Gas turbine complete machine thermal analysis method, device and system

Abstract

The invention relates to a gas turbine complete machine thermal analysis method, device and system. The method comprises the following steps: carrying out modeling treatment on a target gas turbine to obtain a geometric model of the target gas turbine; performing grid division on the geometric model to obtain a geometric model after grid division; based on the operation control rule data of the target gas turbine, generating an operation curve data set; and for each group of operation curves in at least one group of first operation curves, on the basis of the geometric model after grid division and a preset calculation simulation model, carrying out complete machine transient temperature field thermal analysis solution on the target gas turbine by utilizing the operation curves to obtain first transient temperature field data. According to the scheme, the comprehensiveness of transient temperature field analysis of the whole gas turbine is improved.

Description

Technical Field

[0001] This disclosure relates to the field of heavy-duty gas turbine technology, and in particular to a method, apparatus and system for thermal analysis of a gas turbine as a whole. Background Technology

[0002] In related technologies, heavy-duty gas turbines are high-temperature, high-speed rotating power machines that typically operate under complex aerodynamic, thermodynamic, and mechanical loads according to predetermined operating rules. During the integrated design and development of a gas turbine model, key factors such as component lifespan, strength, and overall clearance must be considered. These factors have varying impacts depending on the gas turbine's operating rules, ultimately affecting its reliability, service life, and efficiency. In the research and development of advanced heavy-duty gas turbine models, the design and analysis of these factors require the necessary input conditions provided by Whole Engine Model (WEM) thermal analysis, with the calculation and analysis of the transient and steady-state temperature fields being a core component. While traditional methods for calculating the steady-state and transient temperature fields of the whole engine can approximate solutions through iterative field iteration, the use of interface data iteration and empirical coefficient boundary approximations results in a time-consuming, inefficient, and limited analytical capabilities, making it difficult to meet the development needs of domestically developed heavy-duty gas turbine models. Summary of the Invention

[0003] To overcome the problems existing in related technologies, this disclosure provides a method, apparatus and system for thermal analysis of a gas turbine as a whole.

[0004] According to a first aspect of the present disclosure, a method for thermal analysis of a gas turbine is provided, comprising:

[0005] The target gas turbine is modeled to obtain its geometric model;

[0006] The geometric model is meshed to obtain the meshed geometric model;

[0007] Based on the operation control law data of the target gas turbine, an operation curve dataset is generated; the operation curve dataset includes at least one set of first operation curves; each of the at least one set of first operation curves includes a mapping relationship between time and the operation control law data;

[0008] For each of the at least one set of first operating curves, based on the geometric model after mesh division and the preset calculation simulation model, the target gas turbine is subjected to thermal analysis of the transient temperature field of the whole machine using the operating curves to obtain the first transient temperature field data.

[0009] In some embodiments of this disclosure, the step of meshing the geometric model to obtain a meshed geometric model includes:

[0010] The geometric model is meshed according to preset meshing parameters;

[0011] Obtain the temperature gradient distribution data of the target gas turbine;

[0012] Based on the temperature gradient distribution data, the coordinates of regions with temperature gradients greater than or equal to a preset gradient are selected.

[0013] The region corresponding to the region coordinates in the geometric model is subjected to mesh refinement processing to obtain the geometric model after mesh division.

[0014] In some embodiments of this disclosure, generating an operating curve dataset based on the operating control law data of the target gas turbine includes:

[0015] The operation control law data is interpolated to obtain interpolated operation control law data;

[0016] Multiple sets of operation curves are generated based on the interpolated operation control law data to obtain the operation curve dataset; each set of operation curves includes curves corresponding to different types of operation control law data.

[0017] In some embodiments of this disclosure, after generating the operating curve dataset based on the operating control law data of the target gas turbine, the method further includes:

[0018] The time of the at least one set of first operating curves is adjusted according to a preset adjustment time to obtain at least one set of second operating curves;

[0019] For each of the at least one set of second operating curves, based on the geometric model after mesh division and the preset calculation simulation model, the target gas turbine is subjected to transient temperature field thermal analysis using the operating curves to obtain second transient temperature field data.

[0020] In some embodiments of this disclosure, the step of adjusting the at least one set of first running curves according to a preset adjustment time to obtain at least one set of second running curves includes:

[0021] Obtain the preset adjustment time, the target first operating curve, and the operating condition point to be adjusted; the target first operating curve is any one of the at least one set of first operating curves, and the operating condition point to be adjusted is the time point to be adjusted in the target first operating curve;

[0022] The second operating curve is obtained by adjusting the time point to be adjusted and the corresponding operation control law data according to the preset adjustment time.

[0023] In some embodiments of this disclosure, the method further includes:

[0024] Select the target operating condition point corresponding to the target operating law data from the first or second operating data;

[0025] A third operating curve is generated based on the operating control law data; the third operating curve includes a target sub-curve; the operating time of the target sub-segment is a preset duration, and the operating control law data corresponding to each time point in the target sub-segment is the same as the target operating control law data;

[0026] Based on the geometric model after mesh division and the preset calculation simulation model, the target gas turbine is subjected to a steady-state temperature field thermal analysis using the third operating curve to obtain steady-state temperature field data.

