Digital testing method and device for liquid rocket engine turbine

Abstract

The application provides a digital test method and device for a liquid rocket engine turbine, and relates to the technical field of turbine simulation, and comprises the following steps: obtaining multiple groups of design parameters of a turbine in a liquid rocket engine; for any group of design parameters, performing turbine aerodynamic design according to the design parameters to obtain geometric parameters of the turbine, and constructing a three-dimensional geometric model of the turbine based on the geometric parameters; sequentially performing flow simulation test, thermal analysis simulation test and finite element simulation analysis to obtain turbine efficiency and stress-strain response data of the turbine; calculating the life value of the turbine according to the stress-strain response data; performing reliability analysis on the turbine efficiency and the life value corresponding to each group of design parameters to obtain efficiency reliability analysis results and life reliability analysis results of the turbine. The application can automatically and intelligently complete the overall simulation process of the turbine.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of turbine simulation, in particular to a digital test method and device for a liquid rocket engine turbine. BACKGROUND

[0002] The design process of a liquid rocket engine turbine uses a large number of empirical formulas, and the initial design configuration needs to be tested to verify whether the efficiency, service life and reliability meet the requirements. Simulation test is an effective means to reduce the test cycle and cost of the turbine, but the current simulation test of the turbine needs to go through the steps of aerodynamic design, three-dimensional geometric modeling, flow simulation test, thermal analysis simulation test, finite element simulation analysis, service life estimation and reliability simulation test. If the simulation test result shows that the liquid rocket engine turbine does not meet the design requirements, the staff needs to repeat the above steps until a turbine that meets the requirements is obtained. If the improved design needs to adjust the turbine design parameters, the simulation region discretization, the parameters input into the simulation model and the corresponding spatial position of the parameters involved in the above steps all need to be manually intervened by the staff, which brings a huge workload.

[0003] At the same time, most of the existing turbine simulation models can only perform one or two of the flow simulation test, the thermal analysis simulation test, the finite element simulation analysis, the service life estimation and the reliability simulation test, and the simulation results obtained are not comprehensive. SUMMARY

[0004] The purpose of the embodiments of the present application is to provide a digital test method and device for a liquid rocket engine turbine, which can automatically and intelligently complete the overall simulation process of the turbine, and the simulation results are objective and reliable.

[0005] In a first aspect, a digital test method for a liquid rocket engine turbine is provided, which can include:

[0006] Obtaining a plurality of sets of design parameters of a turbine in a liquid rocket engine;

[0007] For any one set of design parameters, performing turbine aerodynamic design according to the design parameters to obtain geometric parameters of the turbine, and constructing a three-dimensional geometric model of the turbine based on the geometric parameters;

[0008] Performing flow simulation test based on the design parameters and the three-dimensional geometric model to obtain turbine efficiency and flow field parameters of the turbine;

[0009] Performing thermal analysis simulation test based on the flow field parameters and the three-dimensional geometric model to obtain temperature distribution data of the turbine varying with time;

[0010] performing finite element simulation analysis based on the flow field parameter, the temperature distribution data and the design parameter to obtain stress-strain response data of the turbine;

[0011] calculating a life value of the turbine according to the stress-strain response data;

[0012] performing reliability analysis on the turbine efficiency and the life value corresponding to each group of design parameters to obtain efficiency reliability analysis results and life reliability analysis results of the turbine.

[0013] In an optional implementation, the three-dimensional geometric model comprises: a solid domain of the turbine; and the solid domain of the turbine comprises a blade disc of the turbine and a plurality of blades arranged on the blade disc.

[0014] Before performing the flow simulation test based on the design parameter and the three-dimensional geometric model, the method further comprises:

[0015] determining an area between any two adjacent blades as a fluid domain of the turbine;

[0016] inputting the design parameter into a pre-constructed parameter coupling model to obtain fluid domain size parameters, fluid domain boundary conditions and solid domain size parameters corresponding to the design parameter; wherein the parameter coupling model is constructed based on a coupling relationship among the design parameter, the fluid domain size parameters, the fluid domain boundary conditions and the solid domain size parameters;

[0017] discretizing the fluid domain and the solid domain according to the fluid domain size parameters and the solid domain size parameters respectively to obtain a discretized fluid domain and a discretized solid domain.

[0018] In an optional implementation, the design parameter comprises: a material performance parameter of the turbine, inlet / outlet temperature and pressure conditions, a rotating speed and a gas parameter.

[0019] performing the flow simulation test based on the design parameter and the three-dimensional geometric model to obtain turbine efficiency and flow field parameters of the turbine, comprising:

[0020] determining a flow control equation and a turbulence model based on the design parameter;

[0021] constructing a flow simulation model based on the material performance parameter, the fluid domain boundary conditions, the discretized fluid domain, the discretized solid domain, the flow control equation and the turbulence model;

[0022] The turbine's inlet / outlet temperature and pressure conditions, rotational speed, and gas parameters are input into the flow simulation model to obtain the turbine's flow field parameters. The flow field parameters include: turbine surface pressure data over time, turbine surface temperature data over time and corresponding convective heat transfer coefficient, turbine outlet static temperature, inlet total temperature, outlet static pressure, and inlet total pressure.

[0023] The turbine efficiency is calculated based on the turbine's outlet static temperature, inlet total temperature, outlet static pressure, inlet total pressure, and the specific heat ratio of the gas.

[0024] In an optional implementation, a thermal analysis simulation experiment is performed based on the flow field parameters and the three-dimensional geometric model to obtain the turbine's temperature distribution data over time, including:

[0025] A thermal analysis model of the turbine is constructed based on the discretized solid domain;

[0026] The temperature data and convective heat transfer coefficient of the turbine surface over time are input into the thermal analysis model to obtain the temperature distribution data of the turbine solid domain over time.

[0027] In an optional implementation, finite element simulation analysis is performed based on the flow field parameters, the temperature distribution data, and the design parameters to obtain the turbine's stress-strain response data, including:

[0028] Obtain the solid domain finite element structural simulation model of the turbine;

[0029] The rotational speed, the pressure data of the turbine surface over time, and the temperature distribution data of the turbine solid domain over time are input into the finite element structural simulation model of the solid domain to obtain the stress-strain response data of the turbine solid domain.

[0030] In an optional implementation, the stress-strain response data of the turbine solid domain includes: strain data corresponding to different stress values ​​at various locations within the turbine solid domain;

[0031] Based on the stress-strain response data, the turbine's lifespan is calculated, including:

[0032] The damage value of the turbine per operation is calculated based on the maximum stress value in the turbine solid domain and the strain data at the location point corresponding to the maximum stress value.

[0033] The sum of the number of turbine operations when the accumulated damage value reaches a preset threshold is used as the turbine's lifespan value.

[0034] In an optional implementation, reliability analysis is performed on the turbine efficiency and lifespan values ​​corresponding to each set of design parameters to obtain the turbine's efficiency reliability analysis results and lifespan reliability analysis results, including:

[0035] Based on the turbine efficiency corresponding to each set of design parameters, a turbine efficiency set is constructed; according to the standard deviation and mean value of each turbine efficiency in the turbine efficiency set, the turbine efficiency reliability is calculated; the turbine efficiency reliability calculation result is determined as the reliability analysis result of the turbine efficiency;

[0036] Based on the turbine life corresponding to each set of design parameters, a turbine life set is constructed; according to the standard deviation and mean value of each turbine life in the turbine life set, the turbine life reliability is calculated; the turbine life reliability calculation result is determined as the reliability analysis result of the turbine life.

