Stacking method considering elastic deformation of mounting edge of aero-engine rotor part

Abstract

The invention discloses a stacking method considering elastic deformation of mounting edges of aero-engine rotor parts, which comprises the following steps of: defining a global coordinate system of an assembly body, and determining a processing error matrix and a high-low point position matrix according to end jump and column jump measurement data of each stage of rotor mounting edge; determining an installation phase matrix of the ith-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 a mounting seam allowance matching error matrix caused by elastic deformation of the mounting edge; determining a global positioning and orientation matrix of the k-stage rotor after translation, rotation and high and low point corresponding elastic deformation transformation; and then determining a global positioning and orientation matrix of the assembly, determining a stacking optimization model of the concentricity and coaxiality of the n-stage rotors, and finally performing optimization calculation on the installation phase of each stage of rotor by using a genetic algorithm according to the optimization model. According to the method, the aero-engine rotor assembly quality is better, and the one-time success rate is higher.

Description

Technical Field

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

[0002] The rotor assembly quality of aircraft engines directly affects the service performance of aircraft engines, so each assembly link must be strictly controlled. During the assembly production process, due to the processing error of the parts of the aircraft engine rotor, the actual value of its size is different from the ideal value, and there are deviations of different phases and sizes. Although the individual parts meet the requirements, the assembled parts often fail to meet the requirements. The purpose of stacking optimization is to calculate the dimensional deviation of the rotors at each level and improve the phase so that the dimensional characteristics after assembly meet the final requirements. However, the current stacking methods all assume that the aircraft engine rotor parts are rigid bodies, and the deformation of the mounting edge is not considered during the stacking process. In the actual assembly process, the elastic deformation of the mounting edge caused by the bolt preload and interference fit is objective. These deformations will affect the relative position and angle of the rotors at each level during the assembly process, and deviate from the results of the rigid assumption. Therefore, the existing rigid body assumption stacking algorithm is not effective in practical applications, and the purpose of stacking optimization cannot be achieved, affecting the assembly efficiency and the one-time success rate. Summary of the invention

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

[0004] In order to solve the above technical problems, the present invention adopts the following technical solutions:

[0005] A stacking method considering the elastic deformation of the installation edge of the rotor parts of an aeroengine comprises 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 the assembly process; C. calculating the fitting error matrix caused by elastic deformation at the fitting point between the i-th stage rotor and the i+1-th stage rotor during the assembly process; D. determining the installation phase matrix of the i-th stage rotor during the assembly process of the aeroengine rotor; E. after assembly, accumulating the coaxiality deviation matrices of the rotors at each stage step by step to determine the global positioning orientation matrix of the assembly after the n-th stage rotor of the aeroengine is assembled; F. determining the center position of the aeroengine rotor after assembly, and determining the concentricity of the front and rear installation stoppers of the assembly according to the coordinates of the center position; G. determining the stacking optimization model of the concentricity according to the concentricity of the front and rear installation stoppers of the assembly, and using a genetic algorithm to optimize and calculate the installation phase of each stage of the rotor based on this, and determining the optimal stacking assembly angle of each stage of the rotor; H. finally, the optimal assembly θ is calculated. riSubstitute the angle into the assembly concentricity calculation formula, solve it, and realize the prediction.

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

[0007] This scheme provides a new stacking optimization idea that takes into account the elastic deformation of the mounting edge of aircraft engine rotor parts during the assembly process, thereby guiding the assembly of multi-stage rotors of aircraft engines and achieving optimal dimensional parameters such as concentricity after assembly to meet design requirements.

[0008] As a further preference of the present invention, the global coordinate system of the assembly is defined in step A by selecting the end jump center of the reference plane required by the aircraft engine assembly process as the coordinate origin, the axis perpendicular to the end plane and passing through the coordinate origin is 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 plane process is the X axis to establish the global coordinates of the assembly.

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

[0010] It is the positioning error caused by the translation change under the three-dimensional coordinate transformation, represented by a 3×1 vector; It is the orientation error caused by the rotation change under the three-dimensional coordinate transformation, represented by a 3×3 matrix.

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

[0012] in Represents the rotational fit error matrix caused by the elastic deformation of the end faces of the i-th rotor and the i+1-th rotor stopper installation edge, expressed as a 3×3 matrix; The translation fit error matrix of the mounting edges of the stoppers of the i-th rotor and the i+1-th rotor due to the elastic deformation of the cylindrical surface 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 of the aircraft engine rotor is determined in step D as follows:

[0014]

[0015] S ri The rotation matrix of the axial measuring surface of the rotor of this stage relative to the reference surface, θ ri is the rotation angle of the i-th stage rotor installation position relative to the initial installation position around the reference axis.

