CN103776368B - Gas and magnetism composite supporting type aero-engine rotor assembling method and device based on concentricity optimization - Google Patents

Abstract

The rotor assembly method and device of an aero-magnetic composite support type aero-engine based on concentricity optimization belong to the mechanical assembly technology. The measurement method and device are based on the aeromagnetic combination of the rotary shaft system to determine the rotary reference; the angular positioning of the turntable is determined based on the induction synchronizer; based on the four-probe measurement device, the radial error of the rotor radial assembly surface and the axial assembly surface Tilt error, to get the influence weight of the rotor on the coaxiality of the rotor after assembly; measure all the rotors required for assembly respectively, and obtain the influence weight of each rotor on the coaxiality of the rotor after assembly; calculate the weight of each rotor by vector Optimized to get the assembly angle of each rotor. The invention can effectively solve the problem of low coaxiality of the aeroengine rotor after assembly, and has the characteristics of high coaxiality after assembly of the rotor, reduced vibration, easy installation, high flexibility and improved engine performance.

Description

Method and device for aero-engine rotor assembly based on concentricity optimization

technical field

The invention belongs to mechanical assembly technology, and mainly relates to an assembly method and device for an aero-magnetic composite support type aero-engine rotor based on concentricity optimization.

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 damage tolerance 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 uses 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 prior art, a concentricity optimization-based aeromagnetic composite support type aero-engine rotor assembly method and device is proposed to solve the problem of low coaxiality of the aero-engine rotor after assembly and to achieve coaxiality after rotor assembly. The purpose of high-strength, reduce vibration, easy installation, high flexibility, improve engine performance.

The purpose of the present invention is achieved like this:

The structure of an aero-magnetic compound supported aero-engine rotor assembly device based on concentricity optimization 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, a pressure plate on the rotary shaft, The lower pressure plate of the rotary shaft, the fixed length of the induction synchronizer, the sliding rule of the induction synchronizer, the permanent magnet and the coil are composed. Above, the rotary spindle is arranged on the upper end of the lower pressure plate of the rotary shaft, the sliding rule of the induction synchronizer is nested on the outer ring of the lower pressure plate of the rotary shaft, and the fixed length of the induction synchronizer is fixed on the lower part of the inner side of the center of the base, and is located on the induction Above the slider of the synchronizer, the permanent magnet is set 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 set on the outer ring of the rotary spindle and fixed inside the base, 5-10cm above the permanent magnet The self-aligning and tilting worktable is arranged at the center of the rotary shaft system, and the three-jaw hydraulic chuck is arranged at the center of the self-aligning and tilting worktable. The left motion guide rail and the right motion guide rail are symmetrically distributed on the base on both sides of the rotary shaft system. The left column is installed on the left motion guide rail, and the right column is installed on the right motion guide rail. The left column can be moved and adjusted from top to bottom. The left upper pole connecting piece and the left lower pole connecting piece are set on the ground, the left upper horizontal measuring rod is horizontally nested on the left upper pole connecting piece, the upper lever type inductive sensor is fixedly connected with the left upper horizontal measuring rod; the left lower horizontal measuring rod is horizontally nested in the On the left lower pole connecting piece, the lower lever type inductive sensor is fixedly connected with the left lower transverse measuring rod. On the right column, the upper right column connecting piece and the right lower column connecting piece are movably adjusted in sequence from top to bottom. The upper right horizontal measuring rod is horizontally nested on the right upper column connecting piece. The measuring rod is fixedly connected; the lower right horizontal measuring rod is horizontally nested on the connecting piece of the lower right column rod, and the lower telescopic inductive sensor is fixedly connected with the lower right horizontal 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 figure: 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—inductive synchronizer to length, 2f—inductive synchronizer slide rule, 2g—permanent magnet, 2h—coil, 3—alignment and tilting table, 4—three-jaw hydraulic chuck, 5a—left column, 5b—right column, 6a—left lower transverse measuring rod , 6b—lower right horizontal measuring rod, 6c—upper left horizontal measuring rod, 6d—upper right horizontal measuring rod, 7a—lower left column connecting piece, 7b—right lower column connecting piece, 7c—left upper column connecting piece, 7d— Right upper pole connector, 8a—lower lever type inductive sensor, 8b—upper lever type inductive sensor, 9a—down telescopic inductive sensor, 9b—upward telescopic inductive sensor, 10a—left motion guide rail, 10b—right motion guide rail.

