CN116542114B - Method and device for analyzing temperature stress deformation of compressor rotor based on overall parameters - Google Patents

Method and device for analyzing temperature stress deformation of compressor rotor based on overall parameters Download PDF

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CN116542114B
CN116542114B CN202310807475.0A CN202310807475A CN116542114B CN 116542114 B CN116542114 B CN 116542114B CN 202310807475 A CN202310807475 A CN 202310807475A CN 116542114 B CN116542114 B CN 116542114B
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temperature
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mach number
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CN116542114A (en
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程荣辉
杨远龙
庞燕龙
吴坚
田洪宇
张少平
李昆
贺进
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AECC Sichuan Gas Turbine Research Institute
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Abstract

The invention relates to the technical field of aeroengine turbine blade design, and discloses a method and a device for analyzing temperature stress deformation of a compressor rotor based on general parameters.

Description

Method and device for analyzing temperature stress deformation of compressor rotor based on overall parameters
Technical Field
The invention relates to the technical field of aero-engine turbine blade design, and discloses a method and a device for analyzing temperature stress deformation of a compressor rotor based on overall parameters.
Background
The compressor rotor is an important component part of the compressor component, and because the compressor rotor is of a high-speed rotating structure, if the compressor rotor fails, the use safety of an engine is directly affected, and the key content of the safety design of the compressor rotor is as follows: solving and analyzing temperature, stress and displacement results.
At present, temperature stress and displacement solutions of compressor rotors mainly depend on commercial finite elements. Taking the design of a certain engine compressor rotor as an example, the complete finite element evaluation flow of an engine state point is as follows: and calculating the overall parameters of the engine according to the flight envelope state points, calculating the aerodynamic boundary according to the overall parameters, calculating the temperature boundary according to the overall parameters and the aerodynamic boundary, and solving the temperature, stress and displacement of the rotor according to the aerodynamic boundary and the temperature boundary.
Taking an engine as an example, the number of working points in a design envelope is hundreds, and if finite element analysis is fully carried out, huge time cost and labor cost are consumed, so that the engine design is not facilitated.
In order to shorten the design period of the engine and reduce the design cost, the traditional compressor rotor often adopts a method for simplifying state points during design, and different simplification strategies are adopted according to different development stages. Such as: hundreds of state points are often simplified to a plurality of typical points in the early design stage, and preliminary design iteration is rapidly completed; the later design stage often simplifies the state points into tens of key points, covering as important state points for engine operation as possible. The simplified method has the advantages that design iteration can be completed quickly in the initial stage of design, and the defect that dangerous state points are possibly missed is overcome; in the later stage of design, the system has the advantages of covering most key state points, and has the defects of not completely covering the working state points of the engine, increasing the calculation amount of finite elements and correspondingly increasing the time cost and the labor cost.
Disclosure of Invention
The invention aims to provide a method and a device for analyzing temperature stress deformation of a compressor rotor based on overall parameters. Especially, when the temperature, equivalent stress and total displacement result calculation on hundreds or even thousands of state points are needed to be carried out on the compressor, the established function model has good adaptability, can completely cover the working state points of the engine, and can shorten the design period and reduce the design cost.
