Stacking method taking into account elastic deformation of mounting edges of aeroengine rotor parts

Abstract

The application discloses a stacking method considering elastic deformation of an installation edge of an aero-engine rotor part, and comprises the following steps: defining a global coordinate system of an assembly body; determining a machining error matrix and a high-low point position matrix of the installation edge of each stage rotor according to installation edge end jump and column jump measurement data; determining an installation phase matrix of the i-stage rotor; determining a positioning error matrix caused by coordinate translation transformation and a directional error matrix caused by coordinate rotation transformation after the n-stage rotor is assembled; determining an installation stop mouth matching error matrix caused by elastic deformation of the installation edge; determining global positioning and directional matrices of the k-stage rotor after translation, rotation and high-low point corresponding elastic deformation transformation; then determining a global positioning and directional matrix of the assembly body, and determining a stacking optimization model of concentricity and coaxiality of the n-stage rotor; and finally, searching for and calculating the installation phase of each stage rotor by using a genetic algorithm according to the optimization model.

Description

Technical Field

[0001] This invention relates to the field of aircraft engine maintenance and assembly, and in particular to a stacking method that takes into account the elastic deformation of the mounting edges of aircraft engine rotor parts. Background Technology

[0002] The assembly quality of aero-engine rotors directly affects their service performance, therefore strict control must be exercised over each assembly stage. During assembly, due to machining errors in aero-engine rotor parts, their actual dimensions differ from their ideal values, exhibiting skewnesses of varying phases and sizes. Even if individual parts meet requirements, the assembled assembly often results in defects. Stacking optimization aims to calculate the dimensional skewness of each rotor stage and improve phase to ensure the final dimensional characteristics meet requirements. However, current stacking methods assume aero-engine rotor parts are rigid bodies, neglecting deformation of mounting edges during stacking. In actual assembly, elastic deformation of mounting edges due to bolt preload and interference fits is a real phenomenon. These deformations affect the relative positions and angles of each rotor stage during assembly, deviating from the rigidity assumption. Therefore, existing rigid-body-assumption stacking algorithms are ineffective in practical applications, failing to achieve stacking optimization and impacting assembly efficiency and first-pass success rate. Summary of the Invention

[0003] The purpose of this invention is to provide a stacking method that takes into account the elastic deformation of the mounting edge of aero-engine rotor parts, overcoming the shortcomings of the original rigid assumption stacking optimization scheme.

[0004] To solve the above-mentioned technical problems, the present invention adopts the following technical solution:

[0005] A stacking method considering the elastic deformation of the mounting edges of aero-engine rotor parts includes the following steps: A. Defining the global coordinate system of the assembly; B. Calculating the machining error matrix of the i-th stage rotor during assembly; C. Calculating the fit error matrix caused by elastic deformation at the mating point between the i-th stage rotor and the (i+1)-th stage rotor during assembly; D. Determining the mounting phase matrix of the i-th stage rotor during the aero-engine rotor assembly process; E. After assembly, accumulating the coaxiality deviation matrices of each stage rotor to determine the global positioning and orientation matrix of the assembly after assembling the n-th stage rotor of the aero-engine; F. Determining the center position of the aero-engine rotor after assembly, and determining the concentricity of the front and rear mounting stops of the assembly based on the coordinates of the center position; G. Determining the concentricity stacking optimization model based on the concentricity of the front and rear mounting stops of the assembly, and using a genetic algorithm to optimize and calculate the mounting phase of each stage rotor to determine the optimal stacking assembly angle of each stage rotor; H. Finally, setting the optimal assembly θ... riThe angle is substituted into the formula for calculating the concentricity of the assembly, and the solution is obtained to predict its value.

