Method for designing meridian molded line on inner side of turbomachinery cylinder based on flutter suppression

Abstract

The invention discloses a turbomachinery air cylinder inner side meridian molded line design method based on flutter suppression, and relates to the technical field of turbomachinery blade flutter suppression. Obtaining a radial basis function model; the radial basis function model is used for predicting the minimum aerodynamic damping value of the turbomachinery blade; the design parameters of the meridian profile on the inner side of the turbomachinery air cylinder serve as optimization variables, the maximum minimum aerodynamic damping value of a blade corresponding to the design parameters predicted by the radial basis function model serves as an optimization target, iterative optimization is conducted through an intelligent optimization algorithm, and the optimal design parameters are obtained; the design parameters represent radial distances from a plurality of points arranged at equal intervals in the axial direction between the front end position of a meridian molded line inlet section on the inner side of the turbomachinery air cylinder and the front edge position of a blade to a hub; and according to the optimal design parameters, the meridian molded line of the inner side of the turbomachinery air cylinder is determined. According to the method, the design aerodynamic performance of the meridian molded line on the inner side of the turbomachinery air cylinder is improved, and the flutter suppression capacity of the blade is enhanced.

Description

Technical Field

[0001] This application relates to the field of turbine blade flutter suppression technology, and in particular to a method for designing the inner meridional profile of a turbine cylinder based on flutter suppression. Background Technology

[0002] Currently, turbine machinery is continuously evolving towards higher loads and higher efficiency. Furthermore, with the increasing proportion of new energy sources, higher peak-shaving and frequency regulation requirements are being placed on turbine machinery such as steam turbines and gas turbines. Against this backdrop, the demands for optimized turbine machinery design are becoming increasingly stringent. The blade flutter problem caused by unsteady fluid-structure interaction is becoming increasingly prominent. As a key component of turbine machinery, the reliability of blades under complex and variable operating conditions is of paramount importance.

[0003] However, most existing flutter suppression methods rely on the active detuning of the blade itself, neglecting the influence of the cylinder meridional profile. The cylinder meridional profile affects tip clearance and channel flow field, thus impacting blade flutter stability. Non-uniform profiles disrupt stable tip leakage flow and may alter the shock wave structure under transonic conditions. This can lead to a phase reversal of the unsteady aerodynamic forces acting on the vibrating blade, transforming the positive aerodynamic damping that suppresses vibration into negative damping that triggers flutter. Circumferentially asymmetrical profiles subject each blade to a periodically changing aerodynamic environment, and the resulting forced vibrations may reduce the system's flutter margin. Therefore, a reasonable cylinder meridional profile is crucial for blade flutter suppression during the design and manufacturing process. Summary of the Invention

[0004] Therefore, it is necessary to provide a method for designing the inner meridional profile of a turbine cylinder based on chatter suppression to address the aforementioned technical problems.

[0005] The following technical solution is adopted in this specification: This specification provides a method for designing the inner meridional profile of a turbine mechanical cylinder based on chatter suppression, including: Obtain the radial basis function model; the radial basis function model is used to predict the minimum aerodynamic damping value of turbine blades; Using the design parameters of the inner meridional profile of the turbine cylinder as optimization variables and the radial basis function model predicting the minimum aerodynamic damping value of the blade corresponding to the design parameters as the optimization objective, the optimal design parameters are obtained through iterative optimization using an intelligent optimization algorithm. The design parameters represent the radial distances from multiple points equidistant along the axial direction between the front end position of the inlet section of the inner meridional profile of the turbine cylinder and the leading edge position of the blade to the hub. Based on the optimal design parameters, the meridional profile of the inner side of the turbine cylinder is determined.