[0037] In a second aspect, a digital test device for a liquid rocket engine turbine is provided, which can include:

[0038] An acquisition unit is configured to acquire a plurality of sets of design parameters of a turbine in a liquid rocket engine;

[0039] A construction unit is configured to, for any set of design parameters, perform turbine aerodynamic design according to the design parameters to obtain geometric parameters of the turbine, and construct a three-dimensional geometric model of the turbine based on the geometric parameters;

[0040] A simulation unit is configured to perform flow simulation test based on the design parameters and the three-dimensional geometric model to obtain turbine efficiency and flow field parameters of the turbine; perform thermal analysis simulation test based on the flow field parameters and the three-dimensional geometric model to obtain temperature distribution data of the turbine over time; and perform finite element simulation analysis based on the flow field parameters, the temperature distribution data and the design parameters to obtain stress-strain response data of the turbine;

[0041] A calculation unit is configured to calculate a life value of the turbine according to the stress-strain response data;

[0042] An analysis unit is configured to perform reliability analysis on the turbine efficiency and life value corresponding to each set of design parameters to obtain efficiency reliability analysis result and life reliability analysis result of the turbine.

[0043] In a third aspect, an electronic device is provided, which includes a processor, a communication interface, a memory and a communication bus, wherein the processor, the communication interface and the memory complete communication with each other through the communication bus;

[0044] The memory is configured to store a computer program;

[0045] The processor is configured to execute the program stored on the memory to implement the method steps of any of the above first aspect.

[0046] In a fourth aspect, a computer readable storage medium is provided, and the computer readable storage medium stores a computer program. The computer program is executed by a processor to implement the method steps of any one of the first aspect.

[0047] The application firstly performs turbine aerodynamic design according to system parameters of a rocket engine; then a three-dimensional geometric model of the turbine is constructed, and a Boolean operation is performed on the geometric model to obtain a fluid domain; subsequently, the fluid domain and the solid domain are discretized; then a flow simulation test is performed on the fluid domain to obtain pressure and heat exchange conditions of a turbine surface; then a thermal simulation test is performed on the turbine to obtain temperature distribution of the turbine; then a finite element simulation analysis is performed on the turbine to obtain structural response of the turbine; subsequently, the efficiency and the life of the turbine are calculated based on the flow field information and the structural response of the turbine; finally, a reliability simulation test is performed on the turbine based on the above steps to evaluate the reliability of the designed turbine. The application realizes the whole process from the original design of the turbine to performance simulation test, life prediction and reliability simulation test.

[0048] The application realizes the whole process automation of the turbine of the liquid rocket engine from design parameter adjustment to digital test, greatly reduces the labor of the designer for obtaining the turbine meeting the design requirements; the application can complete flow simulation, thermal analysis simulation, structural response simulation, life prediction and reliability simulation, and obtain the life and the reliability of the turbine of the liquid rocket engine, and the simulation results comprehensively consider the aerodynamic performance, the life and the aerodynamic performance reliability and the life reliability under the influence of various uncertain factors (including geometric deviation, temperature and pressure change of the inlet gas, material performance change, etc.), and the simulation results are comprehensive, objective and reliable.

[0049] The application establishes a parameter coupling model, when the design parameters change, the geometric parameters and other parameters will change correspondingly, and the whole method will automatically complete the whole process of geometric modeling, solution domain discretization and simulation test according to the changed parameters, and directly output the efficiency, the life and the reliability of the turbine. The application can greatly reduce the manual adjustment process of the designer in the simulation process through the multi-parameter coupling combined with the automatic digital test method, especially the solution domain discretization link which occupies a large amount of simulation time, thereby significantly improving the efficiency of the simulation test. BRIEF DESCRIPTION OF DRAWINGS

[0050] In order to more clearly illustrate the technical solutions of the embodiments of the application, the following will briefly introduce the drawings needed to be used in the embodiments of the application. It should be understood that the following drawings only show some embodiments of the application, and therefore should not be regarded as a limitation on the scope. For those skilled in the art, other related drawings can also be obtained without creative labor on the basis of these drawings.

[0051] Figure 1A flow chart of a digital test method of a liquid rocket engine turbine provided by an embodiment of the present application;

[0052] Figure 2 A three-dimensional geometric model schematic diagram of a turbine provided by an embodiment of the present application;

[0053] Figure 3 A turbine solid domain and fluid domain schematic diagram provided by an embodiment of the present application;

[0054] Figure 4 A module schematic diagram of a digital test method provided by an embodiment of the present application;

[0055] Figure 5 A structural schematic diagram of a digital test device of a liquid rocket engine turbine provided by an embodiment of the present application;

[0056] Figure 6 A structural schematic diagram of an electronic device provided by an embodiment of the present application. DETAILED DESCRIPTION

[0057] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only some of the embodiments of the present application, but not all the embodiments. Based on the embodiments of the present application, all other embodiments obtained by those of ordinary skill in the art without creative work fall within the scope of the present application.

[0058] The digital test method of a liquid rocket engine turbine provided by the embodiments of the present application can be applied in a server or a terminal with strong computing capability. The server can be a physical server, a server cluster or a distributed system composed of multiple physical servers, or a cloud server providing basic cloud computing services such as cloud service, cloud database, cloud computing, cloud function, cloud storage, network service, cloud communication, middleware service, domain name service, security service, content delivery network (CDN), and big data and artificial intelligence platform. The terminal can be a user equipment (UE) such as a mobile phone, a smart phone, a notebook computer, a digital broadcast receiver, a personal digital assistant (PDA), a tablet computer (PAD), a handheld device, a vehicle-mounted device, a wearable device, a computing device, or other processing devices connected to a wireless modem, a mobile station (MS), a mobile terminal (Mobile Terminal), etc. The terminal and the server can be directly or indirectly connected through wired or wireless communication, which is not limited in the present application.

[0059] The preferred embodiments of the present application are described below in conjunction with the accompanying drawings. It should be understood that the preferred embodiments described herein are merely intended to illustrate and explain the present application, and are not intended to limit the present application, and the embodiments in the present application and the features in the embodiments can be combined with each other without conflict.

[0060] Figure 1 A flowchart of a digital test method of a liquid rocket engine turbine is provided in the embodiments of the present application. As shown in Figure 1 , the method can include:

[0061] In step S110, a plurality of sets of design parameters of the turbine in the liquid rocket engine are obtained; for any set of design parameters, turbine aerodynamic design is performed according to the design parameters to obtain geometric parameters of the turbine, and a three-dimensional geometric model of the turbine is constructed based on the geometric parameters.

[0062] In the embodiments of the present application, the liquid rocket engine is composed of components such as a tank, a pipeline, a valve, a pre-chamber, a turbine, a pump and a thrust chamber; the plurality of sets of design parameters of the turbine are obtained by random selection from a preset uncertainty factor variation range and a design parameter value range; and the design parameter value range is preset by a liquid rocket engine designer to ensure normal operation of the engine.

[0063] In actual application, the design parameters of the turbine should be a set of determined values, but due to fluctuations in the inlet gas parameters and tolerances in the processing size in the actual working process, the design parameters of the turbine will have uncertainty. The parameter with uncertainty is referred to as an uncertainty factor, and the variation range corresponding to the uncertainty factor is referred to as an uncertainty factor variation range.

