CN115659433B - Quantitative evaluation method for mechanical characteristics of aero-engine rotor structure - Google Patents
Quantitative evaluation method for mechanical characteristics of aero-engine rotor structure Download PDFInfo
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Abstract
The application belongs to the field of aeroengine design, and relates to a quantitative evaluation method for mechanical properties of an aeroengine rotor structure, which comprises the steps of carrying out bearing capacity evaluation of the bearing structure in a scheme design stage of the bearing structure, carrying out bearing capacity evaluation and deformation resistance evaluation of the bearing structure in a technical design stage, and carrying out bearing capacity evaluation, deformation resistance evaluation and mechanical environment adaptability evaluation of the bearing structure in a product design stage; quantitative evaluation of rotor structure layout and design results can be rapidly realized, so that an important method and means are provided for rapid and accurate iteration of rotor structure design and scheme; the bearing capacity, the bending resistance and the environment adaptability of the rotor can be effectively ensured, and the working performance of the rotor structure is improved.
Description
Technical Field
The application belongs to the field of aeroengine design, and particularly relates to a quantitative evaluation method for mechanical properties of an aeroengine rotor structure.
Background
With the improvement of the flight Mach number of an aircraft and the improvement of unit parameters of an aviation turbofan engine, the working stress and the environment temperature inside the engine are higher and higher, and the service conditions of the engine are more and more severe. This places greater demands on the structural integrity of the engine components.
Aero turbofan engine structural design is a sum of theory, methods, and techniques designed such that all structural components meet structural integrity requirements. The structural design is a starting point and a landing point of the engine design, and the rotor structural design has critical influence on the implementation of the technical index and the structural reliability of the engine. Therefore, systematic and accurate assessment of the mechanical properties of the rotor structure is an important means and guarantee for measuring the structural layout and structural design integrity of the engine. Rotor structure design and analytical evaluation, i.e. analysis and optimization of rotor structure geometry, support scheme, support stiffness and connection structure, allows a rotor system to obtain reasonable dynamics.
In the past, in the structural design of an aero turbofan engine, a great deal of theoretical analysis and experimental research are carried out on the aspects of strength, rigidity, vibration and the like of the structure, and the safety margin of the strength and the vibration is designed to ensure that the structure can safely and reliably realize the specified function. However, for the rotor component with a certain function, there may be various structural designs that can meet the requirements of the strength, rigidity, vibration and other dynamic characteristics, and which is more favorable for improving the performance and reliability of the engine cannot be selected. Because of the lack of methods and means for systematic and quantitative analytical evaluation of rotor structures.
Disclosure of Invention
The application aims to provide a quantitative evaluation method for mechanical properties of an aeroengine rotor structure, which aims to solve the problem that a method and means for carrying out system and quantitative analysis evaluation on the rotor structure are lacking in the prior art.
The technical scheme of the application is as follows: a quantitative evaluation method for mechanical properties of an aero-engine rotor structure comprises the following steps: carrying out scheme design of a rotor structure, obtaining boundary conditions of the rotor structure at the current stage, setting a scheme design standard set, carrying out bearing capacity assessment of the rotor structure, wherein the bearing capacity assessment comprises average stress coefficients and stress distribution coefficients of the rotor structure, judging whether all parameters in the bearing capacity assessment meet corresponding standards in the scheme design standard set, and if yes, carrying out next stage design; carrying out technical design of a rotor structure, obtaining boundary conditions of the rotor structure at the current stage, setting a technical design standard set, carrying out bearing capacity evaluation and deformation resistance evaluation of the rotor structure, wherein the deformation resistance evaluation comprises rotor bending stiffness distribution, rotor equivalent stiffness and maximum deformation of the rotor under limit inertial load, judging whether each parameter in the bearing capacity evaluation and the deformation resistance evaluation meets the corresponding standard in the technical design standard set, and if so, carrying out the design at the next stage; carrying out product design of a rotor structure, obtaining boundary conditions of the rotor structure at the current stage, setting a product design standard set, carrying out bearing capacity evaluation, deformation resistance evaluation and mechanical environment adaptability evaluation of the rotor structure, wherein the mechanical environment adaptability evaluation comprises rotor rigidity/quality coordination factors and rotor resonance rotating speed strain energy distribution, judging whether each parameter in the bearing capacity evaluation, the deformation resistance evaluation and the mechanical environment adaptability evaluation meets the corresponding standard in the product design standard set, and if so, completing the design of the rotor structure.
