An aero-engine key part dangerous position temperature rapid evaluation method and device, electronic equipment and storage medium

Abstract

The application discloses an aero-engine key part dangerous position temperature rapid evaluation method and device, electronic equipment and storage medium, the method comprises the steps that S1, the temperature value, pressure value and rotating speed value in the flow channel are calculated by using the proportional conversion method, the steady-state temperature of the key part dangerous position is calculated, the transition state temperature calculation reduction model is established, and the model parameters are obtained; S2, the material parameters of the aero-engine key part, the temperature value, pressure value and rotating speed value corresponding to the main flow channel at the life calculation point are substituted into the transition state temperature calculation reduction model to rapidly calculate the transient temperature of the aero-engine key part dangerous position under any state. The application directly calculates the rapid temperature of the key part dangerous position by substituting the mathematical theoretical model established by the flight parameters, avoids the consumption of hardware resources and solving time caused by large-scale simulation solving, improves the calculation speed to the order of millisecond, shortens the design cycle, and reduces the calculation cost.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, and in particular, to a method, apparatus, equipment, and storage medium for rapid temperature assessment of critical components and hazardous parts of aero-engines. Background Technology

[0002] As required, the engine design life must be specified during the engine design process, and a conclusion must be drawn regarding whether the design life is met. In practice, in the early stages of the design phase, only a few states from idle to the design point are analyzed in detail using CFD methods to provide boundary condition inputs for static strength and vibration assessments. However, determining whether the design life requirement is met requires calculations of dozens of life state points within the flight envelope, as well as the stress and temperature of key components under transient conditions in typical mission profiles, before a conclusion can be reached on whether the life meets the design requirements. Currently, temperature calculations involve numerous steps, including overall thermodynamic cycle analysis, main channel aerodynamics of components, overall air system analysis, heat transfer boundary conditions, and temperature field analysis. Only through complex large-scale 3D simulation modeling and analysis can relatively reasonable component temperature distribution calculation results be obtained. This process is computationally intensive and time-consuming. The calculation cycle from upstream overall thermodynamic analysis to downstream temperature analysis is typically measured in months. For engines under development and already in service, lifespan design and evaluation need to be conducted in conjunction with flight missions. While the number of lifespan calculation points can be reduced by grouping and merging flight profiles according to engine load elements, the number of calculation points after typification can still reach dozens. Furthermore, transient temperature, intensity, and lifespan assessments are required based on the flight profiles. If the aforementioned 3D simulation analysis method is used to perform thermal analysis calculations on the temperature distribution of each calculation point, the workload is enormous and difficult to match the speed of overall thermal analysis. This objectively prevents multi-round design iteration optimization during the design phase. In practice, lifespan assessment is often delayed until before production finalization and requires a large amount of manpower to conduct; if the design lifespan requirements are not met, there is no time for improvement.

[0003] In addition, due to repeated corrections to the overall thermodynamic cycle and changes in the life calculation point caused by changes in the engine's installation target, the above temperature analysis process often needs to be repeated.

[0004] In summary, when using existing technologies to perform temperature analysis on key engine components, it is necessary to repeatedly perform complex three-dimensional simulation calculations with high computational costs in multiple rounds, which seriously restricts the design progress and increases the design cycle and cost. Summary of the Invention

[0005] This application provides a method for rapid temperature assessment of critical components of aero-engines, which addresses the technical problem that existing technologies severely restrict design progress and increase design cycle and cost when performing temperature analysis on critical engine components.

[0006] This application is achieved through the following solution:

[0007] A method for rapid temperature assessment of critical components in aero-engines includes the following steps:

[0008] S1. The proportional conversion algorithm is used to calculate the temperature, pressure and rotation speed in the flow channel and the steady-state temperature of the critical parts of the key components. A reduced-order model for temperature calculation under the transient state is established and the model parameters are obtained.

[0009] S2. Substitute the material parameters of the key components of the aero-engine, the temperature, pressure and speed values ​​of the main channel corresponding to the life calculation point into the temperature calculation reduction model under the transition state to quickly calculate the transient temperature of the critical parts of the aero-engine under any state. The material parameters include density, specific heat capacity and thermal conductivity.

[0010] In a preferred embodiment, step S1 specifically includes the following steps:

[0011] S11. Based on the overall engine performance and internal flow calculations, obtain the inlet and outlet section temperatures of key component flow paths and the qualitative temperature of critical component wall surfaces at dangerous locations. and heat transfer coefficient h ;

[0012] S12. Based on the temperature values ​​of the inlet and outlet sections of the critical component flow path and the qualitative temperature of the wall surface of the critical component's dangerous parts... and heat transfer coefficient h Calculate the ratio of qualitative temperature of the wall surface and the ratio of wall surface heat transfer coefficient of the critical parts of the component;

[0013] S13. Obtain the proportional conversion constant of the proportional conversion method based on the ratio of the wall surface qualitative temperature and the ratio of the wall surface heat transfer coefficient;

[0014] S14. Based on the temperature values ​​of the inlet and outlet sections of the flow path of the critical component and the proportional conversion constant, the steady-state temperature of the dangerous part of the critical component is solved by the proportional conversion method.

[0015] S15. Based on the temperature change law of the critical component's dangerous part under transient convective heat transfer boundary conditions, the steady-state temperature of the critical component's dangerous part, and material parameters, establish a reduced-order model for temperature calculation under the transition state and obtain the model parameters.