[0027] In some embodiments of this disclosure, the transient temperature field data includes fluid temperature data and solid temperature data.

[0028] According to a second aspect of the present disclosure, a gas turbine whole-machine thermal analysis apparatus is provided, comprising:

[0029] A modeling unit is used to perform modeling processing on the target gas turbine to obtain the geometric model of the target gas turbine;

[0030] A meshing unit is used to divide the geometric model into meshes, resulting in a meshed geometric model.

[0031] The generation unit is used to generate an operating curve dataset based on the operating control law data of the target gas turbine; the operating curve dataset includes at least one set of first operating curves; each of the at least one set of first operating curves includes a mapping relationship between time and the operating control law data;

[0032] The solution unit is used to perform transient temperature field thermal analysis on the target gas turbine for each of the at least one set of first operating curves, based on the geometric model after mesh division and the preset calculation simulation model, to obtain the first transient temperature field data.

[0033] According to a third aspect of the present disclosure, an electronic device includes: a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor, when executing the computer program, implements the method as described in any one of the first aspects.

[0034] According to a fourth aspect of the present disclosure, a computer-readable storage medium is provided having a computer program stored thereon, which, when executed by a processor, implements the method as described in any one of the first aspects.

[0035] According to a fifth aspect of the present disclosure, a computer program product is provided, including a computer program that, when executed by a processor, implements the method as described in any one of the first aspects.

[0036] The technical solutions provided by the embodiments of this disclosure can include the following beneficial effects: A geometric model of the target gas turbine is obtained by modeling the target gas turbine; the geometric model is meshed to obtain a meshed geometric model; an operating curve dataset is generated based on the operating control law data of the target gas turbine; for each of the at least one set of first operating curves, based on the meshed geometric model and a preset computational simulation model, the transient temperature field thermal analysis of the target gas turbine is performed using the operating curves to obtain first transient temperature field data. Thus, by using operating curves corresponding to various operating conditions to perform transient temperature field thermal analysis of the entire machine, transient temperature field data under different operating conditions is obtained, thereby improving the comprehensiveness of transient temperature field analysis and meeting the research and development needs of heavy-duty gas turbines.

[0037] It should be understood that the above general description and the following detailed description are exemplary and explanatory only, and are not intended to limit this disclosure. Attached Figure Description

[0038] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments consistent with the invention and, together with the description, serve to explain the principles of the invention.

[0039] Figure 1 This is a flowchart illustrating a method for thermal analysis of a gas turbine engine according to an exemplary embodiment.

[0040] Figure 2 This is a simplified two-dimensional geometric model schematic diagram shown in the embodiments of this application.

[0041] Figure 3 This is a schematic diagram of mesh division shown in an embodiment of this application.

[0042] Figure 4 This is a schematic diagram of the operating curve shown in the embodiment of this application.

[0043] Figure 5 This is a schematic diagram of metal temperature monitoring during the transient solution calculation process shown in the embodiments of this application.

[0044] Figure 6 This is a schematic diagram of the overall metal temperature distribution at a certain point in time in an embodiment of this application.

[0045] Figure 7 This is a schematic diagram illustrating the trend of metal temperature change over time at a typical location according to an embodiment of this application.

[0046] Figure 8 This is a block diagram illustrating a gas turbine thermal analysis apparatus according to an exemplary embodiment.

[0047] Figure 9 This is a block diagram illustrating an apparatus for a whole-machine thermal analysis method for a gas turbine, according to an exemplary embodiment. Detailed Implementation

[0048] Exemplary embodiments will now be described in detail, examples of which are illustrated in the accompanying drawings. When the following description relates to the drawings, unless otherwise indicated, the same numerals in different drawings denote the same or similar elements. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the present invention. Rather, they are merely examples of apparatuses and methods consistent with some aspects of the invention as detailed in the appended claims.

[0049] The terminology used in this disclosure is for the purpose of describing particular embodiments only and is not intended to be limiting of the present disclosure. The singular forms “a” and “the” as used in this disclosure and the appended claims are also intended to include the plural forms, unless the context clearly indicates otherwise.

[0050] It should be understood that although the terms first, second, third, etc., may be used to describe various information in embodiments of this disclosure, such information should not be limited to these terms. These terms are only used to distinguish information of the same type from one another. For example, first information may also be referred to as second information without departing from the scope of embodiments of this disclosure, and similarly, second information may also be referred to as first information. Depending on the context, the words “if” and “suppose” as used herein may be interpreted as “when”, “when”, or “in response to a determination”.

