Large-scale rotary equipment disc separation blade sorting optimization method considering eccentric error of blade disc

Abstract

The invention provides a large-scale rotary equipment disc separation blade sorting optimization method considering blade disc eccentric errors, which comprises the following steps of: 1, carrying out high-precision measurement on geometric errors and centroid coordinates of each stage of blade disc of an aero-engine to obtain geometric errors of assembly surfaces of each stage of blade disc; 2, according to the geometric error, the eccentricity of each stage of blade disc at the blade installation position in the global assembly coordinate system and the blade disc mass center coordinate are calculated, and unbalance disturbance generated by blade disc assembly eccentricity is determined; 3, measuring the mass of each blade, and calculating a mass moment vector corresponding to each blade by combining the distance between the mass center of each blade and the center of the blade disc; and 4, carrying out optimal sorting on the blades by taking the vector sum of all the blade mass moment vectors to eliminate the initial unbalance outside the blades as a target. According to the method, the unbalance influence caused by the change of the mass center of the blade disc and the eccentricity of the geometric axis of the blade disc at the height of the blade assembly surface is introduced, and the actual assembly condition can be reflected more truly.

Description

Technical Field

[0001] This invention relates to the field of mechanical assembly technology, and in particular to an optimized method for sorting blades in the disc separation of large rotating equipment, taking into account the eccentricity error of the impeller. Background Technology

[0002] The assembly relationship between blades and bladed disks in an aero-engine directly affects the rotor's dynamic balance and the overall stability of the engine. During actual assembly, factors such as bladed disk manufacturing errors, machining eccentricity, and inaccurate assembly positioning often cause the bladed disk's center of mass to deviate from its design axis from the geometric center at the blade assembly height, resulting in eccentricity errors. These eccentricities not only lead to initial imbalance within the bladed disk itself but also cumulatively affect the mass distribution of the blades assembled on it, leading to significant complex imbalances and impacting the reliability and safety of the entire engine.

[0003] Most current blade sequencing methods rely solely on blade mass or mass moment information, failing to adequately consider the impact of disk geometric eccentricity on overall imbalance. This leads to sequencing optimization results deviating from the actual optimal state, reducing the efficiency and accuracy of dynamic balancing. Therefore, a blade sequencing optimization method that considers the influence of disk eccentricity error is urgently needed to comprehensively improve the assembly quality and dynamic balance performance of multi-stage rotor systems. Summary of the Invention

[0004] The purpose of this invention is to solve the problem of stacking and assembling optimization of aero engines, and to propose an optimization method for the sorting of blades in the separation of large rotating equipment blades, taking into account the eccentricity error of the bladed disk.

[0005] This invention is achieved through the following technical solution: This invention proposes an optimization method for the sorting of blades in large rotating equipment that considers blade disk eccentricity error. The method specifically includes: Step 1: Perform high-precision measurement of the geometric errors and centroid coordinates of each stage of the aero-engine blade disk to obtain the geometric errors of the assembly surfaces of each stage of the blade disk; Step 2: Calculate the eccentricity of each stage of the blade disk at the blade installation position and the centroid coordinate of the blade disk in the global assembly coordinate system based on the geometric error, and determine the unbalance disturbance caused by the eccentricity of the blade disk assembly. Step 3: Measure the mass of each blade and, in conjunction with the distance between the blade's center of mass and the center of the blade disk, calculate the mass moment vector corresponding to each blade. Step 4: With the goal of eliminating the initial imbalance outside the blades by the vector sum of the mass moments of all blades, perform the optimal sorting of the blades, thereby improving the balance performance of the aero-engine considering the influence of blade disk eccentricity error.

[0006] Furthermore, the mass of each stage of the impeller, the height of the blade installation position, the eccentricity error and tilt error of the assembly surface between the centroid coordinate and the impeller were measured, and the results were obtained respectively. i mass of stage rotor Blade installation position height Homogeneous coordinates of the mass center .

