Aeroengine rotor connection apparatus and method

Abstract

The application relates to an aero-engine rotor connecting device and method, which comprises a transfer guide rail, a rotor positioning device, a first pressing device, a transfer tool, a second pressing device and a tightening device. The first pressing device is used for realizing the butt joint of a rotor second-stage disc and a third-stage disc, the second pressing device is used for realizing the butt joint of the rotor third-stage disc and a drum, and the tightening device is used for realizing the bolt tightening at a blind cavity of the third-stage disc. The application further provides an aero-engine rotor connecting method. The application can realize the automation and visualization of the rotor connection, improve the connection quality and assembly efficiency of the aero-engine rotor, and reduce the labor cost.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, and specifically to an aero-engine rotor connection device and method. Background Technology

[0002] The rotor is a core component of an aero-engine, and its assembly quality is crucial to the engine's performance. Because aero-engine rotors operate in environments characterized by high temperature, high pressure, and high speed, problems such as excessive concentricity deviations and uneven bolt preload in rotor assembly directly impact the overall engine's performance parameters and operating efficiency.

[0003] Aero-engine rotor assemblies are often composed of multiple disk-like parts. The connection structure between rotor stages is in the form of "stop-bolt," and the connection process includes stop fitting and bolt tightening. The stop fitting is an interference fit, which achieves the centering function of the rotor. Stop fitting is often performed by temperature difference method (hot fitting / cold fitting). However, because the stop fitting surface of the rotor will deform under temperature changes, manual assembly of the stop fitting will result in insufficient contact of the stop fitting surface due to deformation, thus causing deviation in the coaxiality of the rotor assembly. Bolt tightening achieves the axial tension effect on the rotor, but due to the compact internal structure of the rotor and the inaccessibility by visual inspection, manual tightening is inefficient and results in poor assembly quality. Summary of the Invention

[0004] In view of the above problems, the present invention provides an aero-engine rotor connection device and method, which solves the problem of low efficiency of manual operation in the connection process of aero-engine rotors in the prior art, and improves the assembly efficiency and assembly quality of aero-engine rotors.

[0005] On one hand, the present invention provides an aircraft engine rotor connection device, comprising:

[0006] 1. Base, 2. Transfer guide rail, 3. Rotor positioning device, 4. First clamping device, 6. Transfer fixture, 12. Second clamping device, and 13. Tightening device;

[0007] Preferably, the connecting device further includes a lifting device 7, a frame 8, and a control system 10;

[0008] Preferably, the transfer guide rail 2 and the second clamping device 12 are connected to the upper surface of the base 1; the transfer guide rail 2 is fixedly connected to the middle position of the upper surface of the base 1; and the tightening device 13 is connected to the upper surface of the second clamping device.

[0009] The lower part of the rotor positioning device 3 is connected to the transfer guide rail 2 via a slide rail; the upper part of the rotor positioning device is connected to the first and second stage disk assembly 51 of the rotor 5; the lower outer ring of the rotor positioning device 3 is connected to the lower part of the first pressing device 4.

[0010] The second clamping device 12 is connected to one side of the upper part of the base; the tightening device 13 is located on the same side as the second clamping device;

[0011] The frame 8 is a four-column structure; the frame is used to connect the lifting device 7 and the control system 10 respectively.

[0012] The upper part of the lifting device is connected to the upper part of the frame via a slide rail 2, allowing it to slide forward, backward, left, and right; the lower part of the lifting device is connected to the adapter 6; the lifting device is located above the first clamping device.

[0013] The control system 10 is used to control each movable device.

[0014] Furthermore, the control system includes a display that can rotate circumferentially for easy operation by staff.

[0015] Furthermore, the rotor positioning device 3 includes a base 31, a limiting mechanism, a motor 33, and a rotor support platform 34; the limiting mechanism includes a first limiting member 32, a second limiting member, and a third limiting member.

[0016] Limiting member 1 32, limiting member 2 and limiting member 3 are evenly arranged circumferentially on the base 31, and the upper part of the limiting mechanism is connected to the rotor support platform 34.

[0017] The limiting mechanism is used to fix or release the lower part of the rotor 5 to be assembled. Each limiting component is connected to a corresponding rotor positioning motor for driving, such as... Figure 2 .

