Rapid calculation method and system for transient temperature and stress fields of key engine components

Abstract

The present invention discloses a method and system for rapidly calculating the transient temperature field and stress field of key engine components. The method can calculate the transient temperature and transient stress through the algebraic relationship of a small number of variables, greatly improving the calculation speed. The method can also quickly calculate the temperature and stress responses under different parameter changes, thereby performing rapid parameter optimization, which is significantly helpful for the design stage, material selection, and process adjustment. In addition, the undetermined coefficients of the rapid calculation model are obtained by fitting historical data and do not rely on precise geometric or boundary condition descriptions, which greatly simplifies the modeling process. Moreover, only a small number of coefficients and formulas are required, and the data volume is extremely small, making it suitable for use in network transmission or embedded devices, greatly reducing the pressure on storage space and data transmission.

Description

Technical Field

[0001] The present invention relates to the technical field of temperature and stress analysis, and in particular to a method and system for quickly calculating the transient temperature field and stress field of key engine components, an electronic device, and a computer-readable storage medium. Background Art

[0002] When aircraft engines operate under extreme conditions, such as high temperature, high pressure, high speed and complex loads, key components such as turbine discs, turbine blades, and combustion chambers are often subjected to extremely high temperatures and stresses. The performance and reliability of these key components directly affect the overall efficiency and life of the engine. For the temperature and stress analysis of aircraft engines, traditional numerical calculation methods are usually time-consuming and complex.

[0003] With the development of aviation technology, engineering applications are placing increasing demands on analytical efficiency, especially in design, optimization, and fault prediction. More efficient and rapid computational methods are urgently needed to assist decision-making. Predicting the temperature and stress fields of key components is a critical step in aeroengine design, manufacturing, and maintenance. As engine performance requirements continue to increase, so too are the demands for reliability, safety, and durability. Accurate temperature and stress calculations are crucial for design optimization and life prediction. For example, as domestic and international civil aviation engine life management frameworks mature, assessing the service life consumption and remaining life prediction of key components in service has become a crucial step. Under normal circumstances, key engine components are swapped out, with those that haven't reached their service life being transferred to other engines to maximize their utilization. Therefore, the remaining life assessment of key components must be as accurate as possible, and based on existing historical records, the life loss at the current cutoff state can be quickly tracked and calculated.

[0004] Therefore, through rapid calculations, the temperature distribution and stress concentration of key engine components under various operating conditions can be analyzed more quickly, helping to identify potential weak links or hazardous areas, thereby optimizing the design and improving the safety and reliability of the structure. For example, during the engine's service life, rapid temperature and stress calculation methods can monitor the operating status of key components in real time and predict their lifespan. This can prevent problems such as fatigue failure, reduce the risk of engine failure, and ensure flight safety. Furthermore, as the aviation industry's requirements for engine thrust-to-weight ratio and efficiency continue to increase, rapid temperature and stress calculation methods in high-temperature and high-pressure environments can provide a scientific basis for the development of new high-performance engines, helping to promote innovation and breakthroughs in aviation power technology. Therefore, developing rapid temperature and stress calculation methods for key aerospace engine components can significantly improve computational efficiency, enabling engineers to perform temperature and stress analysis on key components in a shorter time. This is of great significance for accelerating design iterations and reducing development cycles and costs. Summary of the Invention

[0005] The present invention provides a method and system for rapidly calculating the transient temperature and stress fields of key engine components, an electronic device, and a computer-readable storage medium, which can greatly improve calculation speed, facilitate parameter optimization, reduce modeling complexity, and reduce data storage and transmission pressure.

[0006] According to one aspect of the present invention, a method for rapidly calculating the transient temperature field and stress field of key engine components is provided, comprising the following:

[0007] Based on the similarity criterion, a simple calculation model of the temperature of key components with respect to the inlet total temperature, inlet total pressure and rotational speed, as well as a simple calculation model of the stress with respect to the inlet total temperature, inlet total pressure and rotational speed were established;

[0008] Conduct sensitivity parameter analysis on simple calculation models of temperature and stress respectively, and establish transient stress calculation model and steady-state temperature calculation model based on the sensitivity parameter analysis results;

[0009] A transient temperature model of key components under service conditions is established based on a simple temperature calculation model, and the transient temperature model is converted into a transient temperature response model based on the semi-infinite plate assumption and the steady-state temperature calculation model.

[0010] Nonlinear fitting is performed on the undetermined coefficients in the transient temperature response model and the transient stress calculation model, and the two models obtained by nonlinear fitting are used to calculate the transient temperature and transient stress of key components respectively.

[0011] Furthermore, the expression of the steady-state temperature calculation model is:

[0012] ;

[0013] in, represents the steady-state temperature, n Indicates the current speed of the rotor components in the key components, n 0 represents the design speed of the rotor part in the key component, and A1 and A2 represent the coefficients to be determined.