[0007] Furthermore, based on the geometric error measurement results of each rotor stage and the assembly phase of each rotor stage within the assembly, the homogeneous rigid body transformation matrix of each rotor stage from the workpiece coordinate system to the global assembly coordinate system is calculated sequentially. :

[0008] In the formula, It is a 4×4 identity matrix. This is the rigid body transformation matrix of the upper rotor. For the first The rigid body translation matrix caused by the rotor height and eccentricity error. For the first The rotation matrix caused by the tilt error of the stage rotor. The rotation matrix is ​​caused by the assembly phase of the rotor in this stage. This refers to the assembly phase of the rotor relative to the rotor of the previous stage.

[0009] Furthermore, based on the rigid body transformation matrices of each rotor stage, the homogeneous coordinates of the two endpoints of the geometric axes of each rotor stage in the global assembly coordinate system are calculated according to the following formula. and Homogeneous coordinates of the centroid in the global assembly coordinate system :

[0010] In the formula, For the first i The magnitude of the eccentricity error of the stage rotor, For the first i The eccentricity error angle of the stage rotor, For the first i The height of the stage rotor.

[0011] Furthermore, based on the coordinates of the endpoints of the geometric axes of each rotor stage, the eccentricity of the geometric axes at the installation positions of the rotor blades at each stage is calculated. :

[0012] In the formula, and They are respectively of xand y Coordinate components, and They are respectively of x and y Coordinate components, and They are respectively of x and y Coordinate components.

[0013] Furthermore, the mass of each blade to be assembled is precisely measured. And calculate the radial distance from the centroid of each blade to the center of rotation of the bladed disk. Construct the mass moment of each blade ,in, i The blade is assembled in the first position. i On the stage rotor, j The serial number represents the blade.

[0014] Furthermore, step four specifically involves: Step 41: For the first i The unbalance caused by the eccentricity of the impeller assembly is calculated in the stage rotor. :

[0015] In the formula, and They are respectively of x and y Coordinate components, n For the first i The number of blades in the stage rotor; Step 42: Construct the first i The unbalance model of the stage rotor due to the vector sum of the blade mass moments is as follows:

[0016] in, Indicates the first i The sorting method selected for the stage rotors, Indicates the first i The serial number of the stage rotor blades is j The phase of the location of the blade. Represents all permutations of the set. Indicates in Sorting method i The static imbalance of the stage rotor due to the vector sum of the mass moments of the blades; Step 43: Using the first i The initial static imbalance of the stage disk in the assembly coordinate system is minimized, i.e. To optimize the objective, we perform a traversal or optimization algorithm to solve the problem and obtain the th... i Optimal blade arrangement sequence ; Step 44: Perform steps 41 to 43 sequentially on each stage of the rotor to obtain the optimal blade arrangement sequence for each stage of the rotor.

[0017] The beneficial effects of this invention are: 1. This invention breaks through the limitations of traditional blade sorting methods that only consider blade mass or mass moment, and introduces the influence of imbalance caused by the change of the blade disk centroid and the eccentricity of the blade disk geometric axis at the height of the blade assembly surface, which can more realistically reflect the actual assembly situation. 2. The present invention adopts the strategy of "disk separation + independent blade sorting" to support the hierarchical assembly optimization of multi-stage blade disk-blade combinations, which has stronger adaptability and flexibility in actual multi-stage rotor system assembly. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the aero-engine disk separation and assembly model proposed in this invention. Detailed Implementation

[0019] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0020] See Figure 1 This invention proposes an optimization method for the sorting of blades in large rotating equipment that considers blade disk eccentricity error. The method specifically includes: Step 1: Perform high-precision measurement of the geometric errors and centroid coordinates of each stage of the aero-engine blade disk to obtain the geometric errors of the assembly surfaces of each stage of the blade disk; Step 2: Calculate the eccentricity of each stage of the blade disk at the blade installation position and the centroid coordinate of the blade disk in the global assembly coordinate system based on the geometric error, and determine the unbalance disturbance caused by the eccentricity of the blade disk assembly. Step 3: Measure the mass of each blade and, in conjunction with the distance between the blade's center of mass and the center of the blade disk, calculate the mass moment vector corresponding to each blade. Step 4: With the goal of eliminating the initial imbalance outside the blades by the vector sum of the mass moments of all blades, perform the optimal sorting of the blades, thereby improving the balance performance of the aero-engine considering the influence of blade disk eccentricity error.