[0018] Furthermore, the first pressing device 4 includes a first support base 41 and a plurality of pressing units; the plurality of pressing units are evenly arranged on the corners of the first support base 41;

[0019] There are four clamping units;

[0020] Each clamping unit includes a motor support 42, a servo push cylinder 43, a first clamping motor 44, and a first clamping mechanism 45;

[0021] The first clamping mechanism 45 includes a clamping member and a clamping push rod; the outer side of the clamping member is connected to the clamping push rod; the lower part of the clamping member is connected to the upper part of the motor support base;

[0022] The lower part of the pressing push rod is connected to the upper part of the first pressing motor 44 and the servo push cylinder 43;

[0023] The inner side of the servo push cylinder 43 is connected to the outer side of the motor support base;

[0024] The first pressing mechanism 45 moves back and forth and up and down under the drive of the servo push cylinder 43 and the first pressing motor 44;

[0025] The first clamping device 4 is used to clamp the third-stage disc 52 of the rotor 5 with the first- and second-stage disc assembly 51, achieving a stop fit; such as Figure 3 and Figure 8 As shown.

[0026] Furthermore, the second pressing device 12 includes a second support base 121, a second pressing motor 122, a second pressing mechanism 123, a guide column 124, and a sensor 125;

[0027] The second support base 121 includes a first support surface, a second support surface, and a third support surface;

[0028] The bottoms of the second clamping motor 122 and the guide column 124 respectively penetrate the second support surface and connect to the upper part of the second clamping mechanism 123. The sensor 125 is connected to the lower part of the second clamping mechanism 123, and the lower surface of the sensor is connected to the rotor. Figure 4 As shown.

[0029] Furthermore, the tightening device 13 includes a third support base 131, a guide rail 132, a lifting motor 133, a tightening arm 134, a drive mechanism 135, and a tightening gun 136.

[0030] The third support 131 is connected to the upper surface of the second clamping device; the drive mechanism is connected to the side of the third support; the tightening arm 134 is located at the lower part of the drive mechanism, and the tightening gun 136 is connected to the upper part of the drive mechanism; the second clamping mechanism 123 has a hole through which the tightening arm 134 passes.

[0031] The lifting motor 133 is connected to the upper part of the third support base 131; the guide rail 132 is connected to the other side of the third support base 131.

[0032] The tightening device is an automatic tightening device for blind cavity nuts.

[0033] Furthermore, the adapter 6 includes multiple locking units and multiple quick-locking devices; the adapter includes locking unit one, locking unit two, quick-locking device one 61 and quick-locking device two; locking unit one and locking unit two are symmetrically distributed; quick-locking device one and quick-locking device two are symmetrically distributed;

[0034] The quick-locking device 61 is mounted on the adapter 62 and is used to cooperate with the lifting device 7; the locking unit is used to lock the adapter 6 onto the drum 53 of the rotor 5.

[0035] The locking unit includes a locking pin 63, a locking disc 64, a locking seat 65, a rotating shaft 66, and a handle 67; the lower part of the locking seat is connected to the adapter seat 62, and the rear part of the locking seat is connected to the handle 67.

[0036] The locking disc 64 is disposed inside the locking seat; the rotating shaft 66 passes through the locking seat and its lower part is connected to the locking disc; the locking pin 63 is connected to the locking disc 64.

[0037] Furthermore, the adapter 62 is a hollow concave structure, including a frustum one and a frustum two;

[0038] The locking pin 63 includes a connecting plate 631 and a connecting post 632; the connecting post 632 passes through one side of the frustum and connects to the connecting plate 631, forming two pin holes in the frustum; a locking groove 633 is provided on the upper part of the connecting post, and the locking groove 633 is used to connect the edge of the locking disc 64; as shown Figure 6 and Figure 7 As shown;

[0039] The lower parts of the first and second truncated cones are respectively connected to the upper part of the drum 53 of the rotor 5; the two pin holes are aligned with the mounting holes on the drum 53 connected to the second ring, and are used to insert the two locking grooves 633 of the locking pin 63.

