Structured design method, device and storage medium of heavy-duty gas turbine

Abstract

The structured design method, device and storage medium of the heavy-duty gas turbine provided in the application are based on the obtained requirement parameters of the heavy-duty gas turbine, a one-dimensional model of the heavy-duty gas turbine is obtained through IPD data analysis, the performance parameters and component design parameters of the heavy-duty gas turbine are obtained through simulation calculation of the heavy-duty gas turbine by using the one-dimensional model, a whole machine thermal analysis model is established, gap design is performed through the whole machine thermal analysis model, the component design parameters of the heavy-duty gas turbine are optimized and evaluated, the whole machine design parameters of the heavy-duty gas turbine are obtained after design iteration, the whole machine performance of the whole machine design parameters of the heavy-duty gas turbine is evaluated, and the target whole machine design parameters of the heavy-duty gas turbine are obtained. The method provided in the application ensures that the performance of the designed heavy-duty gas turbine can meet the use requirements, reduces design iteration, and improves design efficiency. At the same time, each component can be simulated and modified flexibly, which provides convenience for the whole design process of the heavy-duty gas turbine.

Description

Technical Field

[0001] This application relates to the field of heavy-duty gas turbine technology, and in particular to a structured design method, apparatus and storage medium for heavy-duty gas turbines. Background Technology

[0002] Against the backdrop of my country's vigorous development of domestically produced heavy-duty gas turbines, it is necessary to ensure that the designed heavy-duty gas turbines can meet the usage requirements in order to avoid situations where the heavy-duty gas turbines are poorly designed or fail to meet performance standards.

[0003] In related technologies, inaccurate assessment of component clearance control during the design process of heavy-duty gas turbines can lead to malfunctions and losses in the designed heavy-duty gas turbines. Summary of the Invention

[0004] This application provides a structured design method, apparatus, and storage medium for heavy-duty gas turbines, thereby proposing a structured design method for engine gas turbines.

[0005] The first aspect of this application proposes a structured design method for a heavy-duty gas turbine, including:

[0006] Obtain the required parameters for heavy-duty gas turbines;

[0007] A one-dimensional model of the heavy-duty gas turbine was obtained through IPD data analysis.

[0008] The performance parameters and component design parameters of the heavy-duty gas turbine are obtained by using the one-dimensional model to perform simulation calculations on the heavy-duty gas turbine.

[0009] Establish a thermal analysis model for the entire machine;

[0010] The clearance design is carried out by using a whole-machine thermal analysis model, the component design parameters of the heavy-duty gas turbine are optimized and evaluated, and the whole-machine design parameters of the heavy-duty gas turbine are obtained after design iteration.

[0011] The overall performance of the heavy-duty gas turbine is evaluated by the overall design parameters to obtain the target overall design parameters of the heavy-duty gas turbine.

[0012] A second aspect of this application provides a structured design apparatus for a heavy-duty gas turbine, comprising:

[0013] The acquisition module is used to acquire the required parameters for heavy-duty gas turbines;

[0014] The determination module is used to obtain a one-dimensional model of the heavy-duty gas turbine through IPD data analysis;

[0015] The simulation module is used to perform simulation calculations on the heavy-duty gas turbine using the one-dimensional model to obtain the performance parameters and component design parameters of the heavy-duty gas turbine.

[0016] Establish a module for building a thermal analysis model of the entire machine;

[0017] The design module is used to design gaps through a whole-machine thermal analysis model, optimize and evaluate the component design parameters of the heavy-duty gas turbine, and obtain the whole-machine design parameters of the heavy-duty gas turbine after design iteration.

[0018] The evaluation module performs an overall performance evaluation on the overall design parameters of the heavy-duty gas turbine to obtain the target overall design parameters of the heavy-duty gas turbine.

[0019] The computer storage medium proposed in the third aspect of this application stores computer-executable instructions; after being executed by a processor, the computer-executable instructions can implement the method described in the first aspect above.