[0006] The entire scheme is as follows: Define the global coordinate system of the assembly; determine the machining error matrix and high / low point position matrix based on the end runout and column runout measurement data of each level of rotor installation edge; determine the installation phase matrix of the i-th level rotor; determine the positioning error matrix caused by coordinate translation transformation and the orientation error matrix caused by coordinate rotation transformation after the n-th level rotor is assembled; then determine the installation stop fit error matrix caused by elastic deformation of the installation edge; next, determine the global positioning and orientation matrix of the k-th level rotor after translation, rotation and corresponding elastic deformation transformation of high / low points; then determine the global positioning and orientation matrix of the assembly, determine the stacking optimization model of concentricity and coaxiality of the n-th level rotor; finally, use a genetic algorithm to optimize and calculate the installation phase of each level of rotor based on the optimization model.

[0007] This solution provides a novel stacking optimization approach that considers the elastic deformation of the mounting edges of aero-engine rotor components during assembly. This guides the assembly of multi-stage rotors for aero-engines, achieving optimal dimensional parameters such as concentricity after assembly and meeting design requirements.

[0008] As a further preferred embodiment of the present invention, the definition of the global coordinate system of the assembly in step A specifically involves selecting the end jump center of the reference surface required by the aero-engine assembly process as the coordinate origin, the axis perpendicular to the end surface and passing through the coordinate origin as the Z-axis of the coordinate system, and the axis passing through the coordinate origin, perpendicular to the Z-axis and passing through the zero phase point position defined by the reference surface process as the X-axis, thereby establishing the global coordinate system of the assembly.

[0009] As a further preferred embodiment of the present invention, the machining error matrix of the i-th stage rotor during the assembly process in step B is specifically calculated as follows:

[0010] The positioning error caused by translational changes under three-dimensional coordinate transformation is represented by a 3×1 vector. The orientation error caused by rotational changes under three-dimensional coordinate transformation is represented by a 3×3 matrix.

[0011] As a further preferred embodiment of the present invention, the specific calculation of the fit error matrix caused by elastic deformation at the mating point between the i-th stage rotor and the (i+1)-th stage rotor during the assembly process in step C is as follows:

[0012] in The matrix representing the rotational fit error caused by the elastic deformation of the end face of the mounting edge of the i-th and i+1-th stage rotor stops is represented by a 3×3 matrix. The matrix representing the translational fit error caused by the elastic deformation of the cylindrical surface of the mounting edge of the i-th and i+1-th rotor stops is represented by a 3×1 matrix.

[0013] As a further preferred embodiment of the present invention, the installation phase matrix of the i-th stage rotor during the assembly process of the aero-engine rotor in step D is specifically as follows:

[0014]

[0015] S ri The rotation matrix θ of the rotor axial measurement surface relative to the reference plane in this stage. ri Let be the rotation angle of the i-th stage rotor mounting position relative to the initial mounting position about the reference axis.

[0016] As a further preferred embodiment of the present invention, the step E of accumulating the coaxiality deviation matrix of each rotor stage specifically occurs after the aero-engine rotor is assembled, after each rotor stage undergoes translation, rotation, and elastic deformation transformation corresponding to high and low points.

[0017] As a further preferred embodiment of the present invention, the global positioning and orientation matrix of the assembly after the n-stage rotor of the aero-engine is determined by progressively accumulating the coaxiality deviation matrices of each stage of the rotor is as follows:

[0018]

[0019] As a further preferred embodiment of the present invention, the determination of the center position of the aero-engine rotor in step F is specifically obtained by the following formula: The concentricity of the front and rear mounting stops of the assembly in step F is determined by the following formula: Where matrix I is a 2-order identity matrix.

[0020] As a further preferred embodiment of the present invention, the concentricity stacking optimization model in step G is specifically as follows: c(θ) ri ) = min(c), i = 1, 2, ..., n, θ ri =0°~360°, using a genetic algorithm to optimize the installation phase of each rotor stage, and determining the optimal stacking and assembly angle of each rotor stage, specifically using c as the objective function, θ ri For variables.