[0040] The locking disc 64 is an eccentric disc. By twisting the knob connected to the upper part of the rotating shaft 66, the edge of the locking disc 64 can be engaged and disengaged from the locking groove 633.

[0041] The surface of the middle part of the rotating shaft is provided with a groove for locking the handle shaft 671 connected to the handle 67; one end of the handle shaft 671 is connected to the handle 67, and the other end is connected to the locking seat 65; by rotating the handle 67, the handle shaft 671 can be locked or released from the rotating shaft 66; there are various locking methods for the handle shaft 671 to the rotating shaft 66, such as the cooperation of protrusion and groove.

[0042] The second truncated cone has an operating hole 621 at the position of the locking seat 65 corresponding to the first truncated cone. The operating hole is used to pass the locking pin 63 during operation. The two connecting posts 632 of the locking pin 63 are inserted from bottom to top through the mounting hole of the drum 53 and then through the pin hole of the adapter 62. Then, the locking disc 64 is rotated by the rotating shaft 66 so that the edge of the locking disc 64 is inserted into the locking groove 633 of the locking pin 63, realizing the engagement of the locking disc 64 and the locking pin 63. Then, the handle 67 is rotated to tighten the connection between the locking pin 63 and the locking disc 64, thereby locking the adapter 6 onto the drum 53.

[0043] The components and connection method of the second locking unit are the same as those of the first locking unit; the components and connection method of the second quick-locking device are the same as those of the first quick-locking device.

[0044] The adapter 6 is used in the operation of the first pressing device 4 and the tightening device 13; the first pressing device 4 applies a pressing force to the adapter 6 through the first pressing mechanism 45 to press the rotor 5; when the tightening device 13 descends, it falls on the adapter 6 to achieve radial and axial positioning of the tightening arm 134.

[0045] Preferably, the electrical cabinet 11 provides power support for the various electrical devices of the present invention;

[0046] The control system 10 controls multiple drive motors of the aero-engine rotor connection device in this invention;

[0047] The plurality of drive motors include the drive motor of the transfer guide rail 2, the drive motor of the lifting device 7, the drive motor of the rotor positioning device 3, the drive motor of the first pressing device 4 and the second pressing device 12, and the drive motor of the tightening device 13.

[0048] Real-time data during the pressing and tightening process is displayed on the monitor on the control system 10; when a fault occurs during operation, the indicator light 9 will promptly issue an alarm signal.

[0049] On the other hand, the present invention provides a method for connecting an aircraft engine rotor device, using the aforementioned aircraft engine rotor connection device, comprising the following specific steps:

[0050] Step 1: Connect the first and second stage disk assembly 51 of the rotor to the rotor positioning device 3. The lower end face of the first and second stage disk assembly 51 is connected to the upper end face of the rotor support platform 34. The first and second stage disk assembly 51 is locked by the limiting mechanism 32 driven by the rotor positioning motor 33, and the first and second stage disk assembly 51 is fixedly connected to the rotor positioning device 3.

[0051] Step 2: Connect the rotor third-stage disk 52 to the upper second-stage disk of the first and second-stage disk assembly, and apply clamping force through the first clamping device 4 to clamp it, so as to achieve an interference fit between the second and third-stage disks of the rotor 5.

[0052] Step 3: Connect the upper end face of the rotor drum 53 to the adapter 6, and connect the adapter 6 to the lifting device 7. Apply downward pressure through the lifting device 7 to connect the rotor drum 53 to the upper part of the three-stage disc 52 to obtain the rotor after clamping and installation. Move the rotor after clamping and installation to the lower part of the second clamping device 12 through the transfer guide rail 2.

[0053] Step 4: Use the second clamping device 12 to apply clamping force to the transfer fixture 6 on the upper end face of the drum 53 of the rotor after clamping and installation, so as to achieve an interference fit between the drum 53 and the three-stage disc 52.

[0054] Step 5: Drive the tightening device 13 to descend, and the tightening arm 134 unfolds in the blind cavity of the rotor after it has been pressed and installed, tightening the corresponding nuts on the three-stage disc 52, thus completing the bolt tightening inside the rotor 5.

[0055] Preferably, step three includes the following specific steps:

[0056] The upper end face of the rotor drum 53 is connected to the adapter 62. The adapter 6 is installed on the adapter and connected to the lifting device 7. The rotor drum 53 is connected to the upper part of the three-stage disc 52 through the lifting device.

