servo tightening shaft 3 until the outer rotation boss 125 is engaged in the outer ring groove 621 of the pre-training fixture 6; obtaining the minimum division angle based on all cases of angular alignment between the rotor positioning groove 54 and the nut positioning groove 55; moving from any alignment position of the rotor positioning groove 54 and the nut positioning groove 55 to the next alignment position, the minimum division angle being the minimum angle at which the nut 52 needs to be tightened; manipulating the servo tightening shaft 3 to apply a preset rated torque, and recording the first angle corresponding to the angular alignment position of the pre-training fixture 6; disassembling the pre-training fixture 6 and installing the nut 52 into the second inner stop outer rotation fixture 1. End; Adjust endoscope 13 to the retracted state, and use the assist arm 4 to insert nut 52 into the blind cavity and make it fit against rotor 51; Control the servo tightening shaft 3 to apply the preset minimum torque, and record the second angle corresponding to the angular alignment position of nut 52 at this time; Based on the minimum division angle, the first angle and the second angle, obtain the minimum tightening angle; Control the servo tightening shaft 3 to continue tightening nut 52 to the minimum tightening angle, complete the angular positioning of nut 52, and connect nut 52 to rotor 51; Use the assist arm 4 to move the inner stop external rotation tooling 1. Remove the blind cavity and connect the first end of the mounting device 7 to the second end of the inner stop outer rotation fixture 1. Insert the axial retaining ring 9 and the stop washer 8 radially into the annular space within the elastic baffle 73. Adjust the endoscope 13 to its extended state and use the assist arm 4 to send the mounting device 7 into the blind cavity, aligning the outer stop ear 81 with the nut positioning groove 55 and the inner stop ear 82 with the rotor positioning groove 54. Control the assist arm 4 to feed axially, pushing the stop washer 8 and the axial retaining ring 9 to be installed sequentially at the first end of the nut 52. At this point, it is necessary to determine if the angle of the nut 52 is aligned. If the angle of the nut 52 is not aligned, adjust the appropriate angle compensation in the software according to the actual situation of over-tightening or under-tightening, and repeat the above steps.

[0052] Specifically, the assembly method provided in this embodiment of the invention first uses a pre-training fixture 6 to simulate real working conditions. Utilizing the geometric characteristic that the rotor 51 and the nut positioning groove 55 are coprime in number, the 360° circumference is discretized into several minimum division angles. A standardized first angle reference is obtained through angle sampling under rated torque, fundamentally eliminating measurement errors caused by mechanical clearance and deformation. Secondly, during the actual tightening stage, a second angle is acquired by triggering with the lowest torque, and modulo operations are performed in conjunction with the minimum division angles to accurately calculate the unique minimum tightening angle. The servo tightening shaft 3 automatically performs micro-adjustments, ensuring the pass rate of the angular positioning of the nut 52, completely solving the problems of easy over-tightening, low efficiency, and poor consistency caused by manual adjustment by feel. Finally, the integrated dual-state guidance mechanism of the retractable endoscope 13 and the differential installation device 7 achieve visualized and precise alignment of the locking elements and one-time synchronous pressing in a deep cavity blind-view environment, effectively preventing element detachment, misinstallation, and scratches on parts. This method not only significantly shortens the assembly cycle and reduces the labor intensity and safety risks of workers, but also achieves quality traceability through full-process digital recording. It is applicable to the assembly scenario of aero-engine rotor 51 components with various slot number combinations that meet the coprime condition.

[0053] The assembly method provided by the embodiments of the present invention will be described below through specific examples.

[0054] Assuming the rotor 51 has 7 rotor positioning slots 54 and the nut 52 has 12 nut positioning slots 55, if we want to ensure that one rotor positioning slot 54 and one nut positioning slot 55 are aligned, then there will be 7 × 12 = 84 possible alignment events. These 84 events bisect the 360° of the circumference. Using the formula β = 360° / (7 x 12) = 360° / 84 ≈ 4.286°, we can obtain a minimum division angle β, meaning that there will be an aligned position every other minimum division angle β.

[0055] The alignment position corresponding to tool 6 during preview is also the only one that is determined, denoted as event A. The angle of notch 91 recorded during preview is the first angle. .

[0056] After disassembling the pre-training fixture 6 and installing the nut 52 onto the second end of the inner stop outer rotation fixture 1, adjust the endoscope 13 to the retracted state. Use the assist arm 4 to feed the nut 52 into the blind cavity and make it fit against the rotor 51. Operate the servo tightening shaft 3 to apply the preset minimum torque and record the second angle corresponding to the angular alignment position of the nut 52 at this time. That is, during the actual tightening process, when the detected tightening torque reaches the minimum torque of 1900 N·m, start detecting the encoder value at this time, and record it as the second angle. Second angle This corresponds to any one of the 84 events, denoted as event B.

[0057] There exists a minimum forward rotation angle that transforms event B into a uniquely determined event A, namely the minimum tightening angle θ. Assuming nut 52 rotates n minimum division angles β, any event B can then be transformed into event A. However, it's not actually necessary to rotate n minimum division angles β. Instead, the final tightening angle is obtained by calculating the difference between the two encoder readings, dividing by the minimum division angle β, and taking the remainder θ. When positioning, simply tighten by θ to align the rotor positioning groove 54 and the nut positioning groove 55. The formula for calculating the minimum tightening angle θ is formula (1): (1); in, For minimum tightening angle, From the first angle, For the second angle, It is the smallest division angle. This is to take the remainder of the smallest division angle.

