Low-pressure axial system assembling device for aero-engine and using method of low-pressure axial system assembling device

Abstract

The invention discloses an aero-engine low-pressure axial system assembling device and a using method thereof.The device comprises a base, a framework, a rotating system, a pressing system and a clamping system, the framework is arranged on the base, the rotating system and the pressing system are arranged on the framework, and the clamping system is connected with the base and the framework. According to the low-pressure turbine shaft and low-pressure shaft system connecting device, the low-pressure shaft system is fixed through the rotating system, the torque of the torque wrench is accurately controlled through the pressing system, the clamping system clamps a tool clamp of a workpiece A or clamps and fixes a ground pile, and the stability in the connecting process of a low-pressure turbine shaft and the low-pressure shaft system is improved. The low-pressure axial system assembling device has the advantages of being easy to install and convenient to operate, can achieve whole-process assembling of a low-pressure axial system by a single person, and plays a great role in assembling of the low-pressure axial system.

Description

Technical Field

[0001] The present invention belongs to the technical field of aero-engine assembly, and in particular relates to an assembly device for a low-pressure shaft system of an aero-engine and a method for using the same. Background Art

[0002] Due to the pulsating production requirements of the workshop, the low-pressure shafting of aircraft engines requires pulsating assembly. Typically, the assembly process involves multiple steps, and in most engineering applications, this is accomplished by switching between different steps. This requires different equipment and fixtures. The assembly process requires multiple pieces of equipment and fixtures, often requiring the switching of steps and the coordination of at least two people. This switching process can easily cause damage to the low-pressure shafting.

[0003] To improve the efficiency of aircraft engine low-pressure shafting assembly and improve working conditions, a device for assembling aircraft engine low-pressure shafting is needed. This device can enhance on-site assembly efficiency, reduce labor intensity and safety risks, and provide excellent technical support and economic benefits.

[0004] Patent document CN113211339A discloses a fixture for horizontally balancing single discs of aircraft turboshaft engines. The fixture comprises a first, second, third, and fourth fixtures, respectively, for mounting the engine's first-stage rotor, second- and fourth-stage rotors, and third-stage rotor, as well as the centrifugal impeller. Each fixture utilizes a core rod and a positioning plate to achieve an interference fit for the rotors. Tightening bolts are used to provide auxiliary tightening for the first and third-stage rotors and the centrifugal impeller, meeting the requirements for positioning, connection, and testing of each rotor disc. The device does not have a directly adjustable torque for tightening the nuts.

[0005] Patent publication number CN206561261U discloses a tooling mechanism for assembling nuts between aircraft engine rotor blade discs. This device addresses existing issues with manual assembly, which are difficult due to limited working space, low work efficiency, and the inability to precisely control the nut preload torque within a specified range. The device comprises a robotic arm and a robotic arm support device. The robotic arm includes a motor, a motor base, a first gear pair, a first bevel gear pair, a second bevel gear pair, a drive shaft, a bolt sleeve, a worm, a worm gear, a support cylinder, a connecting base, a base, a universal joint support plate, a gear train transmission mechanism, a belt drive mechanism, and multiple cross universal joints. The lifting mechanism is mounted on the support base. The drive shaft drives the first bevel gear pair, which in turn drives the gear train transmission mechanism, which in turn drives the second bevel gear pair. This device is used for assembling nuts between aircraft engine rotor blade discs and requires electrical power. Summary of the Invention

[0006] In order to solve the above technical problems, the present invention provides an assembly device for a low-pressure shaft system of an aircraft engine and a method for using the same.

[0007] The present invention is achieved through the following technical solutions.

[0008] The present invention provides an assembly device for a low-pressure shaft system of an aircraft engine, comprising a base, a skeleton, a rotation system, a clamping system and a clamping system. The skeleton is arranged on the base, the rotation system and the clamping system are arranged on the skeleton, and the clamping system is connected to the base and the skeleton respectively.