[0057] The locking pin 63 is passed through the operating hole 621. The two connecting pins 632 of the locking pin 63 are inserted from bottom to top through the mounting hole of the drum 53 and then through the pin hole of the adapter 62. Then, the locking disc 64 is rotated by the rotating shaft 66 so that the edge of the locking disc 64 is inserted into the locking groove 633 of the locking pin 63, realizing the engagement of the locking disc 64 and the locking pin 63. Then, the handle 67 is rotated to tighten the connection between the locking pin 63 and the locking disc 64, thereby locking the adapter 6 onto the drum 53.

[0058] After obtaining the clamped rotor, move the clamped rotor to the underside of the second clamping device 12 via the transfer guide rail 2.

[0059] Compared with the prior art, the present invention has at least the following beneficial effects:

[0060] (1) The present invention integrates the stop clamping device and the bolt tightening device in the rotor connection process, which can complete the bolt tightening at the same time as clamping, thereby improving the rotor connection efficiency and assembly quality.

[0061] (2) The stop clamping device of the present invention can clamp each rotor stop connection separately, and can precisely control the clamping force during the clamping process, thus ensuring the stability of the clamping effect;

[0062] (3) The bolt tightening device of the present invention has the functions of automation and visualization, which overcomes the limitations of manual operation due to the narrow blind cavity space inside the rotor, and improves tightening efficiency and accuracy.

[0063] (4) The present invention does not require additional lifting equipment for the hoisting of the rotor and tightening device, which saves costs and improves the working efficiency of the assembly line. Attached Figure Description

[0064] The accompanying drawings are for illustrative purposes only and are not intended to limit the scope of the invention.

[0065] Figure 1 This is a schematic diagram of the structure of an aero-engine rotor connection device according to an embodiment of the present invention;

[0066] Figure 2 This is a schematic diagram of the rotor positioning device according to an embodiment of the present invention;

[0067] Figure 3 This is a schematic diagram of the structure of the first pressing device according to an embodiment of the present invention;

[0068] Figure 4 This is a schematic diagram of the structure of the second pressing device according to an embodiment of the present invention;

[0069] Figure 5 This is a schematic diagram of the tightening device structure according to an embodiment of the present invention;

[0070] Figure 6 This is a schematic diagram of a rotor transfer tooling according to an embodiment of the present invention;

[0071] Figure 7 for Figure 6 The diagram shows a cross-sectional view of the connection structure between the adapter and the rotor.

[0072] Figure 8 This is a schematic diagram of the rotor assembly structure according to an embodiment of the present invention.

[0073] Explanation of reference numerals in the attached drawings: Base 1; Transfer guide rail 2; Rotor positioning device 3; Base 31; Limiting component 1 32; Motor 33; Rotor support platform 34; First clamping device 4; First support seat 41; Motor support seat 42; Servo push cylinder 43; First clamping motor 44; First clamping mechanism 45; Rotor 5; First and second stage disc assembly 51; Third stage disc 52; Drum 53; Adapter fixture 6; Quick lock 61; Adapter seat 62; Operating hole 621; Locking pin 63; Connecting plate 631; Connecting column 632; Lock 633, locking groove, 64, locking seat, 65, rotating shaft, 661, knob, 67, handle shaft, 671; lifting device, 7; frame, 8; signal light, 9; control system, 10; electrical cabinet, 11; second pressing device, 12, second support seat, 121, second pressing motor, 122, second pressing mechanism, 123, guide column, 124, sensor, 125; tightening device, 13, third support seat, 131, guide rail, 132, lifting motor, 133, tightening arm, 134, drive mechanism, 135, tightening gun, 136. Detailed Implementation

[0074] To better understand the above-described objectives, features, and advantages of the present invention, the invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be noted that, unless otherwise specified, the embodiments of the present invention and the features thereof can be combined with each other. Furthermore, the present invention can be implemented in other ways different from those described herein; therefore, the scope of protection of the present invention is not limited to the specific embodiments disclosed below.

[0075] A specific embodiment of the present invention, such as Figure 1-8 A rotor connection device and method for an aero-engine are disclosed.

