A rotor assembly phase optimization method for concentricity and unbalance

Abstract

The application belongs to the field of aero-engines, and particularly relates to a rotor assembly phase optimization method for concentricity and unbalance amount. The method comprises the following steps: step one, constructing a rotor concentricity calculation model and a rotor unbalance amount calculation model; step two, constructing a rotor assembly parameter database according to the rotor concentricity calculation model and the rotor unbalance amount calculation model; and step three, screening an optimal assembly phase with the best concentricity and unbalance amount from the rotor assembly parameter database. The application can further optimize the initial unbalance amount of the rotor on the basis that the concentricity of the rotor meets the engineering requirements, reduce the subsequent balancing difficulty of the rotor, improve the rotor assembly efficiency, and improve the working stability of the rotor connecting interface.

Description

TECHNICAL FIELD

[0001] The application belongs to the field of aero-engines, and particularly relates to a rotor assembly phase optimization method for concentricity and unbalance. BACKGROUND

[0002] The use environment of an aero-engine is very harsh, and especially an engine rotor works under complex working conditions of high temperature, high pressure and high rotating speed. How to stably operate is crucial to safe use and whole machine vibration control of the engine, and the main factors influencing rotor quality are concentricity and unbalance of the rotor.

[0003] At present, in the engineering field, concentricity optimization is mainly taken as a target in the aero-engine rotor assembly process, and the rotor eccentricity is reduced as much as possible through stacking optimization means. In the balancing process after assembly, the rotor unbalance is reduced through the method of adding weights, and the rotor unbalance optimization is not considered in the assembly process, so that the initial unbalance of part of the rotor after assembly is large, and the rotor unbalance needs to be reduced through the method of adding weights in the balancing link, which causes internal stress to exist in the connection interface of the rotor. If a large weight is added to realize the balancing of the rotor, a large misalignment load exists in the connection interface at high speed, which has an adverse effect on the working stability of the rotor. In addition, if the rotor unbalance is too large before balancing, the rotor needs to be disassembled and reassembled, which seriously affects the rotor assembly efficiency and increases the rotor assembly cost.

[0004] Therefore, it is desirable to have a technical solution to overcome or at least alleviate at least one of the aforementioned deficiencies of the prior art. SUMMARY

[0005] The purpose of the present application is to provide a rotor assembly phase optimization method for concentricity and unbalance, so as to solve at least one problem existing in the prior art.

[0006] The technical solution of the present application is:

[0007] A rotor assembly phase optimization method for concentricity and unbalance, comprising:

[0008] Step one, constructing a rotor concentricity calculation model and a rotor unbalance calculation model;

[0009] Step two, constructing a rotor assembly parameter database according to the rotor concentricity calculation model and the rotor unbalance calculation model;

[0010] Step three, selecting an assembly phase with optimal concentricity and unbalance from the rotor assembly parameter database.

[0011] In at least one embodiment of the present application, in step one, the constructing of the rotor concentricity calculation model and the rotor unbalance calculation model comprises:

[0012] obtaining a configuration of a rotor, and determining an assembly phase of the rotor, the rotor comprising a plurality of disk shaft parts connected in sequence along an axial direction;

[0013] determining an origin and a positive direction, and establishing a three-dimensional rectangular coordinate system of the rotor;

[0014] based on the three-dimensional rectangular coordinate system, constructing a rotor concentricity calculation model and a rotor unbalance amount calculation model.

[0015] In at least one embodiment of the present application, the rotor comprises a drum shaft, a turbine front sealing disk, a high-pressure turbine disk and a high-pressure turbine rear shaft connected in sequence along an axial direction, and adjacent parts are connected by bolts.

[0016] In at least one embodiment of the present application, a three-dimensional rectangular coordinate system of the rotor is established with the center of the front end face of the drum shaft as the origin and the heading direction as the positive direction.

[0017] In at least one embodiment of the present application, based on the three-dimensional rectangular coordinate system, the rotor concentricity calculation model is constructed, comprising:

[0018] The rotor concentricity calculation model is:

[0019]

[0020] wherein (x1, y1)~(x n ,y n ) are the shape center coordinates of the rear stop of the corresponding part in the rotor state, r1~r n are the eccentricity of the rear stop of the corresponding part, α1~α n are the eccentricity phase of the rear stop of the corresponding part, l1~l n are the axial length of the corresponding part, d2~d n are the front stop diameter of the corresponding part, h1~h n-1 are the perpendicularity of the corresponding part, β1~β n-1 are the perpendicularity phase of the corresponding part, and n is the number of disk shaft parts.