[0051] Furthermore, various forms of processes shown in the embodiments of this disclosure can be used to reorder, add, or delete steps. For example, the steps described in this application can be executed in parallel, sequentially, or in different orders, as long as the desired result of the technical solution disclosed in this disclosure can be achieved, and this is not limited herein.

[0052] In related technologies, heavy-duty gas turbines are high-temperature, high-speed rotating power machines that typically operate under complex aerodynamic, thermodynamic, and mechanical loads according to predetermined operating rules. During the integrated design and development of a gas turbine model, key factors such as component lifespan, strength, and overall clearance must be considered. These factors have varying impacts depending on the gas turbine's operating rules, ultimately affecting its reliability, service life, and efficiency. In the research and development of advanced heavy-duty gas turbine models, the design and analysis of these factors require the necessary input conditions provided by Whole Engine Model (WEM) thermal analysis, with the calculation and analysis of the transient and steady-state temperature fields being a core component. While traditional methods for calculating the steady-state and transient temperature fields of the whole engine can approximate solutions through iterative field iteration, the use of interface data iteration and empirical coefficient boundary approximations results in a time-consuming, inefficient, and limited analytical capabilities, making it difficult to meet the development needs of domestically developed heavy-duty gas turbine models.

[0053] Furthermore, during the research and development phase, it is necessary to conduct thermal analysis of the gas turbine under different operating conditions, especially for the evaluation of some extreme operating conditions (such as turbine tripping, turning gear restart, etc.), to determine whether problems such as exceeding material temperature limits during transient operation affect the gas turbine's lifespan, or whether drastic solid deformation changes lead to insufficient clearance causing scraping and affecting the safe operation of the gas turbine, thus providing support for downstream professionals. However, traditional whole-machine temperature field calculation methods require a large amount of manpower for manual calculations when conducting simulation analysis of operating curves of different gas turbine models. The entire calculation and analysis process is time-consuming and inefficient, making it difficult to meet the research and development design tasks of heavy-duty gas turbine models.

[0054] Traditional empirical coefficient methods perform transient calculations based on test data from existing gas turbine models, which can meet the transient temperature field design evaluation requirements for gas turbines with the same structure. However, once the gas turbine design changes or new technologies are adopted, the empirical data from the original models can only provide a reference. It lacks the ability to provide forward design support for gas turbines with changed design characteristics. Furthermore, in the early stages of independent model development, the lack of reference model data and test data limits the use of empirical coefficient methods to generate transient thermal boundary conditions.

[0055] To address the aforementioned issues, this disclosure provides a method, apparatus, and system for thermal analysis of a gas turbine. The method involves modeling the target gas turbine to obtain its geometric model; meshing the geometric model to obtain a meshed geometric model; generating an operating curve dataset based on the gas turbine's operational control data; and performing a transient temperature field analysis on each of at least one set of first operating curves, using the meshed geometric model and a pre-defined computational simulation model, to obtain first transient temperature field data. This allows for the use of operating curves corresponding to various operating conditions to perform transient temperature field analysis, obtaining transient temperature field data under different operating conditions, thereby improving the comprehensiveness of transient temperature field analysis and meeting the development needs of heavy-duty gas turbines.

[0056] Figure 1 This is a flowchart illustrating a method for thermal analysis of a gas turbine engine according to an exemplary embodiment, such as... Figure 1 As shown, it should be noted that the gas turbine overall thermal analysis method of this disclosure embodiment is applied to the determination of the transient temperature field of the gas turbine overall. For example... Figure 1 As shown, the method may include the following steps:

[0057] Step 101: Perform modeling on the target gas turbine to obtain its geometric model.

[0058] In one embodiment, the gas turbine is modeled using rationalization assumptions, and its structure is simplified and preprocessed according to design requirements. Simultaneously, to reduce computational costs, unimportant geometric details can be removed. For example... Figure 2 The diagram shown is a simplified two-dimensional geometric model.

[0059] As an example, the above set model can be a three-dimensional model or a two-dimensional model, which can be selected according to actual needs.

[0060] In some embodiments, unnecessary geometric features in the geometric model, such as serrated teeth, can be simplified and preprocessed.

[0061] Step 102: Mesh the geometric model to obtain the meshed geometric model.

[0062] In one embodiment, the mesh can be generated based on the characteristics of each component of the gas turbine and the solution requirements, and different mesh settings can be applied according to the solution requirements. In some embodiments of this application, step 102 may specifically include the following steps:

[0063] The geometric model is meshed according to preset meshing parameters;

[0064] Acquire temperature gradient distribution data of the target gas turbine;

[0065] Based on temperature gradient distribution data, filter the coordinates of regions where the temperature gradient is greater than or equal to a preset gradient.

[0066] The regions corresponding to the area coordinates in the geometric model are subjected to mesh refinement processing to obtain the geometric model after mesh division.

