CN103791812B - Aeroengine rotor assembly method and device based on capacitive sensing and four-jaw hydraulic chuck gripping - Google Patents

Abstract

The aeroengine rotor assembly method grabbing card based on capacitance sensing and four paws oild chuck belongs to mechanical assembly technique with device.Its measuring method and device are to close rotary axis system based on gas magnetic knot to determine rotative benchmark；The angle location of turntable is determined according to photoelectric encoder；Based on four gauge head measurement apparatus, extract radial error and the heeling error of axial fitting surface of rotor radial fitting surface, obtain this rotor on after assembling rotor coaxial degree affect weights；Respectively measure assembling needed for whole rotors, obtain each rotor on assembling after rotor coaxial degree affect weights；The weights of each rotor are carried out vector optimization, obtains the angle of assembling of each rotor.The present invention can effectively solve the problem that after aeroengine rotor assembles, axiality is low, and after having rotor assembling, axiality is high, reduction is vibrated, be easily installed, flexibility ratio is high, improve the feature of engine performance.

Description

Aeroengine rotor assembly method based on capacitive sensing and four-jaw hydraulic chuck gripping method and device

technical field

The invention belongs to mechanical assembly technology, and mainly relates to an aeroengine rotor assembly method and device based on capacitive sensing and four-jaw hydraulic chuck gripping.

Background technique

Aeroengine assembly is the last link in the manufacturing process of aeroengine, and it is also one of the most important manufacturing links. Under the conditions of the existing aero-engine design scheme and processing technology level, the quality of assembly and work efficiency have an important impact on the quality, performance and production efficiency of the engine. Therefore, in the assembly process, the coaxiality of the installed rotor should be improved as much as possible, so as to reduce the vibration of the aero-engine and improve the performance of the aero-engine. However, in actual production, the assembly of aero-engines is completely manual assembly. The level of assembly accuracy and stability depends entirely on the experience and technical level of the assemblers. There is a lack of a high-speed and effective method to guide the assembly of aero-engine rotors. Improve assembly efficiency, reduce aero-engine vibration, and improve aero-engine performance.

As the aero-engine assembly and testing technology is getting more and more attention, the aero-engine assembly and testing technology is getting more and more attention, and has become a research hotspot. More and more researchers have conducted in-depth discussions on aero-engine rotors. Rolls-Royce proposed a solution (System and method for improving the damagetolerance of a rotor assembly. European Patent Publication No.: EP2525049A2), mainly through the Each sub-test system obtains the stress signal of each position of the rotor, and the main system analyzes the signals collected by each subsystem, and analyzes the impact on assembly from the damage tolerance parameters of each rotor, thereby improving the assembly of the aeroengine rotor. The problem with this method is that the influence of the geometric quantity of the rotor on the assembly is not analyzed, and the influence of the geometric quantity on the assembly cannot be improved.

Xi'an Jiaotong University proposed a method for testing the assembly performance of an aero-engine rotor (a method for testing the assembly performance of an aero-engine rotor. Publication number: CN101799354A). The method first adopts the exciter to excite the aero-engine rotor, and uses the vibration sensor and signal acquisition system software to obtain an impulse response signal of a multi-carrier coupled aero-engine rotor; The response signal is analyzed by the dual-tree complex wavelet transform method to obtain the impulse response sub-signals of the eight single-carrier aero-engine rotors; finally, the average assembly performance index is extracted from the obtained eight single-carrier aero-engine rotor impulse response sub-signals , if the obtained average assembly performance index value is greater than or equal to 10, it is judged that the assembly of the aero-engine rotor is qualified; if the obtained average value is less than 10, it is judged to be unqualified and needs to be reworked. The problem with this method is that there is no guidance on the assembly of the aeroengine rotor.