[0020] The technical solutions provided by the embodiments of this application bring at least the following beneficial effects:

[0021] This application proposes a structured design method, apparatus, and storage medium for heavy-duty gas turbines. It obtains the required parameters of the heavy-duty gas turbine, generates a one-dimensional model of the turbine through IPD data analysis, performs simulation calculations on the one-dimensional model to obtain performance parameters and component design parameters, establishes a whole-machine thermal analysis model, performs clearance design based on the thermal analysis model, optimizes and evaluates the component design parameters, and obtains the overall design parameters of the heavy-duty gas turbine after design iteration. Finally, it evaluates the overall performance of the heavy-duty gas turbine based on these design parameters to obtain the target overall design parameters. Therefore, by using the structured design method proposed in this application, the design process of heavy-duty gas turbines ensures that the performance of the designed heavy-duty gas turbine meets the usage requirements, reduces design iterations, and improves design efficiency. Meanwhile, this application provides a structured design for each component of the heavy-duty gas turbine, which allows for flexible simulation and modification of each component, facilitating the entire design process of the heavy-duty gas turbine and making the design results of the heavy-duty gas turbine more accurate.

[0022] Additional aspects and advantages of this application will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of this application. Attached Figure Description

[0023] The above and / or additional aspects and advantages of this application will become apparent and readily understood from the following description of the embodiments taken in conjunction with the accompanying drawings, wherein:

[0024] Figure 1 This is a flowchart illustrating a structural design method for a heavy-duty gas turbine according to an embodiment of this application;

[0025] Figure 2 This is a structural schematic diagram of a structured design apparatus for a heavy-duty gas turbine according to an embodiment of this application. Detailed Implementation

[0026] The embodiments of this application are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application.

[0027] The structural design method and apparatus for heavy-duty gas turbines according to embodiments of this application are described below with reference to the accompanying drawings.

[0028] Example 1

[0029] Figure 1 This is a flowchart illustrating a structured design method for a heavy-duty gas turbine according to an embodiment of this application, as shown below. Figure 1 As shown, it may include:

[0030] Step 101: Obtain the required parameters for heavy-duty gas turbines.

[0031] In this embodiment, the demand parameters for heavy-duty gas turbines are obtained after analyzing the market, competitors, and existing technology maturity.

[0032] Step 102: Obtain a one-dimensional model of the heavy-duty gas turbine through IPD data analysis.

[0033] In an embodiment of the present invention, IPD merges and aggregates the acquired demand parameters to obtain a one-dimensional model of a heavy-duty gas turbine.

[0034] Step 103: Use a one-dimensional model to perform simulation calculations on the heavy-duty gas turbine to obtain the performance parameters and component design parameters of the heavy-duty gas turbine.

[0035] In embodiments of the present invention, the performance parameters and component design parameters of the heavy-duty gas turbine can be obtained by simulating and calculating the cycle parameters of the entire machine using a simulation tool based on a one-dimensional model of the heavy-duty gas turbine.

[0036] Furthermore, in the embodiments of the present invention, during the simulation process based on the one-dimensional model of the heavy-duty gas turbine, the main materials of the components can be selected and evaluated through a material database to obtain the component design parameters of the heavy-duty gas turbine and their corresponding material selections.

[0037] Furthermore, in embodiments of the present invention, component design parameters may include flow path design parameters, airfoil design parameters, compressor design parameters, combustion chamber design parameters, rotor system design parameters, and secondary air system design parameters.

[0038] Specifically, in embodiments of the present invention, the flow path can evaluate the pressure ratio distribution at each stage and the radial distribution of total pressure at each stage outlet under design point operating conditions, and evaluate the endwall boundary layer region. The flow path can include evaluating the radial distribution of total temperature at each stage outlet under design point conditions, assessing the blade height Mach number distribution, the shock wave situation at the tip of the preceding blade, the radial distribution of the inlet and outlet airflow angles of each stage of moving blades, the radial distribution of the inlet and outlet airflow angles of each stage of stationary blades, obtaining the outlet parameters of moving and stationary blades, and interstage matching and packing to suppress flow separation.