[0021] The mass of each stage of the impeller, the height of the blade installation position, the eccentricity error and tilt error of the assembly surface between the centroid coordinate and the impeller are measured, and the results are obtained respectively. i mass of stage rotor Blade installation position height Homogeneous coordinates of the centroid .

[0022] Based on the geometric error measurement results of each rotor stage and the assembly phase of each rotor stage in the assembly, the homogeneous rigid body transformation matrix of each rotor stage from the workpiece coordinate system to the global assembly coordinate system is calculated sequentially. :

[0023] In the formula, It is a 4×4 identity matrix. This is the rigid body transformation matrix of the upper-level rotor. For the first The rigid body translation matrix caused by the rotor height and eccentricity error. For the first The rotation matrix caused by the tilt error of the stage rotor. The rotation matrix is ​​caused by the assembly phase of the rotor in this stage. This refers to the assembly phase of the rotor relative to the rotor of the previous stage.

[0024] Based on the rigid body transformation matrices of each rotor stage, the homogeneous coordinates of the two endpoints of the geometric axes of each rotor stage in the global assembly coordinate system are calculated according to the following formula. and Homogeneous coordinates of the centroid in the global assembly coordinate system :

[0025] In the formula, For the first i The magnitude of the eccentricity error of the stage rotor, For the first i The eccentricity error angle of the stage rotor, For the first i The height of the stage rotor.

[0026] Based on the coordinates of the endpoints of the geometric axes of each rotor stage, the eccentricity of the geometric axes at the installation positions of the rotor blades at each stage can be calculated. :

[0027] In the formula, and They are respectively of x and y Coordinate components, and They are respectively of x and y Coordinate components, and They are respectively of x and y Coordinate components.

[0028] Accurately measure the mass of each blade to be assembled And calculate the radial distance from the centroid of each blade to the center of rotation of the bladed disk. Construct the mass moment of each blade ,in, i The blade is assembled in the first position. i On the stage rotor, j The serial number represents the blade.

[0029] Step four specifically involves: Step 41: For the first i The unbalance caused by the eccentricity of the impeller assembly is calculated in the stage rotor. :

[0030] In the formula, and They are respectively of x and y Coordinate components, n For the first i The number of blades in the stage rotor; Step 42: Construct the first i The unbalance model of the stage rotor due to the vector sum of the blade mass moments is as follows:

[0031] in, Indicates the first i The sorting method selected for the stage rotors, Indicates the first i The serial number of the stage rotor blades is j The phase of the location of the blade. Represents all permutations of the set. Indicates in Sorting method i The static imbalance of the stage rotor due to the vector sum of the mass moments of the blades; Step 43: Using the first i The initial static imbalance of the stage disk in the assembly coordinate system is minimized, i.e. To optimize the objective, a traversal or optimization algorithm (such as a genetic algorithm or simulated annealing algorithm) is used to solve the problem and obtain the th... i Optimal blade arrangement sequence ; Step 44: Perform steps 41 to 43 sequentially on each stage of the rotor to obtain the optimal blade arrangement sequence for each stage of the rotor.

[0032] like Figure 1 The image shown is a schematic diagram of the aero-engine disk separation and assembly model proposed in this invention. Figure 1 In the model shown, This serves as the coordinate system for the first-stage rotor workpiece, and also as the global coordinate system for the assembly. and These represent the geometric axes of the first-stage rotor and the second-stage rotor, respectively. and These represent the blade mounting heights of the first-stage rotor and the second-stage rotor, respectively. and These represent the heights of the first-stage rotor and the second-stage rotor, respectively. and These represent the geometric eccentricities of the first-stage rotor and the second-stage rotor at the blade mounting position height, respectively. and These represent the centroid coordinates of the first-stage and second-stage bladed disks in the assembly's global coordinate system, respectively.

[0033] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Anyone skilled in the art can make various modifications and alterations without departing from the spirit and scope of the present invention. Therefore, the scope of protection of the present invention should be determined by the claims.