[0016] In a preferred embodiment, step S11 specifically includes the following steps:

[0017] S111. Obtain the inlet and outlet section temperatures of key component flow paths based on overall engine performance calculations. and ,in, This refers to the temperature of the airflow at the inlet or upstream of the engine component. This refers to the outlet or downstream airflow temperature of the engine component;

[0018] S112. Obtain the qualitative temperature of the wall surface of the critical component's dangerous part based on internal flow calculation. With heat transfer coefficient .

[0019] In a preferred embodiment, step S12 specifically includes the following steps:

[0020] S121. Calculate the ratio of the qualitative temperature of the wall surface of the critical component in the dangerous area, including calculating the qualitative temperature of the wall surface of the critical component in the known state. and reference condition qualitative temperature dimensionless ratio:

[0021] ; (1)

[0022] S122. Calculate the ratio of wall heat transfer coefficients at critical locations of key components, including calculating the wall heat transfer coefficients at critical locations of key components under known conditions. Heat transfer coefficient compared to reference condition dimensionless ratio:

[0023] ; (2)

[0024] The baseline state is the design point state.

[0025] In a preferred embodiment, step S13 specifically includes the following steps:

[0026] S131. Establish a first calculation model based on the similarity criterion between the wall surface qualitative temperature ratio and the flow path temperature, pressure, and rotational speed:

[0027] ; (3)

[0028] in, n б This indicates the rotational speed corresponding to the reference state of the key component; T б This indicates the temperature corresponding to the reference state of the critical component; P б This indicates the pressure corresponding to the baseline state of the critical component; n The rotational speed corresponding to the current state of the critical component. T The temperature corresponding to the current state of the critical component. P The pressure corresponding to the current state of the critical component.d i These are constant parameters, obtained by fitting qualitative temperature, speed, temperature, and pressure results from simulation or experimental measurements at least four state points from slow speed to design point.

[0029] S132. Establish a second calculation model based on the similarity criterion between the wall heat transfer coefficient ratio and the flow path temperature, pressure, and rotational speed:

[0030] ; (4)

[0031] in, b i These are constant parameters, obtained by fitting the heat transfer coefficient, rotational speed, temperature, and pressure results from simulation or experimental measurements at least four state points from idle to design point;

[0032] S133, Calculate the proportional conversion constant. During the calculation, the proportional conversion constant for at least four state points from the idle speed to the design point is calculated based on the inlet and outlet temperatures of the critical component flow path and the temperatures of the critical parts in dangerous locations, obtained from simulation or experimental measurements at at least four state points from the idle speed to the design point. The proportional conversion constant for any other state is calculated using the following formula:

[0033] ...; (5)

[0034] in, a i The calculation parameters are based on the proportional conversion constants obtained from the above calculations. The ratio of wall heat transfer coefficient to wall qualitative temperature was obtained by fitting.

[0035] In a preferred embodiment, step S14 specifically includes the following steps:

[0036] S141. Based on the temperature values ​​of the inlet and outlet sections of the flow path of the critical component and the proportional conversion constant, the steady-state temperature of the critical component's dangerous parts is calculated using the proportional conversion method:

[0037] ; (6)

[0038] in, This refers to the steady-state temperature of critical components at hazardous locations.

[0039] In a preferred embodiment, step S15 specifically includes the following steps:

[0040] S151. Based on the temperature variation law, steady-state temperature, material parameters, and solid transient convection heat transfer boundary condition of critical component dangerous parts, establish a reduced-order model for temperature calculation under transient state and obtain the model parameters:

[0041] ; (7)

[0042] in, Critical and dangerous parts at the current moment i Temperature at that location; For the critical and dangerous parts of the next moment i Temperature at that location; The steady-state temperature is the temperature of the critical component's critical location over an infinitely long period. For time increments, ρ and c p λ and λ represent the material's density, specific heat capacity, and thermal conductivity, respectively. A The model parameters are obtained by fitting the transient simulation results under arbitrary flight profiles.

[0043] Another embodiment of this application provides a rapid temperature assessment device for critical components of an aero-engine, including:

[0044] The reduced-order model building module is used to calculate the temperature, pressure, and rotational speed values ​​in the flow channel and the steady-state temperature of critical parts using a proportional conversion algorithm, to establish a reduced-order model for temperature calculation under transient conditions and to obtain model parameters.

[0045] The transient temperature rapid calculation module is used to substitute the material parameters of key components of aero-engines, the temperature value, pressure value and speed value of the main channel corresponding to the life calculation point into the temperature calculation reduction model under the transition state to quickly calculate the transient temperature of the dangerous parts of key components of aero-engines. The material parameters include density, specific heat capacity and thermal conductivity.

[0046] Another preferred embodiment of this application also provides an electronic device, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the steps of the rapid temperature assessment method for critical parts of aero-engine components.

[0047] Another preferred embodiment of this application also provides a storage medium, the storage medium including a stored program, which, when the program is executed, controls the device where the storage medium is located to perform the steps of the rapid temperature assessment method for critical parts of aero-engine components.