[0006] Optionally, the process of constructing the radial basis function model includes: Multiple sample design parameters covering the turbine machinery operating space are generated using Latin hypercube sampling. By connecting the points corresponding to each sample design parameter according to the spline curve, the cylinder curve corresponding to each sample design parameter is obtained; Based on the cylinder curve corresponding to each sample design parameter, calculate the minimum aerodynamic damping value of all inter-blade phase angles of the corresponding cylinder curve; Based on various sample design parameters and corresponding minimum aerodynamic damping values, the initial radial basis function model is trained to obtain the radial basis function model.

[0007] Optionally, based on the cylinder curve corresponding to each sample design parameter, the minimum aerodynamic damping value of all inter-blade phase angles of the corresponding cylinder curve is calculated, including: For any sample design parameters; based on the cylinder curve corresponding to the sample design parameters, the blades of the turbomachinery are meshed using finite element methods, and modal vibration analysis of the blades is performed using structural dynamics to obtain the vibration frequency, circular frequency, and displacement coefficient of each blade. For any given blade, the influence of the vibration of neighboring blades on that blade is calculated based on the blade's vibration frequency, and the influence coefficient of that blade is determined. Calculate the modal force of the blade based on its influence coefficient; Based on the relationship between the aerodynamic power and modal force of the blade, as well as the modal force, vibration circular frequency and vibration displacement coefficient of the blade, the aerodynamic power of the blade is determined. The aerodynamic damping of the blade is obtained by normalizing the aerodynamic work through vibration kinetic energy. The minimum aerodynamic damping of the turbine blades corresponding to the sample design parameters is determined as the minimum aerodynamic damping value of all inter-blade phase angles of the corresponding cylinder curve.

[0008] Optionally, the aerodynamic work of the blade is determined based on the relationship between the aerodynamic power and modal force of the blade, as well as the modal force, vibration circular frequency, and vibration displacement coefficient of the blade, including: Substituting the blade's modal force, vibration circular frequency, and vibration displacement coefficient into the relationship between the blade's aerodynamic power and modal force, we obtain the blade's aerodynamic power. The aerodynamic work is obtained by integrating the aerodynamic power of the blade over one vibration cycle. The relationship between the aerodynamic power and modal force of the blade is as follows: ; in, For a moment pneumatic power, The vibration displacement coefficient, The angular frequency of vibration, For a moment Modal forces.

[0009] Optionally, the intelligent optimization algorithm is a genetic algorithm; using the design parameters of the inner meridional profile of the turbine cylinder as the optimization variable, and the radial basis function model predicting the minimum aerodynamic damping value of the blade corresponding to the design parameters as the optimization objective, the intelligent optimization algorithm iteratively searches for the optimal design parameters, including: Determine the initial population; each individual in the initial population represents the design parameters of the inner meridional profile of the turbine cylinder. The initial population is input into the radial basis function model to obtain the minimum aerodynamic damping value of the blade corresponding to the design parameters, and the minimum aerodynamic damping value of the blade corresponding to the design parameters is used as the fitness value. The initial population is updated based on the fitness value using crossover and mutation probabilities. Based on the updated population, the fitness value is recalculated until the aerodynamic damping meets the requirements for suppressing blade flutter. The design parameters corresponding to the minimum aerodynamic damping value that meets the requirements are then determined as the optimal design parameters.

[0010] This specification provides a device for designing the inner meridional profile of a turbine machine cylinder based on chatter suppression, including: The acquisition module is used to acquire the radial basis function model; the radial basis function model is used to predict the minimum aerodynamic damping value of turbine blades. The optimization module uses the design parameters of the inner meridional profile of the turbine cylinder as optimization variables and the minimum aerodynamic damping value of the blade corresponding to the design parameters predicted by the radial basis function model as the optimization objective. It iterative optimization is performed through intelligent optimization algorithm to obtain the optimal design parameters. The design parameters represent the radial distances from multiple points equidistant along the axial direction between the front end position of the inlet section of the inner meridional profile of the turbine cylinder and the leading edge position of the blade to the hub. The design module is used to determine the meridional profile inside the turbine cylinder based on the optimal design parameters.