[0021] Compared with the prior art, the present invention can achieve at least one of the following beneficial effects:

[0022] 1. The method in this scheme can guide the assembly of multi-stage rotors of aero engines, achieve optimal dimensional parameters such as concentricity after assembly, meet design requirements, improve the assembly quality of aero engine rotors, and increase the first-time success rate.

[0023] 2. Using the method described in the scheme, based on the measurement data of the aero-engine mounting edge, and taking into account the elastic deformation of the mounting edge, optimization calculations can be performed with the concentricity and coaxiality of the aero-engine assembly as the optimization objectives. This yields specific concentricity and coaxiality data for each stage of the rotor and the optimal mounting phase for each stage, thereby guiding the assembly of the aero-engine rotor and meeting technical requirements. Attached Figure Description

[0024] Figure 1 A schematic diagram showing the skew caused by positioning and orientation errors during the assembly of an aero-engine rotor. Detailed Implementation

[0025] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, 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. The components of the embodiments of the present invention described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.

[0026] Therefore, the following detailed description of the embodiments of the invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely to illustrate selected embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the invention without inventive effort are within the scope of protection of the invention.

[0027] It should be noted that, unless otherwise specified, the embodiments and features described in this invention can be combined with each other.

[0028] It should be noted that similar labels and letters in the following figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

[0029] In the description of this invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship commonly used when the product of this invention is in use, or the orientation or positional relationship commonly understood by those skilled in the art. They are only used for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention. In addition, the terms "first," "second," etc., are only used to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0030] In the description of this invention, it should also be noted that, unless otherwise explicitly specified and limited, the terms "set," "install," "connect," and "link" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances. Specific Implementation Example 1:

[0032] Figure 1 This paper presents a stacking method considering the elastic deformation of the mounting edges of aero-engine rotor parts, including the following steps: A. Define the global coordinate system of the assembly; B. Calculate the machining error matrix of the i-th stage rotor during assembly; C. Calculate the fit error matrix caused by elastic deformation at the mating point between the i-th stage rotor and the (i+1)-th stage rotor during assembly; D. Determine the mounting phase matrix of the i-th stage rotor during the aero-engine rotor assembly process; E. After assembly, accumulate the coaxiality deviation matrices of each stage rotor to determine the global positioning and orientation matrix of the assembly after the n-th stage rotor is assembled; F. Determine the center position of the aero-engine rotor after assembly, and determine the concentricity of the front and rear mounting stops of the assembly based on the center position coordinates; G. Determine the concentricity stacking optimization model based on the concentricity of the front and rear mounting stops of the assembly, and use a genetic algorithm to optimize and calculate the mounting phase of each stage rotor to determine the optimal stacking assembly angle of each stage rotor; H. Finally, calculate the optimal assembly angle θ. ri The angle is substituted into the formula for calculating the concentricity of the assembly, and the solution is obtained to predict its value.

[0033] The entire scheme is as follows: Define the global coordinate system of the assembly; determine the machining error matrix and high / low point position matrix based on the end runout and column runout measurement data of each level of rotor installation edge; determine the installation phase matrix of the i-th level rotor; determine the positioning error matrix caused by coordinate translation transformation and the orientation error matrix caused by coordinate rotation transformation after the n-th level rotor is assembled; then determine the installation stop fit error matrix caused by elastic deformation of the installation edge; next, determine the global positioning and orientation matrix of the k-th level rotor after translation, rotation and corresponding elastic deformation transformation of high / low points; then determine the global positioning and orientation matrix of the assembly, determine the stacking optimization model of concentricity and coaxiality of the n-th level rotor; finally, use a genetic algorithm to optimize and calculate the installation phase of each level of rotor based on the optimization model.