[0021] According to the rotor concentricity calculation model, the eccentricity and eccentricity phase calculation model of the corresponding part are obtained:

[0022]

[0023] wherein R i is the eccentricity of the corresponding part, is the eccentricity phase of the corresponding part.

[0024] According to the eccentricity and eccentricity phase calculation model, the rotor overall eccentricity corresponding to each assembly phase is calculated, that is, R n .

[0025] In at least one embodiment of the present application, the rotor unbalance calculation model is constructed based on the three-dimensional rectangular coordinate system, which comprises:

[0026] The rotor unbalance calculation model is:

[0027]

[0028] Wherein, (X1, Y1) ~ (X n ,Y n ) are the coordinates of the mass center of the corresponding part relative to the actual rotating shaft in the rotor state, z1 ~ z n are the unbalance of the corresponding part, γ1 ~ γ n are the unbalance phase of the corresponding part, m1 ~ m n are the mass of the corresponding part, l1 ~ l n are the axial length of the corresponding part, and n is the number of disc shaft parts.

[0029] According to the rotor unbalance calculation model, the rotor overall mass center coordinates are calculated:

[0030]

[0031] Wherein, (X, Y) is the rotor overall mass center coordinates.

[0032] The rotor overall unbalance and unbalance phase corresponding to each assembly phase are calculated:

[0033]

[0034] Wherein, G is the rotor overall unbalance, and ψ is the rotor overall unbalance phase.

[0035] In at least one embodiment of the present application, the rotor assembly parameter database comprises: the assembly phase information of the rotor, and the rotor overall eccentricity and the rotor overall unbalance corresponding to each assembly phase.

[0036] In at least one embodiment of the present application, in step three, the assembly phase with the optimal concentricity and unbalance is selected from the rotor assembly parameter database, which comprises:

[0037] The priority level of the concentricity and the unbalance is determined, and the priority level comprises a first priority and a second priority.

[0038] screening a plurality of assembly phases from the rotor assembly parameter database according to the parameter of the first priority;

[0039] screening an optimal assembly phase from the plurality of assembly phases according to the parameter of the second priority.

[0040] In at least one embodiment of the present application, the parameter of the first priority is concentricity, and the parameter of the second priority is unbalance.

[0041] In at least one embodiment of the present application, screening a plurality of assembly phases from the rotor assembly parameter database according to the concentricity comprises:

[0042] screening p% of the assembly phases from the rotor assembly parameter database according to the concentricity, wherein p is a fixed value in 2-5.

[0043] The present application has at least the following beneficial technical effects:

[0044] The rotor assembly phase optimization method for concentricity and unbalance of the present application, in the rotor assembly process, establishes a rotor concentricity and unbalance calculation model, establishes a rotor assembly parameter database, and screens an optimal assembly phase from the database according to the principle of optimizing concentricity and unbalance together. After assembly according to the optimal assembly phase, the rotor initial unbalance can be further optimized on the basis of satisfying the engineering requirements of the rotor concentricity, the subsequent balancing difficulty of the rotor is reduced, the rotor assembly efficiency is improved, and the working stability of the rotor connecting interface is improved. BRIEF DESCRIPTION OF DRAWINGS

[0045] Figure 1 is a schematic diagram of the rotor eccentricity caused by the eccentricity of the part of one embodiment of the present application;

[0046] Figure 2 is a schematic diagram of the rotor eccentricity caused by the perpendicularity of the part of one embodiment of the present application;

[0047] Figure 3 is a schematic diagram of the rotor unbalance caused by the superposition of the spatial positions of the mass center of the part relative to the actual rotating shaft of one embodiment of the present application;

[0048] Figure 4 is a schematic diagram of a high-pressure turbine rotor of one embodiment of the present application.

[0049] Wherein:

[0050] 1-drum shaft; 2-front sealing disc; 3-turbine disc; 4-turbine rear shaft. DETAILED DESCRIPTION

[0051] In order to make the purpose, technical scheme and advantages of the present application clearer, the technical scheme in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar notations represent the same or similar elements or elements having the same or similar functions throughout. The described embodiments are part of the embodiments of the present application, rather than all the embodiments. The embodiments described below with reference to the drawings are exemplary and are intended to explain the present application, and cannot be understood as a limitation on the present application. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative labor fall within the scope of protection of the present application. The embodiments of the present application will be described in detail below with reference to the drawings.

[0052] In the description of the present application, it should be understood that the terms "center", "longitudinal", "transverse", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the scope of protection of the present application.

[0053] The embodiments of the present application will be described in detail below with reference to the drawings. Figures 1 to 4 The present application is further described in detail.