[0011] This specification provides a computer-readable storage medium storing a computer program that, when executed by a processor, implements the above-described method for designing the inner meridional profile of a turbine mechanical cylinder based on chatter suppression.

[0012] This specification provides a computer device, including a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the program, it implements the above-described method for designing the inner meridional profile of a turbine mechanical cylinder based on chatter suppression.

[0013] The above-mentioned technical solutions adopted in this specification can achieve the following beneficial effects: In the turbine cylinder inner meridional profile design method based on flutter suppression provided in this specification, the radial distances from multiple points equidistantly set along the axial direction between the front end of the turbine inlet section and the leading edge of the blade to the hub are used as optimization variables. The optimization objective is to maximize the minimum aerodynamic damping value of the blade corresponding to the design parameters. The design parameters are optimized through an intelligent optimization algorithm. The inner meridional profile of the cylinder corresponding to the optimal design parameters obtained by this method improves the aerodynamic performance of the meridional profile inside the turbine cylinder, makes the flow field in the blade tip clearance and channel more stable, and thus effectively suppresses blade flutter, thereby enhancing the flutter suppression capability of the blade.

[0014] In addition, the introduction of a radial basis function model during the optimization of the design parameters of the inner meridional profile of the cylinder greatly shortens the prediction time of blade flutter, improves prediction efficiency, and effectively enhances the efficiency and adaptability of profile optimization. Attached Figure Description

[0015] The accompanying drawings, which are included to provide a further understanding of this application and form part of this application, illustrate exemplary embodiments and are used to explain this application, but do not constitute an undue limitation of this application. In the drawings:

[0016] Figure 1 A schematic flowchart illustrating a method for designing the inner meridional profile of a turbine machine cylinder based on flutter suppression, as provided in this specification. Figure 2 This specification provides a schematic diagram of a cylinder curve. Figure 3 This is a schematic diagram of blade distribution provided in this specification; Figure 4 This is a schematic diagram of the structure of a radial basis function model provided in this specification; Figure 5 A flowchart for optimizing design parameters is provided in this specification; Figure 6 This specification provides a schematic diagram of a computer device for implementing a method for designing the inner meridional profile of a turbine cylinder based on chatter suppression. Detailed Implementation

[0017] To make the objectives, technical solutions, and advantages of this specification clearer, the technical solutions of this application will be clearly and completely described below in conjunction with specific embodiments and corresponding drawings. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. All other embodiments obtained by those skilled in the art based on the embodiments in this specification without creative effort are within the scope of protection of this application.

[0018] In addition, existing methods for optimizing the inner meridional profile of cylinders require extensive design calculations, resulting in high costs for flutter calculations and limitations in optimization efficiency, making it difficult to meet actual engineering needs.

[0019] Therefore, this invention provides a method for designing the inner meridional profile of a turbine cylinder based on flutter suppression. By rationally adjusting the inner meridional profile, the flow field in the blade tip clearance and channel is made more stable, thereby effectively suppressing blade flutter. Furthermore, a radial basis function (RBF) model is introduced during the optimization of the inner meridional profile parameters. Compared with traditional methods, this significantly shortens the blade flutter prediction time, improves prediction efficiency, and effectively enhances the efficiency and adaptability of profile optimization.

[0020] The technical solutions provided by the various embodiments of this application are described in detail below with reference to the accompanying drawings.

[0021] Figure 1 This is a flowchart illustrating a method for designing the inner meridional profile of a turbine cylinder based on chatter suppression, as described in this specification. The method includes the following steps: S101, Obtain the radial basis function model; the radial basis function model is used to predict the minimum aerodynamic damping value of turbine blades.

[0022] In one embodiment, the process of constructing a radial basis function model includes the following steps: S201 generates multiple sample design parameters covering the turbine machinery operating space through Latin Hypercube Sampling (LHS).