[0014] Furthermore, the transient temperature model is expressed as:

[0015] ;

[0016] in, T represents the transient temperature, Indicates the total inlet pressure of key components, p 0 represents the atmospheric pressure under standard conditions, represents the total inlet temperature of key components, T 0 represents the atmospheric temperature under standard conditions, n Indicates the current speed of the rotor components in the key components, n 0 represents the design speed of the rotor components in the key components, c 1. c 2. c 3. c 4 and c 5 are all undetermined coefficients, ΔT It represents the temperature difference between the two moments. t Indicates the time difference between two moments. k Indicates the adjustment coefficient, which is determined by the engine material. t 0 represents the time constant, t 0= f(ΔT , c p , λ) , c p represents the specific heat capacity at constant pressure, λ Represents thermal conductivity.

[0017] Furthermore, the process of converting the transient temperature model into the transient temperature response model based on the semi-infinite plate assumption and the steady-state temperature calculation model includes the following:

[0018] Based on the semi-infinite plate assumption, the transient temperature model is regarded as a non-steady-state heat conduction process of the semi-infinite plate. Based on the third-category boundary condition and the steady-state temperature calculation model, the transient temperature model is converted into a temperature response model of the key component surface. The influence of the boundary conditions and operating conditions in the temperature response model is reflected through undetermined coefficients, and the influence of the position in the temperature response model is ignored. In this way, the temperature response model is corrected to obtain the transient temperature response model of the key component.

[0019] Furthermore, the transient temperature response model is expressed as:

[0020] ;

[0021] in, express The transient temperature at time represents the steady-state temperature, represents the material density, and B, D and E are unknown coefficients.

[0022] Furthermore, when the time interval between the calculation moment and the initial moment exceeds a preset threshold, the expression of the transient temperature response model is:

[0023] ;

[0024] in, Indicates the transient heat conduction process t Transient temperature at time +1, Indicates the transient heat conduction process t The transient temperature at time t, C represents the unknown coefficient.

[0025] Furthermore, in the transient stress calculation model, the transient stress calculation formula in a certain direction is:

[0026] ;

[0027] ;

[0028] ;

[0029] ;

[0030] in, represents the transient stress, 、 and represent the transient centrifugal stress, thermal stress and aerodynamic stress respectively, Indicates the total inlet pressure of key components, p 0 represents the atmospheric pressure under standard conditions, represents the total inlet temperature of key components, T 0 represents the atmospheric temperature under standard conditions, n Indicates the current speed of the rotor components in the key components, n 0 represents the design speed of the rotor components in the key components, K1, K2, K3, G1, G 11 , G2, G 21 , G3, G 31 and H1 are unknown coefficients.

[0031] In addition, the present invention also provides a system for rapidly calculating transient temperature and stress fields of key engine components, comprising:

[0032] A simple calculation model building module is used to establish a simple calculation model of the temperature of key components with respect to the inlet total temperature, inlet total pressure and rotational speed based on similarity criteria, as well as a simple calculation model of the stress with respect to the inlet total temperature, inlet total pressure and rotational speed;

[0033] Sensitivity parameter analysis module, used to perform sensitivity parameter analysis on simple calculation models of temperature and stress respectively, and establish transient stress calculation model and steady-state temperature calculation model based on the sensitivity parameter analysis results;

[0034] A transient temperature response model building module is used to establish a transient temperature model of key components under service conditions based on a simple temperature calculation model, and to convert the transient temperature model into a transient temperature response model based on the semi-infinite plate assumption and the steady-state temperature calculation model;

[0035] The transient temperature and stress calculation module is used to perform nonlinear fitting on the unknown coefficients in the transient temperature response model and the transient stress calculation model, and use the two models obtained by nonlinear fitting to calculate the transient temperature and transient stress of key components respectively.

[0036] In addition, the present invention also provides an electronic device, including a processor and a memory, wherein the memory stores a computer program, and the processor is configured to execute the steps of the above method by calling the computer program stored in the memory.

[0037] In addition, the present invention also provides a computer-readable storage medium for storing a computer program for rapidly calculating the temperature field and stress field of key components of an aerospace engine. When the computer program is run on a computer, the steps of the method described above are executed.

[0038] The present invention has the following beneficial effects:

[0039] The method for quickly calculating the transient temperature field and stress field of key engine components of the present invention can calculate the transient temperature and transient stress through the algebraic relationship of a small number of variables, while the existing three-dimensional simulation usually requires large-scale calculations through the finite element method or other numerical simulation methods, which consumes a lot of time and computing resources. In particular, in the case of complex structures, non-uniform materials or complex boundary conditions, the simulation calculations may be more complicated, thereby greatly improving the calculation speed. In particular, for application scenarios that require real-time prediction and control of temperature and stress (such as real-time monitoring on industrial production lines), the calculation time of existing three-dimensional simulations is often difficult to meet real-time requirements. The fast algorithm of the present invention can complete the calculation in a very short time and is easy to implement in embedded systems or control systems, making online analysis and real-time feedback more convenient. In addition, the fast algorithm of the present invention can quickly calculate temperature and stress under changes in different parameters (such as materials, temperature, external forces, etc.). The response of the force can be obtained, thereby performing rapid parameter optimization, which is of significant help in the design stage, material selection, and process adjustment. However, three-dimensional simulation requires multiple re-simulations during the parameter optimization process, which is extremely computationally intensive and not suitable for frequent parameter adjustments. In addition, existing three-dimensional simulations often require detailed descriptions of material properties, geometric shapes, boundary conditions, etc., and the modeling process is cumbersome and time-consuming, especially in cases where the structure is complex or involves multi-physical field coupling. The undetermined numbers of the fast calculation model of the present invention are obtained by fitting historical data and do not rely on precise geometric or boundary condition descriptions, which greatly simplifies the modeling process. In addition, three-dimensional simulations usually generate a large amount of grid data and result files, resulting in higher storage and transmission costs. In contrast, the fast algorithm of the present invention only requires a small number of coefficients and formulas, and the amount of data is extremely small, which is suitable for use on network transmission or embedded devices, greatly reducing the pressure on storage space and data transmission.