[0054] The present application provides a rotor assembly phase optimization method for concentricity and unbalance, comprising the following steps:

[0055] Step one, constructing a rotor concentricity calculation model and a rotor unbalance calculation model;

[0056] Step two, constructing a rotor assembly parameter database according to the rotor concentricity calculation model and the rotor unbalance calculation model;

[0057] Step three, selecting the optimal assembly phase of concentricity and unbalance from the rotor assembly parameter database.

[0058] The rotor assembly phase optimization method for concentricity and unbalance of the present application is based on the rotor stacking theory to construct the rotor concentricity calculation model and the rotor unbalance calculation model. The rotor eccentricity is accumulated by the eccentricity of each stage of the rotor disc shaft part and the perpendicularity error, and the accumulation result is determined by the circumferential installation phase angle of each rotor part. The eccentricity mode caused by the part eccentricity and perpendicularity is shown in Figures 1-2 The rotor eccentricity and eccentric phase determine the actual rotation axis (hereinafter referred to as the rotation axis) position of the rotor, and the rotor assembly unbalance is formed by the spatial position of the mass center of each part relative to the actual rotation axis after superposition, as shown in Figure 3As shown.

[0059] The rotor assembly phase optimization method for concentricity and unbalance amount in the application, in step one, a rotor concentricity calculation model and a rotor unbalance amount calculation model are constructed, including:

[0060] The configuration of the rotor is obtained, and the assembly phase of the rotor is determined, the rotor comprising a plurality of disc shaft parts connected in sequence along the axial direction;

[0061] The origin and the positive direction are determined, and a three-dimensional rectangular coordinate system of the rotor is established;

[0062] Based on the three-dimensional rectangular coordinate system, a rotor concentricity calculation model and a rotor unbalance amount calculation model are constructed.

[0063] In the preferred embodiment of the application, taking a high-pressure turbine rotor as an example, as shown, Figure 4 the rotor comprises a drum shaft 1, a turbine front sealing disc 2, a high-pressure turbine disc 3, and a high-pressure turbine rear shaft 4 connected in sequence along the axial direction, and the adjacent parts are connected by bolts. There are three connection interfaces in the rotor, wherein the first interface is connected by 48 bolts, the second interface is connected by 48 bolts, and the third interface is connected by 42 bolts, so in this embodiment, the rotor has a total of 48×48×42=96768 assembly phases. In this embodiment, the center of the front end face of the drum shaft 1 is taken as the origin, and the heading direction is taken as the positive direction, and a three-dimensional rectangular coordinate system of the rotor is established. Among them, the clockwise direction along the heading direction is defined as the adjustment direction of the assembly phase between the adjacent two parts.

[0064] In the preferred embodiment of the application, based on the three-dimensional rectangular coordinate system established above, a rotor concentricity calculation model is constructed, including:

[0065] The rotor concentricity calculation model is:

[0066]

[0067] Wherein, (x1, y1)~(x n ,y n ) are the shape center coordinates of the rear stop of the corresponding part in the rotor state, r1~r n are the rear stop eccentricity of the corresponding part (the part itself parameter, taking the front end face of each part as the reference), α1~α n are the rear stop eccentricity phase of the corresponding part, l1~ln are the axial length of the corresponding part, d2~d n are the front stop diameters of the corresponding part, h1~h n-1 are the perpendicularity of the corresponding part (the part itself parameter, taking the front end face of each part as the reference), β1~β n-1 are the perpendicularity phase of the corresponding part, and n is the number of disc shaft parts.

[0068] According to the rotor concentricity calculation model, the eccentricity and eccentricity phase calculation model of the corresponding part are obtained:

[0069]

[0070] Wherein, R i is the eccentricity of the corresponding part, is the eccentricity phase of the corresponding part;

[0071] According to the eccentricity and eccentricity phase calculation model, the rotor overall eccentricity corresponding to each assembly phase is calculated, that is, R n .

[0072] In this embodiment, the rotor includes 4 disc shaft parts, that is, n is 4, and the eccentricities of all parts are accumulated on one part. The eccentricity of the high-pressure turbine rear shaft is the rotor overall eccentricity, and the rotor overall eccentricity R4 corresponding to each assembly phase calculated according to the rotor concentricity calculation model. It can be understood that the rotor concentricity calculation model is not limited to the rotor overall eccentricity calculation of the rotor with 4 parts. It is applicable to the rotor overall eccentricity calculation of the rotor with any appropriate number of parts under the configuration of the rotor.

