Inertial parameter matrix transfer-based large rotary equipment assembly quality characteristic prediction method

Abstract

The invention provides a large-scale rotary equipment assembly quality characteristic prediction method based on inertial parameter matrix transfer, and the method comprises the steps: carrying out the measurement and modeling of the mass, mass center and inertia tensor of each stage of rotor under a workpiece coordinate system, introducing the eccentric error, tilt error and assembly phase information in an assembly process, constructing a rigid body transformation relation, and carrying out the prediction of the assembly quality characteristics of the large-scale rotary equipment. Inertial parameters of each stage of rotor are accurately transmitted to a global assembly coordinate system. On the basis, integration and transmission of multi-stage inertial parameters are achieved in a modular accumulation mode, and finally accurate prediction of quality characteristics such as static couple unbalance is achieved before the whole machine is assembled.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of mechanical assembly, and particularly relates to a large rotary equipment assembly quality characteristic prediction method based on inertia parameter matrix transmission. BACKGROUND

[0002] As a high-end complex power system, the multi-stage rotor system of an aero-engine is usually composed of multi-stage rotors and forms a whole rotor structure through stack assembly. The mass characteristics of the rotor assembly have a decisive influence on the dynamic performance, vibration level and operation reliability of the engine. In the actual assembly process, due to the combined action of manufacturing errors and assembly deviations, the rotors at different stages often have different degrees of eccentricity and tilt, which leads to complex mass distribution of the whole machine after assembly, significant static unbalance, and easily induces unbalanced vibration of the rotor system, affecting the service life and safety of the whole machine.

[0003] The traditional method usually relies on the whole measurement after assembly and the experience of weight adjustment to balance adjustment, and lacks the ability of systematic modeling and prediction of the mass characteristics of the whole machine before assembly. Especially in the face of complex assembly structure, the existing technology is difficult to fully consider the influence of assembly errors on inertia parameters and unbalance, and cannot realize the feedforward control and quality optimization of the assembly process, which seriously restricts the assembly level of high-performance engines. SUMMARY

[0004] The present application aims to solve the problem of aero-engine stack assembly optimization, and proposes a large rotary equipment assembly quality characteristic prediction method based on inertia parameter matrix transmission.

[0005] The present application is realized by the following technical solutions, and the present application proposes a large rotary equipment assembly quality characteristic prediction method based on inertia parameter matrix transmission, and the method is specifically: Step one, measure the mass, center of mass coordinates and inertia tensor of each rotor workpiece of the aero-engine in the workpiece coordinate system, and generate the inertia parameter matrix according to the measurement results; Step two, measure the eccentricity error and tilt error of each rotor workpiece in the workpiece coordinate system, and calculate the rigid body transformation matrix of each rotor converted from the workpiece coordinate system to the global assembly coordinate system according to the assembly phase; Step three, according to the rigid body transformation matrix of each rotor, perform inertia parameter matrix transmission, and calculate the inertia parameter matrix of each rotor in the global assembly coordinate system; Step four, accumulate the inertia parameter matrices of each rotor in the global assembly coordinate system, calculate the inertia parameter matrix of the aero-engine assembly, and obtain the inertia parameter prediction value of the aero-engine.

[0006] Further, in step one, the mass, the mass center coordinates and the inertia tensor of each rotor are measured, and the mass i of the rotor in the rotor coordinate system of the first , , level rotor

[0007]

[0008] wherein C ix , C iy , C iz are the coordinate components of the first i level rotor in its rotor coordinate system x , y , z , , , , , , are the inertia tensor components of the first i level rotor in its rotor coordinate system.

[0009] Further, in step one, the inertia parameters matrix of the first i level rotor in the rotor coordinate system is constructed according to the measurement results as follows :

[0010] wherein .

[0011] Further, in step two, the axial and radial runout of the upper and lower end mounting edges of each rotor are measured, the eccentricity error and the tilt error of each rotor in the rotor coordinate system are evaluated according to the runout data, and the rigid body transformation matrix of each rotor from the rotor coordinate system to the global assembly coordinate system is calculated in sequence according to the assembly phase :

[0012] wherein is a 4x4 unit matrix, is the rigid body transformation matrix of the upper level rotor, is the rigid body translation matrix caused by the height and eccentricity error of the first level rotor, is the rotation matrix caused by the tilt error of the first level 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.

[0013] Furthermore, in step three, based on the rigid body transformation matrices of each rotor stage, the inertial parameter matrices of each rotor stage in the global assembly coordinate system are calculated according to the following formula. : .

[0014] Furthermore, in step four, the inertial parameter matrices of each rotor stage in the global assembly coordinate system are summed to obtain the inertial parameter matrix of the aero-engine assembly. :

[0015] In the formula, , This refers to the total mass of the aircraft engine assembly. , , The center of mass of the aero-engine assembly is respectively x , y , z Coordinate components, , , , , , These are the inertial tensor components of the aero-engine assembly.