In order to achieve the technical effects, the technical scheme adopted by the invention is as follows:
the method for analyzing the temperature stress deformation of the compressor rotor based on the overall parameters comprises the following steps:
selecting sample state points from an aeroengine flight envelope map, wherein the transverse axis of the flight envelope map is Mach number, and the vertical axis of the flight envelope map is flight height; the sample state points comprise a first point with zero Mach number and zero height, a second point with maximum Mach number and zero height, a third point with maximum Mach number and corresponding to the minimum height in the engine flight envelope, a fourth point with maximum Mach number and corresponding to the maximum height in the engine flight envelope, and a fifth point with maximum height and corresponding to the minimum Mach number; a sixth point with zero Mach number and maximum height, and two state points with the longest engine working time in the flight envelope;
acquiring overall parameters in each sample state point, wherein the overall parameters comprise the total inlet temperature, the total outlet temperature, the total inlet pressure, the total outlet pressure and the rotating speed of a rotor of the compressor;
obtaining the temperature, equivalent stress and total displacement corresponding to each sample state point through finite element analysis, wherein the total displacement is the vector sum of axial deformation, circumferential deformation and radial deformation of the compressor rotor under the corresponding working condition;
taking the total inlet temperature, the total outlet temperature, the total inlet pressure, the total outlet pressure and the rotating speed of a rotor of the compressor as independent variables, and taking the temperature, the equivalent stress and the total displacement corresponding to each sample point obtained by finite element analysis as dependent variables to fit a function model between the temperature of the compressor and the overall parameter, a function model between the equivalent stress of the compressor and the overall parameter and a function model between the total displacement of the compressor and the overall parameter respectively;
and inputting the overall parameters of the compressor in the state to be detected into corresponding function models, and respectively calculating the temperature, equivalent stress and total displacement results corresponding to the point to be detected.
Further, compressor temperatureFunction model between the overall parametersFitting to obtain>Is the total temperature of the inlet of the air compressor>Is the total temperature of the outlet of the air compressor>、/>、/>Are fitting coefficients.
Further, the equivalent stress of the compressorFunction model between the overall parametersFitting to obtain>Is the total temperature of the inlet of the air compressor>Is the outlet assembly of the air compressorWarm (en)>Is the total pressure of the inlet of the air compressor>Is the total pressure of the outlet of the air compressor>Is the rotating speed of the rotor of the air compressor,/-for>、/>、/>、/>、/>、/>、/>Are fitting coefficients.
Further, the total displacement of the compressorFunction model between the overall parametersFitting to obtain>Is the total temperature of the inlet of the air compressor>Is the total temperature of the outlet of the air compressor>Is the total pressure of the inlet of the air compressor>Is the total pressure of the outlet of the air compressor>Is the rotating speed of the rotor of the air compressor,/-for>、/>、/>、/>、/>、/>、/>Are fitting coefficients.
In order to achieve the technical effects, the invention also provides a compressor rotor temperature stress deformation analysis device based on overall parameters, which comprises:
the state point selection module is used for selecting sample state points from an aeroengine flight envelope graph, wherein the transverse axis of the flight envelope graph is Mach number, and the longitudinal axis of the flight envelope graph is flight height; the sample state points comprise a first point with zero Mach number and zero height, a second point with maximum Mach number and zero height, a third point with maximum Mach number and corresponding to the minimum height in the engine flight envelope, a fourth point with maximum Mach number and corresponding to the maximum height in the engine flight envelope, and a fifth point with maximum height and corresponding to the minimum Mach number; a sixth point with zero Mach number and maximum height, and two state points with the longest engine working time in the flight envelope;
the parameter acquisition module is used for acquiring overall parameters in each sample state point, wherein the overall parameters comprise the total inlet temperature, the total outlet temperature, the total inlet pressure, the total outlet pressure and the rotating speed of the compressor rotor;
the finite element analysis module is used for obtaining the temperature, equivalent stress and total displacement corresponding to each sample state point through finite element analysis, and the total displacement is the vector sum of the axial deformation, the circumferential deformation and the radial deformation of the compressor rotor under the corresponding working condition;
the model fitting module is used for respectively fitting a function model between the temperature of the air compressor and the overall parameter, a function model between the equivalent stress of the air compressor and the overall parameter and a function model between the total displacement of the air compressor and the overall parameter by taking the total inlet temperature, the total outlet temperature, the total inlet pressure, the total outlet pressure and the rotating speed of the air compressor rotor of the air compressor as independent variables and taking the temperature, the equivalent stress and the total displacement of each sample point obtained by finite element analysis as dependent variables;
the prediction module is used for receiving the overall parameters of the compressor in the state to be detected, and respectively calculating the temperature, equivalent stress and total displacement results corresponding to the point to be detected according to the corresponding function model.