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

[0017] As a further preferred embodiment of the present invention, the coaxiality deviation matrices of the rotors at each stage are accumulated stage by stage to determine the global positioning orientation matrix of the assembly after the n-stage rotor of the aircraft engine is assembled. Specifically, the matrix is ​​as follows:

[0018]

[0019] As a further preferred embodiment of the present invention, the center position of the aero-engine rotor is determined in step F by the following formula: The concentricity of the front and rear mounting spigots of the assembly in step F is determined by the following formula: Where matrix I is the second-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°, the installation phase of each rotor is calculated by genetic algorithm, and the optimal stacking angle of each rotor is determined with c as the objective function, θ ri is a variable.

[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 be used to guide the assembly of multi-stage rotors of aircraft engines, achieve optimal dimensional parameters such as concentricity after assembly, meet design requirements, and make the assembly quality of aircraft engine rotors better and the success rate higher.

[0023] 2. Using the method in the scheme, the concentricity and coaxiality of the aircraft engine assembly can be optimized based on the measurement data of the aircraft engine installation edge, taking into account the elastic deformation of the installation edge, and performing optimization calculations. The concentricity and coaxiality data of specific rotors at each stage and the optimal installation phase of each rotor stage can be obtained, thereby guiding the assembly of aircraft engine rotors and meeting technical requirements. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 Schematic diagram of the deflection caused by positioning error and orientation error in the assembly of an aircraft engine rotor. DETAILED DESCRIPTION

[0025] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings here can be arranged and designed in various different configurations.

[0026] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the invention claimed for protection, but merely represents selected embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0027] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features of the embodiments may be combined with each other.

[0028] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, further definition and explanation thereof is not required in subsequent drawings.

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

[0030] In the description of the present invention, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "set", "install", "connect", and "connect" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances. Specific embodiment 1:

[0032] Figure 1 A stacking method considering the elastic deformation of the installation edge of the rotor parts of an aero-engine is shown, comprising the following steps: A, defining the global coordinate system of the assembly; B, calculating the machining error matrix of the i-th rotor during the assembly process; C, calculating the fitting error matrix caused by elastic deformation at the fitting point between the i-th rotor and the i+1-th rotor during the assembly process; D, determining the installation phase matrix of the i-th rotor during the assembly process of the aero-engine rotor; E, after assembly, accumulating the coaxiality deviation matrices of the rotors at each stage step by step to determine the global positioning orientation matrix of the assembly after the n-th stage rotor of the aero-engine is assembled; F, determining the center position of the aero-engine rotor after assembly, and determining the concentricity of the front and rear installation stoppers of the assembly according to the coordinates of the center position; G, determining the stacking optimization model of the concentricity according to the concentricity of the front and rear installation stoppers of the assembly, and using the genetic algorithm to optimize and calculate the installation phase of each stage of the rotor based on this, and determining the optimal stacking assembly angle of each stage of the rotor; H, finally calculating the optimal assembly θ ri Substitute the angle into the assembly concentricity calculation formula, solve it, and realize the prediction.

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

[0034] This scheme provides a new stacking optimization idea that takes into account the elastic deformation of the mounting edge of aircraft engine rotor parts during the assembly process, thereby guiding the assembly of multi-stage rotors of aircraft engines and achieving optimal dimensional parameters such as concentricity after assembly to meet design requirements. Specific embodiment 2:

[0036] This embodiment further explains step A on the basis of specific embodiment 1. The global coordinate system of the assembly is defined in step A by selecting the end jump center of the reference plane required by the aircraft engine assembly process as the coordinate origin, the axis perpendicular to the end plane and passing through the coordinate origin is 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 plane process is the X axis to establish the global coordinates of the assembly. Specific embodiment 3:

[0038] This embodiment further illustrates 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] It is the positioning error caused by the translation change under the three-dimensional coordinate transformation, represented by a 3×1 vector; It is the orientation error caused by the rotation change under the three-dimensional coordinate transformation, represented by a 3×3 matrix. Specific embodiment 4:

[0041] This embodiment further illustrates step C on the basis of specific embodiment 1. In step C, the matching error matrix caused by elastic deformation at the matching point between the i-th stage rotor and the i+1-th stage rotor during the assembly process is calculated as follows:

[0042] in Represents the rotational fit error matrix caused by the elastic deformation of the end faces of the i-th rotor and the i+1-th rotor stopper installation edge, expressed as a 3×3 matrix; The translation fit error matrix of the mounting edges of the stoppers of the i-th rotor and the i+1-th rotor due to the elastic deformation of the cylindrical surface is represented by a 3×1 matrix. Specific embodiment 5:

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

[0045] S ri The rotation matrix of the axial measuring surface of the rotor of this stage relative to the reference surface, θ ri is the rotation angle of the i-th stage rotor installation position relative to the initial installation position around the reference axis. Specific embodiment 6:

[0047] This embodiment further explains step E on the basis of specific embodiment 1. In step E, the step of accumulating the coaxiality deviation matrix of each stage of the rotor step by step occurs specifically after the aircraft engine rotor is assembled and each stage of the rotor is transformed by elastic deformation corresponding to translation, rotation and high and low points. Specific embodiment 7:

[0049] This embodiment further illustrates the global positioning and orientation matrix of the assembly based on the specific embodiment 1. The coaxiality deviation matrices of the rotors at each stage are accumulated step by step to determine the global positioning and orientation matrix of the assembly after the n-stage rotor of the aircraft engine is assembled. Specific embodiment 8:

[0051] This embodiment further illustrates step F on the basis of specific embodiment 1. In step F, the center position of the aeroengine rotor is determined by the following formula: The concentricity of the front and rear mounting spigots of the assembly in step F is determined by the following formula: Where matrix I is the second-order identity matrix. Specific embodiment 9:

[0053] This embodiment further illustrates step G on the basis of 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°, the installation phase of each rotor is calculated by genetic algorithm, and the optimal stacking angle of each rotor is determined with c as the objective function, θ ri Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments, or replace some of the technical features therein by equivalents. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A stacking method considering the elastic deformation of the mounting edge of the rotor parts of an aircraft engine, characterized in that: The method comprises the following steps: A. defining the global coordinate system of the assembly; B. calculating the machining error matrix of the i-th rotor during the assembly process; C. Calculate the matching error matrix caused by elastic deformation at the matching point between the i-th rotor and the i+1-th rotor during assembly; D. Determine the installation phase matrix of the i-th stage rotor during the assembly of the aircraft 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 aircraft engine is assembled; F. After assembly, determine the center position of the aircraft engine rotor, and determine the concentricity of the front and rear mounting stoppers of the assembly according to the coordinates of the center position; G. Determine the stacking optimization model of the concentricity according to the concentricity of the front and rear mounting stoppers of the assembly, and use the genetic algorithm to optimize and calculate the installation phase of each level of the rotor based on this, and determine the optimal stacking assembly angle of each level of the rotor; H. Finally, the optimal assembly θ ri Substitute the angle into the assembly concentricity calculation formula, solve it, and realize the prediction.

2. The stacking method according to claim 1, wherein the elastic deformation of the mounting edge of the rotor parts of the aircraft engine is considered, characterized in that: The global coordinate system of the assembly is defined in step A by selecting the end jump circle center of the reference plane required by the aircraft engine assembly process as the coordinate origin, the axis perpendicular to the end plane and passing through the coordinate origin is 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 plane process is the X axis to establish the global coordinates of the assembly.

3. The stacking method considering the elastic deformation of the mounting edge of the aircraft engine rotor parts according to claim 1 is characterized in that: The machining error matrix of the i-th rotor during the calculation and assembly process in step B is specifically as follows:

4. The stacking method considering the elastic deformation of the mounting edge of the aircraft engine rotor parts according to claim 1 is characterized in that: In the calculation process of step C, the matching error matrix caused by elastic deformation at the matching point between the i-th stage rotor and the i+1-th stage rotor is specifically as follows:

5. The stacking method considering the elastic deformation of the mounting edge of the aircraft engine rotor parts according to claim 1, characterized in that: The specific installation phase matrix of the i-th stage rotor during the aero-engine rotor assembly process determined in step D is as follows:

6. The stacking method considering the elastic deformation of the mounting edge of the aircraft engine rotor parts according to claim 1, characterized in that: The step E of accumulating the coaxiality deviation matrix of each rotor level by level specifically occurs after the rotor of the aircraft engine is assembled and the rotors of each level are transformed by elastic deformation corresponding to the translation, rotation and high and low points.

7. The stacking method considering the elastic deformation of the mounting edge of the aircraft engine rotor parts according to claim 1, characterized in that: The coaxiality deviation matrices of the rotors at each stage are accumulated step by step to determine the global positioning and orientation matrix of the assembly after the n-stage rotors of the aircraft engine are assembled as follows:

8. The stacking method considering the elastic deformation of the mounting edge of the aircraft engine rotor parts according to claim 1, characterized in that: The center position of the aeroengine rotor is determined in step F by the following formula: The concentricity of the front and rear mounting spigots of the assembly in step F is determined by the following formula: Where matrix I is the second-order identity matrix.

9. The stacking method considering the elastic deformation of the mounting edge of the aircraft engine rotor parts according to claim 1, characterized in that: The concentricity stacking optimization model in step G is as follows: ri )=min(c),i=1,2…,n,θ ri = 0°~360°, the installation phase of each rotor is calculated by genetic algorithm, and the optimal stacking angle of each rotor is determined with c as the objective function, θ ri is a variable.

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