Preferably, the boundary conditions of the design phase of the solution include stresses sigma of the cells in the rotor structure i And mass m i Allowable stress sigma of unit material b The volume occupied by different stress regions and the total structural volume V;
the calculation formula of the average stress is as follows:
wherein sigma i And m i Respectively representing the stress and the mass of the ith unit in the structure;
carrying out normalization processing to obtain a calculation formula of the average stress coefficient, wherein the calculation formula is as follows:
the calculation formula of the stress distribution coefficient is as follows:dispersing the total stress distribution into a finite number of intervals [ sigma ] in the calculation i ,σ i+1 ) The stress distribution coefficient calculation formula of the discrete points is as follows:
preferably, the boundary conditions of the technical design phase include: elastic modulus and moment of inertia corresponding to each section material and equivalent stiffness K of rotor on designated section c The rotor structure mass M;
the calculation formula of the bending rigidity distribution of the rotor is as follows: f (E) i I i )＝E i I i ；
The calculation formula of the equivalent stiffness of the rotor is as follows:
preferably, the engine rotor-support system operating speed range is coexistent at an i-order resonance speed, and the boundary conditions of the product design stage include: equivalent rigidity and equivalent mass of each substructure of rotor structure, and bending strain energy W of rotor at ith order resonance rotation speed rotor,i And the total strain energy W of the rotor-bearing system at the ith order resonance speed sys,i ；
The calculation formula of the rotor rigidity/quality coordination factor is as follows:
the calculation formula of the rotor resonance rotating speed strain energy distribution is as follows:
according to the quantitative assessment method for mechanical properties of the aero-engine rotor structure, the bearing capacity assessment of the bearing structure is carried out in the scheme design stage of the bearing structure, the bearing capacity assessment and the deformation resistance assessment of the bearing structure are carried out in the technical design stage, and the bearing capacity assessment, the deformation resistance assessment and the mechanical environment adaptability assessment of the bearing structure are carried out in the product design stage; quantitative evaluation of rotor structure layout and design results can be rapidly realized, so that an important method and means are provided for rapid and accurate iteration of rotor structure design and scheme; the bearing capacity, the bending resistance and the environment adaptability of the rotor can be effectively ensured, and the working performance of the rotor structure is improved.
Drawings
In order to more clearly illustrate the technical solution provided by the present application, the following description will briefly refer to the accompanying drawings. It will be apparent that the figures described below are merely some embodiments of the application.
FIG. 1 is a schematic overall flow chart of the present application.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application become more apparent, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application.
The quantitative evaluation method for the mechanical characteristics of the rotor structure of the aeroengine is characterized by accurately describing the comprehensive adaptability of the structural system to the environment/conditions in the working process, and comprises three aspects of rotor structure bearing capacity evaluation, rotor structure deformation resistance evaluation and rotor structure mechanical environment adaptability evaluation.
The rotor design generally includes three phases: the design method comprises the steps of scheme design, technical design and product design, wherein the scheme design stage is used for designing a basic structure frame meeting requirements, the technical design stage is used for designing details of the basic structure frame, and the product design stage is used for perfecting all structures of the bearing structure.
The values of the same parameter will change at different stages, so that the same parameter needs to be acquired again at different stages.
As shown in fig. 1, the method specifically comprises the following steps:
step S100, carrying out scheme design of a rotor structure, obtaining boundary conditions of the rotor structure at the current stage, setting a scheme design standard set, carrying out bearing capacity assessment of the rotor structure, wherein the bearing capacity assessment comprises average stress coefficients and stress distribution coefficients of the rotor structure, judging whether all parameters in the bearing capacity assessment meet corresponding standards in the scheme design standard set, and if so, carrying out next stage design;
the load-bearing capacity evaluation of the structure is mainly to evaluate the influence degree of the structural material and the structural geometric form on the load-bearing capacity of the structure under the working environment, namely, the structure has the maximum load-bearing capacity (the average stress level of the structure is the highest) through the optimization of the structural geometric form and the reasonable selection of the material under the minimum quality. The assessment of the rotor carrying capacity can be translated into an assessment of the disk carrying capacity. The ability of the disk to carry rotational inertial loads is the most sensitive factor in controlling the shape, size and mass of the structure, so it is reasonable to evaluate the bearing ability of the rotor structure as represented by its average stress coefficient and stress distribution coefficient.
Boundary conditions for the design phase of the solution include stresses sigma for each cell in the rotor structure i And mass m i Allowable stress sigma of material corresponding to rotor structure b The volume occupied by different stress regions and the total structural volume V;
1) Average stress coefficient
The calculation formula of the average stress is as follows:
wherein sigma i And m i Respectively representing the stress and the mass of the ith unit in the structure;
for comparison, normalization processing is carried out, and the calculation formula for obtaining the average stress coefficient is as follows:
the average stress coefficient can represent the relationship between the structural load capacity and the mass, i.e., the greater the stress per unit, the greater the average stress coefficient; the larger the required stress of the unit material, the smaller the average stress coefficient.