[0040] In addition, the system for rapidly calculating transient temperature and stress fields of key engine components of the present invention also has the above advantages.

[0041] In addition to the above-described objects, features and advantages, the present invention has other objects, features and advantages. The present invention will be further described in detail below with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] The accompanying drawings, which constitute part of this application, are intended to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are intended to explain the present invention and do not constitute an undue limitation of the present invention. In the accompanying drawings:

[0043] Figure 1 It is a flow chart of a method for rapidly calculating transient temperature and stress fields of key engine components according to a preferred embodiment of the present application;

[0044] Figure 2It is a schematic diagram of the module structure of a system for rapidly calculating transient temperature and stress fields of key engine components according to another embodiment of the present application. DETAILED DESCRIPTION

[0045] It should be noted that, in the absence of conflict, the embodiments and features of the embodiments in this application can be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0046] Reference Figure 1 The preferred embodiment of the present application provides a method for rapidly calculating the transient temperature field and stress field of key engine components, including the following contents:

[0047] Step S1: Based on the similarity criterion, a simple calculation model of the temperature of key components with respect to the inlet total temperature, the inlet total pressure and the rotational speed, and a simple calculation model of the stress with respect to the inlet total temperature, the inlet total pressure and the rotational speed are established;

[0048] Step S2: performing sensitivity parameter analysis on the simple calculation models of temperature and stress respectively, and establishing a transient stress calculation model and a steady-state temperature calculation model based on the sensitivity parameter analysis results;

[0049] Step S3: establishing a transient temperature model of key components under service conditions based on a simple temperature calculation model, and converting the transient temperature model into a transient temperature response model based on a semi-infinite plate assumption and a steady-state temperature calculation model;

[0050] Step S4: Perform nonlinear fitting on the undetermined coefficients in the transient temperature response model and the transient stress calculation model, and use the two models obtained by nonlinear fitting to calculate the transient temperature and transient stress of the key components respectively.

[0051] It can be understood that the method for rapidly calculating the transient temperature and stress fields of key engine components in this embodiment first establishes simple calculation models for temperature and stress with respect to inlet total temperature, inlet total pressure, and speed based on the similarity criterion. These simple calculation models, assuming the engine geometry remains unchanged, can represent the patterns of stress and temperature changes with inlet total temperature, inlet total pressure, and speed, providing a theoretical basis for subsequent transient temperature and stress calculations. Next, sensitivity parameter analysis is performed on the simple temperature and stress calculation models to determine which of the total temperature, total pressure, and speed are key sensitive parameters for temperature and stress. Based on the sensitivity parameter analysis results, a transient stress calculation model and a steady-state temperature calculation model are established. Next, a transient temperature model for the key component under service conditions is established based on the simple temperature calculation model. This transient temperature model is then converted into a transient temperature response model based on the semi-infinite plate assumption and the steady-state temperature calculation model to simulate the transient heat conduction process of the key component, enabling accurate calculation of the transient temperature of the key component at any time. Finally, historical data are used to perform nonlinear fitting on the unknown coefficients in the transient temperature response model and the transient stress calculation model, and the transient temperature and transient stress of the key components can be calculated based on the two fitted models.

[0052] Therefore, the fast calculation method of the present invention can calculate the transient temperature and transient stress through the algebraic relationship of a small number of variables, while the existing three-dimensional simulation usually requires large-scale calculations through the finite element method or other numerical simulation methods, which consumes a lot of time and computing resources. In particular, when the structure is complex, the material is non-uniform, or the boundary conditions are complex, the simulation calculation may be more complicated, thereby greatly improving the calculation speed. In particular, for application scenarios that require real-time prediction and control of temperature and stress (such as real-time monitoring on industrial production lines), the calculation time of existing three-dimensional simulations is often difficult to meet real-time requirements. The fast algorithm of the present invention can complete the calculation in a very short time and is easy to implement in embedded systems or control systems, making online analysis and real-time feedback more convenient. In addition, the fast algorithm of the present invention can quickly calculate the temperature and stress responses under changes in different parameters (such as materials, temperature, external forces, etc.), thereby improving the accuracy of the simulation. It can perform rapid parameter optimization, which is of significant help to the design stage, material selection and process adjustment. However, three-dimensional simulation requires multiple re-simulations during the parameter optimization process, which is extremely computationally intensive and not suitable for frequent parameter adjustments. In addition, existing three-dimensional simulations often require detailed descriptions of material properties, geometric shapes, boundary conditions, etc., and the modeling process is cumbersome and time-consuming, especially in cases where the structure is complex or involves multi-physical field coupling. The undetermined coefficients of the fast calculation model of the present invention are obtained by fitting historical data and do not rely on precise geometric or boundary condition descriptions, which greatly simplifies the modeling process. In addition, three-dimensional simulations usually generate a large amount of grid data and result files, resulting in higher storage and transmission costs. In contrast, the fast algorithm of the present invention only requires a small number of coefficients and formulas, and the amount of data is extremely small, which is suitable for use on network transmission or embedded devices, greatly reducing the pressure on storage space and data transmission.