[0058] Taking actual data as an example, the first angle recorded during previewing... The value is 328.408°. During the actual tightening process, when the tightening torque reaches the detection torque of 1900 N·m, the encoder value at this point is measured, which is the second angle. The minimum division angle β is 4.286°. According to formula (1), the minimum tightening angle can be obtained as follows: =4.128°. At this point, simply tighten nut 52 to the final tightening angle to align one rotor positioning groove 54 with one nut positioning groove 55. The calculation of the final tightening angle is programmed in the software and will be automatically calculated when the tightening torque reaches the detection torque, so the entire tightening process is continuous and automatic.

[0059] The structure of the assembly system for assembling the nut 52 into the rotor 51 in the blind cavity is described below.

[0060] The assembly system includes a gearbox 2, the input end of which is connected to a servo tightening shaft 3, and the output end of the gearbox 2 is provided with an inner stop and outer rotation fixture 1. The inner stop and outer rotation fixture 1 includes an outer rotation sleeve 12, the first end of which is connected to the output end of the gearbox 2, and the second end of which is fitted with a nut 52. An inner stop fixture 11 is fitted inside the outer rotation sleeve 12, the first end of which is connected to the gearbox 2, and the second end of which is used to connect to the rotor 51 to restrict the rotation of the rotor 51. An endoscope 13 is provided at the second end of the inner stop fixture 11. Multiple rotor positioning slots 54 are provided on the rotor 51. A boss group corresponding to the multiple rotor positioning slots 54 is provided at the second end of the inner stop fixture 11. The boss group includes a main inner stop boss 115 and multiple inner stop bosses 116. The main inner stop boss 115 is located within the field of view of the endoscope 13, and the endoscope 13 is used to guide the main inner stop boss 115 to align and connect with the rotor positioning slots 54.

[0061] Firstly, it should be noted that in this invention, the nut 52 is used to connect the rotor 51 and the connected component 53. The first end in this invention refers to the end away from the connected component 53 when the assembly system is in the vertical direction, and the second end refers to the end close to the connected component 53 when the assembly system is in the vertical direction.

[0062] Specifically, the endoscope 13 can be a tubular endoscope 13, which has a retracted state and an extended state. In the retracted state, it is used to guide the inner stop boss 116 on the inner stop tool 11 to align and connect with the rotor positioning groove 54 on the rotor 51. In the extended state, it is used to guide the stop washer assembled on the positioning tool to be smoothly installed into the groove of the tightened rotor 51 and nut 52.

[0063] The main inner stop boss 115 serves as a key feature marker, and its position directly reflects the connection status between the inner stop fixture 11 and the rotor 51. By observing the images transmitted back by the endoscope 13, operators or the control system can clearly see whether the main inner stop boss 115 accurately enters the rotor positioning groove 54, thus achieving visually guided assembly. It should be understood that the main inner stop boss 115 is one of the inner stop bosses 116, or it can be a specially designed marking boss, as long as it is within the field of view of the endoscope 13. This embodiment, through the above structure, achieves flexible connection and precise visual alignment of the inner stop fixture 11, laying the foundation for subsequent tightening operations.

[0064] Please see Figure 15 , Figure 15This is a schematic diagram of the assembly positions of the rotor and nut. The assembly system in this embodiment has a slender structure to facilitate insertion into the blind cavity inside the aero-engine. Gearbox 2 is the core component for power transmission and conversion. The input end of gearbox 2 is connected to a power source, namely the servo tightening shaft 3, which can also be an intelligent servo tightening shaft 3. This power source can output precisely controlled speed and torque. Inside gearbox 2, a gear transmission mechanism (such as the meshing of the driving gear 21 and the driven gear 22) is used to reduce speed and increase torque, converting the high speed and low torque of the servo tightening shaft 3 into low speed and high torque suitable for assembling the high-torque nut 52. The output end of gearbox 2 is connected to the internal stop external rotation tooling 1, which is the direct component for performing the assembly action.

[0065] It should be understood that, in this embodiment, "inner stop and outer rotation" means that, in the working state, the inner stop fixture 11 remains stationary to fix the rotor 51 and prevent it from rotating with the nut 52; while the outer rotation sleeve 12 rotates relative to the inner stop fixture 11 to drive the nut 52 to tighten. By combining the inner and outer sleeves and separating the static and dynamic parts, the radial dimension of the fixture is greatly reduced, enabling it to adapt to the narrow space constraints of the blind cavity, while simultaneously achieving independent control and coordinated operation of the two actions of limiting the rotation of the rotor 51 and tightening the nut 52.

[0066] During assembly, the operator or control system can observe the interior of the blind cavity in real time through the endoscope 13, clearly seeing the relative position of the inner stop boss 116 and the rotor positioning groove 54. By adjusting the tooling posture, the inner stop boss 116 is accurately inserted into the rotor positioning groove 54, thereby ensuring that the rotor 51 is reliably fixed. This visual guidance method improves the success rate and safety of assembly.

[0067] Please refer to it again. Figure 9 Please refer to the following: Figure 14 , Figure 9 for Figure 8 A partial sectional view of the spatial structure of the second end of the inner stop tooling; Figure 14 This invention provides an alignment diagram of the inner stop fixture and rotor in an assembly system for locking components of an aero-engine. In some embodiments, the inner stop fixture 11 includes: an inner stop fixture shaft 111, the first end of which is detachably connected to the fixture connection portion 23; a detector fixing ring 113 is arranged around the outer side of the inner stop fixture shaft 111; an inner stop fixture clip 112 is provided at the second end of the inner stop fixture shaft 111; an inner stop spring 1110 is provided between the detector fixing ring 113 and the inner stop fixture clip 112; the inner stop fixture clip 112 is radially slidably connected to the second end of the inner stop fixture shaft 111 via a sliding spline 119; an inner stop boss 116 is provided on the outer side of the second end of the inner stop fixture clip 112; and the inner stop boss 116 corresponds one-to-one with the rotor positioning groove 54.