Luoxin Precision Parts (Shanghai) Co., Ltd. proposed a coaxiality measurement equipment (a coaxiality measuring instrument. Publication number: CN202024752U). The device includes a pair of transmission spindles arranged on the main body of the instrument that are synchronously controlled by a synchronous mechanism. The inner ends of the transmission spindles are respectively provided with measuring heads and positioning reference planes; above the position between the measuring heads there is a sensor measuring head . It mainly solves the measurement of coaxiality and runout of existing precision parts. The problem with this method is that only measuring the coaxiality of the tested part does not solve the problem of poor coaxiality of the rotor after assembly.

Shenyang Liming Aero Engine (Group) Co., Ltd. proposed a clearance measurement method (a non-contact measurement method for the radial clearance of the engine rotor blade tip. Publication number: CN102175135A). This method adopts capacitance method measurement technology, and the measurement steps are as follows, first assemble the measurement system, calibrate the sensor, determine the relationship between the blade tip radial clearance and voltage, then fix the sensor on the blade, and finally measure the radial clearance of the engine rotor blade tip . The problem with this method is that it does not consider the influence of the axial installation surface on the rotor after assembly during the rotor assembly process.

The test object of aero-engine assembly is the turbine stator and rotor. Under the condition that the machining accuracy of the components meets the requirements, the final inspection depends on the state after installation and fit. The evaluation index is mainly the coaxiality parameter of the assembled rotor. The engine rotates to generate high pressure, and its rotor is composed of a number of single parts assembled together. Ideally, the axis of rotation of each part coincides with the axis of the entire engine. The high-speed rotation speed of a high-performance engine is greater than 10,000rpm, and the axial or radial deflection of a single component will inevitably cause the center of the turbine disc to deviate from the axis of rotation of the engine. Under such conditions, a very large centrifugal force will be generated, causing the rotor to rotate unbalanced , causing engine vibration, so ensuring the coaxiality of each component after assembly is the focus and difficulty of installation.

A model assembly that does not use the coaxiality optimization method, the axial and radial directions of each component have errors such as runout, eccentricity, and tilt due to the limitation of machining accuracy. If it is assembled directly and randomly, it may form a bending situation similar to "banana", that is, the upper part accumulates the eccentricity or tilt error of the lower parts, resulting in a huge overall yaw and tilt after assembly, resulting in the coaxiality of the engine rotor. Very poor, difficult to meet the requirements of use.

At present, domestic engine assembly still adopts traditional assembly methods, mainly manual testing with dial gauges. Assemble the engine from bottom to top, measure after assembling a component to ensure that the whole can meet the threshold condition of coaxiality after each addition of components, and then install another component upwards. Each time, the previous part is used as a reference, and the overall coaxiality is finally required to be within a certain range. This method consumes a lot of time and has a high possibility of rework, which greatly affects the efficiency of installation and the first-time success rate. Usually, a successful assembly takes 4 to 5 days. Moreover, because it is not the best assembly position, it usually needs to be disassembled and assembled 4 to 5 times, and workers are required to assemble with rich experience, and each assembly needs to undergo hot and cold processing. Therefore, the current aero-engine assembly method has low installation efficiency, is not easy to install, and has poor coaxiality after assembly, which affects engine performance.

Contents of the invention

Aiming at the deficiencies in the above-mentioned existing technologies, an aero-engine rotor assembly method and device based on capacitive sensing and four-jaw hydraulic chuck gripping are proposed to solve the problem of low coaxiality of the aero-engine rotor after assembly and achieve rotor assembly High rear coaxiality, reduced vibration, easy installation, high flexibility, and improved engine performance.

The purpose of the present invention is achieved like this:

An aero-engine rotor assembly method based on capacitive sensing and four-jaw hydraulic chuck gripping, the steps of the method are as follows:

Place the rotor under test on the self-aligning and tilting workbench and fix it; measure the axial capacitive sensor of the axial installation reference plane of the measured rotor for tilt adjustment; measure the axial installation reference plane of the radial installation reference plane. The radial capacitive sensor measures the radial installation reference plane for centering; the rotary turntable drives the measured rotor to rotate at a constant speed of 6~10r/min through the centering and tilting worktable, and measures the axis of the axial installation reference plane. The capacitive sensor is sampled at equal intervals on the axial installation reference plane of the rotor under test, and the radial capacitive sensor for measuring the radial installation reference plane is sampled at equal intervals on the radial installation reference plane of the rotor under test; the number of sampling points should meet 1000 to 2000 points per circle; the sampling data on the radial installation reference plane of the tested rotor is fitted by the least square circle to evaluate the eccentricity, and the sampling data on the axial installation reference plane of the tested rotor is passed through the minimum Two times the plane fitting to evaluate the amount of inclination; according to the size and angle of the eccentricity, adjust the centering knob of the self-aligning and tilting workbench; , until the self-aligning and tilting workbench satisfies that the eccentricity of the radial reference plane is in the range of 0-3μm, and the inclination of the axial reference plane is in the range of 0-2″; The capacitive sensor measures the axial installation measurement surface of the rotor under test, and the radial capacitance sensor for measuring the radial installation measurement surface measures the radial installation measurement surface of the rotor under test; the rotary table rotates at a constant speed of 6-10r/min, The axial capacitive sensors for measuring the axially installed measuring surface are sampled at equal intervals on the axially installed measuring surface of the rotor under test, and the radial capacitive sensors for measuring the radially installed measuring surface are respectively sampled at equal intervals on the radially installed measuring surface; sampling The number of points should meet 1000-2000 points per circle; the data sampled by the radial capacitive sensor measuring the radially installed measuring surface on the radially installed measuring surface of the rotor under test is fitted by the least square circle and evaluated for concentricity; The data sampled by the axial capacitive sensor that measures the axially installed measuring surface on the axially installed measuring surface of the rotor under test is fitted by a least squares plane and evaluated for verticality; combined with the radius of the axially installed measuring surface and the measured Measure the height difference between the rotor and the final assembled rotor to obtain the influence weight of the measured rotor on the coaxiality of the assembled rotor; measure all the rotors required for assembly separately to obtain the influence weight of each rotor on the coaxiality of the assembled rotor ; Use the genetic algorithm to carry out vector optimization on the weights of each rotor to obtain the assembly angle of each rotor, and the calculation method of the influence weight of the rotor coaxiality is: In the formula: C represents the concentricity of the radially installed measuring surface of the rotor under test, Indicates the eccentric angle of the fitting circle center of the radially installed measuring surface, H indicates the height difference between the rotor under test and the final assembled rotor, R indicates the radius of the axially installed measuring surface, P indicates the perpendicularity of the axially installed measuring surface of the tested rotor, θ represents the angle at which the highest point of the fitting plane of the axial installation measuring surface is located.