[0053] Among them, in step S1, there are three parameters that determine the working state of the engine, namely, the total temperature of the inlet ( )、Total inlet pressure( ) and rotor speed (n). According to the engine principle, for an engine with constant geometry, when 、 When n is constant, the working state of the engine is constant. When the working state is constant, the flow path process parameters of the engine along each section of the process are also constant, that is, the load is a constant value. For each key component of the engine, the stress, strain, displacement, and temperature field should also be constant. Therefore, there should be a mathematical function that can express the stress field, strain field, displacement field, and temperature field as the 、 , the law of change of n.

[0054] According to the similarity criterion, the aerodynamic parameters in the flow channel meet the similarity criterion, that is, the ratios of similar physical quantities and similar parameters at corresponding points on each cross section are constants, for example: 、 、 、 、 ,in, 、 and Respectively represent i The total inlet pressure, total inlet temperature and speed of each section, 、 They represent the inlet total pressure and inlet total temperature of the inlet section respectively, q m represents the air mass flow rate, represents the speed similarity parameter, represents the air flow similarity parameter, represents the thrust similarity parameter. Therefore, the physical quantities of stress, strain, temperature, and displacement of key components can be expressed as follows: the simple calculation model of key component temperature with respect to inlet total temperature, inlet total pressure, and speed, and the simple calculation model of stress with respect to inlet total temperature, inlet total pressure, and speed can be expressed as: ,in, S Represents physical quantities such as stress, strain, temperature and displacement, c 1. c 2. c 3 and c 4 is the undetermined coefficient, Indicates the total inlet pressure of key components, p 0 represents the atmospheric pressure under standard conditions, which is 1.013×10 5 Pa, represents the total inlet temperature of key components, T 0 represents the atmospheric temperature under standard conditions, which is 288.15K. n Indicates the current speed of the rotor components in the key components, n 0 represents the design speed of the rotor component within the key component. Here, the undetermined coefficients differ for different physical quantities. It is understood that the similarity criterion belongs to the prior art, and the simple calculation model constructed is also prior art. The specific principles will not be elaborated here.

[0055] In addition, in step S2, sensitivity parameter analysis is performed on the simple calculation models of temperature and stress respectively. Sensitivity parameter analysis is a method for evaluating the sensitivity of the model output results to changes in input parameters. It can help identify key influencing factors, optimize model design or reduce uncertainty. The core principle is to quantify the importance of each parameter by systematically adjusting the input parameters and observing the changes in the output results. Among them, for the sensitivity parameter analysis of temperature, through a large number of numerical simulations in the early stage and based on Latin hypercube sampling, the temperature of the key components at different speeds, pressures and temperatures is calculated. By analyzing the correlation coefficient between the temperature simulation results and the above variables, the key sensitive parameters are obtained. It is found that only the speed has a greater impact on the temperature of the key components of the engine, and the total temperature and total pressure have little effect on the temperature of the key components of the engine. Therefore, the present invention ignores the two terms about total temperature and total pressure in the simple calculation model of temperature, so that the steady-state temperature calculation model of the key components can be simplified, which can be expressed as:

[0056] ;

[0057] in, represents the steady-state temperature, n Indicates the current speed of the rotor components in the key components, n 0 represents the design speed of the rotor part in the key component, and A1 and A2 represent the coefficients to be determined.

[0058] In addition, for the sensitivity parameter analysis of stress, since the transient component stress of different key components in different directions can be regarded as consisting of three parts: centrifugal stress, thermal stress and aerodynamic stress, the present invention uses centrifugal stress, thermal stress and aerodynamic stress as outputs, and speed, total pressure and total temperature as inputs to carry out sensitivity parameter analysis. It is found that the correlation coefficient between centrifugal stress and speed and total pressure is high, that is, it is greatly affected by speed and total pressure, thermal stress is mainly affected by temperature, and the change amplitude of aerodynamic stress is smaller than that of centrifugal stress and thermal stress. In order to quickly calculate transient stress, the change of aerodynamic stress over time can be ignored and regarded as a constant. Therefore, in the transient stress calculation model, the transient stress calculation formula in a certain direction is:

[0059] ;

[0060] ;

[0061] ;

[0062] ;

[0063] in, represents the transient stress in a certain direction, 、 and represent the transient centrifugal stress, thermal stress and aerodynamic stress respectively, Indicates the total inlet pressure of key components, p 0 represents the atmospheric pressure under standard conditions, represents the total inlet temperature of key components, T 0 represents the atmospheric temperature under standard conditions, n Indicates the current speed of the rotor components in the key components, n 0 represents the design speed of the rotor components in the key components, K1, K2, K3, G1, G 11 , G2, G 21 , G3, G 31 , H1 are unknown coefficients, where H1 is a constant. After calculating the transient stress components in the six directions, the equivalent transient stress of the key components can be calculated based on the equivalent stress formula, where the equivalent stress formula is expressed as:

[0064] ;

[0065] in, represents the equivalent transient stress of key components, 、 、 represents the principal stress, 、 、 In addition, the equivalent stress formula belongs to the existing technology, and its technical principle will not be described here.