[0068] Specifically, the first end of the inner stop tooling shaft 111 is detachably connected to the gearbox 2 via bolts or other fasteners, forming a first quick-change tooling. This facilitates the replacement of the corresponding inner stop tooling 11 with different models of rotors 51, improving the versatility of the device. Optionally, the first end of the inner stop tooling shaft 111 has axially evenly distributed threaded holes, and the first end of the tooling connecting part 23 has through holes and countersunk holes that mate with these threaded holes. The inner stop tooling shaft 111 and the tooling connecting part 23 are axially connected via inner stop detachable screws 27, thus ensuring that the inner stop tooling shaft 111 and the tooling connecting part 23 are axially connected but cannot rotate circumferentially.

[0069] During the tightening process, the rotor 51 is subjected to the reaction torque generated by the nut 52 during tightening. This reaction torque is transmitted to the inner stop tooling chuck 112 connected to the rotor 51, and then sequentially to the tooling connection part 23 of the inner stop tooling shaft 111 and the gearbox 2, and finally to the gearbox 2. That is, the inner stop tooling 11 transmits the reaction torque to the gearbox 2, and the reaction torque is ultimately borne by the gearbox 2, so that the rotor 51 remains fixed during the tightening of the nut 52, thereby improving the tightening accuracy and efficiency of the nut 52, and also reducing the difficulty of operation for workers.

[0070] Secondly, the detector retaining ring 113 is fixedly sleeved on the outside of the inner stop tooling shaft 111 for installing the subsequent alignment detector 118. The inner stop tooling clamp 112 is located at the second end of the inner stop tooling shaft 111 and is the component that directly contacts the rotor 51.

[0071] Furthermore, by setting the sliding spline 119, the inner stop tooling chuck 112 can rotate synchronously with the inner stop tooling shaft 111 to transmit torque, and can also slide a certain distance axially. The inner stop spring 1110 is sleeved on the outside of the inner stop tooling shaft 111, located between the detector fixing ring 113 and the inner stop tooling chuck 112. During assembly, when the inner stop tooling chuck 112 contacts the end face of the rotor 51, if there is an axial deviation or the feed is too fast, the inner stop tooling chuck 112 will be subject to axial resistance. At this time, the inner stop spring 1110 is compressed and contracted, and the inner stop tooling chuck 112 slides backward relative to the inner stop tooling shaft 111, thereby achieving flexible limiting and avoiding structural damage caused by hard collision between the inner stop boss 116 and the rotor positioning groove 54. It also provides axial buffer margin for the accurate insertion of the inner stop boss 116 into the rotor positioning groove 54, improving the fault tolerance rate of the assembly.

[0072] Please refer to it again. Figure 9 and Figure 14 Please refer to the following: Figure 16 , Figure 16This is a schematic diagram of the alignment detector in the assembly system for locking components of an aero-engine provided by the present invention. In some embodiments, an observation boss 117 is provided on the outer side of the first end of the inner stop tooling head 112, and a plurality of alignment detectors 118 are evenly distributed on the detector fixing ring 113. The observation boss 117, the alignment detectors 118, and the inner stop boss 116 correspond one-to-one.

[0073] Specifically, the observation boss 117, alignment detector 118, and inner stop boss 116 are arranged in a one-to-one correspondence to observe whether the angular position is qualified after installation. The observation boss 117 and the inner stop boss 116 have a fixed circumferential positional relationship on the inner stop tooling clamp 112, and the alignment detector 118 is fixed on the detector fixing ring 113. When the inner stop tooling clamp 112 rotates or remains stationary, the alignment detector 118 can sense the position of the observation boss 117, as well as the relative position of the outer rotating boss 125 and the inner stop boss 116, thereby indirectly determining the circumferential position of the inner stop boss 116. In other words, this correspondence provides a detection basis for subsequent determination of whether the nut positioning groove 55 and the rotor positioning groove 54 are aligned. In specific implementation, the alignment detector 118 can be a proximity switch, photoelectric sensor, or Hall sensor capable of detecting the position of the boss, and its number is consistent with the number of observation bosses 117, evenly distributed along the circumference to improve the reliability of detection.

[0074] Please refer to it again. Figure 9 , Figure 14 and Figure 16 In some embodiments, an endoscope holder 114 is provided at the second end of the inner stop tooling shaft 111, and the inner stop tooling clip 112 has a round cap-shaped structure and surrounds the endoscope holder 114; the endoscope holder 114 is provided with a first through hole, and the inner stop tooling shaft 111 is provided with a through second through hole in the axial direction, the diameter of the first through hole is smaller than the diameter of the second through hole, and the endoscope 13 is inserted into the first through hole and the second through hole; the inner stop tooling clip 112 is provided with a hollow structure, and a main inner stop boss 115 is provided at the hollow structure.

[0075] Specifically, the endoscope holder 114 is used to secure the lens end of the endoscope 13, preventing it from shaking during operation. The first through hole has a smaller diameter and serves as a limit, while the second through hole has a larger diameter, providing a passage for the endoscope 13's cables. This hollow arrangement cleverly utilizes the internal space of the inner stop tooling shaft 111, avoiding potential entanglement or wear problems that might occur with exposed cables.

[0076] The openwork structure provides an observation window for the endoscope 13. The main inner stop boss 115 serves as a key feature marker, and its position directly reflects the connection between the inner stop fixture 11 and the rotor 51. By observing the images transmitted back by the endoscope 13, the operator or control system can clearly see whether the main inner stop boss 115 is accurately inserted into the rotor positioning groove 54, thereby achieving visually guided assembly. It should be understood that the main inner stop boss 115 is one of the inner stop bosses 116, or it can be a specially designed marking boss, as long as it is within the field of view of the endoscope 13. This embodiment achieves flexible connection and precise visual alignment of the inner stop fixture 11 through the above structure, laying the foundation for subsequent tightening operations.