[0048] Compared with the prior art, this application has the following advantages:

[0049] This application provides a method, device, electronic device, and storage medium for rapid temperature assessment of critical components in aero-engines. The method addresses the rapid temperature assessment of critical components in aero-engines. Currently, calculating the temperature field of critical components in a given state requires complex large-scale 3D CFD simulation modeling and analysis, involving specialized analysis stages including overall thermodynamic cycle, main channel aerodynamics, overall air system, heat transfer boundary conditions, and heat transfer analysis. This involves numerous computational analyses, a large computational load, and is geared towards lifespan analysis, requiring temperature field calculations at dozens of state points. Using existing conventional methods, this process takes months. This application constructs a method for assessing critical components' critical parts using engine flight parameters. Compared to traditional methods, it directly calculates the temperature of critical components' critical parts from flight parameters. By using a mathematical theoretical model instead of complex simulation calculations, it avoids the consumption of hardware resources and solution time for large-scale solutions, increasing calculation speed to the millisecond level, improving thermal analysis efficiency, shortening the design cycle, reducing computational costs, and achieving efficient temperature assessment of critical components' critical parts.

[0050] In addition to the purposes, features, and advantages described above, this application has other purposes, features, and advantages. A further detailed description of this application will be provided below with reference to the figures. Attached Figure Description

[0051] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments consistent with this application and, together with the description, serve to explain the principles of this application.

[0052] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, for those skilled in the art, other drawings can be obtained based on these drawings without creative effort, wherein:

[0053] Figure 1 This is a schematic flowchart of a preferred embodiment of the method for rapid temperature assessment of critical components of an aero-engine.

[0054] Figure 2 This is a schematic diagram of the engine cross-sectional parameters;

[0055] Figure 3 This is a schematic diagram comparing the wheel center temperature calculated using the method of the preferred embodiment of this application with the results of three-dimensional finite element transient simulation;

[0056] Figure 4 This is a schematic diagram comparing the rim temperature calculated using the method of the preferred embodiment of this application with the results of three-dimensional finite element transient simulation;

[0057] Figure 5 This is a schematic diagram of a rapid temperature assessment device module for critical components of an aero-engine according to a preferred embodiment of this application;

[0058] Figure 6 This is a schematic block diagram of an electronic device according to a preferred embodiment of this application;

[0059] Figure 7 This is an internal structural diagram of a computer device according to a preferred embodiment of this application. Detailed Implementation

[0060] It should be understood that the specific embodiments described herein are merely illustrative of the technical solutions of this application and are not intended to limit this application.

[0061] To better understand the technical solution of this application, a detailed description will be provided below in conjunction with the accompanying drawings and specific implementation methods.

[0062] It should be noted that the executing entity in this embodiment can be a computing service device with data processing, network communication, and program execution functions, such as a tablet computer, personal computer, or mobile phone, or a rapid temperature assessment device for critical components of aero-engines capable of performing the above functions. The following description uses a rapid temperature assessment device for critical components of aero-engines as the executing entity to illustrate this embodiment and the subsequent embodiments.

[0063] like Figure 1 As shown, a preferred embodiment of this application provides a method for rapid temperature assessment of critical components in aero-engines, including the following steps:

[0064] S1. The proportional conversion algorithm is used to calculate the temperature, pressure and rotation speed in the flow channel and the steady-state temperature of the critical parts of the key components. A reduced-order model for temperature calculation under the transient state is established and the model parameters are obtained.

[0065] S2. Substitute the material parameters of the key components of the aero-engine, the temperature, pressure and speed values ​​of the main channel corresponding to the life calculation point into the temperature calculation reduction model under the transition state to quickly calculate the transient temperature of the critical parts of the aero-engine under any state. The material parameters include density, specific heat capacity and thermal conductivity.

[0066] This embodiment provides a rapid temperature assessment method for critical components of aero-engines. This method addresses the rapid temperature assessment of critical components in aero-engines. Currently, calculating the temperature field of critical components in a given state requires complex, large-scale 3D CFD simulation modeling and analysis, involving specialized analytical steps including overall thermodynamic cycle, main channel aerodynamics, overall air system, heat transfer boundary conditions, and heat transfer analysis. This involves numerous computational analyses, a large computational load, and is geared towards lifespan analysis, requiring temperature field calculations at dozens of state points. Using existing conventional methods, this process takes months. Therefore, to address the aforementioned issues, this embodiment constructs a method for evaluating critical components and their hazardous parts using engine flight parameters. This method first employs a proportional conversion algorithm to calculate the temperature, pressure, and rotational speed within the flow channel, along with the steady-state temperature of the critical component's hazardous parts. A reduced-order temperature calculation model under transient conditions is established, and model parameters are obtained. Then, by substituting the material parameters of the aero-engine's critical components, the corresponding temperature, pressure, and rotational speed of the main flow channel at the life calculation point into the reduced-order temperature calculation model under transient conditions, the transient temperature of the critical component's hazardous parts under any given state can be rapidly calculated without the intervention of complex simulation calculations. As can be seen, compared to traditional methods, this embodiment directly calculates the temperature of critical components and their hazardous parts using flight parameters. By employing a mathematical theoretical model instead of complex simulation calculations, it avoids the consumption of hardware resources and solution time associated with large-scale solutions, increasing the calculation speed to the millisecond level. This improves the efficiency of thermal analysis calculations, shortens the design cycle, reduces computational costs, and achieves efficient evaluation of the temperature of critical components and their hazardous parts.