[0067] In one embodiment, the simplified and preprocessed geometric model can be meshed and configured according to the characteristics of each component of the target gas turbine and the solution requirements. While balancing computational cost and analytical accuracy, the mesh is appropriately refined in regions with high temperature gradients to improve the accuracy of subsequent thermal analysis of the overall turbine temperature field and the convergence of transient solutions, thereby reducing errors. After obtaining the meshing results, the meshing results can be discretized to obtain the mesh data (i.e., the geometric model after meshing). A schematic diagram of the meshing process is shown below. Figure 3 As shown.

[0068] It should be noted that after obtaining the geometric model after mesh generation, it is also necessary to organize the material database according to the material selection scheme and set the corresponding materials for the geometric components.

[0069] Step 103: Generate an operating curve dataset based on the operating control law data of the target gas turbine.

[0070] The operating curve dataset includes at least one set of first operating curves. This dataset can drive the geometric model to simulate the temperature field of the target gas turbine, thereby calculating the laws and trends of thermal deformation changes.

[0071] In some embodiments, interface data of relevant disciplines of the target gas turbine can be collected to obtain the boundary dataset of the operating curve to be calculated, boundary conditions can be set for the geometric model of the target gas turbine for the first transient temperature field data, and the operating curve dataset can be imported into the meshed geometric model.

[0072] Among them, each of the first operating curves in at least one set includes the mapping relationship between time and operating control law data.

[0073] Understandably, the role of the first operating curve is to characterize the load history experienced by the gas turbine during operation using a set of parameters. Furthermore, when the operating curve shows a steady-state dwell period at a certain operating point (such as partial load or 100% load), the steady-state temperature field at that operating point can be obtained under this operating curve. Therefore, both the complete load history and the steady-state temperature field of the required operating point can be generated.

[0074] In this embodiment, the operational control law data can be collected from interface data provided by various disciplines, including secondary air flow path data (mass flow rate, pressure distribution, etc.), compressor and turbine aerodynamic data (airflow temperature, mass flow rate, etc.), and operational engineer startup data (speed, load changes), etc. Interpolation processing can be performed based on the above operational control law data and key operating points to generate an operational curve dataset file.

[0075] In addition, the operating curve dataset can be used to calculate the temperature field and thermal deformation variation patterns and trends of the driving gas turbine.

[0076] In one embodiment, the running curve dataset can be a time-varying load matrix (e.g., it can include time-temperature, time-mass flow rate, time-pressure, etc. correspondences).

[0077] It should be noted that, in the embodiments of this application, interface data of corresponding operating curves can be collected and a dataset of operating curves for the required operating conditions can be formed according to different calculation objectives and needs.

[0078] In some embodiments of this application, step 103 may specifically include the following steps:

[0079] The operation control law data is interpolated to obtain the interpolated operation control law data;

[0080] Multiple sets of operation curves are generated based on the interpolated operation control law data to obtain an operation curve dataset; each set of operation curves includes curves corresponding to different types of operation control law data.

[0081] like Figure 4 As shown, Figure 4 The middle part is a set of operating curves, corresponding to a certain operating condition, which includes the mapping relationship between multiple parameters and time.

[0082] In some embodiments of this application, after step 103, the method may further include the following steps:

[0083] According to a preset adjustment time, at least one set of first operating curves of the first transient temperature field data are time-adjusted to obtain at least one set of second operating curves;

[0084] For each set of operating curves in at least one set of second operating curves obtained from the first transient temperature field data, based on the geometric model after the first transient temperature field data mesh is divided and the preset computational simulation model, the target gas turbine for the obtained first transient temperature field data is subjected to a whole-machine transient temperature field thermal analysis using the operating curves of the obtained first transient temperature field data to obtain the second transient temperature field data. In the embodiments of this application, the preset adjustment time can be preset according to actual needs.

[0085] In this embodiment of the application, at least one set of first operating curves is time-adjusted by a preset adjustment time to generate new operating curves, that is, to obtain at least one set of second operating curves. This enables the analysis and solution of the transient temperature field of the entire gas turbine under more operating conditions, increases the types of operating conditions, improves the comprehensiveness of transient temperature field analysis, and meets the research and development needs of heavy-duty gas turbines.

[0086] In some embodiments of this application, adjusting at least one set of first operating curves of the obtained first transient temperature field data according to a preset adjustment time to obtain at least one set of second operating curves may specifically include the following steps:

[0087] Obtain the preset adjustment time, the target first operating curve, and the operating point to be adjusted; the target first operating curve is any one of at least one set of first operating curves, and the operating point to be adjusted is the time point to be adjusted on the target first operating curve;

[0088] The second operating curve is obtained by adjusting the time point to be adjusted and the corresponding operation control law data according to the preset adjustment time.

[0089] Step 104: For each set of operating curves in at least one set of first operating curves and at least one set of second operating curves, based on the geometric model after meshing and the preset calculation simulation model, the operating curves are used to perform thermal analysis of the transient temperature field of the target gas turbine to obtain the first transient temperature field data.

[0090] It should be noted that the above-mentioned computational simulation model is existing technology and will not be elaborated upon here.