[0039] Furthermore, in embodiments of the present invention, the blade design parameters may include an arc blade shape, an angle of attack estimated by a loss model as the minimum loss angle of attack reference, a surface Mach number, a shape factor distribution, and a peak Mach number of the blade's suction surface.

[0040] Furthermore, in embodiments of the present invention, compressor design parameters may include pressure ratio, adiabatic efficiency, and surge margin.

[0041] Furthermore, in embodiments of the present invention, the combustion chamber design parameters may include combustion efficiency, NOx emissions, CO emissions, outlet temperature, total pressure loss coefficient, maximum pressure pulsation / total pressure, lifetime, and Wobbe number. Also, in embodiments of the present invention, the combustion chamber design parameters may further include design boundary conditions for fuel pressure, fuel temperature, fuel flow rate, total temperature of combustion chamber inlet air, and total pressure of combustion chamber inlet air.

[0042] Furthermore, in embodiments of the present invention, the rotor system design parameters may include a static model (including rotor deflection and bending stress of each design section), lateral vibration characteristics, rotor critical speed variation curve with support stiffness, calculation and evaluation of characteristic frequency and unbalance response at rated speed, rotor torsional vibration characteristics, evaluation of torsional natural frequency, characteristic frequency at rated speed, rotor axial force distribution, and disc strength.

[0043] Furthermore, in embodiments of the present invention, the design parameters of the secondary air system may include the percentage of cold air volume to compressor inlet flow rate, the location and starting boundary of the extraction flow path, the average static pressure of different blade air supply circuits, the cold air volume and leakage of the high-pressure extraction flow path, the cold air volume and leakage of the medium-pressure extraction flow path, the cold air volume and leakage of the low-pressure extraction flow path, and the design flow rate of the internal ducting flow path at different locations.

[0044] Step 104: Establish a thermal analysis model for the entire machine.

[0045] In one embodiment of the present invention, establishing a whole-machine thermal analysis model may include establishing a two-dimensional finite element model composed of axisymmetric and plane stress elements.

[0046] Furthermore, in embodiments of the present invention, the method for establishing a two-dimensional finite element model composed of axisymmetric and plane stress elements may include the following steps:

[0047] Step a: The stator and rotor of the entire heavy-duty gas turbine are combined in a general model. Transient analysis axisymmetric parabolic quadrilateral and triangular meshes are used to describe the axisymmetric regions of the rotor and stator. Some regions that cannot be modeled with axisymmetric elements (such as the axial rotor root, compressor inlet cylinder ribs, or exhaust cylinder struts) are described.

[0048] Step b: Model using plane stress quadrilateral and triangular meshes, evaluate the thickness based on 2D deformation results and transient scaling, mainly considering the airfoil deformation of the compressor and turbine blades.

[0049] Step c: Model the axial rotor slots and roots of the corresponding rotating components using overlapping planar stress meshes.

[0050] Step d: By applying kinematic constraints and gap element analysis models, the relative contact motion of the rotating component with respect to the disk is simplified.

[0051] Step 105: Perform gap design through the whole machine thermal analysis model, optimize and evaluate the component design parameters of the heavy-duty gas turbine, and obtain the whole machine design parameters of the heavy-duty gas turbine after design iteration.

[0052] In embodiments of the present invention, the method for optimizing and evaluating component design parameters of a heavy-duty gas turbine by using a whole-machine thermal analysis model for clearance design may include:

[0053] Clearance design for transient deformation of the entire two-dimensional stator and rotor; and / or

[0054] The clearance design is performed on the increment of blade tip displacement relative to the blade root or blade groove to assess the risk of blade tip abrasion during hot and cold state changes; and / or

[0055] Transient analysis of 2D rotor and stator components was used to evaluate the effect of transient deformation of the rotor and stator on radial clearance.

[0056] Furthermore, in embodiments of the present invention, the method for designing the clearance for the transient deformation of the entire two-dimensional stator and rotor may include the following steps:

[0057] Step 1: Obtain the basic rotor and stator profiles from the transient analysis of the two-dimensional finite element model.