Further, in the model fitting module, the temperature of the compressorFunction model between the overall parametersFitting to obtain->Is the total temperature of the inlet of the air compressor>Is the total temperature of the outlet of the air compressor,、/>、/>are fitting coefficients.
Further, in the model fitting module, the equivalent stress of the compressorFunction model between the parameters and the population is based on +.>Fitting to obtain>Is the total temperature of the inlet of the air compressor>Is the total temperature of the outlet of the air compressor>Is the total pressure of the inlet of the air compressor>Is the total pressure of the outlet of the air compressor>Is the rotating speed of the rotor of the air compressor,/-for>、/>、/>、/>、/>、/>、/>Are fitting coefficients.
Further, in the model fitting module, the total displacement of the compressorFunction model between the parameters and the population is based on +.>Fitting to obtain>Is the total temperature of the inlet of the air compressor>Is the total temperature of the outlet of the air compressor>Is the total pressure of the inlet of the air compressor>Is the total pressure of the outlet of the air compressor>Is the rotating speed of the rotor of the air compressor,/-for>、/>、/>、/>、/>、/>、/>Are fitting coefficients.
Compared with the prior art, the invention has the following beneficial effects: the invention establishes the function model between the temperature of the air compressor and the overall parameters, the function model between the equivalent stress of the air compressor and the overall parameters and the function model between the total displacement of the air compressor and the overall parameters by utilizing the typical state points in the engine flight envelope in a subsection manner, is used for calculating the temperature value, the equivalent stress value and the total displacement value of the state to be measured in a subsection manner, and the fitting model not only can completely cover the working state points of the engine, but also can avoid the problem of data extrapolation, ensures the calculation precision of each function model, can obtain the improvement of the calculation efficiency by thousands of times, and achieves the purposes of shortening the design period and reducing the design cost.
Drawings
FIG. 1 is a schematic view of selected sample status points in the engine flight package diagram of example 1 or 2;
FIG. 2 is a graph showing the deviation between the predicted equivalent stress of the functional model and the overall parameters of the compressor in example 2 and the finite element result;
FIG. 3 is a graph showing the deviation between the estimated temperature of the functional model and the overall parameters of the compressor in example 2 and the finite element result;
FIG. 4 is a graph showing the deviation between the estimated total displacement of the functional model and the overall parameters of the compressor in example 2 and the finite element result;
fig. 5 is a block diagram showing a structure of a compressor rotor temperature stress deformation analysis device based on overall parameters in embodiment 1;
the method comprises the steps of 1, a state point selection module; 2. a parameter acquisition module; 3. a finite element analysis module; 4. a model fitting module; 5. and a prediction module.
Detailed Description
The present invention will be described in further detail with reference to the following examples and drawings. It should not be construed that the scope of the above subject matter of the present invention is limited to the following embodiments, and all techniques realized based on the present invention are within the scope of the present invention.
Example 1
Referring to fig. 1, a method for analyzing temperature stress deformation of a compressor rotor based on overall parameters includes:
selecting a sample state point from an aeroengine flight envelope diagram, wherein the transverse axis of the flight envelope diagram is Mach number Ma, and the longitudinal axis of the flight envelope diagram is flight height H; the sample state points comprise a first point A with zero Mach number and zero height, a second point B with maximum Mach number and zero height, a third point C with maximum Mach number and corresponding to the minimum height in the engine flight envelope, a fourth point D with maximum Mach number and corresponding to the maximum height in the engine flight envelope and a fifth point E with maximum Mach number and corresponding to the minimum Mach number; a sixth point F with zero Mach number and maximum height, and two state points G, K with the longest engine working time in the flight envelope;
acquiring overall parameters in each sample state point, wherein the overall parameters comprise the total inlet temperature, the total outlet temperature, the total inlet pressure, the total outlet pressure and the rotating speed of a rotor of the compressor;
obtaining the temperature, equivalent stress and total displacement corresponding to each sample state point through finite element analysis;
taking the total inlet temperature, the total outlet temperature, the total inlet pressure, the total outlet pressure and the rotating speed of a rotor of the compressor as independent variables, and taking the temperature, the equivalent stress and the total displacement corresponding to each sample point obtained by finite element analysis as dependent variables to fit a function model between the temperature of the compressor and the overall parameter, a function model between the equivalent stress of the compressor and the overall parameter and a function model between the total displacement of the compressor and the overall parameter respectively;
and inputting the overall parameters of the compressor in the state to be detected into corresponding function models, and respectively calculating the temperature, equivalent stress and total displacement results corresponding to the point to be detected.