[0009] Preferably, the rotation system includes a vertical seat bearing, a rotating table, a spoke handwheel A and a reducer. The vertical seat bearing and the reducer are respectively arranged on the skeleton. The spoke handwheel A is connected to the reducer. The reducer is connected to one end of the rotating shaft. The other end of the rotating shaft passes through the rotating table and is connected to the vertical seat bearing.

[0010] Preferably, the turntable includes plate A, plate B and a turntable base, the plate A and plate B are respectively connected to the turntable base, and two plates A and B are symmetrically arranged. Hole A is provided on plate A, and the rotating shaft passes through plate A through hole A.

[0011] Preferably, a stop hole is provided on the plate A, and the number of stop holes provided on a single plate A is greater than or equal to 2. A through hole and a plurality of holes B are provided on the base of the rotating table, and the plurality of holes B are evenly distributed in a circle around the through hole.

[0012] Preferably, the clamping system includes a support column, a rotating device and a clamping assembly, one end of the support column is connected to the frame through a connecting part, and the other end of the support column is connected to the rotating device, a spoke handwheel B and a screw are provided on the rotating device, one end of the screw is connected to the spoke handwheel B, and the other end of the screw is connected to the clamping assembly, and the clamping assembly is connected to the support column.

[0013] Preferably, the clamping assembly includes a connecting ring, a connecting plate and a screw pressure shaft, the support column is slidably connected through the connecting ring, one end of the connecting plate is connected to the connecting ring, the screw pressure shaft is connected through the connecting plate, and the screw is connected to the connecting plate.

[0014] Preferably, the clamping system includes a spoke handwheel C and a clamping assembly, a screw assembly and a clamping plate are provided on the clamping assembly, the clamping assembly is provided on the base, one end of the screw assembly is connected to the spoke handwheel C, and the other end of the screw assembly is rotatably connected to the clamping assembly, the screw assembly passes through the clamping plate through a screw hole and is threadedly connected, and the clamping assembly is slidably connected to the clamping plate.

[0015] Preferably, a support frame and moving wheels are provided on the base, and a stop pin is provided on the inner wall of the frame. The stop pin is vertically arranged and slidably connected to the frame.

[0016] A method for using an assembly device for a low-pressure shafting system of an aircraft engine comprises the following steps:

[0017] S1: Before starting the assembly work, move the assembly device to an open area, place the assembly device on a level ground, and ensure the overall stability. Turn the spoke handwheel A to drive the shaft through the reducer, and then drive the turntable to rotate until the through-hole axis is horizontal. Move the stop pin and insert it into the stop hole to fix the turntable.

[0018] S2: Place the workpiece A to be fixed on one side of the through hole, pass the bolt through the hole B and the corresponding hole on the workpiece B, use a torque wrench to tighten the bolt, turn the spoke handwheel B to rotate the screw, and then make the connecting ring and connecting plate slide down along the support column until the screw pressure shaft is against the torque wrench on which the workpiece B is installed. By turning the screw pressure shaft, force is applied to tighten the bolt with the torque wrench.

[0019] S3: By turning the spoke handwheel C, the clamping plate of the clamping assembly clamps the fixture of workpiece A or clamps the fixed ground stake to facilitate the docking of workpiece A and workpiece B, and then connect workpiece A and workpiece B.

[0020] The beneficial effects of the present invention are:

[0021] The present invention fixes the low-pressure shafting through a rotating system, accurately controls the torque of the torque wrench through a clamping system, and clamps the workpiece A's fixture or the fixed ground pile through a clamping system, thereby improving the stability of the low-pressure turbine shaft and the low-pressure shafting during connection. The device of the present invention has been verified by use and has the characteristics of simple installation and convenient operation. It can realize the full-process assembly of the low-pressure shafting by a single person on the low-pressure shafting assembly device. The fully mechanical setting does not require electricity as a power source, which plays a great role in the assembly of the low-pressure shafting. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a structural schematic diagram of the present invention;

[0023] Figure 2 It is a structural schematic diagram of the present invention;

[0024] Figure 3 It is a structural schematic diagram of the rotary table of the present invention;

[0025] Figure 4 It is a structural schematic diagram of the clip of the present invention;