[0064] In the embodiments of the present application, the design parameters include material performance parameters of the turbine, inlet / outlet temperature and pressure conditions, mass flow, pressure ratio, total temperature, rotating speed and gas parameters; wherein the rotating speed includes rotating speeds in each working stage of the turbine; and the gas parameters include specific heat ratio of the gas.

[0065] In the embodiments of the present application, the geometric parameters include volume, diameter, number and height of blades, flow angle, impeller width, front / rear edge radius and throat width of the turbine.

[0066] In actual application, turbine aerodynamic design can be realized by means of Ug modeling software platform.

[0067] In the embodiments of the present application, the three-dimensional geometric model of the turbine is constructed based on the geometric parameters, including:

[0068] The turbine profiling method based on the geometric parameters and configuration of the turbine constructs turbine hub / back curve to obtain a mathematical expression of a two-dimensional turbine cascade; the two-dimensional turbine cascade curve is generated based on the mathematical expression of the two-dimensional turbine cascade; and the two-dimensional turbine cascade curve is converted into a three-dimensional blade to obtain a three-dimensional geometric model of the turbine.

[0069] In the embodiments of the present application, the geometric parameters of the turbine do not constitute a two-dimensional blade profile, so it is necessary to construct a turbine hub / back curve and derive a mathematical expression of a two-dimensional turbine cascade based on the turbine hub / back curve; the turbine profiling method of the turbine hub / back curve can use any one or more of a Bezier curve method, a parabolic method and a B-spline curve; and the mathematical expression of the two-dimensional turbine cascade includes a front circular arc expression, a hub curve expression, a back curve expression and a tail circular arc expression.

[0070] In actual applications, the construction of the three-dimensional geometric model of the turbine can also be realized by means of the Ug modeling software platform; the mathematical expression of the two-dimensional turbine cascade is drawn into a two-dimensional cascade curve in the Ug software through a "regular curve defined spline" command; and the two-dimensional turbine cascade is stretched into a three-dimensional blade in the Ug software through a stretching operation to obtain a three-dimensional geometric model of the turbine, as shown in Figure 2 ; wherein the stretching height of the two-dimensional turbine cascade is determined by the geometric parameters.

[0071] As shown in Figure 3 , in actual applications, only a three-dimensional geometric model of a turbine disc and a plurality of blades arranged on the turbine disc is constructed; the three-dimensional geometric model is taken as a three-dimensional geometric model of the turbine; wherein the region where the plurality of blades and the turbine disc of the turbine are located is considered as a solid domain of the turbine; and the region between any two adjacent blades of the turbine is determined as a fluid domain of the turbine, which can be obtained by performing a Boolean operation on the three-dimensional geometric model of the turbine.

[0072] In step S120, a flow simulation test is performed based on the design parameters and the three-dimensional geometric model to obtain turbine efficiency and flow field parameters of the turbine; and a thermal analysis simulation test is performed based on the flow field parameters and the three-dimensional geometric model to obtain temperature distribution data of the turbine varying with time.

[0073] In the embodiments of the present application, in order to obtain the efficiency and the service life of the turbine, it is necessary to sequentially perform a flow simulation test, a thermal analysis simulation test and a structure finite element analysis on the turbine; specifically, before the flow simulation test is performed, it is also necessary to:

[0074] The design parameters are input into a pre-constructed parameter coupling model to obtain fluid domain size parameters, fluid domain boundary conditions and solid domain size parameters corresponding to the design parameters; and the fluid domain and the solid domain are discretized according to the fluid domain size parameters and the solid domain size parameters respectively to obtain a discretized fluid domain and a discretized solid domain.

[0075] In the embodiments of the present application, the parameter coupling model is constructed based on the coupling relationship of the design parameters, the fluid domain size parameters, the fluid domain boundary conditions and the solid domain size parameters.

[0076] In the embodiments of the present application, the parameter coupling model can be a calculation formula between the design parameters, the fluid domain size parameters, the fluid domain boundary conditions and the solid domain size parameters; or a regression analysis model or a prediction model based on neural network, etc. trained by using multiple sets of design parameters and the fluid domain size parameters, the fluid domain boundary conditions and the solid domain size parameters corresponding to each set of design parameters; or a quantitative relationship model obtained by performing finite element analysis (FEA), computational fluid dynamics (CFD) or other types of simulation by using computer aided engineering (CAE) software.

[0077] In the embodiments of the present application, the digital test method of the liquid rocket engine turbine is regarded as a complete process, and the coupling relationship of the required parameters in each node in the process is determined in advance, so that when the design parameters change, all subsequent input parameters change according to the change amount of the design parameters, thereby changing each node in the digital test process of the turbine, and realizing intelligent and automatic repeated digital test of the turbine.

[0078] In the embodiments of the present application, the fluid domain boundary conditions include: the coordinate range of the inlet / outlet boundary of the fluid domain, the coordinate range of the symmetry surface, the coordinate range of the wall surface, the coordinate range of the interface through which the fluid domain transmits flow field information to the solid domain, and the flow field information at the position corresponding to any coordinate in the above coordinate ranges.

[0079] In one of the embodiments of the present application, the parameter coupling model composed of the calculation formula or the quantitative relationship model determines the coordinate range of the inlet / outlet boundary of the fluid domain, which can include:

[0080] ;

[0081] ;

[0082] ;

[0083] wherein, and represent the coordinates of the left and right boundaries of the fluid domain; and represent the z coordinates of the left and right boundaries of the fluid domain, respectively; and These represent the x-coordinates of the front and rear boundaries of the fluid domain, respectively. Represents the polynomial coefficients, which can be obtained from design parameters through aerodynamic design and blade cascade shaping methods; This indicates the height of the blade, and its range is:

[0084] ;

[0085] in, The x-coordinate representing the connection point between the forward arc and the blade base / blade back curve can be obtained from design parameters through aerodynamic design and blade cascade shaping methods; The x-coordinate representing the connection point between the rear arc and the blade base / blade back curve can be obtained from design parameters through aerodynamic design and blade cascade shaping methods; and These represent the left and right rotation angles of the fluid domain from the blade-pot curve, respectively. , These represent the average diameter and blade height of the turbine, respectively. This indicates the forward stretching height of the intersection line between the front arc and the leaf base / leaf back curve; This indicates the height of the backward stretch along the intersection of the rear arc and the blade base / blade back curve.

[0086] Based on the parameter coupling model described in this application, the corresponding coordinates in the boundary conditions of the fluid domain, the coordinate range formed by the above coordinates, and the size parameters of the fluid domain can be obtained. On this basis, a three-dimensional geometric model of the turbine can be constructed using a three-dimensional modeling tool based on the above data. At the same time, once the three-dimensional geometric model is constructed, the subsequent discretization and simulation test steps can be automatically executed.

[0087] In this embodiment, when the design parameters change, the geometric parameters obtained from the aerodynamic design based on the design parameters will inevitably change, which will also change the three-dimensional geometric model of the turbine constructed based on the geometric parameters. When the three-dimensional geometric model changes, the coordinate range of the corresponding region will inevitably change. This application automatically adjusts the coordinate range in the corresponding boundary conditions according to the design parameters based on the parameter coupling model, so that the coordinate range of the target region required for the simulation test also changes accordingly. The overall method does not require manual input of the coordinate range of the target region or the specified region, so that the method of this application can realize the digital test process of the turbine in an automated and intelligent manner.