[0076] To illustrate the effectiveness of the method proposed in this invention, the following detailed description of the above technical solution is provided through a specific embodiment. The specific implementation steps are as follows:

[0077] On one hand, the present invention provides an aircraft engine rotor connection device, comprising:

[0078] 1. Base, 2. Transfer guide rail, 3. Rotor positioning device, 4. First clamping device, 6. Transfer fixture, 12. Second clamping device, and 13. Tightening device;

[0079] Preferably, the connecting device further includes a lifting device 7, a frame 8, and a control system 10;

[0080] Preferably, the transfer guide rail 2 and the second clamping device 12 are connected to the upper surface of the base 1; the transfer guide rail 2 is fixedly connected to the middle position of the upper surface of the base 1; and the tightening device 13 is connected to the upper surface of the second clamping device.

[0081] The lower part of the rotor positioning device 3 is connected to the transfer guide rail 2 via a slide rail; the upper part of the rotor positioning device is connected to the first and second stage disk assembly 51 of the rotor 5; the lower outer ring of the rotor positioning device 3 is connected to the lower part of the first pressing device 4.

[0082] The second clamping device 12 is connected to one side of the upper part of the base; the tightening device 13 is located on the same side as the second clamping device;

[0083] The frame 8 is a four-column structure; the frame is used to connect the lifting device 7 and the control system 10 respectively.

[0084] The upper part of the lifting device is connected to the upper part of the frame via a slide rail 2, allowing it to slide forward, backward, left, and right; the lower part of the lifting device is connected to the adapter 6; the lifting device is located above the first clamping device.

[0085] The control system 10 is used to control each movable device.

[0086] Furthermore, the control system includes a display that can rotate circumferentially for easy operation by staff.

[0087] Furthermore, the rotor positioning device 3 includes a base 31, a limiting mechanism, a motor 33, and a rotor support platform 34; the limiting mechanism includes a first limiting member 32, a second limiting member, and a third limiting member.

[0088] Limiting member 1 32, limiting member 2 and limiting member 3 are evenly arranged circumferentially on the base 31, and the upper part of the limiting mechanism is connected to the rotor support platform 34.

[0089] The limiting mechanism is used to fix or release the lower part of the rotor 5 to be assembled. Each limiting component is connected to a corresponding rotor positioning motor for driving, such as... Figure 2 .

[0090] Furthermore, the first pressing device 4 includes a first support base 41 and a plurality of pressing units; the plurality of pressing units are evenly arranged on the corners of the first support base 41;

[0091] There are four clamping units;

[0092] Each clamping unit includes a motor support 42, a servo push cylinder 43, a first clamping motor 44, and a first clamping mechanism 45;

[0093] The first clamping mechanism 45 includes a clamping member and a clamping push rod; the outer side of the clamping member is connected to the clamping push rod; the lower part of the clamping member is connected to the upper part of the motor support base;

[0094] The lower part of the pressing push rod is connected to the upper part of the first pressing motor 44 and the servo push cylinder 43;

[0095] The inner side of the servo push cylinder 43 is connected to the outer side of the motor support base;

[0096] The first pressing mechanism 45 moves back and forth and up and down under the drive of the servo push cylinder 43 and the first pressing motor 44;

[0097] The first clamping device 4 is used to clamp the third-stage disc 52 of the rotor 5 with the first- and second-stage disc assembly 51, achieving a stop fit; such as Figure 3 and Figure 8 As shown.

[0098] Furthermore, the second pressing device 12 includes a second support base 121, a second pressing motor 122, a second pressing mechanism 123, a guide column 124, and a sensor 125;

[0099] The second support base 121 includes a first support surface, a second support surface, and a third support surface;

[0100] The bottoms of the second clamping motor 122 and the guide column 124 respectively penetrate the second support surface and connect to the upper part of the second clamping mechanism 123. The sensor 125 is connected to the lower part of the second clamping mechanism 123, and the lower surface of the sensor is connected to the rotor. Figure 4 As shown.

[0101] Furthermore, the tightening device 13 includes a third support base 131, a guide rail 132, a lifting motor 133, a tightening arm 134, a drive mechanism 135, and a tightening gun 136.