The structure of an aeroengine rotor assembly device based on capacitive sensing and four-jaw hydraulic chuck gripping is that the rotary shaft system is nested at the center of the base, and the rotary shaft system consists of a rotary main shaft, a worktable, and a rotary shaft. The pressure plate, the lower pressure plate of the rotary shaft, the photoelectric encoder, the code plate of the photoelectric encoder, the permanent magnet, the coil, the motor stator and the motor rotor are composed. The disk is arranged on the upper end of the rotary shaft, the rotary spindle is arranged on the upper end of the lower pressure plate of the rotary shaft, the code disc of the photoelectric encoder is nested on the outer ring of the lower pressure plate of the rotary shaft, and the photoelectric encoder is fixed inside the center of the base The lower part is located outside the code disc of the photoelectric encoder. The permanent magnet is sleeved on the outer ring of the rotary spindle and fixed on the upper end of the lower pressure plate of the rotary shaft. The coil is sleeved on the outer ring of the rotary spindle and fixed inside the base. 5-10cm above the magnet; the motor rotor is nested on the outer ring of the lower pressure plate of the rotary shaft, and is located at the lower part of the photoelectric encoder code disc, and the motor stator is fixed at the inner lower part of the center of the base, and is located at the lower part of the photoelectric encoder and the motor The outside of the rotor; the self-aligning and tilting worktable is arranged at the center of the rotary shaft system, and the four-jaw hydraulic chuck is arranged at the center of the self-aligning and tilting worktable; the door-shaped left column and the door-shaped right column are symmetrically distributed on the rotary shaft system The two sides of the door-shaped crossbeam are fixed on the base, and the two ends of the door-shaped beam are fixedly connected with the upper end of the door-shaped left column and the upper end of the door-shaped right column; the left upper column rod can be moved and adjusted from top to bottom on the door-shaped left column. The connecting piece and the left lower pole connecting piece, the left upper horizontal measuring rod is horizontally nested on the left upper pole connecting piece, the upper sensor adapter is fixedly connected with the left upper horizontal measuring pole, and the upper axial capacitive sensor is fixedly connected with the upper sensor adapter ; The lower left transverse measuring rod is horizontally nested on the lower left column connecting piece, the lower sensor adapter is fixedly connected with the lower left transverse measuring rod, and the lower axial capacitive sensor is fixedly connected with the lower sensor adapter; The right upper pole connecting piece and the right lower pole connecting piece are movably adjusted in turn from top to bottom, the right upper transverse measuring rod is horizontally nested on the right upper pole connecting piece, and the upper radial capacitive sensor is fixedly connected with the right upper transverse measuring pole; The lower right transverse measuring rod is horizontally nested on the connecting piece of the lower right column, and the lower radial capacitive sensor is fixedly connected with the lower right transverse measuring rod.

Compared with prior art, the characteristics of the present invention are:

The present invention can obtain the coaxiality weight of each rotor by measuring the concentricity and perpendicularity of each rotor, and then vector-optimize the coaxiality weight of each rotor to obtain a guiding installation angle, saving 40% of installation time and Cost, 98% one-time installation success rate, predictable installation progress, improve engine stability, reduce engine vibration, save engine fuel consumption, reduce _CO2 emissions, and reduce engine noise pollution.

Description of drawings:

Figure 1 is a schematic diagram of the structure of the four-probe measuring device

Figure 2 is a schematic diagram of the rotary shaft system

Part number in the picture: 1—base, 2—rotary shaft system, 2a—rotary spindle, 2b—worktable, 2c—upper pressure plate of rotary shaft, 2d—lower pressure plate of rotary shaft, 2e—photoelectric encoder, 2f— Photoelectric encoder code disc, 2g—permanent magnet, 2h—coil, 2i—motor stator, 2j—motor rotor, 3—alignment and tilting table, 4—four-jaw hydraulic chuck, 5a—door-shaped left column, 5b —door-shaped right column, 5c—door-shaped beam, 6a—lower left horizontal measuring rod, 6b—right lower horizontal measuring rod, 6c—left upper horizontal measuring rod, 6d—right upper horizontal measuring rod, 7a—left lower column connecting piece, 7b —The lower right pole connector, 7c—the upper left pole connector, 7d—the upper right pole connector, 8a—the lower axial capacitive sensor, 8b—the upper axial capacitive sensor, 9a—the lower radial capacitive sensor, 9b— Upper radial capacitive sensor, 10a—lower sensor adapter, 10b—upper sensor adapter.

detailed description

Below in conjunction with accompanying drawing, the present invention is described in further detail:

An aeroengine rotor assembly method and device based on capacitive sensing and four-jaw hydraulic chuck gripping. The method and device are as follows: a four-jaw hydraulic chuck 4 is arranged on the center position of a centering and tilting workbench 3 . The door-shaped left column 5a and the door-shaped right column 5b are symmetrically distributed on both sides of the rotary shaft system 2 and are fixed on the base 1. Solid connection. On the door-shaped left column 5a, the left upper column connector 7c and the left lower column connector 7a are movably adjusted sequentially from top to bottom, and the left upper horizontal measuring rod 6c is horizontally nested on the left upper column connector 7c, and the upper sensor The adapter 10b is fixedly connected to the upper left horizontal measuring rod 6c, and the upper axial capacitive sensor 8b is fixedly connected to the upper sensor adapter 10b; The component 10a is fixedly connected with the lower left lateral measuring rod 6a, and the lower axial capacitive sensor 8a is fixedly connected with the lower sensor adapter 10a. On the door-shaped right column 5b, the right upper column connecting piece 7d and the right lower column connecting piece 7b are movably adjusted sequentially from top to bottom, and the right upper horizontal measuring rod 6d is horizontally nested on the right upper column connecting piece 7d. The radial capacitive sensor 9b is fixedly connected with the upper right transverse measuring rod 6d; the lower right transverse measuring rod 6b is horizontally nested on the lower right pole connector 7b, and the lower radial capacitive sensor 9a is fixedly connected with the lower right transverse measuring rod 6b. The rotary shaft system 2 is nested in the center of the base 1, and the rotary shaft system 2 is composed of a rotary main shaft 2a, a worktable 2b, a rotary shaft upper pressure plate 2c, a rotary shaft lower pressure plate 2d, a photoelectric encoder 2e, a photoelectric encoder Composed of code disc 2f, permanent magnet 2g, coil 2h, motor stator 2i and motor rotor 2j, the workbench 2b is arranged on the upper end of the pressure plate 2c on the rotary shaft, and the pressure plate 2c on the rotary shaft is arranged on the upper end of the rotary main shaft 2a On the upper part, the rotary spindle 2a is arranged on the upper end of the lower pressure plate 2d of the rotary shaft, the photoelectric encoder code disc 2f is nested on the outer ring of the lower pressure plate 2d of the rotary shaft, and the photoelectric encoder 2e is fixed inside the center position of the base 1 The lower part is located outside the code disc 2f of the photoelectric encoder. The permanent magnet 2g is sleeved on the outer ring of the rotary spindle 2a and fixed on the upper end of the lower pressure plate 2d of the rotary shaft. The coil 2h is sleeved on the outer ring of the rotary spindle 2a and fixed on the Inside the base 1, 5-10 cm above the permanent magnet 2g; the motor rotor 2j is nested on the outer ring of the lower pressure plate 2d of the rotary shaft, and is located at the lower part of the photoelectric encoder code plate 2f, and the motor stator 2i is fixed on the base 1 The inner lower part of the central position is located at the lower part of the photoelectric encoder 2e and the outer part of the motor rotor 2j; the rotary shaft system 2 drives the measured rotor to rotate at a constant speed of 6-10r/min, and the lower axial capacitive sensor 8a is in the axial direction of the measured rotor. Sampling at equal intervals is carried out on the installation datum plane, and the lower radial capacitive sensor 9a is sampled at equal intervals on the radial installation datum plane of the rotor under test. The sampling data on the installation datum plane is fitted by the least squares circle to evaluate the eccentricity, and the sampling data on the axial installation datum plane of the rotor under test is fitted by the least squares plane to evaluate the inclination; The workbench 3 is arranged at the center of the rotary shaft system 2. According to the size and angle of the eccentricity, adjust the centering and tilting workbench 3 until the eccentricity of the radial reference plane is within the range of 0-3 μm; according to the eccentricity Size and angle, adjust the centering and tilting workbench 3 until the inclination of the axial reference plane is within the range of 0-2", and the upper right column connecting piece 7d is vertically nested on the upper side of the door-shaped right column 5b, The upper right horizontal measuring rod 6d is horizontally nested on the upper right rod connecting piece 7d, the upper radial capacitive sensor 9b is fixedly connected with the upper right horizontal measuring rod 6d, and the upper radial capacitive sensor 9b is used to measure the radial installation measuring surface of the rotor under test, The left upper pole connector 7c is vertically nested on the upper side of the door-shaped left column 5a, the left upper horizontal measuring rod 6c is horizontally nested on the left upper pole connector 7c, the upper axial capacitive sensor 8b and the upper sensor adapter 10b Fixed connection, the upper axial capacitive sensor 8b measures the axial installation measurement surface of the rotor under test; the rotary shaft system 2 rotates at a constant speed of 6-10r/min, and the upper radial capacitive sensor 9b is installed in the radial direction of the rotor under test for measurement Sampling at equal intervals on the surface, the upper axial capacitance sensor 8b samples at equal intervals on the axial installation measurement surface of the rotor under test; the number of sampling points should satisfy 1000-2000 points per revolution; of The data sampled on the radially installed measuring surface is fitted by the least square circle and the concentricity is evaluated; the data sampled by the upper axial capacitive sensor 8b on the axially installed measuring surface of the rotor under test is fitted by the least square plane And evaluate the verticality, combined with the radius of the axially installed measuring surface and the height difference between the tested rotor and the final assembled rotor, the influence weight of the tested rotor on the coaxiality of the assembled rotor is obtained; For all the rotors, the influence weights of each rotor on the rotor coaxiality after assembly are obtained; the weights of each rotor are vector optimized using the genetic algorithm to obtain the assembly angle of each rotor, and the calculation method of the influence weights of the rotor coaxiality is : In the formula: C represents the concentricity of the radially installed measuring surface of the rotor under test, Indicates the eccentric angle of the fitting circle center of the radially installed measuring surface, H indicates the height difference between the rotor under test and the final assembled rotor, R indicates the radius of the axially installed measuring surface, P indicates the perpendicularity of the axially installed measuring surface of the tested rotor, θ represents the angle at which the highest point of the fitting plane of the axial installation measuring surface is located.