[0058] Step 2: Perform thermal transient analysis on the nominal parameter changes to generate thermal boundary conditions. The characteristics of the thermal boundary conditions are as follows: the two-dimensional profiles of the rotor and stator are divided into regions, and each region has hot air temperature and heat transfer coefficient values ​​at the beginning and end.

[0059] Step 3: Use the temperature points at each time step obtained from the thermal transient simulation to design the gap for the transient deformation of the two-dimensional stator and rotor.

[0060] Furthermore, in embodiments of the present invention, the method for assessing the risk of blade tip abrasion during cold-hot state changes by designing a clearance for the increment of blade tip displacement relative to blade root or blade groove may include the following steps:

[0061] Step 1: Use the center of the upper side of the leaf root as the reference point for the stationary leaf, the center of the bottom of the wheel as the reference point for the moving leaf, and the front and rear edges as evaluation points for gap analysis.

[0062] Step 2: Design the cold and hot displacement of the tip clearance of different airfoil blades by considering the leading edge, trailing edge, and center point.

[0063] In embodiments of the present invention, the displacement of any airfoil position at any transient time step can be defined by scaling its steady-state displacement obtained from the 3D model calculation. Furthermore, the airfoil displacement can be evaluated and scaled based on the variation patterns of three different types of thermal loads, centrifugal loads, and hot air / air loads under transient conditions. Subsequently, the displacements caused by gas, centrifugal, or thermal loads under steady-state conditions are defined as the linear sum of radial and axial airfoil deflections. These deflections further enhance the corresponding displacements in 2D transient analysis, thereby simplifying the workload of 2D modeling and enabling the evaluation of cold and hot displacements of the tip clearance of different airfoil blades with relatively small computational loads.

[0064] Furthermore, in embodiments of the present invention, the method for evaluating the influence of transient deformation of the rotor and stator on radial clearance using transient analysis of 2D rotor-stator components may include the following steps:

[0065] Step 1051: Establish the hot clearance of the whole machine through hot state and early stage safety margin and dangerous expansion difference analysis.

[0066] Step 1052: The hot gap is formed by considering the thermal expansion coefficient of the material to create a cold gap for the static component under specific working conditions.

[0067] Step 1053: Establish cold tolerance values ​​for components by utilizing cold clearance requirements and component structural integrity requirements.

[0068] Step 1054: Use the cold tolerance values ​​of the components to evaluate the influence of transient deformation of the rotor and stator on the radial clearance.

[0069] Furthermore, in embodiments of the present invention, by combining 2D clearance design at different stages, an effective assessment of the axial-radial clearance during the operation of a heavy-duty gas turbine is achieved.

[0070] Furthermore, in an embodiment of the present invention, after optimizing and evaluating the component design parameters of the heavy-duty gas turbine through a whole-machine thermal analysis model and performing clearance design, the whole-machine design parameters of the heavy-duty gas turbine are obtained after continuous correction through design iteration.

[0071] Furthermore, it should be noted that, in one embodiment of the present invention, the overall design parameters of the heavy-duty gas turbine obtained in step 105 may include blade 2D model design parameters, flow channel 2D model design parameters, combustion thermoacoustic analysis and emission analysis results, combustion operation status analysis results, component 2D thermal state model design parameters, secondary air system and axial force evaluation parameters, overall structural integrity design and evaluation parameters, and determined component materials and process schemes.

[0072] Step 106: Evaluate the overall performance of the heavy-duty gas turbine by evaluating its overall design parameters, and obtain the target overall design parameters of the heavy-duty gas turbine.

[0073] In one embodiment of the present invention, the method for evaluating the overall performance of a heavy-duty gas turbine to obtain the overall design parameters of the target heavy-duty gas turbine may include obtaining the target overall design parameters of the heavy-duty gas turbine based on the performance parameters of the heavy-duty gas turbine under different load conditions.