[0016] Furthermore, the mass characteristics of the aero-engine are calculated from the inertial parameter matrix of the aero-engine assembly, and used as the optimization objective for the assembly:

[0017] In the formula, Inertial parameter matrix of aero-engine assembly The element in the i-th row and j-th column, Let be the moment of inertia of the aero-engine assembly about the z-axis in the global coordinate system. and These represent the magnitude and angle of the static imbalance of the aero-engine assembly in the global coordinate system. and These represent the amplitude and angle of the even imbalance of the aero-engine assembly in the global coordinate system.

[0018] The beneficial effects of this invention are: 1.The inertial parameter matrix transmission method can accurately predict the inertial characteristics such as mass, center of mass position and moment of inertia of the whole machine before assembly, provide clear basis for subsequent assembly quality control and optimization, and significantly improve the controllability and predictability of the assembly process.

[0019] 2.The method introduces the eccentric error, tilt error and assembly phase of each level of rotor, accurately maps the inertial parameters of each level to the global coordinate system through rigid body transformation, fully reflects the structural characteristics under the real assembly state, and effectively avoids the prediction deviation caused by error neglect in the traditional method.

[0020] 3.The method adopts a modularized inertial parameter accumulation method, which can adapt to the hierarchical assembly calculation requirements of multi-level rotor structure. By transmitting the inertial parameters level by level, the mass characteristics of the global assembly body are constructed, which provides a general tool chain for modeling and optimization of complex stacked structures. BRIEF DESCRIPTION OF DRAWINGS

[0021] Figure 1 The figure is a schematic diagram of the inertial parameter matrix transmission model of the aircraft engine assembly proposed in the application. DETAILED DESCRIPTION

[0022] The technical solutions in the embodiments of the application will be clearly and completely described below with reference to the drawings in the embodiments of the application. Obviously, the described embodiments are only part of the embodiments of the application, rather than all the embodiments. Based on the embodiments in the application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the application.

[0023] The application proposes a large rotary equipment assembly quality characteristic prediction method based on inertial parameter matrix transmission. The method measures and models the mass, center of mass and inertia tensor of each level of rotor in the workpiece coordinate system, introduces the eccentric error, tilt error and assembly phase information in the assembly process, constructs the rigid body transformation relationship, and accurately transmits the inertial parameters of each level of rotor to the global assembly body coordinate system. On this basis, a modularized accumulation method is used to realize the integration and transmission of multi-level inertial parameters, and finally the static unbalance and other quality characteristics are accurately predicted before the whole machine assembly.

[0024] Specifically, referring to Figure 1 The application proposes a large rotary equipment assembly quality characteristic prediction method based on inertial parameter matrix transmission, and the method is specifically as follows: Step one, measure the mass, center of mass coordinates and inertia tensor of each level of rotor workpiece in the coordinate system, and generate the inertial parameter matrix according to the measurement results; Step 2: Measure the eccentricity and tilting errors of each rotor in the workpiece coordinate system, and calculate the rigid body transformation matrix of each rotor from the workpiece coordinate system to the global assembly coordinate system based on the assembly phase. Step 3: Based on the rigid body transformation matrix of each rotor stage, perform inertial parameter matrix transfer and calculate the inertial parameter matrix of each rotor stage in the global assembly coordinate system. Step 4: Accumulate the inertial parameter matrices of each rotor stage in the global assembly coordinate system to calculate the inertial parameter matrix of the aero-engine assembly, thereby obtaining the predicted values ​​of the aero-engine's inertial parameters.

[0025] In step one, the mass, centroid coordinates, and inertia tensor of each stage of the rotor are measured, and the results are obtained respectively. i Mass in the workpiece coordinate system of the stage rotor centroid coordinates Inertia tensor matrix :

[0026]

[0027] In the formula, C ix , C iy , C iz The first i The stage rotor in its workpiece coordinate system x , y , z Coordinate components, , , , , , The first i The inertial tensor components of the stage rotor in its workpiece coordinate system.

[0028] In step one, the following structure is constructed based on the measurement results: i Inertial parameter matrix in the stage rotor workpiece coordinate system :

[0029] In the formula, .

[0030] In step two, the axial and radial stop runout of the upper and lower mounting edges of each rotor stage is measured. Based on the runout data, the eccentricity error and tilt error of each rotor stage in the workpiece coordinate system are evaluated. Then, according to the assembly phase, the rigid body transformation matrix of each rotor stage is calculated sequentially from the workpiece coordinate system to the global assembly coordinate system. :

[0031] wherein, is a 4x4 unit matrix, is the upper rotor rigid body transformation matrix, is the rigid body translation matrix caused by the height and eccentricity error of the i-th rotor, is the rotation matrix caused by the tilt error of the i-th rotor, is the rotation matrix caused by the assembly phase of the i-th rotor, is the assembly phase of the i-th rotor relative to the (i-1)-th rotor. In step three, according to the rigid body transformation matrix of each rotor, the inertia parameter matrix of each rotor in the global assembly body coordinate system is calculated according to the following formula :

[0032] . .