[0091] In one embodiment, based on the geometric model after the above-mentioned mesh division, a computational simulation model for thermal analysis of the whole machine temperature field is established. Boundary conditions are set according to the contact characteristics and heat transfer characteristics of the target gas turbine structure. Each set of at least one set of first operating curves and at least one set of second operating curves is imported according to the actual analysis requirements. The aerodynamic parameters in the dataset are used as inputs to the boundary conditions to drive the calculation of the temperature field.

[0092] As an example, when calculating the temperature field of operating curves under different operating conditions, the boundary type of the simulation model remains unchanged, and the corresponding operating curve dataset is imported for calculation and solution. The boundary type can be set according to the contact and heat transfer characteristics of the gas turbine structure, such as adiabatic, convective heat transfer, radiative heat transfer, contact heat transfer, etc.

[0093] The solution scheme is calculated to obtain the transient temperature field of the entire machine. After evaluating and checking the results, the analysis results are output to the relevant departments. For example, Figure 5This is a schematic diagram of metal temperature monitoring during the transient solution calculation process according to an embodiment of this application. Figure 6 This is a schematic diagram of the overall metal temperature distribution at a certain point in time in an embodiment of this application. Figure 7 This is a schematic diagram illustrating the trend of metal temperature change over time at a typical location according to an embodiment of this application.

[0094] also, Figure 5 The system records the minimum, maximum, and average metal temperatures during the transient solution calculation process. This can be used to monitor whether the metal temperature is normal during the calculation process. For example, if the maximum metal temperature reaches several thousand degrees Celsius, it indicates a problem, and the calculation needs to be terminated for inspection.

[0095] In this embodiment, the transient temperature field of the gas turbine can be calculated based on the fluid-thermal-structural engineering coupling theory. Fluid and solid heat transfer are solved using a thermal coupling method, based on a combination of the heat conduction differential equation and third-type boundary conditions.

[0096]

[0097] Where ρ is the material density, c T For the specific heat capacity of the material, k is the rate of change of temperature over time. x k y k z Thermal conductivity in the x, y, and z directions, respectively. Let Q be the temperature gradient and Q be the internal heat source term.

[0098]

[0099] Where k is the thermal conductivity of the solid. T represents the normal temperature gradient at the wall, h is the convective heat transfer coefficient, and T is the temperature gradient at the wall. w T is the temperature of the solid wall surface. f This is the mainstream temperature of the fluid.

[0100] q i,j =C p ·m i,j ·(T f,j -T f,i )

[0101] Where, q i,j For the heat transfer of fluid from i to j, C p For the specific heat capacity of a fluid at constant pressure, m i,j T is the mass flow rate of the fluid. f,j T represents the fluid temperature at the outlet section. f,i The inlet section fluid temperature is denoted as .

[0102] h·(T w -Tf ) = C p ·m i,j ·(T f,j -T f,i )

[0103] Among them, h·(T) w -T f C represents the convective heat transfer from the solid to the fluid. p ·m i,j ·(T f,j -T f,i ) represents the total heat absorbed by the fluid.

[0104] In some embodiments of this application, the thermal analysis solution proposed in this application may include thermal solution and thermal-structure coupled solution calculation. The temperature field data of the thermal solution calculation result includes fluid temperature data, solid temperature data, convective heat transfer coefficient data, etc.; the data of the thermal-structure coupled solution calculation result includes thermal solution temperature field data and solid deformation data.

[0105] In some embodiments of this application, the method may further include the following steps:

[0106] Select the target operating condition point corresponding to the target operating law data from the first or second operating data;

[0107] A third operating curve is generated based on the operating control law data; the third operating curve includes a target sub-curve; the operating time of the target sub-segment is a preset duration, and the operating control law data corresponding to each time point in the target sub-segment is the same as the target operating control law data;

[0108] Based on the geometric model after mesh generation and the preset computational simulation model, the steady-state temperature field of the target gas turbine is solved by using the third operating curve to obtain the steady-state temperature field data.

[0109] In some embodiments of this application, radiation heat transfer can be considered when solving the temperature field in the solid domain. The radiation angle coefficient can be calculated using direct integration, algebraic analysis, geometric analysis, or Monte Carlo method based on the component geometry, wall temperature distribution, and the shading relationship between different components. The radiation angle coefficient is used as a characteristic coefficient to calculate the heat flux density of the radiation boundary conditions.

[0110] According to the gas turbine whole-machine thermal analysis method proposed in this disclosure, the target gas turbine is modeled to obtain a geometric model; the geometric model is meshed to obtain a meshed geometric model; based on the operation control law data of the target gas turbine, an operation curve dataset is generated; for each of at least one set of first operation curves, based on the meshed geometric model and a preset computational simulation model, the transient temperature field thermal analysis of the target gas turbine is performed using the operation curves to obtain the first transient temperature field data. Thus, by using operation curves corresponding to various operating conditions to perform transient temperature field thermal analysis of the whole machine, transient temperature field data under different operating conditions are obtained, thereby improving the comprehensiveness of transient temperature field analysis and meeting the R&D needs of heavy-duty gas turbines.