[0067] In a preferred embodiment of this application, step S1 specifically includes the following steps:

[0068] S11. Based on the overall engine performance and internal flow calculations, obtain the inlet and outlet section temperatures of key component flow paths and the qualitative temperature of critical component wall surfaces at dangerous locations. and heat transfer coefficient h ;

[0069] S12. Based on the temperature values ​​of the inlet and outlet sections of the critical component flow path and the qualitative temperature of the wall surface of the critical component's dangerous parts... and heat transfer coefficient h Calculate the ratio of qualitative temperature of the wall surface and the ratio of wall surface heat transfer coefficient of the critical parts of the component;

[0070] S13. Obtain the proportional conversion constant of the proportional conversion method based on the ratio of the wall surface qualitative temperature and the ratio of the wall surface heat transfer coefficient;

[0071] S14. Based on the temperature values ​​of the inlet and outlet sections of the flow path of the critical component and the proportional conversion constant, the steady-state temperature of the dangerous part of the critical component is solved by the proportional conversion method.

[0072] S15. Based on the temperature change law of the critical component's dangerous part under transient convective heat transfer boundary conditions, the steady-state temperature of the critical component's dangerous part, and material parameters, establish a reduced-order model for temperature calculation under the transition state and obtain the model parameters.

[0073] In this embodiment, a reduced-order model for temperature calculation under the transition state is established and model parameters are obtained through steps S11-S14. Firstly, flight parameters are used to calculate the inlet and outlet cross-sectional temperatures of the critical component flow path and the qualitative temperature of the wall surface at the critical location of the critical component. and heat transfer coefficient h Then, the inlet and outlet cross-sectional temperature values ​​of the critical component flow path and the qualitative temperature of the wall surface of the critical component's dangerous parts are calculated. and heat transfer coefficient h The ratio of the qualitative temperature of the wall surface and the ratio of the wall heat transfer coefficient of the critical component's dangerous parts are calculated. Then, based on these ratios, the proportional conversion constant of the proportional conversion algorithm is obtained. This lays the foundation for calculating the temperature, pressure, and rotational speed values ​​within the flow channel and the steady-state temperature of the critical component's dangerous parts using the proportional conversion algorithm. Finally, after obtaining the steady-state temperature of the critical component's dangerous parts using the proportional conversion algorithm, a reduced-order model for temperature calculation under transient convective heat transfer boundary conditions, the steady-state temperature of the critical component's dangerous parts, and material parameters is established, and the model parameters are obtained. In this embodiment, a reduced-order model for temperature calculation under transient conditions is directly established based on flight parameters. The model parameters are obtained without the need for complex simulations. A mathematical theoretical model replaces the complex simulation model to calculate the temperature of critical parts of key components. This avoids the consumption of hardware resources and solution time that would otherwise be required by complex simulation models. The scaling algorithm further simplifies complex relationships, reduces numerical complexity, improves computational efficiency, and reduces computational steps. Therefore, this embodiment establishes a reduced-order model for temperature calculation under transient conditions directly through flight parameters. The scaling algorithm and the model are organically combined to form a whole, working together to improve the calculation speed to the millisecond level, improve the efficiency of thermal analysis calculations, shorten the design cycle, reduce computational costs, and achieve efficient assessment of the temperature of critical parts of key components.

[0074] In a preferred embodiment of this application, step S11 specifically includes the following steps:

[0075] S111. Obtain the inlet and outlet cross sections of the flow path for key components based on the overall engine performance calculation (see...). Figure 2 Temperature value and ,in, This refers to the temperature of the airflow at the inlet or upstream of the engine component. This refers to the outlet or downstream airflow temperature of the engine component;

[0076] S112. Obtain the qualitative temperature of the wall surface of the critical component's dangerous part based on internal flow calculation. With heat transfer coefficient .

[0077] like Figure 2 In the schematic diagram of engine cross-sectional parameters shown, 2 represents the compressor inlet cross-section, 3 represents the compressor outlet cross-section, 4 represents the turbine inlet cross-section, 4.5 represents the low-pressure turbine inlet cross-section, and 5 represents the turbine outlet cross-section. This embodiment, through steps S111~S112, calculates the temperature values ​​of the inlet and outlet cross-sections of key components based on flight parameters such as overall engine performance and internal flow. and Qualitative temperature of critical component wall surface in hazardous areas With heat transfer coefficient h Among them, qualitative temperature and heat transfer coefficient can be directly obtained through three-dimensional CFD simulation calculation, providing input for temperature calculation of critical parts of key components.

[0078] In a preferred embodiment of this application, step S12 specifically includes the following steps:

[0079] S121. Calculate the ratio of the qualitative temperature of the wall surface of the critical component in the dangerous area, including calculating the qualitative temperature of the wall surface of the critical component in the known state. and reference condition qualitative temperature dimensionless ratio:

[0080] ; (1)

[0081] S122. Calculate the ratio of wall heat transfer coefficients at critical locations of key components, including calculating the wall heat transfer coefficients at critical locations of key components under known conditions. Heat transfer coefficient compared to reference condition dimensionless ratio:

[0082] ; (2)

[0083] The baseline state is the design point state.

[0084] In this embodiment, steps S121-S122 are used to calculate the ratio of the qualitative temperature of the wall surface of the critical component in dangerous areas and the ratio of the heat transfer coefficient of the wall surface of the critical component in dangerous areas. The qualitative temperature and heat transfer coefficient under any condition can be quickly calculated using the above ratio.