In this embodiment, a plurality of sample status points are selected from the aeroengine flight envelope, wherein the sample status points at least include a first point A with zero Mach number and zero height, a second point B with maximum Mach number and zero height, a third point C with maximum Mach number and minimum height in the engine flight envelope, a fourth point D with maximum Mach number and maximum height in the engine flight envelope, and a fifth point E with maximum Mach number and minimum height; the working state points of the engine flight spectrum are simplified by the sixth point F with zero Mach number and maximum height and the two state points G, K with the longest working time of the engine in the flight envelope; and then, based on the overall parameters corresponding to all the state points of the engine and simulation, obtaining the temperature, equivalent stress and total displacement corresponding to all the states, respectively fitting a function model between the temperature and the overall parameters of the air compressor, a function model between the equivalent stress and the overall parameters of the air compressor and a function model between the total displacement and the overall parameters of the air compressor, and inputting the overall parameter data of the state to be tested of the engine into the corresponding function model to obtain the temperature, equivalent stress and total displacement results corresponding to the state points to be tested. Compared with the traditional finite element analysis method, the method utilizes the typical state points in the engine flight envelope to establish the function model of the temperature, equivalent stress and total displacement of the compressor rotor, and is used for calculating the temperature value, equivalent stress value and total displacement value of the state to be measured, the fitting model not only can completely cover the working state points of the engine, but also can avoid the problem of data extrapolation, the calculation precision of the function model is ensured, the calculation efficiency of thousands of times is improved, and the purposes of shortening the design period and reducing the design cost are achieved.
Referring to fig. 1 and 5, based on the same inventive concept, the present embodiment further provides a compressor rotor temperature stress deformation analysis device based on general parameters, including:
the system comprises a state point selection module 1, wherein the state point selection module 1 is used for selecting sample state points from an aeroengine flight envelope graph, the transverse axis of the flight envelope graph is Mach number Ma, and the longitudinal axis of the flight envelope graph is flight height H; the sample state points comprise a first point A with zero Mach number and zero height, a second point B with maximum Mach number and zero height, a third point C with maximum Mach number and corresponding to the minimum height in the engine flight envelope, a fourth point D with maximum Mach number and corresponding to the maximum height in the engine flight envelope and a fifth point E with maximum Mach number and corresponding to the minimum Mach number; a sixth point F with zero Mach number and maximum height, and two state points G, K with the longest engine working time in the flight envelope;
a parameter acquisition module 2, wherein the parameter acquisition module 2 is used for acquiring overall parameters in each sample state point, and the overall parameters comprise the total inlet temperature of the compressorTotal outlet temperature->Total pressure of inlet->Total outlet pressure->And the rotational speed of the compressor rotor->；
The finite element analysis module 3 is used for obtaining the temperature, equivalent stress and total displacement corresponding to each sample state point through finite element analysis, wherein the total displacement is the vector sum of the axial deformation, the circumferential deformation and the radial deformation of the compressor rotor under the corresponding working condition;
a model fitting module 4, wherein the model fitting module 4 is used for using the total inlet temperature of the compressorTotal outlet temperature->Total pressure of inlet->Total outlet pressure->And the rotational speed of the compressor rotor->And as independent variables, the temperature, equivalent stress and total displacement corresponding to each sample point obtained by finite element analysis are used as dependent variables, and a function model between the temperature of the compressor and the overall parameters, a function model between the equivalent stress of the compressor and the overall parameters and a function model between the total displacement of the compressor and the overall parameters are respectively fitted. In the model fitting module 4 of the present embodiment, the compressor temperature +.