[0026] In the figure: 101-base, 1-skeleton, 2-moving wheel, 3-clamping assembly, 31-clamping plate, 32-screw hole, 4-workpiece A, 5-spoke handwheel C, 6-workpiece B, 7-with vertical seat bearing, 8-rotating table, 9-spoke handwheel B, 10-screw pressure shaft, 11-support frame, 12-spoke handwheel A, 13-reducer, 14-plate A, 141-hole A, 15-plate B, 16-rotating table base, 161-through hole, 162-hole B, 17-rotating shaft, 18-stop hole, 19-stop pin, 91-support column, 911-connecting part, 92-rotating device, 93-screw, 94-connecting ring, 95-connecting plate. DETAILED DESCRIPTION

[0027] The technical solution of the present invention is further described below, but the scope of protection claimed is not limited to the description.

[0028] Example:

[0029] like Figures 1 to 4 As shown, a low-pressure shafting assembly device for an aircraft engine includes a base 101, a skeleton 1, a rotation system, a clamping system and a clamping system. The skeleton 1 is arranged on the base 101, the rotation system and the clamping system are arranged on the skeleton 1, and the clamping system is connected to the base 101 and the skeleton 1 respectively.

[0030] The rotation system includes a vertical seat bearing 7, a rotating platform 8, a spoke handwheel A12, and a reducer 13. The vertical seat bearing 7 and the reducer 13 are respectively arranged on the frame 1. The spoke handwheel A12 is connected to the reducer 13. The reducer 13 is connected to one end of a rotating shaft 17. The other end of the rotating shaft 17 passes through the rotating platform 8 and is connected to the vertical seat bearing 7. The rotation system can enable the rotating platform 8 to rotate 360 ​​degrees around the rotating shaft 17.

[0031] The rotating table 8 includes a plate A14, a plate B15 and a rotating table base 16. The plate A14 and the plate B15 are respectively connected to the rotating table base 16. The plate A14 and the plate B15 are symmetrically arranged in two pieces. A hole A141 is set on the plate A14, and the rotating shaft 17 passes through the hole A141 and penetrates the plate A14.

[0032] The plate A14 is provided with a stop hole 18. The number of the stop holes 18 provided on a single plate A14 is greater than or equal to 2. By using a stop pin 19 to penetrate different stop holes 18, the rotating table 8 is kept at different angles to ensure that the rotating table 8 can be locked at different angles. The number of the stop holes 18 provided on a single plate A14 is preferably 2, and one stop hole is at Figure 3The bottom of the single plate A14 is shown with another retaining hole on the left side of the plate A14, which allows the rotary table 8 to be locked at 0° and 90°. The rotary table base 16 is provided with a 125-diameter through-hole 161 and a plurality of holes B162. The holes B162 are evenly distributed around the through-hole 161, specifically 16 through-holes 161, to distribute the forces applied after connecting the workpiece B6. When the rotary table base 16 is at the bottom, the rotary table 8 is at a 0° angle. When the rotary table base 16 is perpendicular to the horizontal plane, the rotary table 8 is at a 90° angle.

[0033] The clamping system includes a support column 91, a rotating device 92 and a clamping assembly. One end of the support column 91 is connected to the skeleton 1 through a connecting portion 911, and the other end of the support column 91 is connected to the rotating device 92. A spoke handwheel B9 and a screw 93 are provided on the rotating device 92. One end of the screw 93 is connected to the spoke handwheel B9, and the other end of the screw 93 is connected to the clamping assembly. The clamping assembly is connected to the support column 91.

[0034] The clamping assembly includes a connecting ring 94, a connecting plate 95 and a screw pressure shaft 10, the support column 91 passes through the connecting ring 94 for sliding connection, one end of the connecting plate 95 is connected to the connecting ring 94, the screw pressure shaft 10 passes through the connecting plate 95 for connection, and the screw 93 is connected to the connecting plate 95.