[0077] Optionally, the inner stop tooling head 112 has a round cap-shaped structure, and the outer side of the second end of the inner stop tooling head 112 is chamfered to improve the smoothness of installation.

[0078] Please refer to the following: Figure 10 , Figure 13 and Figure 14 , Figure 10 yes Figure 8 Schematic diagram of the cross-sectional spatial structure of the inner and outer rotating sleeve; Figure 13 This is a diagram showing the alignment of the outer sleeve and nut in the assembly system for locking components of an aero-engine provided by the present invention. Figure 14 This invention provides an alignment diagram of the outer rotating sleeve and nut in an assembly system for locking elements of an aero-engine. In some embodiments, the outer rotating sleeve 12 includes a tightening sleeve 121 and a tightening shaft 122. The first end of the tightening shaft 122 is detachably connected to the gearbox 2, and the second end of the tightening shaft 122 is radially slidably connected to the first end of the tightening sleeve 121 via a spline. Multiple outer rotating bosses 125 are axially distributed on the inner side of the second end of the tightening sleeve 121, and a nut positioning groove 55 is provided on the nut 52. The outer rotating bosses 125 and the nut positioning groove 55 correspond one-to-one. The second end of the tightening sleeve 121 has an annular groove in which a rubber ring 124 is installed. A sleeve retaining ring 128 is provided at the first end of the tightening sleeve 121, and a spring retaining ring 129 is sleeved on the outer side of the tightening shaft 122. An outer rotating spring 123 is provided between the sleeve retaining ring 128 and the spring retaining ring 129.

[0079] Specifically, the outer rotating sleeve 12 adopts a split structure design, consisting of a tightening sleeve 121 and a tightening shaft 122, rather than an integrated structure. This allows for the addition of an outer rotating spring 123, making the outer rotating sleeve 12 an elastic structure. This provides elastic expansion and contraction during the tightening process while avoiding rigid collisions between the tool and the parts. Furthermore, the two-section design better utilizes the strength advantages of the material.

[0080] The first end of the tightening shaft 122 and the output end (driven wheel 22) of the gearbox 2 are connected by an externally detachable screw 1211, forming a second quick-change tooling. This invention, through the first and second quick-change toolings, allows for the rapid replacement of the inner-stop external-rotation tooling 1 suitable for tightening nuts 52 in different sizes and scenarios. This enables the tightening and installation of nuts 52 in different models or positions of aero-engines and other fields, thus improving the applicability of this invention.

[0081] Optionally, the first end of the outer rotating sleeve 12 has axially distributed through holes, and the second end of the driven wheel 22 has a screw hole that mates with the through holes. The outer rotating sleeve 12 and the driven wheel 22 are axially connected by an externally detachable screw 1211, so that the outer rotating sleeve 12 and the driven wheel 22 are axially connected but circumferentially non-rotatable. Power is transmitted to the outer rotating sleeve 12 via the driven wheel 22.

[0082] Secondly, the second end of the tightening shaft 122 and the first end of the tightening sleeve 121 are provided with mutually cooperating triangular splines 126, which are radially slidingly connected. During operation, the servo tightening shaft 3 transmits power to the input end of the gearbox 2, then to the tightening shaft 122 through the output end of the gearbox 2, then to the tightening sleeve 121 through the triangular spline 126, and finally to the nut 52 for tightening through the outer rotating boss 125. The triangular spline 126 is the preferred solution, with high centering accuracy and load-bearing capacity, which can ensure the transmission of large torque between the tightening shaft 122 and the tightening sleeve 121 while allowing relative sliding between them in the axial direction. The outer rotating boss 125 is used to install the nut 52, thereby indirectly determining the relative position of the nut positioning groove 55 and the rotor positioning groove 54.

[0083] Furthermore, to prevent the nut 52 from falling off due to gravity or shaking during insertion into the blind cavity, a rubber ring 124 is provided in this embodiment. The rubber ring 124 is elastic and can generate a radial clamping force on the nut 52, thereby pre-fixing the nut 52 and ensuring that the nut 52 is stably assembled in the tightening sleeve 121 in the untightened state, avoiding the risk that the nut 52 will fall deep into the blind cavity and be difficult to remove.

[0084] Furthermore, to further achieve flexible feeding, this embodiment also includes an external rotation spring 123. During the tightening process, as the nut 52 gradually screws into the rotor 51, the nut 52 will experience axial resistance. At this time, the external rotation spring 123 is compressed and deformed, and the tightening sleeve 121 slides backward relative to the tightening shaft 122, thereby providing feed compensation, effectively absorbing axial errors, and preventing the nut 52 from hardly colliding with the end face of the rotor 51 due to excessive feed or axial dimensional deviation, thus protecting the threaded connection structure 5 and the tooling itself.

[0085] Please refer to it again. Figure 10 In some embodiments, both the tightening sleeve 121 and the tightening shaft 122 are hollow structures. The first end of the tightening shaft 122 is provided with an inner support bearing 1210, and the second end of the tightening shaft 122 is provided with an outer support bearing 127.

[0086] Specifically, the hollow structure reduces the overall weight of the tooling while providing installation space and a movement channel for the inner stop tooling 11. Since the inner stop tooling 11 needs to pass through the interior of the outer rotating sleeve 12 to connect with the rotor 51, the hollow structure enables the reuse of space between the inner and outer tooling, greatly compressing the radial dimensions of the device and allowing it to adapt to narrow blind cavity environments.

[0087] Secondly, the inner support bearing 1210 and the outer support bearing 127 are respectively supported at both ends of the hollow structure of the tightening shaft 122, playing a supporting and guiding role, reducing the friction and wear between the inner stop tool 11 and the outer rotating sleeve 12, and ensuring the stability of the relative movement of the inner and outer components during the high torque tightening process.