Detailed ways

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

A method and device for assembling an aero-engine rotor based on concentricity optimization. The method and device are as follows: a three-jaw hydraulic chuck 4 is arranged on the center position of a centering and tilting workbench 3 . The left moving guide rail 10a and the right moving guide rail 10b are symmetrically distributed on the base 1 on both sides of the rotary shaft system 2, the left column 5a is installed on the left moving guide rail 10a, the right column 5b is installed on the right moving guide rail 10b, and on the left column 5a From top to bottom, the left upper pole connecting piece 7c and the left lower pole connecting piece 7a can be movably and adjusted sequentially. The left upper horizontal measuring pole 6c is horizontally nested on the left upper pole connecting piece 7c. The horizontal measuring rod 6c is fixedly connected; the left lower horizontal measuring rod 6a is horizontally nested on the left lower column connecting piece 7a, and the lower lever type inductive sensor 8a is fixedly connected with the left lower horizontal measuring rod 6a. On the right column 5b, the upper right column connecting piece 7d and the right lower column connecting piece 7b are movably adjusted sequentially from top to bottom, and the upper right horizontal measuring rod 6d is horizontally nested on the right upper column connecting piece 7d. The inductance 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 telescopic inductive 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, an upper pressure plate 2c of the rotary shaft, a lower pressure plate 2d of the rotary shaft, an induction synchronizer scale 2e, The induction synchronizer slide rule 2f, the permanent magnet 2g and the coil 2h are composed, the workbench 2b is arranged on the upper end of the upper end of the rotary shaft pressure plate 2c, and the upper end of the rotary shaft upper pressure plate 2c is arranged on the upper end of the rotary main shaft 2a, and the rotary main shaft 2a It is arranged on the upper end of the lower pressure plate 2d of the rotary shaft, the induction synchronizer sliding rule 2f is nested on the outer ring of the lower pressure plate 2d of the rotary shaft, and the induction synchronizer fixed length 2e is fixedly fitted on the inner lower part of the center position of the base 1, and is located at Above the sliding ruler 2f of the induction synchronizer, the permanent magnet 2g is set on the outer ring of the rotary main shaft 2a, and fixed on the upper end of the lower pressure plate 2d of the rotary shaft, and the coil 2h is set on the outer ring of the rotary main shaft 2a, and fixed inside the base 1 , at a distance of 5-10cm above the permanent magnet 2g; the rotary shaft system 2 drives the tested rotor to rotate at a constant speed of 6-10r/min, and the lower telescopic inductive sensor 9a is equally spaced on the axial installation reference plane of the tested rotor Sampling, the lower lever inductance sensor 8a samples at equal intervals on the radial installation reference plane of the rotor under test, and the number of sampling points should satisfy 1000 to 2000 points per revolution, and the sampling data on the radial installation reference plane of the rotor under test Evaluate the amount of eccentricity through least squares circle fitting, and evaluate the amount of inclination by fitting the sampling data on the axial installation reference plane of the rotor under test through least squares plane fitting; the self-aligning and tilting workbench 3 is arranged on the rotary axis At the center position of the 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 size and angle of the inclination, adjust the centering Tilting workbench 3 until the inclination of the axial reference plane is within the range of 0-2", the upper right column connecting piece 7d is vertically nested on the upper side of the right column 5b, and the upper right horizontal measuring rod 6d is horizontally nested in On the upper right pole connector 7d, the upper telescopic inductance sensor 9b is fixedly connected with the upper right horizontal measuring rod 6d, and the upper telescopic inductance sensor 9b is in contact with the axially installed measuring surface of the rotor under test, and the left upper pole connector 7c is vertical Nested on the upper side of the left column 5a, the upper left horizontal measuring rod 6c is horizontally nested on the left upper column connecting piece 7c, the upper lever type inductive sensor 8b is fixedly connected with the left upper horizontal measuring rod 6c, and the upper lever type inductive sensor 8b is connected to the upper left horizontal measuring rod 6c. The radially installed measuring surface of the measuring rotor is in contact; the rotary shaft system 2 rotates at a constant speed of 6 to 10 r/min, and the upper telescopic inductive sensor 9b samples at equal intervals on the axially installed measuring surface of the tested rotor, and the upper lever type inductive The sensor 8b samples at equal intervals on the radially installed measuring surface of the tested rotor; the number of sampling points should satisfy 1000-2000 points per revolution; the data sampled by the upper lever inductive sensor 8b on the radially installed measuring surface of the tested rotor The concentricity is evaluated by least squares circle fitting; the data sampled by the upper telescopic inductance sensor 9b on the axial installation measuring surface of the rotor under test is fitted by least squares plane and the verticality is evaluated, combined with the axial install The radius of the installed measuring surface and the height difference between the measured rotor and the final assembled rotor can be used to obtain the influence weight of the rotor on the coaxiality of the assembled rotor; measure all the rotors required for assembly separately, and obtain the coaxiality of each rotor to the assembled rotor. The influence weight of axiality; the weight of each rotor is optimized by genetic algorithm to obtain the assembly angle of each rotor, and the calculation method of the influence weight of 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 (1)