[0035] The clamping system includes a spoke handwheel C5 and a clamping assembly 3. The clamping assembly 3 is provided with a screw assembly 51 and a clamping plate 31. The clamping assembly 3 is disposed on a base 101. One end of the screw assembly 51 is connected to the spoke handwheel C5, and the other end of the screw assembly 51 is rotatably connected to the clamping assembly 3. The screw assembly 51 passes through the clamping plate 31 through a screw hole 32 and is threadedly connected. The screw holes 32 between adjacent clamping plates 31 have opposite threads, and the clamping assembly 3 is slidably connected to the clamping plate 31. Rotating the spoke handwheel C5 drives the screw in the screw assembly 51 to rotate, and the clamping plate 31 slides under the action of the threaded connection. Adjacent clamping plates 31 slide toward each other, allowing the clamping plates 31 to clamp objects.

[0036] The base 101 is equipped with a support frame 11 and a movable wheel 2. A stop pin 19 is provided on the inner wall of the frame 1, perpendicularly positioned and slidably connected to the frame 1. The frame 1 is a square, fixed, rigid structure that ensures the levelness and load-bearing requirements of the entire assembly device. The support frame 11 is fixedly connected to one end of the base 101 to assist in the manual propulsion of the assembly device. Beneath the frame 1, an omnidirectionally rotatable movable wheel 2 is designed with a brake mechanism to achieve real-time movement and braking requirements of the device.

[0037] A method for using an assembly device for a low-pressure shafting system of an aircraft engine comprises the following steps:

[0038] S1: Before starting the assembly work, move the assembly device to an open area, place the assembly device on a level ground, and ensure the overall stability. Turn the spoke handwheel A12 to drive the shaft 17 to rotate through the reducer 13, and then drive the rotating table 8 to rotate until the axis of the through hole 161 is horizontal. Move the stop pin 19 and insert it into the stop hole 18 to fix the rotating table 8.

[0039] S2: Place the workpiece A4 to be fixed on one side of the through hole 161, and tighten the bolt through the bolt hole B162 and the corresponding hole on the workpiece B6 using a torque wrench. When using, place the torque wrench on the workpiece B6, turn the spoke handwheel B9 to rotate the screw 93, and then make the connecting ring 94 and the connecting plate 95 slide down along the support column 91 until the screw pressure shaft 10 is against the torque wrench installed on the workpiece B6. By turning the screw pressure shaft 10, the torque wrench applies a torque of about 1000 N·m to tighten the nut of the bolt.

[0040] S3: By turning the spoke handwheel C5, the clamping plate 31 of the clamping assembly 3 clamps the fixture of the workpiece A4 or clamps the fixed ground pile, so that the workpiece A4 and the workpiece B6 can be connected. Then, the workpiece A4 and the workpiece B6 can be connected by nuts. When installing the workpiece A4, a torque of about 220N·m is required to tighten the nut of the corresponding bolt. Use a torque wrench to connect the nut with the bottom of the rotary table 8 through the fixture. By applying force on the torque wrench, the nut can be easily tightened to complete the installation of the workpiece A4. When clamping the fixed ground pile, the reaction force can be used to fix the low-pressure shaft system assembly device.

[0041] The workpiece A4 is a low-pressure turbine shaft, and the workpiece B6 is a low-pressure shaft system.

Claims

1. A low-pressure shaft assembly device for an aircraft engine, characterized by: The invention comprises a base (101), a frame (1), a rotation system, a pressing system and a clamping system, wherein the frame (1) is arranged on the base (101), the rotation system and the pressing system are arranged on the frame (1), and the clamping system is connected to the base (101) and the frame (1) respectively.

2. The low-pressure shafting assembly device for an aircraft engine according to claim 1, characterized in that: The rotating system comprises a vertical seat bearing (7), a rotating platform (8), a spoke handwheel A (12) and a reducer (13); the vertical seat bearing (7) and the reducer (13) are respectively arranged on the skeleton (1); the spoke handwheel A (12) is connected to the reducer (13); the reducer (13) is connected to one end of a rotating shaft (17); the other end of the rotating shaft (17) passes through the rotating platform (8) and is connected to the vertical seat bearing (7).