[0085] In a preferred embodiment of this application, step S13 specifically includes the following steps:

[0086] S131. Establish a first calculation model based on the similarity criterion between the wall surface qualitative temperature ratio and the flow path temperature, pressure, and rotational speed:

[0087] ; (3)

[0088] in, n б This indicates the rotational speed corresponding to the reference state of the key component; T б This indicates the temperature corresponding to the reference state of the critical component; P б This indicates the pressure corresponding to the baseline state of the critical component; n The rotational speed corresponding to the current state of the critical component. T The temperature corresponding to the current state of the critical component. P The pressure corresponding to the current state of the critical component. d i These are constant parameters, obtained by fitting qualitative temperature, speed, temperature, and pressure results from simulation or experimental measurements at least four state points from slow speed to design point.

[0089] S132. Establish a second calculation model based on the similarity criterion between the wall heat transfer coefficient ratio and the flow path temperature, pressure, and rotational speed:

[0090] ; (4)

[0091] in, b i These are constant parameters, obtained by fitting the heat transfer coefficient, rotational speed, temperature, and pressure results from simulation or experimental measurements at least four state points from idle to design point;

[0092] S133, Calculate the proportional conversion constant. During the calculation, the proportional conversion constant for at least four state points from the idle speed to the design point is calculated based on the inlet and outlet temperatures of the critical component flow path and the temperatures of the critical parts in dangerous locations, obtained from simulation or experimental measurements at at least four state points from the idle speed to the design point. The proportional conversion constant for any other state is calculated using the following formula:

[0093] ...; (5)

[0094] in, a i The calculation parameters are based on the proportional conversion constants obtained from the above calculations. The ratio of wall heat transfer coefficient to wall qualitative temperature was obtained by fitting.

[0095] This embodiment establishes a calculation model based on similarity criteria in steps S131-S133, relating the wall heat transfer coefficient ratio to flow path temperature, pressure, and rotational speed. It also calculates proportional conversion constants for various states. In this application, the proportional conversion constant depends on the heat dissipation level of the critical component under a certain state. It can be expressed as a polynomial function of the local heat dissipation coefficient and qualitative temperature under that state compared to the ratio of the local heat dissipation coefficient to the qualitative temperature under a reference state (generally selected as the design point state). These two ratios are determined according to similarity criteria. The proportional conversion coefficient is quickly calculated, establishing a bridge between the mainstream inlet and outlet temperatures of the critical component and the temperatures of the critical component's hazardous areas.

[0096] In a preferred embodiment of this application, step S14 specifically includes the following steps:

[0097] S141. Based on the temperature values ​​of the inlet and outlet sections of the flow path of the critical component and the proportional conversion constant, the steady-state temperature of the critical component's dangerous parts is calculated using the proportional conversion method:

[0098] ; (6)

[0099] in, This refers to the steady-state temperature of critical components at hazardous locations.

[0100] This embodiment calculates the steady-state temperature of critical components at dangerous locations using a proportional conversion algorithm based on the inlet and outlet temperatures of the flow path and a proportional conversion constant. This allows for the calculation of the steady-state temperature of critical components at dangerous locations under any given state, taking into account flow path temperature, pressure, and rotational speed. The advantages and objectives of this embodiment include the ability to directly and efficiently obtain accurate steady-state temperatures of critical components at dangerous locations using the inlet and outlet temperatures of the flow path, avoiding large-scale simulation numerical calculations.

[0101] In a preferred embodiment of this application, step S15 specifically includes the following steps:

[0102] S151. Based on the temperature variation law, steady-state temperature, material parameters, and solid transient convection heat transfer boundary condition of critical component dangerous parts, establish a reduced-order model for temperature calculation under transient state and obtain the model parameters:

[0103] ; (7)

[0104] in, Critical and dangerous parts at the current moment i Temperature at that location; For the critical and dangerous parts of the next moment i Temperature at that location; The steady-state temperature is the temperature of the critical component's critical location over an infinitely long period. For time increments, ρ and c p λ and λ represent the material's density, specific heat capacity, and thermal conductivity, respectively. A The model parameters are obtained by fitting the transient simulation results under arbitrary flight profiles.

[0105] In summary, formula (6) can be substituted into formula (7), and the transient temperature of critical parts can be calculated based on material parameters such as density, specific heat capacity, and thermal conductivity. Using the above method, the calculation results for a certain cross-section are compared with the results of the three-dimensional finite element transient simulation. Figure 3 and Figure 4 As shown, the calculation results of this application are within the acceptable range for engineering applications, and meet the engineering requirements.

[0106] This embodiment establishes a reduced-order temperature calculation model under transient convective heat transfer boundary conditions, steady-state temperature, material parameters, and solid transient convective heat transfer boundary conditions based on the temperature variation law of critical components and dangerous parts under transient convective heat transfer boundary conditions. The model parameters are then obtained. The flight parameters of this reduced-order temperature calculation model under transient conditions are directly established, eliminating the need for complex simulations. A mathematical theoretical model replaces a complex simulation model for calculating the temperature of critical components and dangerous parts. This avoids the consumption of hardware resources and solution time associated with complex simulation models, increasing the calculation speed to the millisecond level, improving thermal analysis calculation efficiency, shortening the design cycle, reducing calculation costs, and enabling rapid calculation of transient temperatures of critical components and dangerous parts under any conditions. This achieves efficient assessment of the temperature of critical components and dangerous parts.