1. An aeromagnetic composite support type aero-engine rotor assembly device based on concentricity optimization, characterized in that the rotary shaft system (2) is nested at the center of the base (1), and the rotary shaft system (2) is composed of Rotary spindle (2a), worktable (2b), rotary shaft upper pressure plate (2c), rotary shaft lower pressure plate (2d), induction synchronizer scale (2e), induction synchronizer slide rule (2f), permanent magnet (2g) and a coil (2h), the workbench (2b) is arranged on the upper end of the upper end of the rotary shaft pressure plate (2c), and the upper end of the rotary shaft upper pressure plate (2c) is arranged on the upper end of the rotary main shaft (2a), The rotary spindle (2a) is arranged on the upper end of the lower pressure plate (2d) of the rotary shaft, the sliding rule of the induction synchronizer (2f) is nested on the outer ring of the lower pressure plate (2d) of the rotary shaft, and the length of the induction synchronizer (2e) It is fixed on the inner lower part of the center position of the base (1), and is located above the slider (2f) of the induction synchronizer; the permanent magnet (2g) is sleeved on the outer ring of the rotary main shaft (2a), and fixed on the lower pressure plate of the rotary shaft ( 2d) The upper end, the coil (2h) is sleeved on the outer ring of the rotary spindle (2a), and fixed inside the base (1), 5-10cm above the permanent magnet (2g); the centering and tilting workbench (3 ) is arranged at the center of the rotary shaft system (2), and the three-jaw hydraulic chuck (4) is arranged at the center of the centering and tilting table (3); the left moving guide rail (10a) and the right moving guide rail (10b) are symmetrical Distributed on the base (1) on both sides of the rotary shaft system (2), the left column (5a) is installed on the left motion guide rail (10a), and the right column (5b) is installed on the right motion guide rail (10b). The left upper pole connector (7c) and the left lower pole connector (7a) are movably and adjusted sequentially from top to bottom on the column (5a), and the left upper horizontal measuring rod (6c) is horizontally nested in the left upper pole connector ( 7c), the upper lever-type inductive sensor (8b) is fixedly connected with the left upper horizontal measuring rod (6c); 8a) It is fixedly connected with the lower left transverse measuring rod (6a); on the right upright post (5b), it can be moved and adjusted sequentially from top to bottom to set the upper right post connecting piece (7d) and the right lower post connecting piece (7b), the upper right The horizontal measuring rod (6d) is horizontally nested on the upper right column connecting piece (7d), and the upper telescopic inductive sensor (9b) is fixedly connected with the upper right horizontal measuring rod (6d); the lower right horizontal measuring rod (6b) is horizontally nested On the lower right mast connector (7b), the lower telescopic inductance sensor (9a) is fixedly connected with the lower right lateral measuring rod (6b).