2) Coefficient of stress distribution
The stress distribution coefficient refers to the proportional relation of the structural volume occupied by each stress level in the range of the maximum stress and the minimum stress of the rotor structure in the working state. The calculation formula of the stress distribution coefficient is as follows:
since the numerical simulation results are discrete, the total stress distribution can be discretized into a finite number of intervals [ sigma ] in the calculation i ,σ i+1 ) The stress distribution coefficient calculation formula of the discrete points is as follows:
it can be derived that the larger the total volume of the structure, the smaller the stress distribution coefficient; the larger the volume occupied by a stress interval, the larger the stress distribution coefficient.
If any parameter does not meet the design standard requirement, correcting the structure corresponding to the parameter, evaluating the bearing capacity again, and repeating the process until the design of the stage is completed.
Step S200, carrying out technical design of a rotor structure, obtaining boundary conditions of the rotor structure at the current stage, setting a technical design standard set, carrying out bearing capacity evaluation and deformation resistance evaluation of the rotor structure, wherein the deformation resistance evaluation comprises rotor bending stiffness distribution, rotor equivalent stiffness and maximum deformation of the rotor under limit inertial load, judging whether each parameter in the bearing capacity evaluation and the deformation resistance evaluation meets the corresponding standard in the technical design standard set, and if so, carrying out the design at the next stage;
according to the structural characteristics of the rotor system of the aviation turbofan engine, the main anti-deformation capability of the rotor structure in structural design is as follows: 1) Has good bending rigidity in the transverse direction; 2) The disc shaft joint has good angular rigidity; 3) The maximum deformation of the rotor under the limit inertial load is thus measured separately.
Technical design stageThe boundary conditions of (2) include: elastic modulus and moment of inertia corresponding to each section material and equivalent stiffness K of rotor on designated section c The rotor structure mass M; this phase requires that all parameters in step S100 are acquired simultaneously and that the load bearing capacity assessment is performed again according to the method in step S100.
1) Rotor bending stiffness distribution
The flexural rigidity distribution of the rotor can reflect the influence of the geometric shape of the rotor structure (without considering the influence of the bearing) on the flexural rigidity and the characteristics distributed along the axial direction, so that the influence relation of the structural characteristics of the rotor on the rigidity of the rotor is represented, and the calculation formula of the flexural rigidity distribution of the rotor is as follows:
f(E i I i )＝E i I i
wherein E is i And I i The elastic modulus and the moment of inertia of the ith cross-sectional material are respectively expressed, namely, the larger the elastic module or the moment of inertia of a cross-sectional material is, the larger the bending stiffness of the rotor of the cross-sectional material is, and after each cross-sectional material is calculated, the bending stiffness distribution of the rotor is obtained.
2) Rotor equivalent (specific) stiffness
The equivalent specific stiffness of the rotor refers to the equivalent bending stiffness that the unit mass of the rotor system can provide in a given section, and is used to describe the proportional relationship between the bending stiffness of the rotor system (geometry and material) itself and the structural mass. The calculation formula of the equivalent stiffness of the rotor is as follows:
K c representing the equivalent stiffness of the rotor in a given section, taking into account the manner of support and not taking into account the effect of the stiffness of the support; k (K) ρ The larger indicates the better overall bending stiffness of the rotor.
3) Maximum deformation of rotor under limit inertial load
The maximum deflection of the rotor under extreme inertial loading is the maximum lateral or angular deflection of the designed engine under inertial loading as a result of a specified maximum overload/maneuver, which reflects the combined resistance of the structure to deformation as a function of mass and stiffness distribution. The calculation mode is a general calculation mode in the field, and is not described in detail.
And when any parameter in the bearing capacity evaluation and the deformation resistance evaluation in the technical design stage does not meet the corresponding standard in the technical design standard set, correcting the structure corresponding to the parameter, evaluating the bearing capacity or the deformation resistance again, and repeating the process until the design in the stage is completed.
Step S300, carrying out product design of a rotor structure, obtaining boundary conditions of the rotor structure at the current stage, setting a product design standard set, and carrying out bearing capacity assessment, deformation resistance assessment and mechanical environment adaptability assessment of the rotor structure, wherein the mechanical environment adaptability assessment comprises rotor rigidity/quality coordination factors and rotor resonance rotating speed strain energy distribution, judging whether each parameter in the bearing capacity assessment, the deformation resistance assessment and the mechanical environment adaptability assessment meets corresponding standard in the product design standard set, and if so, completing the design of the rotor structure.