[0066] In addition, in step S3, the transient temperature-time response curve of the key component is usually in the form of an exponential equation. The transient temperature at any time can be considered to be in the form of a quasi-steady-state temperature + time term. Therefore, in order to facilitate the calculation of the transient temperature of the key component, the present invention establishes a transient temperature model of the key component under service conditions based on a simple temperature calculation model, which is used as the theoretical basis for transient temperature calculation. The transient temperature model can be expressed as:

[0067] ;

[0068] in, T represents the transient temperature, Indicates the total inlet pressure of key components, p 0 represents the atmospheric pressure under standard conditions, which is 1.013×10 5 Pa, represents the total inlet temperature of key components, T 0 represents the atmospheric temperature under standard conditions, which is 288.15K. n Indicates the current speed of the rotor components in the key components,n 0 represents the design speed of the rotor components in the key components, c 1. c 2. c 3. c 4 and c 5 are all undetermined coefficients, ΔT It represents the temperature difference between the two moments. ΔT=T 2- T 1, t Indicates the time difference between two moments. t = t 2- t 1, k Indicates the adjustment coefficient, which is determined by the engine material and is used to characterize the rate of change of heat from engine start to shutdown. t 0 represents the time constant, t 0= f(ΔT , c p , λ) , c p represents the specific heat capacity at constant pressure, λ Indicates thermal conductivity, which is determined by material data.

[0069] Then, based on the semi-infinite plate assumption and the steady-state temperature calculation model, the transient temperature model is converted into a transient temperature response model. Specifically, based on the semi-infinite plate assumption, the transient temperature model is regarded as a non-steady-state heat conduction process of the semi-infinite plate, and based on the third-class boundary conditions and the steady-state temperature calculation model, the transient temperature model is converted into a temperature response model of the key component surface. The influence of the boundary conditions and operating conditions in the temperature response model is reflected through undetermined coefficients, and the influence of the position in the temperature response model is ignored, so as to correct the temperature response model and obtain the transient temperature response model of the key component.

[0070] It can be understood that the transient temperature model of the key components of the engine under service conditions can be regarded as a non-steady-state heat conduction process of a semi-infinite plate. According to the operating environment of the key components of the engine, it can be considered that the heat transfer process of the key components of the engine meets the third type of boundary conditions in the heat conduction problem, that is, the temperature on one side of the key component is the steady-state temperature. T ∞ Therefore, the temperature response model of the key component surface can be established, which can be expressed as:

[0071] ;

[0072] in, express Time position x The temperature at T0 represents the atmospheric temperature under standard conditions, which is 288.15K. a represents the thermal diffusivity, h represents the heat transfer coefficient, λ represents the thermal conductivity, represents the error function, Represents the co-error function. The range of the error function is (-1, 1), while the range of the co-error function is (0, 2).

[0073] Under the assumption of a semi-infinite plate, the thermal response of key components is mainly determined by the initial conditions and surface conditions, while the area far from the surface is not affected by changes in boundary conditions within a finite time. This assumption makes the solutions of the error function and the complementary error function universal and applicable to a variety of boundary conditions and operating conditions. They can be regarded as universal functions unrelated to the specific problem. Therefore, the influence of boundary conditions and operating conditions can be reflected by the undetermined coefficients, thus converting the above temperature response model into: , A and B represent unknown coefficients, where the value range of A is (-1, 1) and the value range of B is (0, 2). In addition, the present invention predicts the temperature of a specific point instead of calculating the temperature and stress of the entire surface, so the position can be ignored. x The impact of exponential form Only keep the quadratic term, because the linear term is about position x The function can be omitted. Position in x The term can also be ignored, thus obtaining the modified transient temperature response model of the key components under the third type of boundary conditions, which can be expressed as: According to experience, the undetermined coefficient A is set to 1. , and the heat transfer coefficient h By using the similarity criterion and dimensionless speed and temperature, the exponential term Available Indicates that the left side of the modified transient temperature response model is divided by By moving the items other than to the right, we can obtain the final transient temperature response model, which can be expressed as:

[0074] ;

[0075] in, express The transient temperature at time represents the steady-state temperature, represents the material density, and B, D, and E are unknown coefficients. This formula shows that the transient temperature of a key component at any moment can be calculated using the atmospheric temperature and steady-state temperature under standard conditions.

[0076] Optionally, to ensure the accuracy of transient temperature calculation, when the time interval between the calculation moment and the initial moment exceeds a preset threshold, the temperature of the key component at the previous moment is used to infer the temperature at the next moment. That is, the transient temperature response model can be expressed as:

[0077] ;

[0078] in, Indicates the transient heat conduction process t Transient temperature at time +1, Indicates the transient heat conduction process t The transient temperature at time , C represents the unknown coefficient. In addition, .