[0088] In this embodiment of the application, the flow field parameters include: pressure data of turbine surface changing over time, temperature data of turbine surface changing over time and corresponding convective heat transfer coefficient, turbine outlet static temperature, inlet total temperature, outlet static pressure and inlet total pressure.

[0089] In the embodiment of the present application, the actual temperature data of the turbine changing over time obtained through the flow simulation test is not all used in the thermal analysis simulation test, but only the temperature data of the turbine surface changing over time, that is, the interactive interface of the fluid domain and the solid domain of the turbine (also referred to as the fluid-structure coupling interface) is needed; therefore, after obtaining the temperature data of the turbine changing over time, the discrete units belonging to the fluid-structure coupling interface are screened from the position coordinates of each discrete unit according to the position coordinate range of the interactive interface of the fluid domain and the solid domain pre-acquired, to obtain target discrete units; the temperature data of each target discrete unit changing over time and the corresponding convective heat transfer coefficient are taken as the temperature distribution data of the turbine surface changing over time, and are used in the thermal analysis model for the thermal analysis simulation test.

[0090] In the embodiment of the present application, the flow simulation test is performed based on the design parameters and the three-dimensional geometric model, to obtain the turbine efficiency and the flow field parameters of the turbine, including:

[0091] Based on the design parameters, the flow control equation and the turbulence model are determined; based on the material performance parameters, the boundary conditions of the fluid domain, the discretized fluid domain, the discretized solid domain, the flow control equation and the turbulence model, the flow simulation model is constructed; the inlet / outlet temperature and pressure conditions, the rotating speed and the gas parameters of the turbine are input into the flow simulation model, to obtain the flow field parameters of the turbine; based on the outlet static temperature, the inlet total temperature, the outlet static pressure, the inlet total pressure and the specific heat ratio of the gas, the efficiency of the turbine is calculated.

[0092] In the embodiment of the present application, the fluid domain is discretized to obtain a fluid domain containing a plurality of discrete units, and each discrete unit corresponds to a position coordinate; and the corresponding temperature distribution data is the temperature value corresponding to each discrete unit.

[0093] In the embodiment of the present application, the efficiency calculation formula of the turbine is as follows:

[0094] ;

[0095] wherein, Tt represents the outlet static temperature of the turbine, Tin represents the inlet total temperature of the turbine; Pout represents the outlet static pressure of the turbine; Pin represents the inlet total pressure; Cp represents the specific heat ratio of the gas.

[0096] In the embodiment of the present application, the thermal analysis simulation test is performed based on the flow field parameters and the three-dimensional geometric model, to obtain the temperature distribution data of the turbine changing over time, including:

[0097] Based on the discrete solid domain, a thermal analysis model of the turbine is constructed; the time-varying temperature data of the turbine surface and the convective heat transfer coefficient are input into the thermal analysis model to obtain time-varying temperature distribution data of the turbine solid domain.

[0098] In the embodiments of the present application, the working process of the turbine includes four working stages of starting, stabilizing, shutting down and cooling, and the time-varying temperature data of the turbine surface and the corresponding convective heat transfer coefficient in the flow field parameters are only the heat exchange conditions of the turbine in the stable working stage; for the starting stage, the turbine is in a low-temperature environment, and the boundary condition of the thermal analysis can be set according to the type of the propellant; for the stable working stage, the boundary condition of the thermal analysis is derived from the convective heat transfer coefficient obtained by the flow simulation; for the shutdown and cooling stages, the boundary condition of the thermal analysis is the same as that of the starting stage; the thermal analysis simulation test of the turbine is performed based on the heat exchange conditions of the four working stages of the turbine and the thermal analysis model of the turbine to obtain the time-varying temperature distribution data of the turbine solid domain.

[0099] In the embodiments of the present application, the stress-strain response data of the turbine is obtained by performing the finite element simulation analysis on the flow field parameters, the temperature distribution data and the design parameters.

[0100] In the embodiments of the present application, the stress-strain response data of the turbine is obtained by performing the finite element simulation analysis on the flow field parameters, the temperature distribution data and the design parameters.

[0101] The finite element structure simulation model of the turbine solid domain is obtained; the rotating speed, the time-varying pressure data of the turbine surface and the time-varying temperature distribution data of the turbine solid domain are input into the finite element structure simulation model of the turbine solid domain to obtain the stress-strain response data of the turbine solid domain.

[0102] In the embodiments of the present application, the finite element structure simulation model of the turbine solid domain is constructed in advance, the rotating speed, the time-varying pressure data of the turbine surface and the time-varying temperature distribution data of the turbine solid domain are taken as the boundary conditions of the finite element structure simulation model of the turbine solid domain, the stress-strain response data of the turbine solid domain is obtained through the structure finite element simulation analysis; wherein the stress-strain response data includes the stress data and the corresponding strain data of each position point in the turbine solid domain.

[0103] In the embodiments of the present application, in the structure finite element simulation analysis, since the rotating speeds of the turbine in each working stage are different, the structure finite element simulation analysis is performed in stages for each working stage, so that the time-varying stress-strain response data of the turbine solid domain is obtained.

[0104] In the embodiments of the present application, the life value of the turbine is calculated according to the stress-strain response data, including:

[0105] According to the maximum stress value in the turbine solid domain and strain data corresponding to the maximum stress value, a damage value of the turbine per working time is calculated; and when the damage value is accumulated to a preset threshold value, the sum of the working times of the turbine is taken as a life value of the turbine.

[0106] In the embodiment of the present application, the preset threshold value can be 1; when the damage value of the turbine is accumulated to 1, the turbine is considered to be invalid, and the sum of the working times (i.e. the number of start-stop times) of the turbine at this time is considered to be the life of the turbine.

[0107] In the embodiment of the present application, the life value calculation formula of the turbine is as follows:

[0108] ;

[0109] wherein N represents the life value of the turbine; the damage value of the turbine per working time is the sum of the low-cycle fatigue damage and the ratcheting damage, representing the low-cycle fatigue damage; representing the ratcheting damage; representing the low-cycle fatigue life; representing the ratcheting life;

[0110] The formula of the low-cycle fatigue life is as follows:

[0111] ;

[0112] wherein, representing the total strain range of the position point corresponding to the maximum stress value; ,b, and c respectively represent the fatigue strength coefficient, the fatigue strength index, the fatigue plasticity coefficient and the fatigue plasticity index of the turbine material; E represents the elastic modulus of the turbine material;

[0113] The parameterized expression of the ratcheting life is as follows:

[0114] ;

[0115] wherein, representing the residual plastic strain, representing the limit strain.

[0116] In step S140, the reliability analysis is performed on the turbine efficiency and the life value corresponding to each group of design parameters to obtain the efficiency reliability analysis result and the life reliability analysis result of the turbine.

[0117] In the embodiment of the present application, the reliability analysis is performed on the turbine efficiency and the life value corresponding to each group of design parameters to obtain the efficiency reliability analysis result and the life reliability analysis result of the turbine, including:

[0118] Based on the turbine efficiency corresponding to each group of design parameters, a turbine efficiency set is constructed; according to the standard deviation and mean value of each turbine efficiency in the turbine efficiency set, the turbine efficiency reliability is calculated; the turbine efficiency reliability calculation result is determined as the reliability analysis result of the turbine efficiency; based on the life corresponding to each group of design parameters, a turbine life set is constructed; according to the standard deviation and mean value of each turbine life in the turbine life set, the turbine life reliability is calculated; the turbine life reliability calculation result is determined as the reliability analysis result of the turbine life.