The mechanical environment adaptability of the rotor structure, namely the dynamic sensitivity characteristic of the structure, is to reflect the response degree of the rotor system to the internal and external periodic exciting forces. The assessment of the mechanical environment adaptation capability of a rotor system can be divided into two aspects: firstly, evaluating the resonance prevention safety margin of a rotor system; and secondly, evaluating the energy distribution and the possible damage degree of the rotor system under the resonance state. Therefore, in order to fully reflect the mechanical environment adaptability (dynamic sensitivity) of the rotor structure, parameters such as the rotor rigidity/quality coordination factor, the divergence thereof, the strain energy distribution under the rotor resonance rotating speed and the like are evaluated.
Coexisting in the i-order resonance rotation speed in the working rotation speed range of the engine rotor-supporting system, wherein the boundary conditions of the product design stage comprise: equivalent rigidity and equivalent mass of each substructure of rotor structure, and bending strain energy W of rotor at ith order resonance rotation speed rotor,i And the total strain energy W of the rotor-bearing system at the ith order resonance speed sys,i ；
All parameters in the steps S100-S200 are required to be collected simultaneously at the stage, and the carrying capacity evaluation is carried out again according to the method in the step S100; the deformation resistance evaluation is performed again in accordance with the method in step S200.
1) Rotor stiffness/mass coordination factor and divergence
The stiffness/mass coordination factor (M-H factor for short) has the same unit as the circular frequency unit (radian/second) and can be used for reflecting the mutual similarity and the coupling degree between the dynamic characteristics of all the substructures.
The calculation formula of the rotor rigidity/quality coordination factor is as follows:
wherein k is i And m i Equivalent stiffness and equivalent mass for the ith sub-structure. That is, the greater the equivalent stiffness of a substructure, the greater the rotor stiffness/mass coordination factor; the greater the equivalent mass of a substructure, the less the rotor stiffness/mass coordination factor.
2) Rotor resonance rotational speed strain energy distribution
The rotor resonance rotational speed strain energy distribution refers to the ratio of the rotor bending strain energy to the total strain energy corresponding to each order of resonance rotational speed within the highest operating rotational speed. The calculation formula of the rotor resonance rotating speed strain energy distribution is as follows:
the resonance rotational speed strain energy of the rotor represents the proportion of the strain energy occupied by the rotor in the rotor-supporting system, when W rotor,i The larger the rotor resonance rotational speed strain energy is, the larger the rotor resonance rotational speed strain energy is; when W is sys,i The greater the rotor resonance rotational speed strain energy is, the less.
And when any parameter in the bearing capacity evaluation, the deformation resistance and the mechanical environment adaptability evaluation in the product design stage does not meet the corresponding standard in the technical design standard set, correcting the structure corresponding to the parameter, evaluating the bearing capacity evaluation, the deformation resistance or the mechanical environment adaptability again, and repeating the process until the design in the stage is completed.
And setting the standard value range of each parameter to be evaluated in the scheme design standard set, the technical design standard set and the product design standard set, and if the calculated result is in the range corresponding to the standard value, indicating that the standard is met, otherwise, not meeting the standard.
For a rigid rotor (high-pressure rotor), the proportion of the strain energy of the whole rotor in a resonance state (or working condition) is calculated, and the proportion of the strain energy of the shaft in the whole strain energy is generally not more than 20%. And during finite element calculation, defining the stiffness parameters of all fulcrums according to the actual stiffness value of the rotor support.
The method comprises the steps of carrying out bearing capacity assessment of a bearing structure in a scheme design stage of the bearing structure, carrying out bearing capacity assessment and deformation resistance assessment of the bearing structure in a technical design stage, and carrying out bearing capacity assessment, deformation resistance assessment and mechanical environment adaptability assessment of the bearing structure in a product design stage; quantitative evaluation of rotor structure layout and design results can be rapidly realized, so that an important method and means are provided for rapid and accurate iteration of rotor structure design and scheme; the bearing capacity, the bending resistance and the environment adaptability of the rotor can be effectively ensured, and the working performance of the rotor structure is improved.