[0111] Figure 8 This is a block diagram of a gas turbine thermal analysis apparatus according to an exemplary embodiment. (Refer to...) Figure 8 The device includes a modeling unit 801, a partitioning unit 802, a generation unit 803, and a solution unit 804.

[0112] Among them, the modeling unit 801 is used to perform modeling processing on the target gas turbine to obtain the geometric model of the target gas turbine;

[0113] Meshing unit 802 is used to mesh the geometric model to obtain the meshed geometric model;

[0114] The generation unit 803 is used to generate an operating curve dataset based on the operating control law data of the target gas turbine; the operating curve dataset includes at least one set of first operating curves; each of the at least one set of first operating curves includes a mapping relationship between time and operating control law data;

[0115] Solver 804 is used to perform transient temperature field thermal analysis on the target gas turbine based on the meshed geometric model and the preset calculation simulation model for each of at least one set of first operating curves and at least one set of second operating curves, and obtain the first transient temperature field data.

[0116] In some embodiments of this application, the partitioning unit 802 may specifically be used for:

[0117] The geometric model is meshed according to preset meshing parameters;

[0118] Acquire temperature gradient distribution data of the target gas turbine;

[0119] Based on temperature gradient distribution data, filter the coordinates of regions where the temperature gradient is greater than or equal to a preset gradient.

[0120] The regions corresponding to the area coordinates in the geometric model are subjected to mesh refinement processing to obtain the geometric model after mesh division.

[0121] In some embodiments of this application, the generation unit 803 may specifically be used for:

[0122] The operation control law data is interpolated to obtain the interpolated operation control law data;

[0123] Multiple sets of operation curves are generated based on the interpolated operation control law data to obtain an operation curve dataset; each set of operation curves includes curves corresponding to different types of operation control law data.

[0124] In some embodiments of this application, the apparatus may further include an adjustment unit, which may specifically be used for:

[0125] According to a preset adjustment time, at least one set of first operating curves of the first transient temperature field data are time-adjusted to obtain at least one set of second operating curves;

[0126] For each set of operating curves in at least one set of second operating curves obtained from the first transient temperature field data, based on the geometric model after the first transient temperature field data grid is divided and the preset calculation simulation model, the transient temperature field thermal analysis of the target gas turbine obtained from the first transient temperature field data is performed using the operating curves of the first transient temperature field data to obtain the second transient temperature field data.

[0127] In some embodiments of this application, the adjustment unit may also be used for:

[0128] Obtain the preset adjustment time, the target first operating curve, and the operating point to be adjusted; the target first operating curve is any one of at least one set of first operating curves, and the operating point to be adjusted is the time point to be adjusted on the target first operating curve;

[0129] The second operating curve is obtained by adjusting the time point to be adjusted and the corresponding operation control law data according to the preset adjustment time.

[0130] In some embodiments of this application, the apparatus may further include:

[0131] The selection unit is used to select the target operation control law data corresponding to the target operating point in the first operating data or the second operating data.

[0132] The generation unit is also used to generate a third operating curve based on the operating control law data; the third operating curve includes a target sub-curve; the operating time of the target sub-segment is a preset time, and the operating control law data corresponding to each time point in the target sub-segment is the same as the target operating control law data;

[0133] The solver unit is also used to perform a thermal analysis of the steady-state temperature field of the target gas turbine based on the meshed geometric model and the preset computational simulation model, using the third operating curve to obtain steady-state temperature field data.

[0134] In some embodiments of this application, transient temperature field data includes fluid temperature data and solid temperature data.

[0135] Regarding the apparatus in the above embodiments, the specific manner in which each module performs its operation has been described in detail in the embodiments related to the method, and will not be elaborated upon here.

[0136] According to the gas turbine thermal analysis apparatus proposed in this disclosure, a geometric model of the target gas turbine is obtained by modeling the target gas turbine; the geometric model is then meshed to obtain a meshed geometric model; based on the operation control law data of the target gas turbine, an operation curve dataset is generated; for each of at least one set of first operation curves, based on the meshed geometric model and a preset computational simulation model, the transient temperature field thermal analysis of the target gas turbine is performed using the operation curves to obtain first transient temperature field data. Thus, by using operation curves corresponding to various operating conditions to perform transient temperature field thermal analysis of the entire gas turbine, transient temperature field data under different operating conditions is obtained, thereby improving the comprehensiveness of transient temperature field analysis and meeting the R&D needs of heavy-duty gas turbines.

[0137] Figure 9 This is a block diagram illustrating an apparatus for a method of thermal analysis of a gas turbine engine, according to an exemplary embodiment. For example, apparatus 900 may be an electronic device, such as a mobile phone, computer, digital broadcasting terminal, messaging device, game console, tablet device, medical device, fitness equipment, personal digital assistant, etc.