[0102] The third support 131 is connected to the upper surface of the second clamping device; the drive mechanism is connected to the side of the third support; the tightening arm 134 is located at the lower part of the drive mechanism, and the tightening gun 136 is connected to the upper part of the drive mechanism; the second clamping mechanism 123 has a hole through which the tightening arm 134 passes.

[0103] The lifting motor 133 is connected to the upper part of the third support base 131; the guide rail 132 is connected to the other side of the third support base 131.

[0104] The tightening device is an automatic tightening device for blind cavity nuts.

[0105] Furthermore, the adapter 6 includes multiple locking units and multiple quick-locking devices; the adapter includes locking unit one, locking unit two, quick-locking device one 61 and quick-locking device two; locking unit one and locking unit two are symmetrically distributed; quick-locking device one and quick-locking device two are symmetrically distributed;

[0106] The quick-locking device 61 is mounted on the adapter 62 and is used to cooperate with the lifting device 7; the locking unit is used to lock the adapter 6 onto the drum 53 of the rotor 5.

[0107] The locking unit includes a locking pin 63, a locking disc 64, a locking seat 65, a rotating shaft 66, and a handle 67; the lower part of the locking seat is connected to the adapter seat 62, and the rear part of the locking seat is connected to the handle 67.

[0108] The locking disc 64 is disposed inside the locking seat; the rotating shaft 66 passes through the locking seat and its lower part is connected to the locking disc; the locking pin 63 is connected to the locking disc 64.

[0109] Furthermore, the adapter 62 is a hollow concave structure, including a frustum one and a frustum two;

[0110] The locking pin 63 includes a connecting plate 631 and a connecting post 632; the connecting post 632 passes through one side of the frustum and connects to the connecting plate 631, forming two pin holes in the frustum; a locking groove 633 is provided on the upper part of the connecting post, and the locking groove 633 is used to connect the edge of the locking disc 64; as shown Figure 6 and Figure 7 As shown;

[0111] The lower parts of the first and second truncated cones are respectively connected to the upper part of the drum 53 of the rotor 5; the two pin holes are aligned with the mounting holes on the drum 53 connected to the second ring, and are used to insert the two locking grooves 633 of the locking pin 63.

[0112] The locking disc 64 is an eccentric disc. By twisting the knob connected to the upper part of the rotating shaft 66, the edge of the locking disc 64 can be engaged and disengaged from the locking groove 633.

[0113] The surface of the middle part of the rotating shaft is provided with a groove for locking the handle shaft 671 connected to the handle 67; one end of the handle shaft 671 is connected to the handle 67, and the other end is connected to the locking seat 65; by rotating the handle 67, the handle shaft 671 can be locked or released from the rotating shaft 66; there are various locking methods for the handle shaft 671 to the rotating shaft 66, such as the cooperation of protrusion and groove.

[0114] The second truncated cone has an operating hole 621 at the position of the locking seat 65 corresponding to the first truncated cone. The operating hole is used to pass the locking pin 63 during operation. The two connecting posts 632 of the locking pin 63 are inserted from bottom to top through the mounting hole of the drum 53 and then through the pin hole of the adapter 62. Then, the locking disc 64 is rotated by the rotating shaft 66 so that the edge of the locking disc 64 is inserted into the locking groove 633 of the locking pin 63, realizing the engagement of the locking disc 64 and the locking pin 63. Then, the handle 67 is rotated to tighten the connection between the locking pin 63 and the locking disc 64, thereby locking the adapter 6 onto the drum 53.

[0115] The components and connection method of the second locking unit are the same as those of the first locking unit; the components and connection method of the second quick-locking device are the same as those of the first quick-locking device.

[0116] The adapter 6 is used in the operation of the first pressing device 4 and the tightening device 13; the first pressing device 4 applies a pressing force to the adapter 6 through the first pressing mechanism 45 to press the rotor 5; when the tightening device 13 descends, it falls on the adapter 6 to achieve radial and axial positioning of the tightening arm 134.