[0088] Please refer again. Figure 9 , Figure 10 and Figure 3 Please refer to the following: Figure 17 , Figure 17 The diagram shows a comparison of the inner stop boss and the outer rotating boss before and after adjustment in the assembly system for the locking element of an aero-engine provided by the present invention. In some embodiments, the number of nut positioning grooves 55 and rotor positioning grooves 54 are coprime, and the number of inner stop bosses 116 and outer rotating bosses 125 are coprime.

[0089] Specifically, the number of nut positioning slots 55 and rotor positioning slots 54 are coprime, corresponding to the number of inner stop bosses 116 and outer rotating bosses 125 being coprime. After successful installation, only one of the multiple alignment detectors 118 should observe that the angles of the observation bosses 117 and 125 are aligned. During operation, the wiring of the alignment detectors 118 is routed through the hollow structure at the center of the inner stop tooling shaft 111 to the vision display screen 262. The image recognition software built into the vision display screen 262 automatically identifies the image with the smallest angular deviation observed by the multiple alignment detectors 118 and calculates the minimum angle to be tightened accordingly.

[0090] It should be understood that the term "coprime" in this embodiment refers to two integers whose greatest common divisor is 1, meaning they have no common divisor other than 1. This quantitative relationship is not arbitrary, but is designed to solve the technical problems of difficult alignment and easy over-tightening during the assembly of the high-torque nut 52.

[0091] In the assembly of low-pressure turbine shafts for aero-engines, after tightening nut 52, it is necessary not only to reach the preset lower limit of preload but also to meet the process requirement of aligning nut positioning groove 55 with rotor positioning groove 54 in order to install locking elements such as retaining washers. If the number of nut positioning grooves 55 and rotor positioning grooves 54 is the same or they have a common divisor, multiple alignment positions will appear in the circumferential direction, with a large angular interval between adjacent alignment positions. When nut 52 is tightened to the lower limit of preload, if it is not aligned, it may be necessary to continue tightening by a larger angle to reach the next alignment position. Due to the characteristics of threaded connections, continuing to tighten by a large angle under high torque can easily lead to a sharp increase in preload, exceeding the upper limit of preload, causing thread damage or connection failure.

[0092] In this embodiment, by setting the number of nut positioning slots 55 and rotor positioning slots 54 to be coprime, according to the principle of number theory, within a 360-degree radius, there must exist one and only one position where the positioning slots of the two are perfectly aligned. More importantly, this coprime design significantly reduces the maximum tightening angle required to reach the closest alignment position at any initial angle. That is, when the servo tightening shaft 3 controls the nut 52 to reach the lower limit of the preload force, even if they are not aligned, for example... Figure 17 In part (a), simply tightening by a small angle is sufficient to meet the alignment requirements. Figure 17 (b) In this case, because the additional tightening angle is small, the resulting additional preload is also within a controllable range, thus effectively avoiding the problem of torque exceeding the limit due to the pursuit of alignment. Similarly, the number of inner stop bosses 116 and outer rotating bosses 125 is also set to be coprime, and the principle is the same as above, ensuring that the detector can accurately capture the unique alignment position and avoid misjudgment caused by multiple solutions.

[0093] Please refer to it again. Figure 1 , Figure 8 and Figure 12 , Figure 12 A horizontal attitude diagram of the assembly system for locking elements of an aero-engine provided by the present invention; in some embodiments, the assembly system includes: a booster arm 4; a hoisting module 26, including a boom 261 and a display screen 262 disposed on the boom 261; a first end of the boom 261 is connected to the booster arm 4; a first end of the tooling connection part 23 is provided with a control handle 24 and an attitude switching slide 25, and a second end of the boom 261 is disposed in the attitude switching slide 25.

[0094] Specifically, the assist arm 4 can be a mechanical assist arm 4, a pneumatic balancer or an electric hoist, or other equipment with load balancing and movement functions. Its function is to counteract most of the gravity of the assembly system, so that operators can easily move and position the assembly system in three-dimensional space.

[0095] The boom 261, acting as a bridge connecting the assembly system and the auxiliary arm 4, has a lifting point at its first end, which connects to the auxiliary arm 4 via a quick connector. A posture switching groove 25 is formed on the tooling connection part 23. The second end of the boom 261 is installed within the posture switching groove 25 via a pin or slider, and can slide or be fixed in different positions within the groove. Thus, the operator can adjust the angle and posture of the assembly system relative to the boom 261 according to the space constraints and operating habits of the assembly site; for example, adjusting the assembly system to... Figure 8 The vertical position shown, or Figure 12 The horizontal posture shown.

[0096] The display screen 262 installed on the boom 261 is used to display in real time the images inside the blind cavity collected by the endoscope 13, the real-time torque value fed back by the torque sensor, the rotation angle fed back by the angle sensor, and the detection results of the alignment detector 118. It displays whether the main inner stop boss 115 has entered the rotor positioning groove 54 on the rotor 51, and whether the outer rotating boss 125 is aligned with the observation boss 117 at a unique position. This realizes the visualization of the assembly process and helps the operator to intuitively judge the assembly status.

[0097] The control handle 24 is mounted on the side of the tooling connection part 23 for easy gripping by the operator. The control handle 24 integrates control buttons for controlling the forward rotation, reverse rotation, start, and stop actions of the servo tightening shaft 3, enabling the operator to precisely control the assembly actions.

[0098] In some embodiments, the assembly system of the present invention may further include a torque monitoring unit and an angle monitoring unit (alignment detector 118).