[0138] Reference Figure 9 The device 900 may include one or more of the following components: a processing component 902, a memory 904, a power component 906, a multimedia component 908, an audio component 910, an input / output (I / O) interface 912, a sensor component 914, and a communication component 916.

[0139] Processing component 902 typically controls the overall operation of device 900, such as operations associated with display, telephone calls, data communication, camera operation, and recording. Processing component 902 may include one or more processors 920 to execute instructions to perform all or part of the steps of the methods described above. Furthermore, processing component 902 may include one or more modules to facilitate interaction between processing component 902 and other components. For example, processing component 902 may include a multimedia module to facilitate interaction between multimedia component 908 and processing component 902.

[0140] Memory 904 is configured to store various types of data to support the operation of device 900. Examples of this data include instructions for any application or method operating on device 900, contact data, phonebook data, messages, pictures, videos, etc. Memory 904 can be implemented by any type of volatile or non-volatile storage device or a combination thereof, such as static random access memory (SRAM), electrically erasable programmable read-only memory (EEPROM), erasable programmable read-only memory (EPROM), programmable read-only memory (PROM), read-only memory (ROM), magnetic storage, flash memory, magnetic disk, or optical disk.

[0141] The power supply component 906 provides power to the various components of the device 900. The power supply component 906 may include a power management system, one or more power sources, and other components associated with generating, managing, and distributing power to the device 900.

[0142] Multimedia component 908 includes a screen that provides an output interface between device 900 and user. In some embodiments, the screen may include a liquid crystal display (LCD) and a touch panel (TP). If the screen includes a touch panel, the screen may be implemented as a touchscreen to receive input signals from the user. The touch panel includes one or more touch sensors to sense touches, swipes, and gestures on the touch panel. The touch sensors may sense not only the boundaries of touch or swipe actions but also the duration and pressure associated with the touch or swipe operation. In some embodiments, multimedia component 908 includes a front-facing camera and / or a rear-facing camera. When device 900 is in an operating mode, such as shooting mode or video mode, the front-facing camera and / or rear-facing camera may receive external multimedia data. Each front-facing camera and rear-facing camera may be a fixed optical lens system or have focal length and optical zoom capabilities.

[0143] Audio component 910 is configured to output and / or input audio signals. For example, audio component 910 includes a microphone (MIC) configured to receive external audio signals when device 900 is in an operating mode, such as call mode, recording mode, and voice recognition mode. The received audio signals may be further stored in memory 904 or transmitted via communication component 916. In some embodiments, audio component 910 also includes a speaker for outputting audio signals.

[0144] I / O interface 912 provides an interface between processing component 902 and peripheral interface modules, such as keyboards, click wheels, buttons, etc. These buttons may include, but are not limited to, home buttons, volume buttons, power buttons, and lock buttons.

[0145] Sensor assembly 914 includes one or more sensors for providing status assessments of various aspects of device 900. For example, sensor assembly 914 may detect the on / off state of device 900, the relative positioning of components such as the display and keypad of device 900, changes in position of device 900 or a component of device 900, the presence or absence of user contact with device 900, orientation or acceleration / deceleration of device 900, and temperature changes of device 900. Sensor assembly 914 may include a proximity sensor configured to detect the presence of nearby objects without any physical contact. Sensor assembly 914 may also include a light sensor, such as a CMOS or CCD image sensor, for use in imaging applications. In some embodiments, sensor assembly 914 may also include an accelerometer, gyroscope, magnetometer, pressure sensor, or temperature sensor.

[0146] Communication component 916 is configured to facilitate wired or wireless communication between device 900 and other devices. Device 900 can access wireless networks based on communication standards, such as WiFi, 2G, or 3G, or combinations thereof. In one exemplary embodiment, communication component 916 receives broadcast signals or broadcast-related information from an external broadcast management system via a broadcast channel. In one exemplary embodiment, communication component 916 also includes a near-field communication (NFC) module to facilitate short-range communication. For example, the NFC module may be implemented based on radio frequency identification (RFID) technology, Infrared Data Association (IrDA) technology, ultra-wideband (UWB) technology, Bluetooth (BT) technology, and other technologies.

[0147] In an exemplary embodiment, the apparatus 900 may be implemented by one or more application-specific integrated circuits (ASICs), digital signal processors (DSPs), digital signal processing devices (DSPDs), programmable logic devices (PLDs), field-programmable gate arrays (FPGAs), controllers, microcontrollers, microprocessors, or other electronic components to perform the methods described above.

[0148] In an exemplary embodiment, a non-transitory computer-readable storage medium including instructions is also provided, such as a memory 904 including instructions, which can be executed by a processor 920 of the device 900 to perform the above-described method. For example, the non-transitory computer-readable storage medium may be a ROM, random access memory (RAM), CD-ROM, magnetic tape, floppy disk, and optical data storage device, etc.