[0074] Furthermore, in embodiments of the present invention, the performance parameters of the heavy-duty gas turbine under different load conditions include pressure, temperature, relative humidity, various loss coefficients, inlet air flow rate, pressure ratio, isentropic efficiency, combustion efficiency, outlet temperature, fuel type, pressure and temperature, and various bleed air parameters of the secondary air system.

[0075] Furthermore, in embodiments of the present invention, during the process of evaluating the overall performance of the heavy-duty gas turbine's overall design parameters, the design data at non-design points will be updated, and corresponding performance evaluations will be performed.

[0076] Furthermore, in embodiments of the present invention, after obtaining the target overall design parameters of the heavy-duty gas turbine, the manufacturing process design and manufacturing flow design will also be carried out, as well as the design of the instrumentation and control system software, hardware and system, subsystem and partial risk assessment FMEA, manufacturing material specification and finalized general drawing.

[0077] Furthermore, in embodiments of the present invention, after obtaining the target overall design parameters of the heavy-duty gas turbine, the system will also construct overall cost data, formulate evaluation methods, simulate the overall startup and operation envelope, define the verification test requirements and test point design requirements of the heavy-duty gas turbine, and improve performance data, basic design data, and operation concepts.

[0078] The structured design method for heavy-duty gas turbines proposed in this application obtains the required parameters of the heavy-duty gas turbine, generates a one-dimensional model of the heavy-duty gas turbine through IPD data analysis, performs simulation calculations on the heavy-duty gas turbine using the one-dimensional model to obtain performance parameters and component design parameters, establishes a whole-machine thermal analysis model, performs clearance design based on the whole-machine thermal analysis model, optimizes and evaluates the component design parameters of the heavy-duty gas turbine, and obtains the whole-machine design parameters after design iteration. Finally, the whole-machine performance of the heavy-duty gas turbine is evaluated based on the whole-machine design parameters to obtain the target whole-machine design parameters. Therefore, by using the structured design method for heavy-duty gas turbines proposed in this application, the whole-machine performance of the heavy-duty gas turbine is evaluated during the design process to obtain the target whole-machine design parameters, thereby ensuring that the performance of the designed heavy-duty gas turbine meets the usage requirements, reducing design iterations, and improving design efficiency. Meanwhile, this application provides a structured design for each component of the heavy-duty gas turbine, which allows for flexible simulation and modification of each component, facilitating the entire design process of the heavy-duty gas turbine and making the design results of the heavy-duty gas turbine more accurate.

[0079] Example 2

[0080] Figure 2 This is a structural schematic diagram of a structured design apparatus for a heavy-duty gas turbine according to an embodiment of this application, such as... Figure 2 As shown, the device may include:

[0081] Module 201 is used to acquire the required parameters of heavy-duty gas turbines;

[0082] Module 202 is used to obtain a one-dimensional model of a heavy-duty gas turbine through IPD data analysis;

[0083] Simulation module 203 is used to perform simulation calculations on a heavy-duty gas turbine using a one-dimensional model to obtain the performance parameters and component design parameters of the heavy-duty gas turbine.

[0084] Module 204 is established to create a thermal analysis model of the entire machine.

[0085] Design module 205 is used to design gaps through the whole machine thermal analysis model, optimize and evaluate the component design parameters of the heavy-duty gas turbine, and obtain the whole machine design parameters of the heavy-duty gas turbine after design iteration.

[0086] Evaluation module 206 evaluates the overall performance of the heavy-duty gas turbine by assessing its overall design parameters, and obtains the target overall design parameters of the heavy-duty gas turbine.