[0023] The sample design parameters represent the radial distances from the hub to multiple points equidistantly spaced along the axial direction between the front end of the turbine inlet section and the leading edge of the blade. Taking the inlet section of a gas turbine compressor cylinder as an example, the cylinder curve is referenced. Figure 2 First, two fixed points are determined at the front end of the inlet section and at the leading edge of the blade, respectively. The radial distance from the fixed point at the front end of the inlet section to the hub is denoted as... H in The radial distance from the fixed point on the leading edge of the blade to the hub is denoted as...H b Several points are equidistantly positioned along the axial direction at the inlet section location. The positions of these points are determined by their radial coordinates. The radial coordinates of these points are completely independent and range from [value missing]. H in arrive H b Within a range. Taking 8 points as an example, specific design parameters... The mathematical expression can be represented by the following formula:

[0024] (1) in, For the first The radial distance from each point to the wheel hub; .

[0025] S202, connect the points corresponding to each sample design parameter according to the spline curve to obtain the cylinder curve corresponding to each sample design parameter.

[0026] For any sample design parameters, spline curves are used to connect the points corresponding to the sample design parameters to generate a complete cylinder curve.

[0027] S203, based on the cylinder curve corresponding to each sample design parameter, calculate the minimum aerodynamic damping value of all inter-blade phase angles of the corresponding cylinder curve.

[0028] In one embodiment, the minimum aerodynamic damping value of all inter-blade phase angles of the corresponding cylinder curve is calculated based on the cylinder curve corresponding to each sample design parameter, including the following steps: S301, for any sample design parameters; based on the cylinder curve corresponding to the sample design parameters, perform finite element mesh generation on the blades of the turbomachinery, and perform modal vibration analysis of the blades according to the structural dynamics method to obtain the vibration frequency, vibration circular frequency and vibration displacement coefficient of each blade.

[0029] Optionally, mode shapes of various orders can also be obtained. Mode shapes are inherent properties of the blade, including but not limited to bending vibration and torsional vibration.

[0030] In one embodiment, using a fluid dynamics solution method, steady aerodynamic calculations are first performed to obtain a multi-channel aerodynamic flow field as the initial field for subsequent calculations. Then, the intermediate blades are allowed to move periodically according to the mode shapes and frequencies obtained through structural dynamics, acquiring the unsteady aerodynamic flow field of the oscillating blades. After obtaining the unsteady flow field results, the aerodynamic damping of the local blades is solved. The unsteady flow field results include the surface pressure of the blades.

[0031] S302, For any blade, calculate the influence of the vibration of neighboring blades on the blade based on the blade's vibration frequency, and determine the influence coefficient of the blade.

[0032] The aerodynamic damping at all inter-blade phase angles is obtained using the influence coefficient method. Specifically, the inter-blade phase angle is first calculated. : (2) In the formula This refers to the number of nodes; N b This represents the number of leaves.

[0033] In one embodiment, such as Figure 3 As shown, taking 5 blades as an example, this illustrates the use of the influence coefficient method in solving aerodynamic damping at different inter-blade phase angles.

[0034] The middle blade, number 0, is the blade under study. (See figure.) C p ( j , k This indicates that when all blades vibrate in phase... j No. 1 blade pair k The influence of blade number. When the inter-blade phase angle of vibration between adjacent blades is fixed at... σ hour, j No. 1 blade pair k The influence of blade number 1 should be phase-transformed, denoted as . According to Figure 3 The numbering method shown represents the sum of the influence coefficients of each blade on the middle blade (number 0) under the traveling wave vibration mode:

[0035] (3) in, The influence coefficient of blade number 0.

[0036] Considering the symmetry of the geometric structure, n The effect of blade # on blade #0 is equal to the effect of blade #0 on - n The effect of blade number 1, namely: (4) At this point, formula (3) can be rewritten as: (5) By calculating the modal forces using the aforementioned influence coefficients, the aerodynamic damping distribution under all inter-blade phase angles can be reconstructed.