[0099] A torque monitoring unit is located at the connection between the gearbox 2 and the outer sleeve 12. It is used to monitor the input torque of the servo tightening shaft 3 to preliminarily determine whether the preload of the threaded connection structure 5 has reached the preset lower limit or exceeded the preset upper limit. For example, through software monitoring, an alarm will be triggered if the torque is below the lower limit or exceeds the upper limit.

[0100] An angle monitoring unit is set in the gap between the outer rotating sleeve 12 and the inner stop tool 11. When the result of the torque monitoring unit reaches the lower limit of the preload, the alignment detector 118 is used to observe whether the outer rotating boss 125 is aligned with the observation boss 117. If they are not aligned, the field of view of the alignment detector 118 with the smallest tightening angle needs to be found, the minimum angle is calculated and tightened, and the angle monitoring unit is used to determine whether the minimum angle has been reached.

[0101] Thus, by setting up a torque monitoring unit to ensure that the preload reaches the lower limit during tightening, and by setting up an angle monitoring unit to ensure that the preload does not exceed the upper limit during subsequent tightening, the tightening stability is controlled, reducing the risk of repeated disassembly due to insufficient preload. The torque and angle monitoring units may include a torque sensor, an angle sensor, and a corresponding display device.

[0102] The following describes the assembly method of the present invention for assembling the nut 52 into the rotor 51 in the blind cavity, including the following steps S1 to S6.

[0103] Step S1: According to the preset posture, switch the position of the second end of the boom 261 in the posture switching slide 25, connect the first end of the boom 261 to the assist arm 4, and control the assist arm 4 to move the assembly system to the preset installation position.

[0104] Specifically, due to the complex internal structure of aero engines and the varying orientations of blind cavity openings, the assembly system requires attitude adjustment capabilities. Operators determine the preset attitude based on the site conditions and adjust the overall tilt angle or direction of the assembly system by changing the orientation of the second end of the boom 261 within the tooling connection 23 and the installation position in the slide 25. After adjustment, the lifting point at the first end of the boom 261 is connected to the auxiliary arm 4 (such as a robotic arm or pneumatic lifting device) in the workshop. The auxiliary arm 4 counteracts most of the device's weight, and operators control its movement via the handle 24, precisely moving the inner stop and outer rotation tooling 1 to the preset installation position at the blind cavity opening, preparing for subsequent insertion into the blind cavity.

[0105] Step S2: Install nut 52 onto outer rotating boss 125 of outer rotating sleeve 12, and operate assist arm 4 to extend inner stop outer rotating fixture 1 into blind cavity.

[0106] Specifically, before the assembly system enters the blind cavity, the nut 52 to be assembled must be pre-installed on the inner stop-outer rotation fixture 1. The operator places the nut 52 into the second end of the outer rotation sleeve 12, so that the nut positioning groove 55 on the nut 52 engages one-to-one with the outer rotation boss 125 on the inner side of the tightening sleeve 121, achieving circumferential positioning. At the same time, the rubber ring 124 at the second end of the tightening sleeve 121 holds the outer wall of the nut 52 under elastic action, preventing the nut 52 from falling off during movement. Subsequently, the operating assist arm 4 is slowly advanced, so that the inner stop-outer rotation fixture 1 extends axially into the blind cavity inside the engine until the second end of the inner stop fixture 11 approaches the shaft end of the rotor 51.

[0107] Step S3: Align and connect the main inner stop boss 115 with the rotor positioning groove 54 using the endoscope 13.

[0108] Specifically, due to the obstructed view within the blind cavity, the operator cannot directly observe the internal situation. At this time, the endoscope 13 at the second end of the inner stop fixture 11 is activated, and the image from the endoscope 13 is transmitted in real time to the display screen 262 on the boom 261. The operator observes the image on the display screen 262 to locate the rotor positioning groove 54 on the end face of the rotor 51. Because the inner stop fixture clamp 112 has a hollow structure, the main inner stop boss 115 is located within the field of view of the endoscope 13, allowing the operator to clearly see the relative position of the main inner stop boss 115 and the rotor positioning groove 54. By fine-tuning the posture of the assist arm 4, the main inner stop boss 115 is aligned with the rotor positioning groove 54, and the inner stop fixture 11 is slowly advanced, allowing the inner stop boss 116 to insert into the rotor positioning groove 54. At this point, the inner stop fixture 11 and the rotor 51 are relatively fixed in the circumferential direction, restricting the rotational freedom of the rotor 51 and providing a counter-torque support for the subsequent tightening of the nut 52. During this process, the flexible connection mechanism of the inner stop spring 1110 and the sliding spline 119 can buffer the impact of axial feed and prevent hard impact damage to the rotor 51 or tooling.

[0109] In step S4, the servo tightening shaft 3 drives the nut 52 to rotate until the nut 52 and the rotor 51 reach the preset lower limit of the preload force.

[0110] Specifically, after the inner stop fixture 11 is connected to the rotor 51, the servo tightening shaft 3 is activated. The servo tightening shaft 3 reduces speed and increases torque through the gearbox 2, driving the outer rotating sleeve 12 to rotate. The outer rotating sleeve 12 drives the nut 52 to rotate through the outer rotating boss 125, and the nut 52 is screwed into the shaft end of the rotor 51 under the action of the thread. The servo tightening shaft 3 has a built-in torque sensor to monitor the tightening torque in real time. When the torque reaches the preset lower limit of the preload, the servo tightening shaft 3 stops rotating. It should be understood that the preset lower limit of the preload is the minimum preload value set according to design requirements to ensure the reliability of the connection. At this time, the nut 52 has been initially tightened, but the final assembly requirement of aligning the nut positioning groove 55 with the rotor positioning groove 54 may not yet be met, and further steps are needed for judgment.

[0111] Step S5: The alignment detector 118 checks whether the alignment condition is met. The alignment condition is that one of the multiple external rotating bosses 125 is uniquely aligned with one of the multiple observation bosses 117.