>Function model between the overall parametersFitting to obtain>、/>、/>Are fitting coefficients. Compressor temperature->The function model between the total temperature and the overall parameter is that the total temperature of the inlet of the compressor is adopted>Total outlet temperature->The temperature corresponding to each sample point obtained by finite element analysis is a dependent variable, and the process of solving the matrix by finite element iteration is converted into algebraic solution of a coefficient equation, so that the calculated amount is greatly reduced. Equivalent stress of compressor->Function model between the overall parametersFitting to obtain>、/>、/>、/>、/>、/>、/>Are fitting coefficients. Equivalent stress of compressor->The function model between the total temperature and the overall parameter is that the total temperature of the inlet of the compressor is adopted>Total outlet temperature->Total pressure of inlet->Total outlet pressure->And the rotational speed of the compressor rotor->And as independent variables, the equivalent stress corresponding to each sample point obtained by finite element analysis is a dependent variable, and the process of solving the matrix by finite element iteration is converted into algebraic solution of a coefficient equation, so that the calculated amount is greatly reduced. Total displacement of compressor->Function model between the overall parametersFitting to obtain>、/>、/>、/>、/>、/>、/>Are fitting coefficients. Total displacement of compressor->The function model between the total temperature and the overall parameter is that the total temperature of the inlet of the compressor is adopted>Total outlet temperature->Total pressure of inlet->Total outlet pressure->And the rotational speed of the compressor rotor->And as independent variables, the total displacement corresponding to each sample point obtained by finite element analysis is used as a dependent variable, and the process of solving the matrix by finite element iteration is converted into algebraic solution of a coefficient equation, so that the calculated amount is greatly reduced.
The prediction module 5 is used for receiving the overall parameters of the compressor in the state to be detected, and respectively calculating the temperature, equivalent stress and total displacement results corresponding to the point to be detected according to the corresponding function model.
Example 2
In order to verify the reliability of the invention, 8 state points of an engine are selected, a calculation model is built, and the building process of each function model is as follows:
step 1, for a compressor rotor, the temperature of the compressor rotor is mainly subjected to the total temperature of an inlet of the compressorAnd total outlet temperatureInfluence, thus select->And->As fitting parameters; the equivalent stress of the compressor rotor is mainly subjected to the rotation speed of the compressor rotor>Related centrifugal force, inlet total pressure->And total outlet pressure->Related aerodynamic force, total inlet temperature +.>And total outlet temperatureThe influence of the relevant thermal equivalent stress is thus chosen +.>、/>、/>、/>And->As fitting parameters; the total displacement of the compressor rotor is mainly equal to the rotational speed of the compressor rotor>Related centrifugal deformation, total inlet pressure +.>And total outlet pressure->Pneumatic deformation and total inlet temperature>And total outlet temperature->Influence of the related thermal deformations, thus select +.>、/>、/>、And->As a fitting parameter.
In the engine flight envelope, the stable operating point is up to hundreds. To ensure computational accuracy, each function model should avoid data extrapolation. Therefore, when screening sample state points for constructing the calculation model, 5 key parameters screened in the step 1 are avoided、/>、/>、/>And->Extrapolation occurs. The sample state points selected in this embodiment are shown in fig. 1, and the second point B, the third point C and the fourth point D of the right boundary point can ensure +.>、/>、/>、/>And->The upper limits of these five parameters; the first point A, the sixth point F and the fifth point E in the left boundary point can be guaranteed +.>、/>、/>、/>And->The lower limits of these five parameters; the long point G and the long two points K in the long-term working point can ensure the reliability of the result under the important working condition, and simultaneously ensure that the number of the state points is at least 8 and is larger than the maximum number of the calculated model coefficients (as in the embodiment +.>、/>、/>、/>、/>、/>、/>These 7 coefficients) ensures the reliability of the linear regression algorithm.