[0033] In step four, the inertia parameter matrices of each rotor in the global assembly body coordinate system are accumulated to obtain the inertia parameter matrix of the aero-engine assembly body :

[0034] wherein, , is the total mass of the aero-engine assembly body, , , are the coordinate components of the mass center of the aero-engine assembly body, x , y , z , , , , , , are the inertia tensor components of the aero-engine assembly body.

[0035] The mass characteristics of the aero-engine are calculated from the inertia parameter matrix of the aero-engine assembly body, which is taken as the optimization target of the assembly:

[0036] wherein, is the element in the i-th row and the j-th column of the inertia parameter matrix of the aero-engine assembly body , is the moment of inertia of the aero-engine assembly body about the z axis in the global coordinate system, ​and respectively are the amplitude and angle of the static unbalance of the aero-engine assembly in the global coordinate system, and respectively are the amplitude and angle of the static unbalance of the aero-engine assembly in the global coordinate system.

[0037] As Figure 1 shown, is the aero-engine assembly inertia parameter matrix transfer model diagram proposed by the present application. In Figure 1 the transfer model shown, is the second stage rotor workpiece coordinate system, is the first stage rotor workpiece coordinate system, and also is the assembly global coordinate system, represents the coordinate transformation matrix from the second stage rotor workpiece coordinate system to the assembly global coordinate system, and respectively represent the inertia parameter matrix of the second stage rotor in the second stage rotor workpiece coordinate system and the assembly global coordinate system.

[0038] Although the present application has been disclosed in the above preferred embodiments, it is not intended to limit the present application, and any person skilled in the art can make various modifications and modifications without departing from the spirit and scope of the present application, therefore the protection scope of the present application should be defined by the claims.

Claims

1. A large-scale slewing equipment assembly quality characteristic prediction method based on inertia parameter matrix transmission, characterized in that, The method is specifically: Step one, measuring the mass, mass center coordinates and inertia tensor of each rotor workpiece in the coordinate system of the aero-engine, and generating an inertia parameter matrix according to the measurement results; Step two, measuring the eccentricity error and tilt error of each rotor workpiece in the coordinate system, and calculating the rigid body transformation matrix of each rotor from the workpiece coordinate system to the global assembly coordinate system according to the assembly phase; Step three, transferring the inertia parameter matrix according to the rigid body transformation matrix of each rotor, and calculating the inertia parameter matrix of each rotor in the global assembly coordinate system; Step four, accumulating the inertia parameter matrix of each rotor in the global assembly coordinate system, calculating the inertia parameter matrix of the aero-engine assembly, and obtaining the inertia parameter prediction value of the aero-engine.

2. The method of claim 1, wherein, In step one, the mass, the mass center coordinates and the inertia tensor of each stage rotor are measured, and the mass i , the mass center coordinates , and the inertia tensor matrix of the stage rotor in the workpiece coordinate system are obtained respectively. : In the formula, C ix , C iy , C iz The first i The stage rotor in its workpiece coordinate system x , y , z Coordinate components, , , , , , The first i The inertial tensor components of the stage rotor in its workpiece coordinate system.

3. The method of claim 2, wherein, In step one, the following inertia parameter matrix of the workpiece in the coordinate system of the stage rotor is constructed according to the measurement results i :​ In the formulae, .

4. The method of claim 3, wherein, In step two, the axial and radial stop gap runout of the upper and lower end mounting edges of each stage rotor is measured, the eccentricity error and tilt error of each stage rotor in the workpiece coordinate system are evaluated according to the runout data, and the rigid body transformation matrix of each stage rotor converted from the workpiece coordinate system to the global assembly coordinate system is sequentially calculated according to the assembly phase : wherein, is a 4x4 unit matrix, is the superior rotor rigid body transformation matrix, is the rigid body translation matrix caused by the first level rotor height and eccentricity error, is the rotation matrix caused by the first level rotor tilt error, is the rotation matrix caused by the current rotor assembly phase, is the current rotor assembly phase relative to the superior rotor assembly phase.

5. The method of claim 4, wherein, In step three, the inertia parameter matrix of each rotor in the global assembly coordinate system is calculated according to the rigid transformation matrix of each rotor, according to the following formula : 。 6. The method of claim 5, wherein, In step four, the inertia parameter matrix of each rotor in the global assembly coordinate system is accumulated to obtain the inertia parameter matrix of the aero-engine assembly : wherein , is the total mass of the aeroengine assembly, , , are the coordinate components of the center of mass of the aeroengine assembly, x , y , z are the coordinate components of the center of mass of the aeroengine assembly, , , , , , are the coordinate components of the inertia tensor of the aeroengine assembly.

7. The method of claim 6, wherein, The mass characteristics of the aero-engine are calculated from the inertia parameter matrix of the aero-engine assembly, which is used as the optimization target of the assembly: wherein is the inertia parameter matrix of the aero-engine assembly is the element in the i-th row and j-th column of the inertia parameter matrix, is the moment of inertia of the aero-engine assembly about the z-axis in the global coordinate system, and are the amplitude and angle of the static unbalance of the aero-engine assembly in the global coordinate system, respectively, and are the amplitude and angle of the couple unbalance of the aero-engine assembly in the global coordinate system, respectively.

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