[0087] The structured design apparatus for heavy-duty gas turbines proposed in this application obtains the required parameters of the heavy-duty gas turbine, generates a one-dimensional model of the heavy-duty gas turbine through IPD data analysis, performs simulation calculations on the heavy-duty gas turbine using the one-dimensional model to obtain performance parameters and component design parameters, establishes a whole-machine thermal analysis model, performs clearance design based on the whole-machine thermal analysis model, optimizes and evaluates the component design parameters of the heavy-duty gas turbine, and obtains the whole-machine design parameters after design iteration. Finally, the whole-machine performance of the heavy-duty gas turbine is evaluated based on the whole-machine design parameters to obtain the target whole-machine design parameters. Therefore, by using the structured design method for heavy-duty gas turbines proposed in this application, the whole-machine performance of the heavy-duty gas turbine is evaluated during the design process to obtain the target whole-machine design parameters, thereby ensuring that the performance of the designed heavy-duty gas turbine meets the usage requirements, reducing design iterations, and improving design efficiency. Meanwhile, this application provides a structured design for each component of the heavy-duty gas turbine, which allows for flexible simulation and modification of each component, facilitating the entire design process of the heavy-duty gas turbine and making the design results of the heavy-duty gas turbine more accurate.

[0088] To implement the above embodiments, this disclosure also proposes a computer storage medium.

[0089] The computer storage medium provided in this embodiment stores an executable program; after the executable program is executed by a processor, it can achieve the following: Figure 1 The method shown.

[0090] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to specific features, structures, materials, or characteristics described in connection with that embodiment or example, which are included in at least one embodiment or example of this application. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0091] Any process or method described in the flowchart or otherwise herein can be understood as representing a module, segment, or portion of code comprising one or more executable instructions for implementing custom logic functions or processes, and the scope of the preferred embodiments of this application includes additional implementations in which functions may be performed not in the order shown or discussed, including substantially simultaneously or in reverse order depending on the functions involved, as should be understood by those skilled in the art to which embodiments of this application pertain.

[0092] Although embodiments of this application have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting this application. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of this application.

Claims

1. A method of structured design of a heavy-duty gas turbine, characterized in that, The method comprises: obtaining demand parameters of a heavy-duty gas turbine; performing data analysis on the demand parameters by IPD to obtain a one-dimensional model of the heavy-duty gas turbine; performing simulation calculation on the heavy-duty gas turbine by using the one-dimensional model to obtain performance parameters and component design parameters of the heavy-duty gas turbine; establishing a whole-machine thermal analysis model; performing gap design by the whole-machine thermal analysis model, and optimizing and evaluating the component design parameters of the heavy-duty gas turbine, to obtain whole-machine design parameters of the heavy-duty gas turbine after design iteration; performing whole-machine performance evaluation on the whole-machine design parameters of the heavy-duty gas turbine, to obtain target whole-machine design parameters of the heavy-duty gas turbine; the establishing of the whole-machine thermal analysis model comprises establishing a two-dimensional finite element model composed of axisymmetric and plane stress elements, the establishing of the two-dimensional finite element model composed of axisymmetric and plane stress elements comprises: combining the stator and the rotor of the whole heavy-duty gas turbine in a general model, and using axisymmetric parabolic quadrilateral and triangular meshes for transient analysis to describe some regions of the rotor and the stator axisymmetric regions that cannot be modeled by axisymmetric elements; modeling by using plane stress quadrilateral and triangular meshes, evaluating thickness according to 2D deformation results and transient scaling, and considering compressor and turbine blade deformation and rotor deformation; modeling the axial rotor groove and root of the corresponding rotating component by using overlapping plane stress meshes; simplifying the relative contact motion of the rotating component relative to the wheel disc by applying kinematic constraints and gap element analysis model.

2. The method of claim 1, wherein, the performing of the gap design by the whole-machine thermal analysis model and the optimizing and evaluating of the component design parameters of the heavy-duty gas turbine comprise: gap design on transient deformation of the whole two-dimensional stator and rotor; and / or gap design on the increment of blade tip displacement relative to the blade root or blade groove to evaluate the risk of blade tip rub in the cold and hot state change process; and / or utilizing transient analysis of the 2D rotor and stator components to evaluate the influence of transient deformation of the rotor and the stator on the radial gap.