[0119] In the embodiment of the present application, the turbine efficiency set and the turbine life set satisfy the normal distribution, therefore the standard deviation and mean value of the turbine efficiency set and the turbine life set are calculated by using the statistical method, and the reliability is calculated; the reliability calculation formula is as follows:

[0120] ;

[0121] Among them, represents the turbine efficiency reliability or the turbine life reliability; represents the turbine efficiency set or the standard deviation of the turbine efficiency set, t represents the turbine life or the turbine efficiency, represents the mean value of the turbine efficiency set or the normal distribution of the turbine efficiency set.

[0122] In the embodiment of the present application, the application conditions of the target application scene of the turbine are obtained in advance, if the turbine efficiency and life value corresponding to any group of design parameters satisfy the application conditions of the target application scene, the group of design parameters is determined as the target design parameter; if the turbine efficiency and life value corresponding to each group of design parameters do not satisfy the application conditions of the target application scene, a plurality of new design parameters are obtained by revaluating in the uncertainty factor change range and the design parameter value range, and the turbine digital test is reperformed until the turbine design parameters whose turbine efficiency and life value satisfy the application conditions are obtained.

[0123] In the embodiment of the present application, the digital test method of the liquid rocket engine turbine can be realized by means of Ug software and ANSYS software, and the specific steps are as follows:

[0124] Firstly, aerodynamic design is performed: the liquid rocket engine system is composed of components such as tank, pipeline, valve, pre-chamber, turbine, pump and thrust chamber, and the system level design parameters are proposed by the designer to ensure the normal operation of the engine. The design parameters of the turbine include mass flow, pressure ratio, total temperature, rotating speed and gas property parameters. According to the given design parameters of the system, the turbine aerodynamic design is carried out by referring to the Liquid Rocket Engine Design, and the geometric parameters such as flow angle, impeller width, leading / trailing edge radius and throat width are obtained.

[0125] The application integrates the aerodynamic design of the turbine in the Ug modeling software platform, and the design language is Ug parametric expression. Taking the calculation of isentropic adiabatic work Lad as an example, the parametric expression in Ug is as follows:

[0126] ;

[0127] wherein k is the specific heat ratio of the gas flowing through the turbine, R is the gas constant, tk is the total temperature of the turbine inlet, representing the pressure ratio, and these parameters are known parameters before the design.

[0128] In order to pass the turbine design parameters and geometric parameters in the Ug software to the DesignModeler module of the ANSYS software, so as to change the turbine design parameters and geometric parameters directly on the ANSYS software platform in the subsequent improved design. Taking the turbine speed n, diameter D and blade height hs as examples, the naming method of the Ug parametric modeling language transmission parameter is as follows:

[0129] ;

[0130] ;

[0131] ;

[0132] The above naming method realizes the transmission of the geometric parameters of the Ug software to the Design Modeler module of the ANSYS software;

[0133] Secondly, three-dimensional modeling is carried out: although the turbine geometric parameters are obtained, the geometric parameters have not yet formed a two-dimensional blade profile. The commonly used turbine blade / blade back curve construction methods include Bezier curve method, parabolic method and B-spline curve method. The mathematical expressions of the turbine two-dimensional blade are derived through the above methods. The expressions of the blade include front circular arc expression, blade basin curve expression, blade back curve expression and tail circular arc expression. The above expressions are drawn into the curve of the two-dimensional blade in the Ug software through the "regular curve definition spline" command. On the basis of obtaining the two-dimensional blade curve, the two-dimensional blade is stretched into a three-dimensional blade in the Ug software through stretching operation, and the stretching height is determined by the aerodynamic design of step 110.

[0134] Further, the solid domain and the fluid domain are discretized:

[0135] The design parameters and basic geometric parameters of the turbine are transmitted to the Design Modeler module of the ANSYS software platform, and the above parameters are set as Parameter in the Design Modeler module. The above set Parameter is displayed and edited in the Parameter Set module of the ANSYS software platform.

[0136] The three-dimensional model of the turbine is transmitted to the Design Modeler module of the ANSYS software platform, and the fluid domain of the turbine is obtained in the module by means of Boolean operation. The Name Selection option is used to name the inlet / outlet boundary, the symmetric surface, the wall surface of the fluid domain, and the interface for transmitting the flow field information from the fluid domain to the solid domain, so that the ANSYS software can automatically identify the simulation setting area with the change of the turbine design.

[0137] Subsequently, the fluid domain and the solid domain are transmitted to the Meshing module of the ANSYS software platform, and the size parameters of the solid domain and the fluid domain are set respectively, and the solid domain and the fluid domain are discretized in the Meshing module: the solid domain and the fluid domain are discretized into a large number of sub-regions, and appropriate sub-region size can reduce the simulation test time while ensuring the accuracy of the simulation test, and the sub-region size is determined by the size of the solid domain and the fluid domain; as follows:

[0138] ;

[0139] wherein, represents the turbine volume transmitted by the Ug software to the ANSYS software module.

[0140] Then, the flow-thermal-solid multi-physical field simulation analysis: taking the obtained discretized fluid domain as the object of flow simulation test, and taking the design parameters including the inlet / outlet temperature and pressure conditions of the turbine, the rotating speed and the gas parameters as the input parameters of the flow simulation test. Based on the CFX module of the ANSYS software platform, the flow simulation model of the turbine is constructed through the flow control equation and the turbulence model, and the corresponding parameters are defined in the CFX module as follows:

[0141] ;

[0142] ;

[0143] ;

[0144] wherein, , , respectively represent the design parameters transmitted by the Ug software to the ANSYS software module;

[0145] The temperature and pressure conditions are input at the specified interface inlet and outlet of the fluid domain, and the gas parameters are input at the specified region fluid domain; the temperature data and the convective heat transfer coefficient of the interface blade_fluid of the fluid domain at the specified interface of the fluid domain which changes with time are input into the interface blade_solid of the solid domain at the specified interface of the solid domain which is in contact with the fluid domain.

[0146] The flow simulation test is carried out to obtain the gas pressure and the convection heat transfer condition of the turbine blade surface. The turbine efficiency is calculated by the following formula:

[0147]

[0148] wherein, is the turbine outlet static temperature, is the turbine inlet total temperature, is the turbine outlet static pressure, is the inlet total pressure, is the specific heat ratio of the gas.

[0149] The turbine efficiency formula is edited as an expression in the CFX module and is set as an output parameter. The output parameter will be displayed in the Parameter Set module of the ANSYS software platform.

[0150] The discrete solid domain is taken as the simulation object of the present step, and the thermal analysis model of the turbine is established based on the Thermal module of the ANSYS software. The working process of the turbine includes four working stages of starting-up, steady, shutdown and cooling. The above flow simulation only obtains the heat transfer condition of the steady working stage. For the starting-up stage, the thermal analysis boundary condition can be set according to the type of propellant; for the steady working stage, the thermal analysis boundary condition is derived from the convection heat transfer coefficient obtained by the flow simulation; for the shutdown and cooling stages, the thermal analysis boundary condition is the same as that of the starting-up stage. The thermal analysis test is carried out to obtain the temperature distribution of the turbine solid domain.