[0112] Specifically, since the number of nut positioning slots 55 and rotor positioning slots 54 are coprime, according to the principle of number theory, there must exist a unique alignment position in the circumferential direction. To detect whether this alignment position exists, this embodiment uses alignment detectors 118 for judgment. Multiple alignment detectors 118 (such as proximity switches or photoelectric sensors) on the detector fixing ring 113 monitor the positions of multiple observation bosses 117 on the inner stop tooling clamp 112 in real time. Since the observation bosses 117 correspond one-to-one with the inner stop bosses 116, and the inner stop bosses 116 are connected to the rotor positioning slots 54, the position of the observation bosses 117 reflects the position of the rotor positioning slots 54. Simultaneously, the outer rotating bosses 125 correspond one-to-one with the nut positioning slots 55, and their positions reflect the position of the nut 52. Alignment is determined to be satisfied if and only if one of the outer rotating bosses 125 and one of the observation bosses 117 completely coincide in the circumferential direction, i.e., the nut positioning slots 55 and rotor positioning slots 54 are aligned. If the detector does not detect the alignment signal, it means that although nut 52 has reached the lower limit of preload, the angle position is not aligned and the stop washer cannot be installed.

[0113] In step S6, if the alignment conditions are not met, the servo tightening shaft 3 continues to drive the nut 52 to rotate until the alignment conditions are met.

[0114] Specifically, if step S5 determines that the alignment condition is not met, the control system controls the servo tightening shaft 3 to continue rotating. Due to the characteristics of the coprime design, the maximum supplementary tightening angle is limited to a small range, so only a small rotation is needed to find the unique alignment position. The servo tightening shaft 3 rotates slowly, and the alignment detector 118 continuously scans. Once it detects that the outer rotating boss 125 is uniquely aligned with the observation boss 117, the servo tightening shaft 3 immediately stops. At this time, the nut 52 meets both the lower limit requirement of preload and achieves angular alignment, completing a high-quality assembly. Because the supplementary tightening angle is extremely small, the resulting additional preload is extremely small and will not cause the preload to exceed the upper limit, thus avoiding the risk of over-tightening. Finally, the operator controls the auxiliary arm 4 to exit the fixture, install locking components such as the stop washer and axial retaining ring, and complete the entire assembly process.

[0115] In summary, when the nut 52 is tightened onto the rotor 51 using the assembly system and method of the present invention, the main inner stop boss 115 on the inner stop tooling 11 is guided by the endoscope 13 to align and connect with the rotor positioning groove 54 on the rotor 51. Multiple alignment detectors 118 are used to indirectly observe and guide the alignment of the nut positioning groove 55 and the rotor positioning groove 54 after the lower limit of the preload is met. Combined with the function of the assist arm 4 and the intelligent servo tightening shaft 3, and with the assistance of the operating handle 24 and the display screen 262, the visual, high-precision, high-efficiency, and automated tightening of the aircraft engine nut 52 is achieved. It is suitable for tightening the high-torque nut 52 in the blind cavity. The tightening device is equipped with torque and angle sensors. Combined with the guidance and feedback from the tubular endoscope 13 and alignment detector 118, it can effectively monitor whether problems occur during the tightening process, such as insufficient or excessive torque, thread seizing, unsuccessful connection between the inner stop boss 116 and the rotor positioning groove 54, or misalignment of the nut positioning groove 55 and the rotor positioning groove 54. This ensures the quality and accuracy of tightening, improves the repeatability between multiple tightening operations, and enhances the stability of tightening. This assembly system and method, working together, can achieve the tightening assembly goal in one go, avoiding preload errors caused by subsequent tedious adjustments and the dangers of tools hitting parts in the blind cavity. This not only facilitates worker operation but also improves assembly accuracy and safety.

[0116] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0117] The embodiments described above are merely illustrative of several implementations of the present invention, and while the descriptions are specific and detailed, they should not be construed as limiting the scope of the present invention. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these modifications and improvements all fall within the scope of protection of the present invention. Therefore, the scope of protection of this patent should be determined by the appended claims.

Claims

1. An assembly system for locking elements of an aircraft engine, for installing an axial retaining ring (9) and a locking washer (8) at the connection between an aircraft engine shaft-end rotor (51) and a nut (52), characterized in that, include: Assist arm (4); The inner stop and outer rotation tool (1) is connected at its first end to the assist arm (4); The first end of the pre-training fixture (6) is detachably connected to the second end of the inner stop and outer rotation fixture (1); the first end of the pre-training fixture (6) is provided with a first simulation structure and a second simulation structure, the first simulation structure is the same as the first end structure of the rotor (51), and the second simulation structure is the same as the first end structure of the nut (52). The first end of the mounting device (7) is detachably connected to the second end of the inner stop outer rotation tooling (1); the second end of the mounting device (7) is provided with a plurality of elastic baffles (73) along the axial direction, and the plurality of elastic baffles (73) surround and clamp the mounting axial retaining ring (9) and the stop washer (8); the outer peripheral surface of the first end of the stop washer (8) is provided with a plurality of outer stop ears (81), and the second end of the stop washer (8) is provided with a plurality of inner stop ears (82); An endoscope (13) is provided at the second end of the inner stop and outer rotation tool (1). The endoscope (13) is used to guide the outer stop ear (81) to connect with the nut positioning groove (55) and the inner stop ear (82) to connect with the rotor positioning groove (54).

2. The assembly system for locking elements of an aircraft engine according to claim 1, characterized in that, The first end of the pre-training fixture (6) is provided with an inner ring (61) and an outer ring (62). The first simulation structure includes a plurality of inner ring grooves (611) provided on the inner ring (61), and the inner ring grooves (611) correspond one-to-one with the rotor positioning grooves (54) on the rotor (51). The second simulation structure includes a plurality of outer ring grooves (621) provided on the outer ring (62), and the outer ring grooves (621) correspond one-to-one with the nut positioning grooves (55) on the nut (52).