3. The method of claim 2, wherein, the gap design on the transient deformation of the whole two-dimensional stator and rotor comprises: obtaining rotor and stator contour lines from transient analysis of the two-dimensional finite element model; performing thermal transient analysis on nominal parameter changes to generate thermal boundary conditions, the thermal boundary conditions being characterized by the following: the two-dimensional contours of the rotor and the stator are divided into regions, and there are thermal air temperature and heat transfer coefficient values at the beginning and end of each region; utilizing temperature points of each time step obtained from thermal transient simulation to perform gap design on transient deformation of the two-dimensional stator and rotor.

4. The method of claim 2, wherein, the gap design on the increment of blade tip displacement relative to the blade root or blade groove to evaluate the risk of blade tip rub in the cold and hot state change process comprises: taking the center of the upper side of the blade root as a stator reference point, taking the center of the bottom of the wheel disc as a rotor reference point, and taking the leading edge and the trailing edge as evaluation points for gap analysis; designing the cold and hot state displacement of the blade tip gap of different airfoil blades by the leading edge, the trailing edge and the center point.

5. The method of claim 2, wherein, the utilizing of transient analysis of the 2D rotor and stator components to evaluate the influence of transient deformation of the rotor and the stator on the radial gap comprises: Establishing the hot gap of the whole machine by hot state and early safety margin and dangerous expansion difference analysis; The hot gap is formed by considering the thermal expansion coefficient of the material to form the cold gap of the rotating and static components under a specific working condition; By the cold gap requirement and the component structure integrity requirement, the cold gap is used to establish the component cold tolerance value; The influence of the transient deformation of the rotor and the stator on the radial gap is evaluated by using the component cold tolerance value.

6. The method of claim 1, wherein, The component design parameters include through flow, blade type design parameters, compressor design parameters, combustion chamber design parameters, rotor system design parameters, secondary air system design parameters.

7. The method of claim 1, wherein, The whole machine performance evaluation of the whole machine design parameters of the heavy gas turbine is performed to obtain the target whole machine design parameters of the heavy gas turbine, which includes obtaining the target whole machine design parameters of the heavy gas turbine according to the performance parameters of the heavy gas turbine under different load working conditions.

8. The method of claim 7, wherein, The performance parameters of the heavy gas turbine under different load working conditions include pressure, temperature, various loss coefficients, inlet air flow, pressure ratio, isentropic efficiency, combustion efficiency, outlet temperature, and various bleed air parameters of the secondary air system.

9. A structural design apparatus for heavy-duty gas turbines, characterized by It comprises: An acquisition module is configured to acquire demand parameters of a heavy gas turbine; A determination module is configured to perform data analysis on the demand parameters by IPD to obtain a one-dimensional model of the heavy gas turbine; A simulation module is configured to perform simulation calculation on the heavy gas turbine by using the one-dimensional model to obtain performance parameters and component design parameters of the heavy gas turbine; An establishment module is configured to establish a whole machine thermal analysis model; A design module is configured to perform gap design by the whole machine thermal analysis model, optimize and evaluate the component design parameters of the heavy gas turbine, and obtain the whole machine design parameters of the heavy gas turbine after design iteration; An evaluation module is configured to perform whole machine performance evaluation on the whole machine design parameters of the heavy gas turbine to obtain the target whole machine design parameters of the heavy gas turbine; The establishment module is configured to establish a two-dimensional finite element model composed of axisymmetric and plane stress elements, The two-dimensional finite element model composed of axisymmetric and plane stress elements comprises: The stator and rotor of the whole heavy gas turbine are combined in a general model, and the transient analysis axisymmetric parabolic quadrilateral and triangular mesh is used to describe some areas of the rotor and stator axisymmetric region that cannot be modeled by axisymmetric elements; The plane stress quadrilateral and triangular mesh is used for modeling, the thickness is evaluated according to the 2D deformation results and transient scaling, and the airfoil deformation of the compressor and turbine blades is considered; The overlapping plane stress mesh is used to model the axial rotor slot and root of the corresponding rotating component; The relative contact motion of the rotating component relative to the disc is simplified by applying kinematic constraints and gap element analysis model.

10. A computer storage medium, wherein, The computer storage medium stores computer executable instructions; the computer executable instructions are executed by the processor to realize the method in any one of claims 1-8.

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