[0117] Preferably, the electrical cabinet 11 provides power support for the various electrical devices of the present invention;

[0118] The control system 10 controls multiple drive motors of the aero-engine rotor connection device in this invention;

[0119] The plurality of drive motors include the drive motor of the transfer guide rail 2, the drive motor of the lifting device 7, the drive motor of the rotor positioning device 3, the drive motor of the first pressing device 4 and the second pressing device 12, and the drive motor of the tightening device 13.

[0120] Real-time data during the pressing and tightening process is displayed on the monitor on the control system 10; when a fault occurs during operation, the indicator light 9 will promptly issue an alarm signal.

[0121] On the other hand, the present invention provides a method for connecting an aircraft engine rotor device, using the aforementioned aircraft engine rotor connection device, comprising the following specific steps:

[0122] Step 1: Connect the first and second stage disk assembly 51 of the rotor to the rotor positioning device 3. The lower end face of the first and second stage disk assembly 51 is connected to the upper end face of the rotor support platform 34. The first and second stage disk assembly 51 is locked by the limiting mechanism 32 driven by the rotor positioning motor 33, and the first and second stage disk assembly 51 is fixedly connected to the rotor positioning device 3.

[0123] Step 2: Connect the rotor third-stage disk 52 to the upper second-stage disk of the first and second-stage disk assembly, and apply clamping force through the first clamping device 4 to clamp it, so as to achieve an interference fit between the second and third-stage disks of the rotor 5.

[0124] Step 3: Connect the upper end face of the rotor drum 53 to the adapter 6, and connect the adapter 6 to the lifting device 7. Apply downward pressure through the lifting device 7 to connect the rotor drum 53 to the upper part of the three-stage disc 52 to obtain the rotor after clamping and installation. Move the rotor after clamping and installation to the lower part of the second clamping device 12 through the transfer guide rail 2.

[0125] Step 4: Use the second clamping device 12 to apply clamping force to the transfer fixture 6 on the upper end face of the drum 53 of the rotor after clamping and installation, so as to achieve an interference fit between the drum 53 and the three-stage disc 52.

[0126] Step 5: Drive the tightening device 13 to descend, and the tightening arm 134 unfolds in the blind cavity of the rotor after it has been pressed and installed, tightening the corresponding nuts on the three-stage disc 52, thus completing the bolt tightening inside the rotor 5.

[0127] Preferably, step three includes the following specific steps:

[0128] The upper end face of the rotor drum 53 is connected to the adapter 62. The adapter 6 is installed on the adapter and connected to the lifting device 7. The rotor drum 53 is connected to the upper part of the three-stage disc 52 through the lifting device.

[0129] The locking pin 63 is passed through the operating hole 621. The two connecting pins 632 of the locking pin 63 are inserted from bottom to top through the mounting hole of the drum 53 and then through the pin hole of the adapter 62. Then, the locking disc 64 is rotated by the rotating shaft 66 so that the edge of the locking disc 64 is inserted into the locking groove 633 of the locking pin 63, realizing the engagement of the locking disc 64 and the locking pin 63. Then, the handle 67 is rotated to tighten the connection between the locking pin 63 and the locking disc 64, thereby locking the adapter 6 onto the drum 53.

[0130] After obtaining the clamped rotor, move the clamped rotor to the underside of the second clamping device 12 via the transfer guide rail 2.

[0131] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention.