Step 2, obtaining the temperature, equivalent stress and total displacement corresponding to each sample state point through finite element analysis;
step 3, for equivalent stressIs associated with the overall parameter +.>、/>、/>、/>And->The functional relation of (2) can be expressed as +.>；
Because of equivalent stressIn which the centrifugal force is dominant and is equal to the square of the rotational speed of the compressor rotor +.>Is a linear relationship, thus, a function +.>For the rotational speed of the compressor rotor->The expanded term of (2) needs to be reserved to the quadratic term; aerodynamic force related item->And the thermal equivalent stress ∈ ->Has less influence on the equivalent stress, thus the function +.>For->The expanded term of (2) remains to the primary term. Applying the above procedure to the compressor equivalent stress +.>In the function model between the total parameters, can be obtained。
Likewise, for temperatureIs related to the overall parameter +.>Can be expressed as a functional relationship of；
Because the compressor rotor does not involve complex temperature changes such as combustion, air film heat exchange and the like, the function is realizedFor->Retaining the expanded primary item to obtain->。
Likewise, for total displacementIs a functional model of->、/>、/>、/>And->The functional relation of (2) can be expressed as +.>；
Total displacement ofAnd equivalent stress->Similarly, the compressor rotor speed +.>To the secondary term, the remainder to the primary term, thus can be obtained。
Then, according to the finite element calculation result in the step 2, the equivalent stress can be solved by a linear regression algorithmTemperature->And total displacement->Model coefficients are calculated.
Step 4, substituting the relevant overall parameters of each state point to be detected into the model by using the function model) The temperature, equivalent stress and total displacement result of the compressor rotor at the full envelope operating point of the engine can be directly calculated.
And solving the results of equivalent stress, temperature and total displacement of 67 state points, and comparing the results with the corresponding data results of 67 state points analyzed by finite element. The comparison results are shown in fig. 2-4:
as can be seen from FIG. 2, by adopting the analysis method for temperature stress deformation of the compressor rotor based on the overall parameters, the relative equivalent stress deviation of the obtained equivalent stress predicted value can be controlled to be-2% -1%, and the equivalent stress of the compressor rotor is usually not more than 1200Mpa, so that the equivalent stress deviation can be controlled to be-24-12 Mpa, and the engineering requirement can be met.
As can be seen from fig. 3, the relative temperature deviation of the temperature predicted value obtained by the method for analyzing the temperature stress deformation of the compressor rotor based on the overall parameters can be controlled to be +/-1%, and the temperature of the compressor rotor is usually not more than 600 ℃, so that the temperature deviation can be controlled to be +/-6 ℃ to meet engineering requirements.
As can be seen from FIG. 4, the relative total displacement deviation of the total displacement predicted value obtained by the method for analyzing the temperature stress deformation of the compressor rotor based on the overall parameters can be controlled to be-1% -3.5%, and the deformation of the compressor rotor is usually not more than 3mm, so that the total displacement deviation can be controlled to be-0.03% -0.105 mm, and the engineering requirements are met.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, and alternatives falling within the spirit and principles of the invention.