[0073] In the preferred embodiment of the present application, based on the above-mentioned three-dimensional rectangular coordinate system, a rotor unbalance calculation model is constructed, including:

[0074] The rotor unbalance calculation model is:

[0075]

[0076] Wherein, (X1,Y1)~(X n ,Y n ) are the coordinates of the mass center of the corresponding part relative to the actual rotating shaft under the rotor state, z1~z n are the unbalance of the corresponding part, γ1~γ n are the unbalance phase of the corresponding part, m1~m n are the mass of the corresponding part, l1~l n are the axial length of the corresponding part, and n is the number of disc shaft parts.

[0077] According to the rotor unbalance calculation model, the rotor overall mass center coordinates are calculated:

[0078]

[0079] Wherein, (X,Y) is the rotor overall mass center coordinates;

[0080] The rotor overall unbalance and unbalance phase corresponding to each assembly phase are calculated:

[0081]

[0082] wherein G is the rotor overall unbalance, and ψ is the rotor overall unbalance phase.

[0083] In the present embodiment, the rotor comprises 4 disc shaft parts, i.e. n is 4, and the spatial positions of the mass centers of the parts relative to the actual rotation shaft are superimposed to obtain the rotor overall unbalance G, and the rotor overall unbalance G corresponding to each assembly phase calculated finally according to the rotor unbalance calculation model. It can be understood that the rotor unbalance calculation model is not limited to the rotor overall unbalance calculation of the rotor with 4 parts, and is applicable to the rotor overall unbalance calculation of the rotor with any appropriate number of parts under the rotor configuration.

[0084] The rotor assembly phase optimization method for concentricity and unbalance of the present application is based on the rotor concentricity calculation model and the rotor unbalance calculation model, and a rotor assembly parameter database is constructed, which comprises the assembly phase information of the rotor, and the rotor overall eccentricity and the rotor overall unbalance corresponding to each assembly phase. In the present embodiment, based on the two calculation models, an enumeration method is adopted to establish the rotor assembly parameter database containing all assembly phases through program design, and the rotor assembly parameter database containing all 96768 assembly phases can be established through program calculation.

[0085] The rotor assembly phase optimization method for concentricity and unbalance of the present application is used to screen out the assembly phase with smaller eccentricity and unbalance, i.e. the assembly phase for double optimization of concentricity and initial unbalance. First, the priority levels of the concentricity and the unbalance are determined, which include the first priority level and the second priority level; then, a plurality of assembly phases are screened out from the rotor assembly parameter database according to the parameters of the first priority level; and finally, the optimal assembly phase is screened out from the plurality of assembly phases according to the parameters of the second priority level.

[0086] In the preferred embodiment of the present application, the priority levels of the optimization parameters are selected according to the rotor structure characteristics, the parameter of the first priority level is the concentricity, and the parameter of the second priority level is the unbalance. Based on the actual data results, the first p% (recommended 2% to 5%) of assembly phases with smaller concentricity are selected from all assembly phases, and then the assembly phase with the smallest unbalance is further screened out from the above-mentioned assembly phases, which is the final optimized assembly phase. In the present embodiment, the first 1935 groups of data (2% of the assembly phases with the smallest eccentricity) are screened out from the 96768 groups of data, and then the assembly phase with the smallest overall unbalance of the rotor is screened out from the above-mentioned 1935 groups of data, which is the optimal assembly phase.

[0087] The rotor assembly phase optimization method for concentricity and unbalance amount of the application can further optimize the rotor unbalance amount on the basis of ensuring that the rotor concentricity meets the engineering requirements after assembly according to the optimal assembly phase, and avoid the situation that the initial unbalance amount of the rotor after assembly is too large; the initial unbalance amount of the rotor is small after assembly according to the optimal assembly phase, which can reduce the subsequent rotor balancing difficulty, reduce the balancing process, and improve the rotor assembly efficiency; the initial unbalance amount of the rotor after assembly is small according to the optimal assembly phase, which can reduce the balancing weight of the balancing link, and improve the stability of the rotor connecting interface.

[0088] The above is only a specific embodiment of the application, but the protection scope of the application is not limited thereto, any person skilled in the art can easily think of changes or replacements within the technical range disclosed by the application, which should be covered within the protection scope of the application. Therefore, the protection scope of the application should be subject to the protection scope of the claims.