[0151] The finite element structure simulation model of the turbine solid domain is established based on the Structural module of the ANSYS software. The boundary condition of the finite element structure simulation model is derived from the temperature distribution of the solid domain, the gas pressure distribution of the flow simulation and the rotating speed. The stress-strain response of the turbine solid region is obtained by simulation analysis. The pressure data of the interface blade_fluid in the fluid domain which changes with time is input into the interface blade_solid in the solid domain which is specified by the boundary condition. The temperature distribution data of the solid domain solid which is specified in the thermal analysis is input into the solid domain solid which is specified in the finite element structure simulation.

[0152] ​Since the working process of turbine is divided into four working stages of start-stable-shut down-cooling, the rotating speed of turbine is different in each stage. In order to set the rotating speed changing with time in the Structural module, the relationship between rotating speed and time is input in the form of table by using the APDL language of ANSYS, and the rotating speed is set as Parameter. The above Parameter can be displayed and edited in the Parameter Set module of ANSYS software. The rotating speed comes from the design parameter, and the parameterized expression is as follows:

[0153] ;

[0154] In the flow-heat-solid coupling simulation of turbine, the rotating speed of flow simulation needs to be consistent with the structure field. In the Parameter Set module, the rotating speed of structure field is bound with that of flow field according to the simulation sequence, so that the synchronous change of rotating speed can be realized.

[0155] Then, the life prediction is carried out: according to the stress-strain response of turbine solid domain, the stress-strain data of the maximum stress position is extracted by compiling APDL language. The low cycle fatigue damage and ratchet damage calculation formula of liquid rocket engine turbine is compiled by APDL language, the above extracted stress-strain data is substituted into the above compiled damage calculation formula, and the damage value of turbine working once is obtained. When the damage value accumulates to 1, it is considered that the turbine fails. At this time, the start-shut down times are the life of turbine. The life value is set as Parameter. The above Parameter can be displayed in the Parameter Set module.

[0156] Then, the reliability simulation test is carried out:

[0157] In the actual working process of turbine, the inlet gas parameter fluctuates, and the processing size has tolerance. The above parameters are called uncertainty factors. In the change range of uncertainty factors, the life reliability and efficiency reliability of turbine under uncertainty factors are obtained by using the Six Sigma Analysis module of ANSYS software, constantly calling Ug software and ANSYS software modules. The above life reliability and efficiency reliability are set as Parameter. The above Parameter can be displayed in the Parameter Set module.

[0158] Finally, turbine design improvement: the turbine design, simulation test, life estimation, reliability simulation test related parameters are integrated in Parameter Set module, as shown in Figure 4, the turbine geometry parameters can be adjusted in the module, and ANSYS software will call Ug software to complete the geometric modeling, then ANSYS software outputs the life reliability and efficiency reliability, if the turbine design does not meet the requirements, the turbine geometry parameters can be adjusted in Parameter Set module until the turbine meeting the design requirements is obtained.

[0159] In the above embodiment of the application, the method further comprises: constructing parameter coupling of the fluid domain:

[0160] Taking the stationary blade fluid domain as an example, an initial flow domain covering the blade is created in the ANSYS software module, a circular ring completely enveloping the blade is defined in the reference surface, the inner diameter D 2 of the circular ring is defined as: D

[0161] ;

[0162] ;

[0163] wherein, , respectively represent the turbine average diameter and the blade height passed by Ug software to the ANSYS software module;

[0164] The whole blade disc is cut to separate the blade entity, and the left and right boundaries of the flow field are taken as the blade basin surface; wherein the rotation angles and of the surface to the left and right depend on the number of blades, and are respectively:

[0165] ;

[0166] ;

[0167] wherein, represents the number of turbine blades passed by Ug software to the ANSYS software module. and respectively represent the rotation angles and ;

[0168] The front and rear boundaries of the front and rear boundary surfaces obtained by stretching rotation are stretched, the front boundary stretching length L 1 is 4 times of the blade width to ensure the stability of the inlet flow, and the rear boundary stretching length L 2 is half of the axial spacing between the moving blade and the stationary blade, and the corresponding expression is:

[0169] ​ ;

[0170] ;

[0171] wherein, , represent turbine blade width and turbine blade and turbine vane axial distance respectively passed to ANSYS software module by Ug software. and represent the length of the stretch respectively.

[0172] The boundary obtained by stretching is subjected to a Boolean operation with the initial flow domain to obtain the turbine vane flow domain. Similar operations are performed on the turbine blade to obtain the turbine blade and turbine vane flow domain. The solid domain of the turbine disk is subjected to a symmetrical cutting to reduce the calculation domain, and the obtained solid domain is shown in FIG. 4. Figure 3 .

[0173] The fluid domain and the solid domain established above are the research objects of the subsequent simulation test. The input parameters are input into the specified area of the simulation model to carry out the simulation test, and the turbine parameters concerned by the designers are obtained. When the size of the fluid domain and the solid domain changes, the spatial coordinates of the specified area of the input parameters change accordingly. In order to avoid the designers from manually adjusting the specified area of the input parameters of the simulation model due to the change of the size of the fluid domain and the solid domain during the simulation test, the spatial coordinates of the specified area are integrated into the parameter coupling model.

[0174] In the embodiment of the present application, a rectangular coordinate system is established with the center of the turbine disk as the origin o, the axial direction of the turbine disk as the x axis, the blade height direction as the z axis, and the direction perpendicular to the xoz plane as the y axis. The turbine cascade is composed of two front and rear circular arcs and a middle blade platform / back curve. The coordinates of the front circular arc are as follows:

[0175] ;

[0176] wherein, represents the center of the front circular arc; represents the radius of the front circular arc; represents the height of the blade, and its range is the above ; represents the x coordinate of the connecting point of the front circular arc and the blade platform / back curve. The center of the front circular arc and the x coordinate of the connecting point of the front circular arc and the blade platform / back curve can be obtained by the aerodynamic design and cascade modeling method through the design parameters.

[0177] The coordinates of the rear circular arc are as follows:

[0178] ;

[0179] wherein, represents the center of the rear circular arc; represents the radius of the trailing circle arc; represents the height of the blade, and its range is from 0 to 1 ; represents the x coordinate of the connecting point of the trailing circle arc and the blade suction / pressure surface curve. The center of the trailing circle arc and the x coordinate of the connecting point of the trailing circle arc and the blade suction / pressure surface curve can be obtained by aerodynamic design and cascade modeling method through design parameters.

[0180] The blade suction surface curve is expressed as a polynomial as follows:

[0181] ;

[0182] wherein, represents the coefficient of the polynomial, and the coefficient of the polynomial can be obtained by aerodynamic design and cascade modeling method through design parameters.

[0183] The blade suction surface curve is expressed as a polynomial as follows:

[0184] ;

[0185] wherein, represents the coefficient of the polynomial, and the coefficient of the polynomial can be obtained by aerodynamic design and cascade modeling method through design parameters.

[0186] The left and right boundaries of the fluid domain are obtained by rotating the blade suction surface curve to the left and right by an angle of and , respectively, so that the coordinates of the left and right boundaries of the fluid domain are:

[0187] ;

[0188] The front boundary of the fluid domain is obtained by stretching the intersection line of the front circle arc and the blade suction / pressure surface curve forward by L1, and the rear boundary of the fluid domain is obtained by stretching the intersection line of the rear circle arc and the blade suction / pressure surface curve backward by L2, so that the x coordinates of the front and rear boundaries of the fluid domain are:

[0189] ;

[0190] The upper and lower boundaries of the fluid domain are controlled by the bottom and top coordinates of the blade, so that the z coordinates of the upper and lower boundaries of the fluid domain are:

[0191] ;

[0192] According to the coordinates of each boundary, a coordinate set of each region involved in the simulation test process can be established, and the coordinate set is named as the designated region shown in Table 1, including a fluid domain inlet, a fluid domain outlet, a fluid domain, a solid domain, and the like.