Claims (2)

1. The method for analyzing the temperature stress deformation of the compressor rotor based on the overall parameters is characterized by comprising the following steps of:
selecting sample state points from an aeroengine flight envelope map, wherein the transverse axis of the flight envelope map is Mach number, and the vertical axis of the flight envelope map is flight height; the sample state points comprise a first point with zero Mach number and zero height, a second point with maximum Mach number and zero height, a third point with maximum Mach number and corresponding to the minimum height in the engine flight envelope, a fourth point with maximum Mach number and corresponding to the maximum height in the engine flight envelope, and a fifth point with maximum height and corresponding to the minimum Mach number; a sixth point with zero Mach number and maximum height, and two state points with the longest engine working time in the flight envelope;
acquiring overall parameters in each sample state point, wherein the overall parameters comprise the total inlet temperature, the total outlet temperature, the total inlet pressure, the total outlet pressure and the rotating speed of a rotor of the compressor;
obtaining the temperature, equivalent stress and total displacement corresponding to each sample state point through finite element analysis, wherein the total displacement is the vector sum of axial deformation, circumferential deformation and radial deformation of the compressor rotor under the corresponding working condition;
taking the total inlet temperature, the total outlet temperature, the total inlet pressure, the total outlet pressure and the rotating speed of a rotor of the compressor as independent variables, and taking the temperature, the equivalent stress and the total displacement corresponding to each sample point obtained by finite element analysis as dependent variables to fit a function model between the temperature of the compressor and the overall parameter, a function model between the equivalent stress of the compressor and the overall parameter and a function model between the total displacement of the compressor and the overall parameter respectively; wherein the temperature of the compressorFunction model between the overall parametersFitting to obtain->、/>、/>Are fitting coefficients; equivalent stress of compressor->Function model between the overall parameters
The fitting is performed to obtain the product,、/>、/>、/>、/>、/>、/>are fitting coefficients; total displacement of compressor->Function model between the overall parameters
The fitting is performed to obtain the product,、/>、/>、/>、/>、/>、/>are fitting coefficients>Is the total temperature of the inlet of the air compressor>Is the total temperature of the outlet of the air compressor>Is the total pressure of the inlet of the air compressor>Is the total pressure of the outlet of the air compressor>The rotational speed of the rotor of the air compressor;
and inputting the overall parameters of the compressor in the state to be detected into corresponding function models, and respectively calculating the temperature, equivalent stress and total displacement results corresponding to the point to be detected.
2. The compressor rotor temperature stress deformation analysis device based on the overall parameters is characterized by comprising:
the state point selection module is used for selecting sample state points from an aeroengine flight envelope graph, wherein the transverse axis of the flight envelope graph is Mach number, and the longitudinal axis of the flight envelope graph is flight height; the sample state points comprise a first point with zero Mach number and zero height, a second point with maximum Mach number and zero height, a third point with maximum Mach number and corresponding to the minimum height in the engine flight envelope, a fourth point with maximum Mach number and corresponding to the maximum height in the engine flight envelope, and a fifth point with maximum height and corresponding to the minimum Mach number; a sixth point with zero Mach number and maximum height, and two state points with the longest engine working time in the flight envelope;
the parameter acquisition module is used for acquiring overall parameters in each sample state point, wherein the overall parameters comprise the total inlet temperature, the total outlet temperature, the total inlet pressure, the total outlet pressure and the rotating speed of the compressor rotor;
the finite element analysis module is used for obtaining the temperature, equivalent stress and total displacement corresponding to each sample state point through finite element analysis, and the total displacement is the vector sum of the axial deformation, the circumferential deformation and the radial deformation of the compressor rotor under the corresponding working condition;
the model fitting module is used for respectively fitting a function model between the temperature of the air compressor and the overall parameter, a function model between the equivalent stress of the air compressor and the overall parameter and a function model between the total displacement of the air compressor and the overall parameter by taking the total inlet temperature, the total outlet temperature, the total inlet pressure, the total outlet pressure and the rotating speed of the air compressor rotor of the air compressor as independent variables and taking the temperature, the equivalent stress and the total displacement of each sample point obtained by finite element analysis as dependent variables; wherein the temperature of the compressorFunction model between the parameters and the population is based on +.>Fitting to obtain->、/>、/>Are fitting coefficients; equivalent stress of compressor->Function model between the overall parameters
The fitting is performed to obtain the product,、/>、/>、/>、/>、/>、/>are fitting coefficients; total displacement of compressor->Function model between the overall parameters
The fitting is performed to obtain the product,、/>、/>、/>、/>、/>、/>are fitting coefficients>Is the total temperature of the inlet of the air compressor>Is the total temperature of the outlet of the air compressor>Is the total pressure of the inlet of the air compressor>Is the total pressure of the outlet of the air compressor>The rotational speed of the rotor of the air compressor;
the prediction module is used for receiving the overall parameters of the compressor in the state to be detected, and respectively calculating the temperature, equivalent stress and total displacement results corresponding to the point to be detected according to the corresponding function model.
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