[0107] As can be seen, to address the problem of low efficiency in temperature analysis of critical components and dangerous parts in current engine designs, this application proposes a rapid analysis and evaluation method for the temperature of critical components and dangerous parts based on aero-engine flight parameters. The overall scheme is as follows:

[0108] A proportional conversion algorithm is used to calculate the temperature, pressure, and rotational speed within the flow channel, as well as the steady-state temperature of critical components in hazardous areas. A reduced-order model for temperature calculation under transient conditions is established, and the model parameters are obtained. This reduced-order model is then used to calculate the temperature under transient conditions. Based on the reduced-order model, the temperature, pressure, and rotational speed values ​​corresponding to the main flow channel at the lifespan calculation point are substituted into the reduced-order model, enabling efficient calculation of the temperature of critical components in hazardous areas.

[0109] Based on the above overall scheme, this invention focuses on solving the method for determining the proportional conversion constant in the proportional conversion algorithm, as well as the method for establishing and determining the parameters of the transition state temperature reduction calculation model.

[0110] This application argues that the proportional conversion constant depends on the heat dissipation level of the critical component under a certain state, and can be expressed as a polynomial function of the ratio of the local heat dissipation coefficient and qualitative temperature under that state to the ratio of the local heat dissipation coefficient to the qualitative temperature under the reference state (the reference state is generally selected as the design point state). These two ratios are determined based on similarity criteria. The reduced-order calculation model for the transient temperature of the critical component is given based on the temperature variation law under the transient convective heat transfer boundary conditions of the solid. Furthermore, the model coefficients can be obtained from the transient three-dimensional simulation results or transient temperature test results under a certain cross-section.

[0111] In summary, a complete calculation method for rapidly obtaining the temperature of critical parts of key components from engine flight parameters has been established.

[0112] like Figure 5 As shown, another embodiment of this application also provides a rapid temperature assessment device for critical components of an aero-engine, comprising:

[0113] The reduced-order model building module is used to calculate the temperature, pressure, and rotational speed values ​​in the flow channel and the steady-state temperature of critical parts using a proportional conversion algorithm, to establish a reduced-order model for temperature calculation under transient conditions and to obtain model parameters.

[0114] The transient temperature rapid calculation module is used to substitute the material parameters of key components of aero-engines, the temperature value, pressure value and speed value of the main channel corresponding to the life calculation point into the temperature calculation reduction model under the transition state to quickly calculate the transient temperature of the dangerous parts of key components of aero-engines. The material parameters include density, specific heat capacity and thermal conductivity.

[0115] The rapid temperature assessment device for critical components of aero-engines provided in this application, employing the rapid temperature assessment method for critical components of aero-engines described in the above embodiments, can solve the technical problems that severely restrict design progress and increase design cycle and cost. Compared with the prior art, the beneficial effects of the rapid temperature assessment device for critical components of aero-engines provided in this application are the same as those of the rapid temperature assessment method for critical components of aero-engines provided in the above embodiments, and other technical features in the rapid temperature assessment device for critical components of aero-engines are the same as those disclosed in the methods of the above embodiments, and will not be repeated here.

[0116] like Figure 6 As shown, a preferred embodiment of this application also provides an electronic device, including a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, it implements the steps of the rapid temperature assessment method for critical parts of aero-engine components described in the above embodiments.

[0117] The electronic device provided in this application employs the rapid temperature assessment method for critical components of aero-engines described in the above embodiments, which can solve the technical problems that severely restrict design progress and increase design cycle and cost. Compared with the prior art, the beneficial effects of the electronic device provided in this application are the same as those of the rapid temperature assessment method for critical components of aero-engines provided in the above embodiments, and other technical features of the electronic device are the same as those disclosed in the methods of the above embodiments, and will not be repeated here.

[0118] like Figure 7 As shown, a preferred embodiment of this application also provides a computer device, which may be a terminal or a liveness detection server, and its internal structure diagram may be as follows. Figure 7 As shown. The computer device includes a processor, memory, and a network interface connected via a system bus. The processor provides computing and control capabilities. The memory includes non-volatile storage media and internal memory. The non-volatile storage media stores the operating system and computer programs. The internal memory provides an environment for the operation of the operating system and computer programs in the non-volatile storage media. The network interface is used to communicate with other external computer devices via a network connection. When the computer program is executed by the processor, it implements the steps of the aforementioned rapid temperature assessment method for critical components of aero-engines.

[0119] Those skilled in the art will understand that Figure 7 The structure shown is merely a block diagram of a portion of the structure related to the present application and does not constitute a limitation on the computer device to which the present application is applied. Specific computer devices may include more or fewer components than those shown in the figure, or combine certain components, or have different component arrangements.

[0120] The computer equipment provided in this application, employing the rapid temperature assessment method for critical components of aero-engines described in the above embodiments, can solve the technical problems that severely restrict design progress and increase design cycle and cost. Compared with the prior art, the beneficial effects of the computer equipment provided in this application are the same as those of the rapid temperature assessment method for critical components of aero-engines provided in the above embodiments, and other technical features of the electronic equipment are the same as those disclosed in the methods of the above embodiments, and will not be repeated here.

[0121] A preferred embodiment of this application also provides a storage medium, the storage medium including a stored program, which, when the program is executed, controls the device where the storage medium is located to perform the steps of the rapid temperature assessment method for critical parts of aero-engine components described in the above embodiments.