[0037] S303, calculate the modal force of the blade based on its influence coefficient.

[0038] (6) in, For the blade at time modal forces, The angular frequency is given by Re(·) in rad·s, where Re(·) represents the operation of taking the real part, and i is the imaginary unit. It is a surface micro-element.

[0039] S304. Based on the relationship between the aerodynamic power and modal force of the blade, as well as the modal force, vibration circular frequency and vibration displacement coefficient of the blade, determine the aerodynamic power of the blade.

[0040] Optionally, the blade at time pneumatic power for: (7) In the formula, For the blade during vibration at time The surface pressure is obtained from unsteady aerodynamic calculations. Let be the normal vector of the blade surface. The velocity vector of the vibration is obtained by finite element modal analysis, and the specific calculation is expressed by the following formula: (8) In the formula, For modal vibration modes, The vibration displacement coefficient is the ratio of the maximum displacement calculated numerically to the maximum displacement in the mode shape. All of the above parameters were obtained through numerical calculations.

[0041] time Modal force MF ( t The aerodynamic force is calculated from the surface integral of the projection of the aerodynamic force onto the mode shape, as shown in the following formula: (9) Combining equations (7) and (9), the relationship between the aerodynamic power and modal force of the blade is obtained as follows: (10) In one embodiment, the aerodynamic work of the blade is determined based on the relationship between the blade's aerodynamic power and modal force, as well as the blade's modal force, vibration circular frequency, and vibration displacement coefficient. This includes: substituting the blade's modal force, vibration circular frequency, and vibration displacement coefficient into the relationship between the blade's aerodynamic power and modal force to obtain the blade's aerodynamic power; integrating the blade's aerodynamic power over one vibration cycle to obtain the aerodynamic work; the formula for calculating the aerodynamic work is: (11) S305, by normalizing the aerodynamic work through vibration kinetic energy, the aerodynamic damping of the blade is obtained.

[0042] The formula for calculating aerodynamic damping is: (12) (13) It is vibrational kinetic energy. It's the density of the leaves. The amplitude of the local unit is used as the criterion for judging whether the blade flutters, based on the aerodynamic damping calculated by formulas (12) and (13). If the aerodynamic damping is greater than 0, the blade will not flutter; if it is less than 0, flutter will occur.

[0043] S306, the minimum aerodynamic damping of the turbine blades corresponding to the sample design parameters is determined as the minimum aerodynamic damping value of all inter-blade phase angles of the corresponding cylinder curve.

[0044] S204. Based on various sample design parameters and corresponding minimum aerodynamic damping values, the initial radial basis function model is trained to obtain the radial basis function model.

[0045] Based on the above method for calculating the minimum aerodynamic damping value, a blade aerodynamic damping calculation model can be constructed, using cylinder curve parameters. As a variable, the minimum aerodynamic damping is determined by the inter-blade phase angles under the corresponding cylinder parameters. Let the target parameter be denoted as . .

[0046] Based on multiple sample design parameters and the corresponding minimum aerodynamic damping value The data is then preprocessed, including normalization and denoising, to ensure data quality and model training stability.

[0047] After data preprocessing, an RBF model is constructed. This model is a multi-layer fully connected deep neural network, and its structure is as follows: Figure 4 As shown, the model consists of an input layer, a hidden layer, and an output layer. The input is the design parameters mentioned above, and the output is the minimum aerodynamic damping of all inter-blade phase angles corresponding to the profile. The basis functions used in this embodiment of the RBF model are as follows: (14) In the formula, x This is the input vector of the neural network; c i For the first i The center point of each unit basis function; | x−c i | is the input vector xDistances to each center point; The smoothing factor of the Gaussian function can be calculated using the following formula: (15) In the formula, The scaling factor is a preset value, which is set to 1.0-2.0 in this embodiment.

[0048] The output layer of the RBF neural network is a linear weighted sum of the outputs of the hidden layer nodes, and the final output can be expressed by the following formula: (16) In the formula, This represents the weight of the corresponding hidden layer node.