Claims

1. A method for optimizing the assembly phase of a rotor with respect to concentricity and unbalance, characterized in that, The application relates to a method for determining an optimal assembly phase of a rotor, comprising the following steps: Step 1: constructing a rotor concentricity calculation model and a rotor unbalance amount calculation model; Step 2: constructing a rotor assembly parameter database according to the rotor concentricity calculation model and the rotor unbalance amount calculation model; Step 3: screening an optimal assembly phase with the best concentricity and unbalance amount from the rotor assembly parameter database. In step 1, the construction of the rotor concentricity calculation model and the rotor unbalance amount calculation model comprises the following steps: obtaining the configuration of a rotor and determining the assembly phase of the rotor, wherein the rotor comprises a plurality of disc shaft parts connected in sequence along an axial direction; determining an origin and a positive direction, and establishing a three-dimensional rectangular coordinate system of the rotor; constructing a rotor concentricity calculation model and a rotor unbalance amount calculation model based on the three-dimensional rectangular coordinate system; the construction of the rotor concentricity calculation model based on the three-dimensional rectangular coordinate system comprises the following steps: the rotor concentricity calculation model is as follows: Wherein, (x1, y1)~(x n , y n ) are the shape center coordinates of the rear stop of the corresponding parts in the rotor state, r1~r n are the eccentricity of the corresponding parts, α1~α n are the eccentricity phase of the corresponding parts, l1~l n are the axial length of the corresponding parts, d2~d n are the diameter of the front stop of the corresponding parts, h1~h n-1 are the perpendicularity of the corresponding parts, β1~β n-1 are the phase of the perpendicularity of the corresponding parts, and n is the number of disc shaft parts. according to the rotor concentricity calculation model, an eccentricity amount and an eccentricity phase calculation model of a corresponding part are obtained: wherein R i is the eccentricity of the corresponding part, is the eccentricity phase of the corresponding part; According to the eccentricity and eccentricity phase calculation model, the rotor overall eccentricity corresponding to each assembly phase is calculated, that is, R n .

2. The rotor assembly phase optimization method for concentricity and unbalance amount according to claim 1, characterized by, the rotor comprises a drum shaft, a turbine front sealing disc, a high-pressure turbine disc and a high-pressure turbine rear shaft connected in sequence along an axial direction, and adjacent parts are connected through bolts.

3. The rotor assembly phase optimization method for concentricity and unbalance amount according to claim 2, characterized by, the center of the front end surface of the drum shaft is taken as the origin, and the heading direction is taken as the positive direction to establish the three-dimensional rectangular coordinate system of the rotor.

4. The rotor assembly phase optimization method for concentricity and unbalance amount according to claim 3, characterized by, the construction of the rotor unbalance amount calculation model based on the three-dimensional rectangular coordinate system comprises the following steps: the rotor unbalance amount calculation model is as follows: Wherein, (X1, Y1)~(X n , Y n ) are coordinates of the mass center of the corresponding part relative to the actual rotating shaft in the rotor state, z1~z n are unbalance amounts of the corresponding parts, γ1~γ n are phases of the unbalance amounts of the corresponding parts, m1~m n are masses of the corresponding parts, l1~l n are axial lengths of the corresponding parts, and n is the number of disc shaft parts. according to the rotor unbalance amount calculation model, the overall centroid coordinates of the rotor are calculated: wherein (X, Y) are the overall centroid coordinates of the rotor; the overall unbalance amount and the unbalance amount phase of the rotor corresponding to each assembly phase are calculated: wherein G is the overall unbalance amount of the rotor, and psi is the overall unbalance amount phase of the rotor.

5. The rotor assembly phase optimization method for concentricity and unbalance amount according to claim 4, characterized by, the rotor assembly parameter database comprises the assembly phase information of the rotor, the overall eccentricity amount of the rotor and the overall unbalance amount of the rotor corresponding to each assembly phase.

6. The rotor assembly phase optimization method for concentricity and unbalance amount according to claim 5, wherein in step 3, the screening of the optimal assembly phase with the best concentricity and unbalance amount from the rotor assembly parameter database comprises the following steps: determining the priority level of the concentricity and the unbalance amount, wherein the priority level comprises a first priority level and a second priority level; screening a plurality of assembly phases from the rotor assembly parameter database according to the parameters of the first priority level; screening an optimal assembly phase from the plurality of assembly phases according to the parameters of the second priority level.

7. The rotor assembly phase optimization method for concentricity and unbalance amount according to claim 6, characterized by, the parameters of the first priority level are the concentricity, and the parameters of the second priority level are the unbalance amount.

8. The rotor assembly phase optimization method for concentricity and unbalance amount according to claim 7, characterized by, the screening of the plurality of assembly phases from the rotor assembly parameter database according to the concentricity comprises the following steps: p% of the assembly phases are screened from the rotor assembly parameter database according to the concentricity, wherein p is a fixed value in the range of 2-5.

Images