[0079] In addition, in step S4, since step S2 has constructed a transient stress calculation model and step S3 has constructed a transient temperature response model, but the undetermined coefficients in the two models are still uncertain, the present invention uses a nonlinear fitting method based on historical data to determine the values ​​of the undetermined coefficients. The core idea of ​​nonlinear fitting is to use nonlinear functions to describe the relationship between variables and find the optimal model parameters by minimizing the residual sum of squares. It specifically includes the following processes: 1) Model assumption: First, select a suitable nonlinear function form, such as an exponential function, a logarithmic function, or a high-order polynomial; 2) Initial parameter estimation: Select the initial values ​​of the model parameters. Nonlinear regression is more sensitive to the initial parameters, so the rationality of the initial values ​​will affect the convergence speed and fitting effect; 3) Error function construction: According to the selected model form, the residual sum of squares (RSS) is constructed as the error function; 4) Optimization solution: Use the Levenberg-Marquardt algorithm to minimize RSS and find the optimal solution for the parameters through iterative optimization; 5) Model evaluation: Use goodness of fit (such as R 2 The fitting effect of the model can be evaluated by means of nonlinear fitting method, such as residual analysis, to check whether there is overfitting or underfitting. Through nonlinear fitting method, the values ​​of the undetermined coefficients in the steady-state temperature calculation model, transient stress calculation model and transient temperature response model can be obtained, such as A1, A2, B, C, D, E, K1, K2, K3, G1, G 11 , G2, G 21 , G3, G 31 Then, by substituting the three known variables of total temperature, total pressure and speed into the model, the transient temperature and transient stress of key components at different times can be calculated respectively.

[0080] It is understood that this application also conducted comparative tests on the fast calculation method of the present invention and existing three-dimensional simulation methods. The time from parameter input to result display of the fast calculation method of the present invention is generally controlled within 10 seconds, and the time for the prediction calculation step is only 1.72 seconds. In comparison, the complete process of conventional three-dimensional simulation calculation (including model construction, mesh division, naming and pre-processing settings) takes more than 6 hours on a 50-core computer, and the pure calculation time is about 3.5 hours. It can be seen that the fast calculation method of the present application significantly improves calculation efficiency, shortens time costs, and can quickly provide prediction results of temperature and stress distribution in a short time, which is suitable for real-time health monitoring and life prediction.

[0081] In addition, if Figure 2 As shown, another embodiment of the present invention further provides a system for rapidly calculating transient temperature and stress fields of key engine components, preferably using the aforementioned method for rapidly calculating transient temperature and stress fields of key engine components, comprising:

[0082] A simple calculation model building module is used to establish a simple calculation model of the temperature of key components with respect to the inlet total temperature, inlet total pressure and rotational speed based on similarity criteria, as well as a simple calculation model of the stress with respect to the inlet total temperature, inlet total pressure and rotational speed;

[0083] Sensitivity parameter analysis module, used to perform sensitivity parameter analysis on simple calculation models of temperature and stress respectively, and establish transient stress calculation model and steady-state temperature calculation model based on the sensitivity parameter analysis results;

[0084] A transient temperature response model building module is used to establish a transient temperature model of key components under service conditions based on a simple temperature calculation model, and to convert the transient temperature model into a transient temperature response model based on the semi-infinite plate assumption and the steady-state temperature calculation model;

[0085] The transient temperature and stress calculation module is used to perform nonlinear fitting on the unknown coefficients in the transient temperature response model and the transient stress calculation model, and use the two models obtained by nonlinear fitting to calculate the transient temperature and transient stress of key components respectively.

[0086] It can be understood that the fast calculation system of this embodiment can calculate transient temperature and transient stress through the algebraic relationship of a small number of variables, while existing three-dimensional simulations usually require large-scale calculations through the finite element method or other numerical simulation methods, which consumes a lot of time and computing resources. In particular, in the case of complex structures, non-uniform materials or complex boundary conditions, the simulation calculations may be more complicated, thereby greatly improving the calculation speed. In particular, for application scenarios that require real-time prediction and control of temperature and stress (such as real-time monitoring on industrial production lines), the calculation time of existing three-dimensional simulations is often difficult to meet real-time requirements. The fast calculation system of the present invention can complete the calculation in a very short time and is easy to implement in embedded systems or control systems, making online analysis and real-time feedback more convenient. In addition, the fast calculation system of the present invention can quickly calculate the temperature and stress responses under changes in different parameters (such as materials, temperature, external forces, etc.). This allows for rapid parameter optimization, which is significantly helpful for the design stage, material selection, and process adjustment processes. However, three-dimensional simulation requires multiple re-simulations during the parameter optimization process, which results in a huge amount of computation and is not suitable for frequent parameter adjustments. In addition, existing three-dimensional simulations often require detailed descriptions of material properties, geometric shapes, boundary conditions, etc., and the modeling process is cumbersome and time-consuming, especially in cases where the structure is complex or involves multi-physical field coupling. The undetermined coefficients of the rapid calculation model of the present invention are obtained by fitting historical data and do not rely on precise geometric or boundary condition descriptions, which greatly simplifies the modeling process. In addition, three-dimensional simulations usually generate a large amount of grid data and result files, resulting in higher storage and transmission costs. In contrast, the rapid calculation system of the present invention only requires a small number of coefficients and formulas, and the amount of data is extremely small, making it suitable for use on network transmission or embedded devices, greatly reducing the pressure on storage space and data transmission.