[0122] It should be noted that the steps shown in the flowchart in the accompanying drawings can be executed in a computer system such as a set of computer-executable instructions, and although a logical order is shown in the flowchart, in some cases the steps shown or described may be executed in a different order than that shown here.

[0123] If the functions described in this embodiment are implemented as software functional units and sold or used as independent products, they can be stored in one or more computing device-readable storage media. Based on this understanding, the parts of this application's embodiments that contribute to the prior art or the technical solutions can be embodied in the form of a software product. This software product is stored in a storage medium and includes several instructions to cause a computing device (which may be a personal computer, server, mobile computing device, or network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of this application. The aforementioned storage media include: USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, optical disks, and other media capable of storing program code.

[0124] Those skilled in the art will understand that embodiments of this application can be provided as methods, systems, or computer program products. Therefore, this application can take the form of a completely hardware embodiment, a completely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, this application can 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 this application can be implemented in various computer languages, such as the object-oriented programming language Java and the interpreted scripting language JavaScript.

[0125] This application is described with reference to flowchart illustrations and / or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of this application. It will be understood that each block of the flowchart illustrations and / or block diagrams, and combinations of blocks in the flowchart illustrations and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, special-purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, generate instructions for implementing the flowchart... Figure 1 One or more processes and / or boxes Figure 1 A device that provides the functions specified in one or more boxes.

[0126] These computer program instructions may also be stored in a computer-readable storage medium that can direct a computer or other programmable data processing device to function in a particular manner, such that the instructions stored in the computer-readable storage medium produce an article of manufacture including instruction means, which are implemented in a process Figure 1 One or more processes and / or boxes Figure 1 The function specified in one or more boxes.

[0127] These computer program instructions may also be loaded onto a computer or other programmable data processing equipment to cause a series of operational steps to be performed on the computer or other programmable equipment to produce a computer-implemented process, thereby providing instructions that execute on the computer or other programmable equipment for implementing the process. Figure 1 One or more processes and / or boxes Figure 1 The steps of the function specified in one or more boxes.

[0128] This application also provides a computer program product, including a computer program that, when executed by a processor, implements the steps of the above-described method for rapid temperature assessment of critical parts of aero-engine components.

[0129] The computer program product provided in this application can solve the technical problems that severely restrict design progress and increase design cycle and cost. Compared with the prior art, the beneficial effects of the computer program product provided in this application are the same as those of the rapid temperature assessment method for critical parts of aero-engines provided in the above embodiments, and will not be repeated here.

[0130] Although preferred embodiments of this application have been described, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments as well as all changes and modifications falling within the scope of this application.

[0131] Obviously, those skilled in the art can make various modifications and variations to this application without departing from the spirit and scope of this application. Therefore, if such modifications and variations fall within the scope of the claims of this application and their equivalents, this application also intends to include such modifications and variations.

Claims

1. A method for rapid temperature assessment of critical components in aero-engines, characterized in that, Including the following steps: S1. Calculate the temperature, pressure, and rotational speed values ​​within the flow channel, along with the steady-state temperature of critical components at dangerous locations, using a proportional conversion algorithm. Establish a reduced-order temperature calculation model under transient conditions and obtain the model parameters. Specific steps include: S11. Based on the overall engine performance and internal flow calculations, obtain the inlet and outlet section temperatures of key component flow paths and the qualitative temperature of critical component wall surfaces at dangerous locations. and heat transfer coefficient h ; S12. Based on the temperature values ​​of the inlet and outlet sections of the critical component flow path and the qualitative temperature of the wall surface of the critical component's dangerous parts... and heat transfer coefficient h Calculate the ratio of qualitative temperature of the wall surface and the ratio of wall surface heat transfer coefficient of the critical parts of the component; S13. Obtain the proportional conversion constant of the proportional conversion method based on the ratio of the wall surface qualitative temperature and the ratio of the wall surface heat transfer coefficient; S14. Based on the temperature values ​​of the inlet and outlet sections of the flow path of the critical component and the proportional conversion constant, the steady-state temperature of the dangerous part of the critical component is solved by the proportional conversion method. S15. Based on the temperature change law of the critical component's dangerous part under transient convective heat transfer boundary conditions, the steady-state temperature of the critical component's dangerous part, and material parameters, establish a reduced-order model for temperature calculation under the transition state and obtain the model parameters. S2. Substitute the material parameters of the key components of the aero-engine, the temperature, pressure and speed values ​​of the main channel corresponding to the life calculation point into the temperature calculation reduction model under the transition state to quickly calculate the transient temperature of the critical parts of the aero-engine under any state. The material parameters include density, specific heat capacity and thermal conductivity.

2. The method for rapid temperature assessment of critical components and hazardous parts of aero-engines according to claim 1, characterized in that, Step S11 specifically includes the following steps: S111. Calculate the inlet and outlet cross-sectional temperatures of key component flow paths based on overall engine performance. and ,in, This refers to the temperature of the airflow at the inlet or upstream of the engine component. This refers to the outlet or downstream airflow temperature of the engine component; S112. Obtain the qualitative temperature of the wall surface of the critical component's dangerous part based on internal flow calculation. With heat transfer coefficient .