[0049] Finally, the initialized sample design parameters and the corresponding minimum aerodynamic damping value are substituted into formula (16) to solve for the weights of the hidden nodes, thus completing the training of the RBF model.

[0050] S102, taking the design parameters of the inner meridional profile of the turbine cylinder as the optimization variable and the minimum aerodynamic damping value of the blade corresponding to the design parameters predicted by the radial basis function model as the optimization objective, the optimal design parameters are obtained by iterative optimization through intelligent optimization algorithm; the design parameters represent the radial distance from multiple points equidistantly set along the axial direction between the front end position of the inlet section of the inner meridional profile of the turbine cylinder and the leading edge position of the blade to the hub.

[0051] In one embodiment, the intelligent optimization algorithm is a genetic algorithm. Using the design parameters of the inner meridional profile of the turbine cylinder as optimization variables and the radial basis function model predicting the minimum aerodynamic damping value of the blade corresponding to the design parameters as the optimization objective, the intelligent optimization algorithm iteratively searches for optimal design parameters, including: determining an initial population; each individual in the initial population represents a design parameter of the inner meridional profile of the turbine cylinder; inputting the initial population into the radial basis function model to obtain the minimum aerodynamic damping value of the blade corresponding to the design parameters, and using the minimum aerodynamic damping value of the blade corresponding to the design parameters as a fitness value; updating the initial population based on the fitness value using crossover and mutation probabilities; recalculating the fitness value based on the updated population until the aerodynamic damping meets the blade flutter suppression requirements, and determining the design parameters corresponding to the minimum aerodynamic damping value that meets the requirements as the optimal design parameters.

[0052] Specifically, based on the aforementioned RBF model, a suitable optimization algorithm is used to optimize the model's predicted values. The mathematical description of this optimization problem is as follows:

[0053] (17) This embodiment introduces a genetic algorithm to optimize the cylinder curve parameters corresponding to minimum aerodynamic damping. Specifically, in this embodiment, the optimization variable is the design parameter, and the objective function is minimum aerodynamic damping. The optimization process is described in detail below. Figure 5 As shown, Figure 5 The flowchart for optimizing design parameters specifically includes:

[0054] ① First, set an appropriate initial population size based on the number of parameters of the specific cylinder curve to be optimized; ② Input the initial population into the trained RBF model for iterative prediction; ③ Evaluate the fitness of the current population and select appropriate crossover probability, mutation probability, and maximum number of iterations; ④ After the convergence curve stabilizes, determine whether the termination condition is met, i.e. whether the aerodynamic damping meets the requirements for suppressing blade flutter. If it is met, the optimization ends; otherwise, return to step ① until the objective function, i.e., the aerodynamic damping, meets the requirements, and the optimization ends, obtaining the optimal design parameters.

[0055] S103, determine the meridional profile inside the turbine cylinder based on the optimal design parameters.

[0056] Based on the optimal design parameters, the points corresponding to the optimal design parameters are connected by spline curves to obtain the inner meridional profile of the turbine cylinder with good chatter suppression effect.

[0057] The execution subject of the method provided by this invention can be a server, which can be a server set up on a business platform, or a device such as a desktop computer or laptop computer that can execute the solution in this specification.

[0058] When applying the meridional profile design method for the inner side of a turbine cylinder based on chatter suppression provided in this manual, it is not necessary to consider... Figure 1 The steps shown are executed in sequence. The specific execution order of each step can be determined as needed, and this manual does not impose any restrictions on it.