3. The low-pressure shafting assembly device for an aircraft engine according to claim 2, characterized in that: The rotating table (8) includes a plate A (14), a plate B (15) and a rotating table base (16). The plate A (14) and the plate B (15) are respectively connected to the rotating table base (16). The plate A (14) and the plate B (15) are symmetrically arranged in two pieces. A hole A (141) is provided on the plate A (14), and the rotating shaft (17) passes through the plate A (14) through the hole A (141).

4. The low-pressure shafting assembly device for an aircraft engine according to claim 3, characterized in that: The plate A (14) is provided with a stop hole (18), and the number of the stop holes (18) provided on a single plate A (14) is greater than or equal to 2. The rotating table base (16) is provided with a through hole (161) and a plurality of holes B (162), and the plurality of holes B (162) are evenly distributed around the through hole (161) in a circumferential manner.

5. The low-pressure shaft assembly device for an aircraft engine according to claim 1, characterized in that: The clamping system comprises a support column (91), a rotating device (92) and a clamping assembly. One end of the support column (91) is connected to the frame (1) through a connecting portion (911), and the other end of the support column (91) is connected to the rotating device (92). A spoke handwheel B (9) and a screw (93) are provided on the rotating device (92). One end of the screw (93) is connected to the spoke handwheel B (9), and the other end of the screw (93) is connected to the clamping assembly. The clamping assembly is connected to the support column (91).

6. The low-pressure shafting assembly device for an aircraft engine according to claim 5, characterized in that: The pressing assembly comprises a connecting ring (94), a connecting plate (95) and a screw pressing shaft (10); the supporting column (91) passes through the connecting ring (94) for sliding connection; one end of the connecting plate (95) is connected to the connecting ring (94); the screw pressing shaft (10) passes through the connecting plate (95) for connection; and the screw rod (93) is connected to the connecting plate (95).

7. The low-pressure shafting assembly device for an aircraft engine according to claim 1, characterized in that: The clamping system comprises a spoke handwheel C (5) and a clamping assembly (3), wherein a screw assembly (51) and a clamping plate (31) are arranged on the clamping assembly (3), and the clamping assembly (3) is arranged on a base (101). One end of the screw assembly (51) is connected to the spoke handwheel C (5), and the other end of the screw assembly (51) is rotatably connected to the clamping assembly (3), the screw assembly (51) passes through the clamping plate (31) through a screw hole (32) and is threadedly connected, and the clamping assembly (3) is slidably connected to the clamping plate (31).

8. The low-pressure shafting assembly device for an aircraft engine according to claim 1, characterized in that: A support frame (11) and a moving wheel (2) are provided on the base (101), and a stop pin (19) is provided on the inner wall of the frame (1). The stop pin (19) is vertically arranged and slidably connected to the frame (1).

9. A method for using the low-pressure shafting assembly device for an aircraft engine according to any one of claims 1 to 8, characterized in that: The following steps are involved: S1: Before the assembly work begins, move the assembly device to an open area, place the assembly device on a level ground, and ensure the overall stability. Turn the spoke hand wheel A (12) to drive the rotating shaft (17) through the reducer (13), and then drive the rotating table (8) to rotate until the axis of the through hole (161) is horizontal. Move the stop pin (19) and insert it into the stop hole (18) to fix the rotating table (8). S2: Place the workpiece A (4) to be fixed on one side of the through hole (161), insert the bolt through the hole B (162) and the corresponding hole on the workpiece B (6), use a torque wrench to tighten the bolt, turn the spoke hand wheel B (9) to rotate the screw (93), and then make the connecting ring (94) and the connecting plate (95) slide down along the support column (91) until the screwing pressure shaft (10) is pressed against the torque wrench on which the workpiece B (6) is installed, and the torque wrench is tightened by rotating the screwing pressure shaft (10); S3: By rotating the spoke hand wheel C (5), the clamping plate (31) of the clamping assembly (3) clamps the fixture of the workpiece A (4) or the clamping fixed pile, so that the workpiece A (4) and the workpiece B (6) can be docked, and then the workpiece A (4) and the workpiece B (6) can be connected.

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