[0193] Table 1: Designated region naming explanation table

[0194]

[0195] Corresponding to the method, the embodiment of the application further provides a digital test device of a liquid rocket engine turbine, as shown in Figure 5 The digital test device of the liquid rocket engine turbine comprises:

[0196] The acquisition unit 510 is configured to acquire a plurality of groups of design parameters of the turbine in the liquid rocket engine.

[0197] The construction unit 520 is configured to, for any one group of design parameters, perform turbine aerodynamic design according to the design parameters to obtain geometric parameters of the turbine, and construct a three-dimensional geometric model of the turbine based on the geometric parameters.

[0198] The simulation unit 530 is configured to perform flow simulation test based on the design parameters and the three-dimensional geometric model to obtain turbine efficiency and flow field parameters of the turbine, perform thermal analysis simulation test based on the flow field parameters and the three-dimensional geometric model to obtain temperature distribution data of the turbine varying with time, and perform finite element simulation analysis based on the flow field parameters, the temperature distribution data, and the design parameters to obtain stress-strain response data of a solid domain of the turbine.

[0199] The calculation unit 540 is configured to calculate a life value of the turbine according to the stress-strain response data.

[0200] The analysis unit 550 is configured to perform reliability analysis on the turbine efficiency and the life value corresponding to each group of design parameters to obtain efficiency reliability analysis results and life reliability analysis results of the turbine.

[0201] The functions of each functional unit of the digital test device of the liquid rocket engine turbine provided in the above embodiments of the application can be realized through the above method steps, and therefore, the specific working process and beneficial effects of each unit in the digital test device of the liquid rocket engine turbine provided in the embodiments of the application will not be repeated here.

[0202] The embodiment of the application further provides an electronic device, as shown in Figure 6 The electronic device comprises a processor 610, a communication interface 620, a memory 630, and a communication bus 640, wherein the processor 610, the communication interface 620, and the memory 630 complete mutual communication through the communication bus 640.

[0203] a memory 630, configured to store a computer program;

[0204] the processor 610 is configured to implement the following steps when executing the program stored in the memory 630:

[0205] obtain a plurality of groups of design parameters of a turbine in a liquid rocket engine;

[0206] for any one group of design parameters, perform turbine aerodynamic design according to the design parameters to obtain geometric parameters of the turbine, and construct a three-dimensional geometric model of the turbine based on the geometric parameters;

[0207] perform flow simulation test based on the design parameters and the three-dimensional geometric model to obtain turbine efficiency and flow field parameters of the turbine;

[0208] perform thermal analysis simulation test based on the flow field parameters and the three-dimensional geometric model to obtain temperature distribution data of the turbine varying with time;

[0209] perform finite element simulation analysis based on the flow field parameters, the temperature distribution data and the design parameters to obtain stress-strain response data of a solid domain of the turbine;

[0210] calculate a life value of the turbine according to the stress-strain response data;

[0211] perform reliability analysis on the turbine efficiency and the life value corresponding to each group of design parameters to obtain efficiency reliability analysis result and life reliability analysis result of the turbine.

[0212] The communication bus mentioned above can be a Peripheral Component Interconnect (PCI) bus or an Extended Industry Standard Architecture (EISA) bus, etc. The communication bus can be divided into an address bus, a data bus, a control bus, etc. For ease of representation, only one thick line is used in the figure, but it does not mean that there is only one bus or only one type of bus.

[0213] The communication interface is configured to perform communication between the electronic device and other devices.

[0214] The memory can include a Random Access Memory (RAM) and can also include a Non-Volatile Memory (NVM), e.g., at least one disk memory. Optionally, the memory can also be at least one storage device located away from the aforementioned processor.

[0215] The processor described above can be a general processor, including a central processing unit (CPU), a network processor (NP), etc.; can also be a digital signal processor (DSP), an application specific integrated circuit (ASIC), a field-programmable gate array (FPGA) or other programmable logic device, a discrete gate or transistor logic device, a discrete hardware component.

[0216] The implementation manners and beneficial effects of the electronic device in the above embodiments can be achieved by referring to the steps in the above embodiments, and thus, the specific working process and beneficial effects of the electronic device provided by the embodiments of the present application are not repeated here. Figure 1 The implementation manners and beneficial effects of the electronic device in the above embodiments can be achieved by referring to the steps in the above embodiments, and thus, the specific working process and beneficial effects of the electronic device provided by the embodiments of the present application are not repeated here.

[0217] In another embodiment provided by the present application, a computer readable storage medium is provided, and the computer readable storage medium stores instructions, when the instructions are run on a computer, the computer executes the digital test method of the liquid rocket engine turbine in any one of the above embodiments.

[0218] In another embodiment provided by the present application, a computer program product containing instructions is provided, when the instructions are run on a computer, the computer executes the digital test method of the liquid rocket engine turbine in any one of the above embodiments.

[0219] Those skilled in the art should understand that the embodiments in the embodiments of the present application can be provided as a method, a system or a computer program product. Therefore, the embodiments in the present application can be in the form of a complete hardware embodiment, a complete software embodiment or an embodiment combining software and hardware aspects. Moreover, the embodiments in the present application can be in 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 codes.

[0220] The computer program instructions can also be loaded onto a computer or other programmable data processing apparatus to cause a series of operational steps to be performed on the computer or other programmable apparatus to produce a computer-implemented process such that the instructions which execute on the computer or other programmable apparatus provide steps for implementing the functions specified in the flowchart block or blocks. Figure 1 one or more flowcharts and / or blocks Figure 1 means for functionally implementing the steps listed in the flowchart block or blocks.

[0221] These computer program instructions can also be stored in a computer-readable memory that can direct a computer or other programmable data processing apparatus to function in a particular manner, such that the instructions stored in the computer-readable memory produce an article of manufacture including instructions which implement the function specified in the flowchart block or blocks. Figure 1 one or more flowcharts and / or blocks Figure 1 means for functionally implementing the steps listed in the flowchart block or blocks.

[0222] The computer program instructions can also be loaded onto a computer or other programmable data processing apparatus to cause a series of operational steps to be performed on the computer or other programmable apparatus to produce a computer-implemented process such that the instructions which execute on the computer or other programmable apparatus provide steps for implementing the functions specified in the flowchart block or blocks. Figure 1 one or more flowcharts and / or blocks ​ means for functionally implementing the steps listed in the flowchart block or blocks.

[0223] While preferred embodiments of the application have been described, modifications and variations can be apparent to those skilled in the art once aware of the general underlying concepts. Therefore, it is intended that the scope of the appended claims should include all such modifications and variations.

[0224] It will be apparent to those skilled in the art that various modifications and variations can be made to the embodiments of the present application without departing from the spirit or scope of the application. Thus, it is intended that the present application cover the modifications and variations of this application provided they come within the scope of the appended claims and their equivalents.