The foregoing is merely illustrative of the present application, and the present application is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present application should be included in the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (4)
1. The quantitative evaluation method for the mechanical properties of the rotor structure of the aero-engine is characterized by comprising the following steps of:
carrying out scheme design of a rotor structure, obtaining boundary conditions of the rotor structure at the current stage, setting a scheme design standard set, carrying out bearing capacity assessment of the rotor structure, wherein the bearing capacity assessment comprises average stress coefficients and stress distribution coefficients of the rotor structure, judging whether all parameters in the bearing capacity assessment meet corresponding standards in the scheme design standard set, and if yes, carrying out next stage design;
carrying out technical design of a rotor structure, obtaining boundary conditions of the rotor structure at the current stage, setting a technical design standard set, carrying out bearing capacity evaluation and deformation resistance evaluation of the rotor structure, wherein the deformation resistance evaluation comprises rotor bending stiffness distribution, rotor equivalent stiffness and maximum deformation of the rotor under limit inertial load, judging whether each parameter in the bearing capacity evaluation and the deformation resistance evaluation meets the corresponding standard in the technical design standard set, and if so, carrying out the design at the next stage;
carrying out product design of a rotor structure, obtaining boundary conditions of the rotor structure at the current stage, setting a product design standard set, carrying out bearing capacity evaluation, deformation resistance evaluation and mechanical environment adaptability evaluation of the rotor structure, wherein the mechanical environment adaptability evaluation comprises rotor rigidity/quality coordination factors and rotor resonance rotating speed strain energy distribution, judging whether each parameter in the bearing capacity evaluation, the deformation resistance evaluation and the mechanical environment adaptability evaluation meets the corresponding standard in the product design standard set, and if so, completing the design of the rotor structure.
2. The quantitative assessment method for mechanical properties of an aeroengine rotor structure according to claim 1, wherein the quantitative assessment method comprises the following steps: the boundary conditions of the design phase of the solution include the stress sigma of each unit in the rotor structure i And mass m i Allowable stress sigma of unit material b The volume occupied by different stress regions and the total structural volume V;
the calculation formula of the average stress is as follows:
wherein sigma i And m i Respectively representing the stress and the mass of the ith unit in the structure;
carrying out normalization processing to obtain a calculation formula of the average stress coefficient, wherein the calculation formula is as follows:
the calculation formula of the stress distribution coefficient is as follows:dispersing the total stress distribution into a finite number of intervals [ sigma ] in the calculation i ,σ i+1 ) The stress distribution coefficient calculation formula of the discrete points is as follows: />
3. The quantitative assessment method for mechanical properties of an aircraft engine rotor structure according to claim 1, wherein the boundary conditions of the technical design phase include: elastic modulus and moment of inertia corresponding to each section material and equivalent stiffness K of rotor on designated section c The rotor structure mass M;
the calculation formula of the bending rigidity distribution of the rotor is as follows: f (E) i I i )＝E i I i Wherein E is i And I i Respectively representing the elastic modulus and the moment of inertia of the ith cross-sectional material;
the calculation formula of the equivalent stiffness of the rotor is as follows:
4. the quantitative assessment method for mechanical properties of an aeroengine rotor structure according to claim 1, wherein the engine rotor-support system operating speed range is coexistent at i-order resonance speed, and the boundary conditions of the product design stage include: equivalent rigidity and equivalent mass of each substructure of rotor structure, and bending strain energy W of rotor at ith order resonance rotation speed rotor,i And the total strain energy W of the rotor-bearing system at the ith order resonance speed sys,i ；
The calculation formula of the rotor rigidity/quality coordination factor is as follows:wherein k is i And m i Equivalent stiffness and equivalent mass for the i-th substructure;
the calculation formula of the rotor resonance rotating speed strain energy distribution is as follows:
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| CN113432816A (en) * | 2021-06-11 | 2021-09-24 | 中北大学 | Method for testing and controlling unevenness of coupling rigidity of aircraft engine rotor |
| CN113435035A (en) * | 2021-06-25 | 2021-09-24 | 中国航发沈阳发动机研究所 | Method for evaluating axial force of rotor through contact trace of bearing inner ring |
| CN113486561A (en) * | 2021-07-20 | 2021-10-08 | 中国科学院工程热物理研究所 | Engine rotor dynamic characteristic improving method based on strain energy distribution |
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| US3588265A (en) * | 1968-04-19 | 1971-06-28 | Westinghouse Electric Corp | System and method for providing steam turbine operation with improved dynamics |
| CN113432816A (en) * | 2021-06-11 | 2021-09-24 | 中北大学 | Method for testing and controlling unevenness of coupling rigidity of aircraft engine rotor |
| CN113435035A (en) * | 2021-06-25 | 2021-09-24 | 中国航发沈阳发动机研究所 | Method for evaluating axial force of rotor through contact trace of bearing inner ring |
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