Claims

1. A method for optimizing the sorting of blades in a large rotating equipment disc separation system, considering disc eccentricity error, characterized in that... The method is specifically as follows: Step 1: Perform high-precision measurement of the geometric errors and centroid coordinates of each stage of the aero-engine blade disk to obtain the geometric errors of the assembly surfaces of each stage of the blade disk; Step 2: Calculate the eccentricity of each stage of the blade disk at the blade installation position and the centroid coordinate of the blade disk in the global assembly coordinate system based on the geometric error, and determine the unbalance disturbance caused by the eccentricity of the blade disk assembly. Step 3: Measure the mass of each blade and, based on the distance between the blade's center of mass and the center of the blade disk, calculate the mass moment vector corresponding to each blade. Step 4: With the goal of eliminating the initial imbalance outside the blades by the vector sum of the mass moments of all blades, perform the optimal sorting of the blades, thereby improving the balance performance of the aero-engine considering the influence of blade disk eccentricity error.

2. The method according to claim 1, characterized in that, The mass of each stage of the impeller, the blade installation height, the eccentricity error and tilt error of the assembly surface between the centroid coordinate and the impeller, were measured, and the results were obtained respectively. i mass of stage rotor Blade installation position height Homogeneous coordinates of the centroid .

3. The method according to claim 2, characterized in that, Based on the geometric error measurement results of each rotor stage and the assembly phase of each rotor stage in the assembly, the homogeneous rigid body transformation matrix of each rotor stage from the workpiece coordinate system to the global assembly coordinate system is calculated sequentially. : In the formula, It is a 4×4 identity matrix. This is the rigid body transformation matrix of the upper-level rotor. For the first The rigid body translation matrix caused by the rotor height and eccentricity error. For the first The rotation matrix caused by the tilt error of the stage rotor. The rotation matrix is ​​caused by the assembly phase of the rotor in this stage. This refers to the assembly phase of the rotor relative to the rotor of the previous stage.

4. The method according to claim 3, characterized in that, Based on the rigid body transformation matrices of each rotor stage, the homogeneous coordinates of the two endpoints of the geometric axes of each rotor stage in the global assembly coordinate system are calculated according to the following formula. and Homogeneous coordinates of the centroid in the global assembly coordinate system : In the formula, For the first i The magnitude of the eccentricity error of the stage rotor, For the first i The eccentricity error angle of the stage rotor, For the first i The height of the stage rotor.

5. The method according to claim 4, characterized in that, Based on the coordinates of the endpoints of the geometric axes of each rotor stage, the eccentricity of the geometric axes at the installation positions of the rotor blades at each stage can be calculated. : In the formula, and They are respectively of x and y Coordinate components, and They are respectively of x and y Coordinate components, and They are respectively of x and y Coordinate components.

6. The method according to claim 5, characterized in that, Accurately measure the mass of each blade to be assembled And calculate the radial distance from the centroid of each blade to the center of rotation of the bladed disk. Construct the mass moment of each blade ,in, i The blade assembly is located at the... i On the stage rotor, j The serial number represents the blade.

7. The method according to claim 6, characterized in that, Step four specifically involves: Step 41: For the first i The unbalance caused by the eccentricity of the impeller assembly is calculated in the stage rotor. : In the formula, and They are respectively of x and y Coordinate components, n For the first i The number of blades in the stage rotor; Step 42: Construct the first i The unbalance model of the stage rotor due to the vector sum of the blade mass moments is as follows: in, Indicates the first i The sorting method selected for the stage rotors, Indicates the first i The serial number of the stage rotor blades is j The phase of the location of the blade. Represents all permutations of the set. Indicates in Sorting method i The static imbalance of the stage rotor due to the vector sum of the mass moments of the blades; Step 43: Using the first i The initial static imbalance of the stage disk is minimized in the assembly coordinate system, i.e. To optimize the objective, we perform a traversal or optimization algorithm to solve the problem and obtain the th... i Optimal blade arrangement sequence ; Step 44: Perform steps 41 to 43 sequentially on each stage of the rotor to obtain the optimal blade arrangement sequence for each stage of the rotor.

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