Claims (2)

1. An aeroengine rotor assembly method based on capacitive sensing and four-jaw hydraulic chuck gripping, is characterized in that the method is: the rotor to be tested is placed on the centering and tilting workbench and fixed; the measuring axis is installed The axial capacitive sensor of the datum plane measures the axial installation datum plane of the rotor under test for tilt adjustment; the radial capacitive sensor for measuring the radial installation datum plane measures the radial installation datum plane for centering; the rotary turntable The centering and tilting workbench drives the tested rotor to rotate at a constant speed of 6-10r/min, and the axial capacitive sensor for measuring the axial installation datum plane samples at equal intervals on the axial installation datum plane of the tested rotor, and measures The radial capacitive sensor of the radial installation datum plane is sampled at equal intervals on the radial installation datum plane of the rotor under test; the number of sampling points should satisfy 1000-2000 points per revolution; The sampling data is fitted by the least square circle to evaluate the eccentricity, and the sampled data on the axial installation reference plane of the rotor to be tested is fitted by the least square plane to evaluate the inclination; according to the size and angle of the eccentricity, adjust The centering knob of the centering and tilting workbench; according to the size and angle of the inclination, adjust the centering and tilting knob of the centering and tilting workbench until the centering and tilting workbench meets the eccentricity of the radial reference plane between 0 and In the range of 3μm, the inclination of the axial reference plane is in the range of 0~2″; the axial capacitive sensor measuring the axial installation measuring surface measures the axial installation measurement surface of the rotor under test, and measures the axial installation measurement surface of the radial installation measurement surface. The radial capacitance sensor measures the radial installation measurement surface of the rotor under test; the rotary turntable rotates at a constant speed of 6~10r/min, and the axial capacitance sensor for measuring the axial installation measurement surface is installed on the axial installation measurement of the rotor under test. Sampling at equal intervals on the surface, measuring radial capacitive sensors on the radially installed measuring surface are sampled at equal intervals on the radially installed measuring surface; the number of sampling points should satisfy 1000-2000 points per circle; The data sampled by the capacitive sensor on the radially installed measuring surface of the tested rotor is fitted by the least square circle and evaluated for concentricity; the axial capacitive sensor that measures the axially installed measuring surface is installed on the axially The data sampled on the measuring surface is fitted by the least squares plane and evaluated for verticality; combined with the radius of the axially installed measuring surface and the height difference between the measured rotor and the final assembled rotor, the coaxiality of the rotor after assembly is obtained measure all the rotors required for assembly respectively, and obtain the influence weights of each rotor on the rotor coaxiality after assembly; use the genetic algorithm to carry out vector optimization on the weights of each rotor, and obtain the assembly angle of each rotor, and the rotor The calculation method of the influence weight of coaxiality is: In the formula: C represents the concentricity of the radially installed measuring surface of the rotor under test, Indicates the eccentric angle of the fitting circle center of the radially installed measuring surface, H indicates the height difference between the rotor under test and the final assembled rotor, R indicates the radius of the axially installed measuring surface, P indicates the perpendicularity of the axially installed measuring surface of the tested rotor, θ represents the angle at which the highest point of the fitting plane of the axial installation measuring surface is located. 