3. The assembly system for locking elements of an aircraft engine according to claim 1, characterized in that, The mounting device (7) includes: The outer retaining ring fixture (71) is connected to the second end of the inner stop outer rotation fixture (1). The second end of the outer retaining ring fixture (71) is provided with a plurality of outer retaining bosses (78). The outer retaining bosses (78) correspond one-to-one with the bosses of the nut (52). At least one of the outer retaining bosses (78) is provided with a shim (74) at its second end. At least two of the outer retaining bosses (78) are provided with elastic baffles (73) on their inner circumferential surfaces. The inner retaining ring fixture (72) is connected to the second end of the inner stop outer rotation fixture (1), and the outer retaining ring fixture (71) surrounds the inner retaining ring fixture (72) in annular shape. The inner retaining ring fixture (72) can slide axially along the inner wall of the outer retaining ring fixture (71).

4. The assembly system for locking elements of an aircraft engine according to claim 3, characterized in that, The plurality of the outer stop bosses (78) include a mounting boss (781) and a reserved boss (782). The mounting boss (781) is provided with the shim block (74) and the elastic baffle (73), and the reserved boss (782) is provided with the outer stop ear (81).

5. The assembly system for locking elements of an aircraft engine according to claim 3, characterized in that, The outer retaining ring fixture (71) is connected to the second end of the inner stop external rotation fixture (1) by an outer retaining screw (75), the inner retaining ring fixture (72) is connected to the second end of the inner stop external rotation fixture (1) by an inner retaining screw (76), and the elastic baffle (73) is fixed to the inner circumferential surface of the outer retaining boss (78) by a baffle screw (77).

6. The assembly system for locking elements of an aircraft engine according to claim 3, characterized in that, The inner retaining ring fixture (72) is provided with a through clearance groove (721), and the endoscope (13) is inserted in the clearance groove (721). The endoscope (13) includes a light source.

7. The assembly system for locking elements of an aircraft engine according to claim 1, characterized in that, The endoscope (13) has a retracted state and an extended state; The second end of the inner stop and outer rotation tooling (1) is provided with a plurality of inner stop bosses (116) along the circumferential direction, and the inner stop bosses (116) correspond one-to-one with the rotor positioning grooves (54); In the retracted state, the endoscope (13) is used to guide the inner stop boss (116) to align and connect with the rotor positioning groove (54); in the extended state, the endoscope (13) is used to guide the outer stop ear (81) to connect with the nut positioning groove (55), and the inner stop ear (82) to connect with the rotor positioning groove (54).

8. The assembly system for locking elements of an aircraft engine according to claim 1, characterized in that, The axial retaining ring (9) is provided with a notch (91), and both ends of the notch (91) are provided with through holes (92).

9. The assembly system for locking elements of an aircraft engine according to claim 1, characterized in that, The system includes a gearbox (2) connected to the assist arm (4), the input end of the gearbox (2) is connected to the servo tightening shaft (3), and the output end of the gearbox (2) is provided with the inner stop and outer rotation tooling (1).

10. An assembly method for a locking element in an aircraft engine, characterized in that, An assembly system for locking elements of an aero-engine as described in any one of claims 1 to 9 is used to install an axial retaining ring (9) and a locking washer (8) at the connection between the rotor (51) and the nut (52) at the shaft end of the aero-engine, the assembly method comprising: Align and connect the inner ring groove (611) of the pre-training fixture (6) with the inner stop boss (116) of the inner stop outer rotation fixture (1), and adjust the position of the outer rotation boss (125) of the inner stop outer rotation fixture (1) by means of the servo tightening shaft (3) until the outer rotation boss (125) is inserted into the outer ring groove (621) of the pre-training fixture (6); Based on the number of times the rotor positioning groove (54) and the nut positioning groove (55) are aligned at all angles, the minimum division angle is obtained; from any alignment position of the rotor positioning groove (54) and the nut positioning groove (55) to the next alignment position, the minimum division angle is the minimum angle at which the nut (52) needs to be tightened; The servo tightening shaft (3) is manipulated to apply a preset rated torque, and the first angle corresponding to the angle alignment position of the pre-training fixture (6) is recorded. Disassemble the pre-training fixture (6) and install the nut (52) to the second end of the inner stop outer rotation fixture (1); Adjust the endoscope (13) to the retracted state, and use the assist arm (4) to send the nut (52) into the blind cavity and make it fit against the rotor (51); The servo tightening shaft (3) is manipulated to apply a preset minimum torque, and the second angle corresponding to the angular alignment position of the nut (52) at this time is recorded; Based on the minimum division angle, the first angle, and the second angle, the minimum tightening angle is obtained; The servo tightening shaft (3) is manipulated to continue tightening the nut (52) to the minimum tightening angle, thereby completing the angular positioning of the nut (52) and connecting the nut (52) to the rotor (51). The inner stop and outer rotation tool (1) is moved out of the blind cavity by the assist arm (4), the first end of the mounting device (7) is connected to the second end of the inner stop and outer rotation tool (1), and the axial retaining ring (9) and the stop washer (8) are sequentially inserted into the annular space of the elastic baffle (73) in the radial direction. The endoscope (13) is adjusted to the extended state, and the installation device (7) is sent into the blind cavity by the assist arm (4) so ​​that the outer stop ear (81) is aligned with the nut positioning groove (55) and the inner stop ear (82) is aligned with the rotor positioning groove (54). The control arm (4) feeds axially, pushing the stop washer (8) and the axial retaining ring (9) to be installed sequentially at the first end of the nut (52).

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