[0034] This solution provides a novel stacking optimization approach that considers the elastic deformation of the mounting edges of aero-engine rotor components during assembly. This guides the assembly of multi-stage rotors for aero-engines, achieving optimal dimensional parameters such as concentricity after assembly and meeting design requirements. Specific Implementation Example 2:

[0036] This embodiment further explains step A based on specific embodiment 1. In step A, the global coordinate system of the assembly is defined by selecting the end jump center of the reference surface required by the aero-engine assembly process as the coordinate origin, the axis perpendicular to the end surface and passing through the coordinate origin as the Z-axis of the coordinate system, and the axis passing through the coordinate origin, perpendicular to the Z-axis and passing through the zero phase point position defined by the reference surface process as the X-axis, thus establishing the global coordinate system of the assembly. Specific Implementation Example 3:

[0038] This embodiment further explains step B based on specific embodiment 1. In step B, the machining error matrix of the i-th stage rotor during the assembly process is calculated as follows:

[0039] The positioning error caused by translational changes under three-dimensional coordinate transformation is represented by a 3×1 vector. The orientation error caused by rotational changes under three-dimensional coordinate transformation is represented by a 3×3 matrix. Specific Implementation Example 4:

[0041] This embodiment further explains step C based on specific embodiment 1. In step C, the specific calculation of the fit error matrix caused by elastic deformation at the mating point between the i-th stage rotor and the (i+1)-th stage rotor during the assembly process is as follows:

[0042] in The matrix representing the rotational fit error caused by the elastic deformation of the end face of the mounting edge of the i-th and i+1-th stage rotor stops is represented by a 3×3 matrix. The matrix representing the translational fit error caused by the elastic deformation of the cylindrical surface of the mounting edge of the i-th and i+1-th rotor stops is represented by a 3×1 matrix. Specific Implementation Example 5:

[0044] This embodiment further explains step D based on specific embodiment 1. In step D, the installation phase matrix of the i-th stage rotor during the aero-engine rotor assembly process is determined as follows:

[0045] S ri The rotation matrix θ of the rotor axial measurement surface relative to the reference plane in this stage. ri Let be the rotation angle of the i-th stage rotor mounting position relative to the initial mounting position about the reference axis. Specific Implementation Example 6:

[0047] This embodiment further explains step E based on specific embodiment 1. In step E, the coaxiality deviation matrix of each level of rotor is accumulated step by step. Specifically, this occurs after the aero-engine rotor is assembled and the rotors of each level undergo translation, rotation and elastic deformation transformation corresponding to high and low points. Specific Implementation Example 7:

[0049] This embodiment further explains the global positioning and orientation matrix of the assembly based on specific embodiment 1. The coaxiality deviation matrices of each rotor stage are accumulated level by level to determine the global positioning and orientation matrix of the assembly after assembling the n-stage rotor of the aero-engine, which is as follows: Specific Implementation Example 8:

[0051] This embodiment further explains step F based on specific embodiment 1. The determination of the center position of the aero-engine rotor in step F is specifically obtained by the following formula: The concentricity of the front and rear mounting stops of the assembly in step F is determined by the following formula: Where matrix I is a 2-order identity matrix. Specific Implementation Example 9:

[0053] This embodiment further explains step G based on specific embodiment 1. The concentricity stacking optimization model in step G is as follows: c(θ) ri ) = min(c), i = 1, 2, ..., n, θ ri =0°~360°, using a genetic algorithm to optimize the installation phase of each rotor stage, and determining the optimal stacking and assembly angle of each rotor stage, specifically using c as the objective function, θ ri The variable is '('). Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A stacking method considering the elastic deformation of the mounting edge of an aero-engine rotor component, characterized in that: The steps include: A. Defining the global coordinate system of the assembly; B. Calculating the machining error matrix of the i-th stage rotor during the assembly process; C. Calculate the fit error matrix caused by elastic deformation at the fit point between the i-th stage rotor and the (i+1)-th stage rotor during the assembly process; D. Determine the installation phase matrix of the i-th stage rotor during the assembly process of the aero-engine rotor; E. After assembly, the coaxiality deviation matrices of each stage of the rotor are accumulated step by step to determine the global positioning and orientation matrix of the assembly after the n-stage rotor of the aero-engine is assembled. F. After assembly, determine the center position of the aero-engine rotor, and determine the concentricity of the front and rear mounting stops of the assembly based on the center position coordinates; G. Based on the concentricity of the front and rear mounting stops of the assembly, determine the concentricity stacking optimization model, and use a genetic algorithm to optimize and calculate the installation phase of each stage of the rotor, determining the optimal stacking assembly angle of each stage of the rotor; H. Finally, perform the optimal assembly... The angle is substituted into the assembly concentricity calculation formula and solved to predict its position; the determination of the center position of the aero-engine rotor in step F is specifically obtained through the following formula: The concentricity of the front and rear mounting stops of the assembly in step F is determined by the following formula: Where matrix I is a 2-order identity matrix. This is the rotation matrix of the rotor's axial measurement surface relative to the reference plane. Let be the rotation angle of the i-th stage rotor mounting position relative to the initial mounting position about the reference axis. The positioning error is caused by translational changes under three-dimensional coordinate transformation; among which The matrix represents the rotational fit error matrix caused by the elastic deformation of the end face of the mounting edge of the i-th stage rotor and the (i+1)-th stage rotor stop. This represents the translational fit error matrix of the mounting edges of the i-th and i+1-th stage rotors due to the elastic deformation of the cylindrical surface.

2. The stacking method considering the elastic deformation of the mounting edge of aero-engine rotor parts according to claim 1, characterized in that: In step A, defining the global coordinate system of the assembly specifically involves selecting the end point of the reference surface required by the aero-engine assembly process as the origin of the coordinate system, the axis perpendicular to the reference surface and passing through the origin of the coordinate system as the Z-axis, and the axis passing through the origin of the coordinate system, perpendicular to the Z-axis, and passing through the zero-phase point position defined by the reference surface process as the X-axis, thus establishing the global coordinate system of the assembly.

3. The stacking method considering the elastic deformation of the mounting edge of aero-engine rotor parts according to claim 2, characterized in that: In step B, the machining error matrix of the i-th stage rotor during the assembly process is calculated as follows: .

4. The stacking method considering the elastic deformation of the mounting edge of aero-engine rotor parts according to claim 3, characterized in that: In step C, the specific calculation of the fit error matrix at the mating point between the i-th stage rotor and the (i+1)-th stage rotor during the assembly process, due to elastic deformation, is as follows: , This represents the rotational fit error matrix of the mounting edges of the i-th and i+1-th stage rotors due to the elastic deformation of the end faces.

5. The stacking method considering the elastic deformation of the mounting edge of the aero-engine rotor parts according to claim 4, characterized in that: In step D, the installation phase matrix of the i-th stage rotor during the aero-engine rotor assembly process is determined as follows: .

6. The stacking method considering the elastic deformation of the mounting edge of aero-engine rotor parts according to claim 1, characterized in that: In step E, the coaxiality deviation matrix of each rotor is accumulated step by step. This occurs after the aero-engine rotor is assembled and after each rotor undergoes translation, rotation, and elastic deformation corresponding to high and low points.

7. The stacking method considering the elastic deformation of the mounting edge of aero-engine rotor parts according to claim 5, characterized in that: The coaxiality deviation matrices of each rotor stage are accumulated sequentially to determine the global positioning and orientation matrix of the assembly after the n-stage rotor of the aero-engine is assembled, as follows: .

8. The stacking method considering the elastic deformation of the mounting edge of aero-engine rotor parts according to claim 7, characterized in that: The concentricity stacking optimization model in step G is as follows: When using a genetic algorithm to optimize and calculate the installation phase of each rotor stage, and determining the optimal stacking and assembly angle of each rotor stage, the objective function is specifically c. For variables.

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