2. An aeroengine rotor assembly device based on capacitive sensing and four-jaw hydraulic chuck gripping, is characterized in that the rotary shaft system (2) is nested on the center position of the base (1), and the rotary shaft system ( 2) Composed of rotary spindle (2a), worktable (2b), rotary shaft upper pressure plate (2c), rotary shaft lower pressure plate (2d), photoelectric encoder (2e), photoelectric encoder code disc (2f), permanent Magnets (2g), coils (2h), motor stators (2i) and motor rotors (2j), the workbench (2b) is arranged on the upper end of the upper pressure plate (2c) on the rotary shaft, and the upper pressure plate (2c) on the rotary shaft ( 2c) Arranged on the upper end of the rotary spindle (2a), the rotary spindle (2a) is arranged on the upper end of the lower pressure plate (2d) of the rotary shaft, and the photoelectric encoder code disc (2f) is nested on the lower pressure plate (2d) of the rotary shaft ) on the outer ring, the photoelectric encoder (2e) is fixed on the inner lower part of the center of the base (1), and is located outside the code disc (2f) of the photoelectric encoder, and the permanent magnet (2g) is sleeved on the outer ring of the rotary spindle (2a) and fixed on the upper end of the lower pressure plate (2d) of the rotary shaft, the coil (2h) is sleeved on the outer ring of the rotary shaft (2a), and fixed inside the base (1), 5- 10cm; the motor rotor (2j) is nested on the outer ring of the lower pressure plate (2d) of the rotary shaft, and is located at the bottom of the photoelectric encoder code plate (2f), and the motor stator (2i) is fixedly fitted in the center of the base (1) The inner lower part is located at the lower part of the photoelectric encoder (2e) and the outside of the motor rotor (2j); the centering and tilting workbench (3) is arranged at the center of the rotary shaft system (2), and the four-jaw hydraulic chuck (4) is arranged At the center position of the centering and tilting workbench (3); the door-shaped left column (5a) and the door-shaped right column (5b) are symmetrically distributed on both sides of the rotary shaft system (2) and fixed on the base (1) On the top, the two ends of the door-shaped crossbeam (5c) are fixedly connected with the upper end of the door-shaped left column (5a) and the upper end of the door-shaped right column (5b); on the door-shaped left column (5a) from top to bottom, it can be moved and adjusted sequentially. The left upper pole connecting piece (7c) and the left lower pole connecting piece (7a), the left upper transverse measuring pole (6c) is horizontally nested on the left upper pole connecting piece (7c), the upper sensor adapter (10b) and the left upper transverse The measuring rod (6c) is fixedly connected, and the upper axial capacitive sensor (8b) is fixedly connected with the upper sensor adapter (10b); the lower left horizontal measuring rod (6a) is horizontally nested on the The sensor adapter (10a) is fixedly connected with the left lower transverse measuring rod (6a), and the lower axial capacitive sensor (8a) is fixedly connected with the lower sensor adapter (10a); on the door-shaped right column (5b) from top to The lower right upper pole connecting piece (7d) and the right lower pole connecting piece (7b) are movably adjusted in turn, and the upper right horizontal measuring pole (6d) is horizontally nested on the right upper pole connecting piece (7d), and the upper radial The capacitive sensor (9b) is fixedly connected with the upper right horizontal measuring rod (6d); Horizontal measuring rod (6b) is fixedly connected .