[0059] The above describes a method for designing the inner meridional profile of a turbine machine cylinder based on chatter suppression, provided by one or more embodiments of this specification. Based on the same idea, this specification also provides a corresponding device for designing the inner meridional profile of a turbine machine cylinder based on chatter suppression, which includes: The acquisition module is used to acquire the radial basis function model; the radial basis function model is used to predict the minimum aerodynamic damping value of turbine blades. The optimization module uses the design parameters of the inner meridional profile of the turbine cylinder as optimization variables and the minimum aerodynamic damping value of the blade corresponding to the design parameters predicted by the radial basis function model as the optimization objective. It iterative optimization is performed through intelligent optimization algorithm to obtain the optimal design parameters. The design parameters represent the radial distances from multiple points equidistant along the axial direction between the front end position of the inlet section of the inner meridional profile of the turbine cylinder and the leading edge position of the blade to the hub. The design module is used to determine the meridional profile inside the turbine cylinder based on the optimal design parameters.

[0060] Specific limitations regarding the design device for the inner meridional profile of a turbine machine cylinder based on chatter suppression can be found in the limitations of the design method for the inner meridional profile of a turbine machine cylinder based on chatter suppression described above, and will not be repeated here. Each module in the aforementioned design device for the inner meridional profile of a turbine machine cylinder based on chatter suppression can be implemented entirely or partially through software, hardware, or a combination thereof. These modules can be embedded in or independent of the processor in a computer device, or stored in the memory of a computer device as software, so that the processor can call and execute the operations corresponding to each module.

[0061] This specification also provides a computer-readable storage medium storing a computer program that can be used to execute the above-described... Figure 1 A method for designing the inner meridional profile of a turbine cylinder based on flutter suppression is provided.

[0062] This instruction manual also provides Figure 6 The schematic diagram of the computer device shown is as follows: Figure 6 At the hardware level, the computer device includes a processor, internal bus, network interface, memory, and non-volatile memory, and may also include other hardware required for business operations. The processor reads the corresponding computer program from the non-volatile memory into memory and then runs it to achieve the above-mentioned functions. Figure 1 A method for designing the inner meridional profile of a turbine cylinder based on flutter suppression is provided.

[0063] Those skilled in the art will understand that all or part of the processes in the methods of the above embodiments can be implemented by a computer program instructing related hardware. The computer program can be stored in a non-volatile computer-readable storage medium, and when executed, it can include the processes of the embodiments of the methods described above. Any references to memory, storage, databases, or other media used in the embodiments provided in this application can include at least one of non-volatile and volatile memory. Non-volatile memory can include read-only memory (ROM), magnetic tape, floppy disk, flash memory, or optical storage, etc. Volatile memory can include random access memory (RAM) or external cache memory. By way of illustration and not limitation, RAM can be in various forms, such as static random access memory (SRAM) or dynamic random access memory (DRAM), etc.

[0064] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

Claims

1. A method for designing the inner meridional profile of a turbine mechanical cylinder based on flutter suppression, characterized in that, include: Obtain the radial basis function model; the radial basis function model is used to predict the minimum aerodynamic damping value of turbine blades; Using the design parameters of the inner meridional profile of the turbine cylinder as optimization variables and the radial basis function model predicting the minimum aerodynamic damping value of the blade corresponding to the design parameters as the optimization objective, the optimal design parameters are obtained through iterative optimization using an intelligent optimization algorithm. The design parameters represent the radial distances from multiple points equidistant along the axial direction between the front end position of the inlet section of the inner meridional profile of the turbine cylinder and the leading edge position of the blade to the hub. Based on the optimal design parameters, the meridional profile of the inner side of the turbine cylinder is determined.

2. The method according to claim 1, characterized in that, The process of constructing a radial basis function model includes: Multiple sample design parameters covering the turbine machinery operating space are generated using Latin hypercube sampling. By connecting the points corresponding to each sample design parameter according to the spline curve, the cylinder curve corresponding to each sample design parameter is obtained; Based on the cylinder curve corresponding to each sample design parameter, calculate the minimum aerodynamic damping value of all inter-blade phase angles of the corresponding cylinder curve; Based on various sample design parameters and corresponding minimum aerodynamic damping values, the initial radial basis function model is trained to obtain the radial basis function model.