[0087] In addition, another embodiment of the present invention further provides an electronic device, including a processor and a memory, wherein the memory stores a computer program, and the processor is configured to execute the steps of the above method by calling the computer program stored in the memory.

[0088] In addition, another embodiment of the present invention further provides a computer-readable storage medium for storing a computer program for rapidly calculating the temperature field and stress field of key components of an aerospace engine. When the computer program is run on a computer, the steps of the method described above are executed.

[0089] Common forms of computer-readable storage media include floppy disks, flexible disks, hard disks, magnetic tape, any other magnetic media, CD-ROMs, any other optical media, punch cards, paper tape, any other physical medium with a pattern of holes, random access memory (RAM), programmable read-only memory (PROM), erasable programmable read-only memory (EPROM), flash-EPROM, any other memory chip or cartridge, or any other medium that can be read by a computer. Instructions can further be transmitted or received via a transmission medium. The term transmission medium may include any tangible or intangible medium that can be used to store, encode, or carry instructions for execution by a machine, including digital or analog communication signals or other intangible media that facilitate communication of such instructions. Transmission media include coaxial cables, copper wire, and fiber optics, including the wires of a bus used to transmit computer data signals.

[0090] Those skilled in the art will appreciate that the embodiments of the present application may be provided as methods, systems, or computer program products. Therefore, the present application may take the form of a fully hardware embodiment, a fully software embodiment, or an embodiment combining software and hardware. Furthermore, the present application may take the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code. The solutions in the embodiments of the present application may be implemented in various computer languages, such as the object-oriented programming language Java and the interpreted scripting language JavaScript.

[0091] The present application is described with reference to the flowcharts and / or block diagrams of the methods, devices (systems), and computer program products according to the embodiments of the present application. It should be understood that each process and / or block in the flowchart and / or block diagram, as well as the combination of processes and / or blocks in the flowchart and / or block diagram, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, a special-purpose computer, an embedded processor, or other programmable data processing device to produce a machine, so that the instructions executed by the processor of the computer or other programmable data processing device generate instructions for implementing the processes in the flowchart and / or block diagram. Figure 1 a process or multiple processes and / or boxes Figure 1 A device that provides the functions specified in a block or multiple blocks.

[0092] These computer program instructions may also be stored in a computer readable memory that can direct a computer or other programmable data processing device to work in a specific manner, so that the instructions stored in the computer readable memory produce an article of manufacture comprising an instruction device, which implements the process Figure 1 a process or multiple processes and / or boxes Figure 1 The function specified in one or more boxes.

[0093] These computer program instructions can also be loaded onto a computer or other programmable data processing device so that a series of operational steps are executed on the computer or other programmable device to produce a computer-implemented process, thereby providing the instructions executed on the computer or other programmable device for implementing the process. Figure 1 a process or multiple processes and / or boxes Figure 1 A step that specifies a function in one or more boxes.

[0094] Although the preferred embodiments of the present application have been described, those skilled in the art may make additional changes and modifications to these embodiments once they have learned the basic creative concept. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments and all changes and modifications that fall within the scope of the present application.

[0095] Obviously, those skilled in the art may make various changes and modifications to this application without departing from the spirit and scope of this application. Thus, if these modifications and variations of this application fall within the scope of the claims of this application and their equivalents, this application is intended to include these modifications and variations.

[0096] The foregoing description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Those skilled in the art will readily appreciate that various modifications and variations of the present invention are possible. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention are intended to be within the scope of protection of the present invention.

Claims

1. A method for rapid calculation of transient temperature and stress fields of key engine components, characterized in that: Includes the following: Based on the similarity criterion, a simple calculation model of the temperature of key components with respect to the inlet total temperature, inlet total pressure and rotational speed, as well as a simple calculation model of the stress with respect to the inlet total temperature, inlet total pressure and rotational speed were established; Conduct sensitivity parameter analysis on simple calculation models of temperature and stress respectively, and establish transient stress calculation model and steady-state temperature calculation model based on the sensitivity parameter analysis results; A transient temperature model of key components under service conditions is established based on a simple temperature calculation model, and the transient temperature model is converted into a transient temperature response model based on the semi-infinite plate assumption and the steady-state temperature calculation model. Perform nonlinear fitting on the unknown coefficients in the transient temperature response model and the transient stress calculation model, and use the two models obtained by nonlinear fitting to calculate the transient temperature and transient stress of key components respectively; The process of converting the transient temperature model into the transient temperature response model based on the semi-infinite plate assumption and the steady-state temperature calculation model includes the following: Based on the semi-infinite plate assumption, the transient temperature model is regarded as a non-steady-state heat conduction process of the semi-infinite plate. Based on the third-category boundary condition and the steady-state temperature calculation model, the transient temperature model is converted into a temperature response model of the key component surface. The influence of the boundary conditions and operating conditions in the temperature response model is reflected through undetermined coefficients, and the influence of the position in the temperature response model is ignored. In this way, the temperature response model is corrected to obtain the transient temperature response model of the key component.