3. The method for rapid temperature assessment of critical components and hazardous parts of aero-engines according to claim 2, characterized in that, Step S12 specifically includes the following steps: S121. Calculate the ratio of the qualitative temperature of the wall surface of the critical component in the dangerous area, including calculating the qualitative temperature of the wall surface of the critical component in the known state. and reference condition qualitative temperature dimensionless ratio: ； S122. Calculate the ratio of wall heat transfer coefficients at critical locations of key components, including calculating the wall heat transfer coefficients at critical locations of key components under known conditions. Heat transfer coefficient compared to reference state dimensionless ratio: ； The baseline state is the design point state.

4. The method for rapid temperature assessment of critical components and hazardous parts of aero-engines according to claim 3, characterized in that, Step S13 specifically includes the following steps: S131. Establish a first calculation model based on the similarity criterion between the wall surface qualitative temperature ratio and the flow path temperature, pressure, and rotational speed: ； in, n б This indicates the rotational speed corresponding to the reference state of the key component; T б This indicates the temperature corresponding to the reference state of the critical component; P б This indicates the pressure corresponding to the baseline state of the critical component; n The rotational speed corresponding to the current state of the key component. T The temperature corresponding to the current state of the critical component. P The pressure corresponding to the current state of the critical component. d i These are constant parameters, obtained by fitting qualitative temperature, speed, temperature, and pressure results from simulation or experimental measurements at least four state points from slow speed to design point. S132. Establish a second calculation model based on the similarity criterion between the wall heat transfer coefficient ratio and the flow path temperature, pressure, and rotational speed: ； in, b i These are constant parameters, obtained by fitting the heat transfer coefficient, rotational speed, temperature, and pressure results from simulation or experimental measurements at least four state points from idle to design point; S133, Calculate the proportional conversion constant. During the calculation, the proportional conversion constant for at least four state points from the idle speed to the design point is calculated based on the inlet and outlet temperatures of the critical component flow path and the temperatures of the critical component's dangerous parts obtained from simulation or experimental measurements at at least four state points from the idle speed to the design point. The proportional conversion constant for any other state is calculated using the following formula: ……； in, a i The calculation parameters are based on the proportional conversion constants obtained from the above calculations. The ratio of wall heat transfer coefficient to wall qualitative temperature was obtained by fitting.

5. The method for rapid temperature assessment of critical components and hazardous parts of aero-engines according to claim 4, characterized in that, Step S14 specifically includes the following steps: S141. Based on the temperature values ​​of the inlet and outlet sections of the flow path of the critical component and the proportional conversion constant, the steady-state temperature of the critical component's dangerous parts is calculated using the proportional conversion method: ； in, This refers to the steady-state temperature of critical components at hazardous locations.

6. The method for rapid temperature assessment of critical components and hazardous parts of aero-engines according to claim 5, characterized in that, Step S15 specifically includes the following steps: S151. Based on the temperature variation law, steady-state temperature, material parameters, and solid transient convection heat transfer boundary condition of critical component dangerous parts, establish a reduced-order model for temperature calculation under transient state and obtain the model parameters: ； in, Critical and dangerous parts at the current moment i Temperature at that location; For the critical and dangerous parts of the next moment i Temperature at that location; The steady-state temperature is the temperature of the critical component's critical location over an infinitely long period. For time increments, ρ and c p λ and λ represent the material's density, specific heat capacity, and thermal conductivity, respectively. A The model parameters are obtained by fitting the transient simulation results under arbitrary flight profiles.

7. A rapid temperature assessment device for critical components of an aero-engine, characterized in that, include: The reduced-order model building module is used to calculate the temperature, pressure, and rotational speed values ​​within the flow channel and the steady-state temperature of critical components in dangerous areas using a proportional conversion algorithm. It establishes a reduced-order temperature calculation model under transient conditions and obtains the model parameters. Specifically, it is used for: Based on the overall engine performance and internal flow calculations, the inlet and outlet cross-sectional temperatures of the critical component flow path and the qualitative temperature of the critical component's dangerous parts were obtained. and heat transfer coefficient h ; Based on the inlet and outlet cross-sectional temperature values ​​of the critical component flow path and the qualitative temperature of the wall surface of the critical component's hazardous area... and heat transfer coefficient h Calculate the ratio of qualitative temperature of the wall surface and the ratio of wall surface heat transfer coefficient of the critical parts of the component; The proportional conversion constant of the proportional conversion method is obtained based on the ratio of the wall surface qualitative temperature and the ratio of the wall surface heat transfer coefficient; The steady-state temperature of the critical component's dangerous parts is calculated using a proportional conversion method based on the temperature values ​​of the inlet and outlet sections of the flow path of the critical component and the proportional conversion constant. Based on the temperature change law of critical component dangerous parts under transient convective heat transfer boundary conditions, the steady-state temperature of critical component dangerous parts, and material parameters, a reduced-order model for temperature calculation under transient state is established and the model parameters are obtained. The transient temperature rapid calculation module is used to substitute the material parameters of key components of aero-engines, the temperature value, pressure value and speed value of the main channel corresponding to the life calculation point into the temperature calculation reduction model under the transition state to quickly calculate the transient temperature of the dangerous parts of key components of aero-engines. The material parameters include density, specific heat capacity and thermal conductivity.

8. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that, When the processor executes the computer program, it implements the steps of the rapid temperature assessment method for critical parts of aero-engine components as described in any one of claims 1 to 6.

9. A storage medium comprising a stored program that, when the program is executed, controls a device containing the storage medium to perform the steps of the rapid temperature assessment method for critical parts of an aero-engine as described in any one of claims 1 to 6.

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