3. The method according to claim 2, characterized in that, Based on the cylinder curve corresponding to each sample design parameter, calculate the minimum aerodynamic damping value for all inter-blade phase angles of the corresponding cylinder curve, including: For any sample design parameters; based on the cylinder curve corresponding to the sample design parameters, the blades of the turbomachinery are meshed using finite element methods, and modal vibration analysis of the blades is performed using structural dynamics to obtain the vibration frequency, circular frequency, and displacement coefficient of each blade. For any given blade, the influence of the vibration of neighboring blades on that blade is calculated based on the blade's vibration frequency, and the influence coefficient of that blade is determined. Calculate the modal force of the blade based on its influence coefficient; Based on the relationship between the aerodynamic power and modal force of the blade, as well as the modal force, vibration circular frequency and vibration displacement coefficient of the blade, the aerodynamic power of the blade is determined. The aerodynamic damping of the blade is obtained by normalizing the aerodynamic work through vibration kinetic energy. The minimum aerodynamic damping of the turbine blades corresponding to the sample design parameters is determined as the minimum aerodynamic damping value of all inter-blade phase angles of the corresponding cylinder curve.

4. The method according to claim 3, characterized in that, Based on the relationship between the aerodynamic power and modal force of the blade, as well as the modal force, vibration circular frequency, and vibration displacement coefficient of the blade, the aerodynamic work of the blade is determined, including: Substituting the blade's modal force, vibration circular frequency, and vibration displacement coefficient into the relationship between the blade's aerodynamic power and modal force, we obtain the blade's aerodynamic power. The aerodynamic work is obtained by integrating the aerodynamic power of the blade over one vibration cycle. The relationship between the aerodynamic power and modal force of the blade is as follows: ； in, For a moment pneumatic power, The vibration displacement coefficient, The angular frequency of vibration, For a moment Modal forces.

5. The method according to claim 1, characterized in that, The intelligent optimization algorithm is a genetic algorithm; it uses the design parameters of the inner meridional profile of the turbine cylinder as the optimization variable, and the radial basis function model predicts that the minimum aerodynamic damping value of the blade corresponding to the design parameters is maximized as the optimization objective. The intelligent optimization algorithm iteratively searches for the optimal design parameters, including: Determine the initial population; each individual in the initial population represents the design parameters of the inner meridional profile of the turbine cylinder. The initial population is input into the radial basis function model to obtain the minimum aerodynamic damping value of the blade corresponding to the design parameters, and the minimum aerodynamic damping value of the blade corresponding to the design parameters is used as the fitness value. The initial population is updated based on the fitness value using crossover and mutation probabilities. Based on the updated population, the fitness value is recalculated until the aerodynamic damping meets the requirements for suppressing blade flutter. The design parameters corresponding to the minimum aerodynamic damping value that meets the requirements are then determined as the optimal design parameters.

6. A device for designing the inner meridional profile of a turbine mechanical cylinder based on flutter suppression, characterized in that, include: The acquisition module is used to acquire the radial basis function model; the radial basis function model is used to predict the minimum aerodynamic damping value of turbine blades. The optimization module uses the design parameters of the inner meridional profile of the turbine cylinder as optimization variables and the minimum aerodynamic damping value of the blade corresponding to the design parameters predicted by the radial basis function model as the optimization objective. It iterative optimization is performed through intelligent optimization algorithm to obtain the optimal design parameters. The design parameters represent the radial distances from multiple points equidistant along the axial direction between the front end position of the inlet section of the inner meridional profile of the turbine cylinder and the leading edge position of the blade to the hub. The design module is used to determine the meridional profile inside the turbine cylinder based on the optimal design parameters.

7. A computer-readable storage medium, characterized in that, The storage medium stores a computer program, which, when executed by a processor, implements the method described in any one of claims 1 to 5.

8. A computer device, characterized in that, It includes a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the program to implement the method described in any one of claims 1 to 5.

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