[0149] In an exemplary embodiment, a computer program product is also provided, including a computer program that implements the above-described method when executed by a processor 920 of the device 900.

[0150] Other embodiments of the invention will readily occur to those skilled in the art upon consideration of the specification and practice of the invention disclosed herein. This disclosure is intended to cover any variations, uses, or adaptations of the invention that follow the general principles of the invention and include common knowledge or customary techniques in the art not disclosed herein. The specification and examples are to be considered exemplary only, and the true scope and spirit of the invention are indicated by the following claims.

[0151] It should be understood that the present invention is not limited to the precise structure described above and shown in the accompanying drawings, and various modifications and changes can be made without departing from its scope. The scope of the invention is limited only by the appended claims.

Claims

1. A method for thermal analysis of a gas turbine as a whole, characterized in that, include: The target gas turbine is modeled to obtain its geometric model; The geometric model is meshed to obtain the meshed geometric model; Based on the operation control law data of the target gas turbine, an operation curve dataset is generated; the operation curve dataset includes at least one set of first operation curves; each of the at least one set of first operation curves includes a mapping relationship between time and the operation control law data; For each of the at least one set of first operating curves, based on the geometric model after mesh division and the preset calculation simulation model, the target gas turbine is subjected to thermal analysis of the transient temperature field of the whole machine using the operating curves to obtain the first transient temperature field data.

2. The method for thermal analysis of a gas turbine as described in claim 1, characterized in that, The step of meshing the geometric model to obtain a meshed geometric model includes: The geometric model is meshed according to preset meshing parameters; Obtain the temperature gradient distribution data of the target gas turbine; Based on the temperature gradient distribution data, the coordinates of regions with temperature gradients greater than or equal to a preset gradient are selected. The region corresponding to the region coordinates in the geometric model is subjected to mesh refinement processing to obtain the geometric model after mesh division.

3. The method for thermal analysis of a gas turbine as described in claim 1, characterized in that, The operation curve dataset generated based on the operation control law data of the target gas turbine includes: The operation control law data is interpolated to obtain interpolated operation control law data; Multiple sets of operation curves are generated based on the interpolated operation control law data to obtain the operation curve dataset; each set of operation curves includes curves corresponding to different types of operation control law data.

4. The method for thermal analysis of a gas turbine as described in claim 1, characterized in that, After generating the operating curve dataset based on the operating control law data of the target gas turbine, the method further includes: The time of the at least one set of first operating curves is adjusted according to a preset adjustment time to obtain at least one set of second operating curves; For each of the at least one set of second operating curves, based on the geometric model after mesh division and the preset calculation simulation model, the target gas turbine is subjected to transient temperature field thermal analysis using the operating curves to obtain second transient temperature field data.

5. The method for thermal analysis of a gas turbine as described in claim 4, characterized in that, The step of adjusting the time of the at least one set of first running curves according to a preset adjustment time to obtain at least one set of second running curves includes: Obtain the preset adjustment time, the target first operating curve, and the operating condition point to be adjusted; the target first operating curve is any one of the at least one set of first operating curves, and the operating condition point to be adjusted is the time point to be adjusted in the target first operating curve; The second operating curve is obtained by adjusting the time point to be adjusted and the corresponding operation control law data according to the preset adjustment time.

6. The method for thermal analysis of a gas turbine as described in claim 4, characterized in that, Also includes: Select the target operating condition point corresponding to the target operating law data in the first or second operating curve; A third operating curve is generated based on the operating control law data; the third operating curve includes a target sub-curve; the operating time of the target sub-segment is a preset duration, and the operating control law data corresponding to each time point in the target sub-segment is the same as the target operating control law data; Based on the geometric model after mesh division and the preset calculation simulation model, the target gas turbine is subjected to a steady-state temperature field thermal analysis using the third operating curve to obtain steady-state temperature field data.

7. A thermal analysis device for a gas turbine, characterized in that, include: A modeling unit is used to perform modeling processing on the target gas turbine to obtain the geometric model of the target gas turbine; A meshing unit is used to divide the geometric model into meshes, resulting in a meshed geometric model. The generation unit is used to generate an operating curve dataset based on the operating control law data of the target gas turbine; the operating curve dataset includes at least one set of first operating curves; each of the at least one set of first operating curves includes a mapping relationship between time and the operating control law data; The solution unit is used to perform transient temperature field thermal analysis on the target gas turbine for each of the at least one set of first operating curves, based on the geometric model after mesh division and the preset calculation simulation model, to obtain the first transient temperature field data.

8. An electronic device, characterized in that, include: A memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor, when executing the computer program, implements the method as described in any one of claims 1 to 6.

9. A computer-readable storage medium having a computer program stored thereon, characterized in that, When the computer program is executed by a processor, it implements the method as described in any one of claims 1 to 6.

10. A computer program product, comprising a computer program, characterized in that, The computer program, when executed by a processor, implements the method as described in any one of claims 1 to 6.

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