Claims

1. A method of digitally testing a liquid rocket engine turbine, characterized in that, The method comprises: acquiring a plurality of sets of design parameters of a turbine in a liquid rocket engine; the design parameters comprising: material performance parameters of the turbine, inlet / outlet temperature and pressure conditions, rotating speed and gas parameters; for any one set of design parameters, performing turbine aerodynamic design according to the design parameters to obtain geometric parameters of the turbine, and constructing a three-dimensional geometric model of the turbine based on the geometric parameters; the three-dimensional geometric model comprising: a solid domain of the turbine; the solid domain of the turbine comprising a turbine disc and a plurality of blades arranged on the turbine disc; determining an area between any two adjacent blades as a fluid domain of the turbine; inputting the design parameters into a pre-constructed parameter coupling model to obtain fluid domain size parameters, fluid domain boundary conditions and solid domain size parameters corresponding to the design parameters; wherein the parameter coupling model is constructed based on a coupling relationship among the design parameters, the fluid domain size parameters, the fluid domain boundary conditions and the solid domain size parameters; discretizing the fluid domain and the solid domain according to the fluid domain size parameters and the solid domain size parameters respectively to obtain a discretized fluid domain and a discretized solid domain; determining a flow control equation and a turbulence model based on the design parameters; constructing a flow simulation model based on the material performance parameters, the fluid domain boundary conditions, the discretized fluid domain, the discretized solid domain, the flow control equation and the turbulence model; inputting the inlet / outlet temperature and pressure conditions of the turbine, the rotating speed and the gas parameters into the flow simulation model to obtain flow field parameters of the turbine; wherein the flow field parameters comprise: pressure data of the turbine surface changing over time, temperature data of the turbine surface changing over time and corresponding convective heat transfer coefficients, outlet static temperature of the turbine, inlet total temperature, outlet static pressure and inlet total pressure; calculating the efficiency of the turbine based on the outlet static temperature, the inlet total temperature, the outlet static pressure, the inlet total pressure of the turbine and the specific heat ratio of the gas; performing thermal analysis simulation test based on the flow field parameters and the three-dimensional geometric model to obtain temperature distribution data of the turbine changing over time; performing finite element simulation analysis based on the flow field parameters, the temperature distribution data and the design parameters to obtain stress-strain response data of the turbine; calculating the life value of the turbine according to the stress-strain response data; performing reliability analysis on the efficiency and the life value of the turbine corresponding to each set of design parameters to obtain efficiency reliability analysis results and life reliability analysis results of the turbine.

2. The method of claim 1, wherein, performing thermal analysis simulation test based on the flow field parameters and the three-dimensional geometric model to obtain temperature distribution data of the turbine changing over time, comprising: constructing a thermal analysis model of the turbine based on the discretized solid domain; inputting the temperature data of the turbine surface changing over time and the convective heat transfer coefficients into the thermal analysis model to obtain temperature distribution data of the turbine solid domain changing over time.

3. The method of claim 1, wherein, performing finite element simulation analysis based on the flow field parameters, the temperature distribution data and the design parameters to obtain stress-strain response data of the turbine, comprising: acquiring a finite element structure simulation model of the turbine solid domain; inputting the rotating speed, the pressure data of the turbine surface changing over time and the temperature distribution data of the turbine solid domain changing over time into the finite element structure simulation model of the solid domain to obtain stress-strain response data of the turbine solid domain.

4. The method of claim 1, wherein, The stress-strain response data of the turbine solid domain comprises strain data corresponding to different stress values of each position point of the turbine solid domain. According to the stress-strain response data, the life value of the turbine is calculated, comprising: calculating the damage value of the turbine for each working time according to the maximum stress value in the turbine solid domain and the strain data at the position point corresponding to the maximum stress value; accumulating the sum of the working times of the turbine when the damage value reaches a preset threshold as the life value of the turbine.

5. The method of claim 1, wherein, The reliability analysis is performed on the turbine efficiency and the life value corresponding to each group of design parameters to obtain the efficiency reliability analysis result and the life reliability analysis result of the turbine, comprising: based on the turbine efficiency corresponding to each group of design parameters, a turbine efficiency set is constructed; according to the standard deviation and the mean value of each turbine efficiency in the turbine efficiency set, the turbine efficiency reliability is calculated; the turbine efficiency reliability calculation result is determined as the reliability analysis result of the turbine efficiency; based on the life corresponding to each group of design parameters, a turbine life set is constructed; according to the standard deviation and the mean value of each turbine life in the turbine life set, the turbine life reliability is calculated; the turbine life reliability calculation result is determined as the reliability analysis result of the turbine life.

6. A digital test apparatus for a liquid rocket engine turbine, characterized in that, The device comprises: an acquisition unit configured to acquire a plurality of groups of design parameters of a turbine in a liquid rocket engine; the design parameters comprise material performance parameters of the turbine, inlet / outlet temperature and pressure conditions, rotating speed and gas parameters; a construction unit configured to, for any one group of design parameters, perform turbine aerodynamic design according to the design parameters to obtain geometric parameters of the turbine, and construct a three-dimensional geometric model of the turbine based on the geometric parameters; the three-dimensional geometric model comprises a solid domain of the turbine; the solid domain of the turbine comprises a blade disc of the turbine and a plurality of blades arranged on the blade disc; The simulation unit is configured to determine a region between any two adjacent blades as a fluid domain of the turbine; input the design parameters into a pre-constructed parameter coupling model to obtain fluid domain size parameters, fluid domain boundary conditions and solid domain size parameters corresponding to the design parameters; the parameter coupling model is constructed based on a coupling relationship among the design parameters, the fluid domain size parameters, the fluid domain boundary conditions and the solid domain size parameters; discretize the fluid domain and the solid domain according to the fluid domain size parameters and the solid domain size parameters respectively to obtain a discretized fluid domain and a discretized solid domain; determine a flow control equation and a turbulence model based on the design parameters; construct a flow simulation model based on the material performance parameters, the fluid domain boundary conditions, the discretized fluid domain, the discretized solid domain, the flow control equation and the turbulence model; input the inlet / outlet temperature and pressure conditions of the turbine, the rotating speed and the fuel gas parameters into the flow simulation model to obtain flow field parameters of the turbine; the flow field parameters include pressure data of a turbine surface changing over time, temperature data of the turbine surface changing over time and corresponding convective heat transfer coefficients, an outlet static temperature of the turbine, an inlet total temperature, an outlet static pressure and an inlet total pressure; calculate the efficiency of the turbine based on the outlet static temperature, the inlet total temperature, the outlet static pressure, the inlet total pressure of the turbine and the specific heat ratio of the fuel gas; perform a thermal analysis simulation test based on the flow field parameters and the three-dimensional geometric model to obtain temperature distribution data of the turbine changing over time; perform a finite element simulation analysis based on the flow field parameters, the temperature distribution data and the design parameters to obtain stress-strain response data of the turbine; The calculation unit is configured to calculate a life value of the turbine according to the stress-strain response data; The analysis unit is configured to perform reliability analysis on the turbine efficiency and the life value corresponding to each group of design parameters to obtain efficiency reliability analysis results and life reliability analysis results of the turbine.

7. An electronic device, comprising: The electronic device includes a processor, a communication interface, a memory and a communication bus, wherein the processor, the communication interface and the memory complete mutual communication through the communication bus; The memory is configured to store a computer program; The processor is configured to execute the program stored on the memory to implement the method of any one of claims 1-5.

8. A computer-readable storage medium, characterized in that, The computer readable storage medium stores a computer program, and the computer program is executed by the processor to implement the method of any one of claims 1-5.

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