Claims

1. An aircraft engine rotor connection device, characterized in that, It includes a base (1), a transfer guide rail (2), a rotor positioning device (3), a first clamping device (4), a transfer tool (6), a second clamping device (12), and a tightening device (13); The rotor positioning device (3) and the second pressing device (12) are arranged adjacent to each other on both sides of the base (1); the rotor positioning device (3) and the first pressing device (4) are arranged on the transfer guide rail (2); the second pressing device (12) is connected to the tightening device (13); The adapter (6) includes multiple locking units and multiple quick-locking devices; The locking unit locks the drum (53) of the rotor (5) with a quick-locking device. The first clamping device (4) applies clamping force to the adapter (6) through its first clamping mechanism to clamp the rotor (5); the tightening device (13) falls on the adapter (6) when it descends to achieve radial and axial positioning of the tightening arm (134); The first clamping device (4) includes multiple clamping units; The plurality of clamping units are used to clamp the rotor’s third-stage disc (52) and the first- and second-stage disc assembly (51); The adapter includes locking unit one, locking unit two, quick-locking device one (61) and quick-locking device two; A quick-locking device (61) is mounted on an adapter (62); the locking unit is used to lock the adapter (6) onto the drum (53) of the rotor (5); The locking unit includes a locking pin (63), a locking disc (64), a locking seat (65), a rotating shaft (66), and a handle (67); the lower part of the locking seat is connected to the adapter (62), and the rear part of the locking seat is connected to the handle (67). The locking disc (64) is located inside the locking seat; the rotating shaft (66) passes through the locking seat and its lower part is connected to the locking disc; the locking pin (63) is connected to the locking disc (64); The adapter (62) includes a first frustum and a second frustum; The lower parts of the first and second truncated cones are respectively connected to the upper part of the drum (53) of the rotor (5); The second truncated cone has an operating hole (621) at the position of the locking seat (65) corresponding to the first truncated cone. The components and connection method of the second locking unit are the same as those of the first locking unit; the components and connection method of the second quick-locking device are the same as those of the first quick-locking device. The tightening device is a blind cavity nut automatic tightening device; It also includes connection methods using aircraft engine rotor connection equipment, including: Step 1: Connect one side of the first and second stage disk assembly (51) of the rotor to the rotor positioning device, and the other side of the first and second stage disk assembly to the rotor support platform. Drive the limiting mechanism through the rotor positioning motor to lock the first and second stage disk assembly, and fix the first and second stage disk assembly on the rotor positioning device. Step 2: Connect one side of the rotor's third-stage disk (52) to the other side of the second-stage disk of the first and second-stage disk assembly, and apply a clamping force through the first clamping device to clamp it, thereby achieving the connection between the rotor's second and third-stage disks; Step 3: Connect one side of the rotor drum (53) to the adapter (6). The adapter connects one side of the rotor drum to the other side of the three-stage disc through a lifting device to obtain the rotor after clamping and installation. Move the rotor after clamping and installation to the underside of the second clamping device (12) through the transfer guide rail. Step 4: Use the second clamping device (12) to apply clamping force to the other side of the rotor drum after clamping and installation to achieve interference fit between the drum and the three-stage disc. Step 5: Drive the tightening device (13) to descend, and the tightening arm (134) unfolds in the blind cavity of the rotor after it has been pressed and installed, tightening the nuts on the three-stage disc to complete the tightening of the bolts inside the rotor.

2. The aircraft engine rotor connection device according to claim 1, characterized in that, The rotor positioning device (3) includes a limiting mechanism, a motor (33) and a rotor support platform (34). The limiting mechanism is connected to the rotor support platform; The limiting mechanism is connected to the motor (33); the limiting mechanism is used to fix or loosen the lower part of the rotor (5) to be assembled.

3. The aircraft engine rotor connection device according to claim 1, characterized in that, The clamping unit includes a motor support (42), a servo push cylinder (43), a first clamping motor (44), and a first clamping mechanism (45). The first pressing mechanism moves back and forth and up and down under the drive of the servo push cylinder and the first pressing motor.

4. The aero-engine rotor connection device according to claim 3, characterized in that, The first clamping mechanism (45) includes a clamping member and a clamping push rod; one side of the clamping member is connected to one side of the clamping push rod; the other side of the clamping member is connected to one side of the motor support base (42); The other side of the clamping push rod is connected to the first clamping motor and the servo push cylinder. The other side of the servo push cylinder (43) is connected to the other side of the motor support.

5. The aero-engine rotor connection device according to claim 1, characterized in that, The second pressing device (12) includes a second support base (121), a second pressing motor (122), a second pressing mechanism (123), and a guide column (124). The second pressing mechanism (123), the second pressing motor (122), and the guide column (124) are all mounted on the second support base (121); The second clamping mechanism (123) is used to clamp the rotor (5).

6. The aircraft engine rotor connection device according to claim 1, wherein the tightening device (13) includes a third support base (131), a tightening arm (134), a drive mechanism (135), and a tightening gun (136); the third support base is disposed on the second pressing device (12); the drive mechanism is connected to the third support base; and the tightening arm and the tightening gun are respectively connected to the drive mechanism.

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