2. The method for rapidly calculating transient temperature and stress fields of key engine components according to claim 1, characterized in that: The expression of the steady-state temperature calculation model is: Among them, T ∞ represents the steady-state temperature, n represents the current speed of the rotor part in the key component, n0 represents the design speed of the rotor part in the key component, and A1 and A2 represent unknown coefficients.

3. The method for rapidly calculating transient temperature and stress fields of key engine components according to claim 1, characterized in that: The expression of the transient temperature model is: Where T represents the transient temperature, p* represents the total inlet pressure of the key component, p0 represents the atmospheric pressure under standard conditions, T* represents the total inlet temperature of the key component, T0 represents the atmospheric temperature under standard conditions, n represents the current speed of the rotor component in the key component, n0 represents the design speed of the rotor component in the key component, c1, c2, c3, c4 and c5 are all unknown coefficients, ΔT represents the temperature difference between the previous and next moments, t represents the time difference between the previous and next moments, k represents the adjustment coefficient, which is determined by the engine material, t0 represents the time constant, t0=f(ΔT, c p ,λ),c p represents the specific heat capacity at constant pressure, and λ represents the thermal conductivity.

4. The method for rapidly calculating transient temperature and stress fields of key engine components according to claim 1, wherein: The expression of the transient temperature response model is: Among them, T(τ) represents the transient temperature at time τ, T ∞ represents the steady-state temperature, ρ represents the material density, and B, D, and E are unknown coefficients.

5. The method for rapidly calculating transient temperature and stress fields of key engine components according to claim 4, characterized in that: When the time interval between the calculation moment and the initial moment exceeds the preset threshold, the expression of the transient temperature response model is: Among them, T t+1 Indicates the transient temperature at time t+1 during the transient heat conduction process, T t represents the transient temperature at time t during the transient heat conduction process, and C represents the unknown coefficient.

6. The method for rapidly calculating transient temperature and stress fields of key engine components according to claim 1, characterized in that: In the transient stress calculation model, the transient stress calculation formula in a certain direction is: s = s 离心应力 +s 热应力 +s 气动应力 ; s 气动应力 =H1; Where σ represents the transient stress, σ 离心应力 , σ 热应力 and σ 气动应力 They represent the transient centrifugal stress, thermal stress and aerodynamic stress respectively, p* represents the total inlet pressure of the key component, p0 represents the atmospheric pressure under standard conditions, T* represents the total inlet temperature of the key component, T0 represents the atmospheric temperature under standard conditions, n represents the current speed of the rotor component in the key component, n0 represents the design speed of the rotor component in the key component, K1, K2, K3, G1, G 11 , G2, G 21 , G3, G 31 and H1 are unknown coefficients.

7. A rapid calculation system for transient temperature and stress fields of key engine components, characterized by: include: A simple calculation model building module is used to establish a simple calculation model of the temperature of key components with respect to the inlet total temperature, inlet total pressure and rotational speed based on similarity criteria, as well as a simple calculation model of the stress with respect to the inlet total temperature, inlet total pressure and rotational speed; Sensitivity parameter analysis module, used to perform sensitivity parameter analysis on simple calculation models of temperature and stress respectively, and establish transient stress calculation model and steady-state temperature calculation model based on the sensitivity parameter analysis results; A transient temperature response model construction module is used to establish a transient temperature model of key components under service conditions based on a simple temperature calculation model, and convert the transient temperature model into a transient temperature response model based on a semi-infinite plate assumption and a steady-state temperature calculation model. The process of converting the transient temperature model into a transient temperature response model based on the semi-infinite plate assumption and the steady-state temperature calculation model includes the following: Based on the semi-infinite plate assumption, the transient temperature model is regarded as an unsteady-state heat conduction process of the semi-infinite plate. Based on the third-category boundary condition and the steady-state temperature calculation model, the transient temperature model is converted into a temperature response model of the key component surface. The influence of the boundary conditions and operating conditions in the temperature response model is reflected through undetermined coefficients, and the influence of the position in the temperature response model is ignored. In this way, the temperature response model is modified to obtain the transient temperature response model of the key component. The transient temperature and stress calculation module is used to perform nonlinear fitting on the unknown coefficients in the transient temperature response model and the transient stress calculation model, and use the two models obtained by nonlinear fitting to calculate the transient temperature and transient stress of key components respectively.

8. An electronic device, characterized in that: The method comprises a processor and a memory, wherein the memory stores a computer program, and the processor is configured to execute the steps of the method according to any one of claims 1 to 6 by calling the computer program stored in the memory.

9. A computer-readable storage medium for storing a computer program for rapidly calculating the temperature field and stress field of key components of an aerospace engine, characterized in that: When the computer program is run on a computer, the steps of the method according to any one of claims 1 to 6 are executed.

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