Method and device for realizing aeroelasticity analysis of gas compressor

Abstract

The invention discloses a method and a device for realizing aeroelasticity analysis of a gas compressor, and the embodiment of the invention relates to a method for analyzing aeroelasticity of a gas compressor based on one-dimensional and three-dimensional modeling, which greatly improves the analysis efficiency of the vibration characteristics of a blade under a surge condition. By optimizing the modeling process and reducing the calculation cost, the surge problem of the gas compressor is recognized more quickly, optimization is conducted in the design stage, and the reliability and stability of the gas compressor are improved.

Description

Technical Field

[0001] This application relates to, but is not limited to, the technical fields of aerospace engineering and mechanical engineering, and particularly to a method and device for realizing the aerodynamic elastic analysis of a compressor. Background Art

[0002] A compressor is a key component in the power and energy industries, and its performance and safety are crucial. During the operation of the compressor, a surge phenomenon may occur. The surge phenomenon is a serious safety threat caused by the mismatch between the working ability of the compressor and the downstream system requirements. Surge will cause large-amplitude oscillations of the internal airflow of the compressor, and the blades will bear huge periodic alternating loads. In severe cases, it may lead to blade fracture, affecting the stable operation and structural integrity of the compressor.

[0003] The compressor compresses the gas flowing through it into high-pressure gas by doing work on the gas. Within the range of stable operation, the pressurization ability of the compressor is limited. When the downstream causes the gas pressure to exceed the working ability of the compressor, a flow breakdown will occur inside the compressor, the pressurization ability will drop sharply, and the downstream high-pressure gas will flow back into the compressor, resulting in surge. During the surge process, the airflow in the compressor undergoes large-amplitude oscillations, and the blades will bear huge periodic alternating loads. In severe cases, it will eventually cause blade fracture.

[0004] In the design of compressors, it is usually necessary to reserve a safety margin to prevent the compressor from crossing the stable boundary, thereby preventing the occurrence of surge. However, with the development of technology, modern compressors need to operate at higher pressure ratios, which significantly reduces the stable flow range of the compressor, the operating point is close to the stable boundary, and the safety margin is insufficient. In addition, during the start-stop and rapid acceleration of aeroengines and gas turbines and other transitional states, the compressor still has the risk of crossing the stable boundary. As the blades wear, the stable boundary of the compressor may also shrink. Therefore, it is necessary to evaluate and prevent the possible surge of the compressor at the design stage. By calculating the unsteady forces on the blades during the surge process, evaluating the risk of blade fatigue fracture, and optimizing the design to make the compressor blades have a certain anti-surge ability.

[0005] The aerodynamic elastic problem of the compressor is closely related to the surge phenomenon. Studying the relationship between the two is of great significance for improving the performance and safety of the compressor. Summary of the Invention

[0006] This application provides a method and device for realizing the aerodynamic elastic analysis of a compressor, which can quickly analyze and evaluate the aeroelastic problems under surge conditions at the early stage of compressor design.

[0007] An embodiment of this application provides a method for realizing the aerodynamic elastic analysis of a compressor, including: A three-dimensional computational fluid dynamics (CFD) model of the compressor, a one-dimensional CFD model of the upstream and downstream pipelines of the compressor, and a finite element method (FEM) model of the compressor blades are established; The one-dimensional CFD model is used to trigger surge, and the three-dimensional CFD model of the compressor calculates the unsteady aerodynamic force information on the blade surface, and the unsteady aerodynamic force information is used as the input of the FEM model of the blade to extract the key data of the compressor; After the compressor exhibits a surge phenomenon, the aeroelastic response of the blades during the surge process is analyzed, including forced vibration analysis and flutter analysis.

[0008] In an exemplary instance, the three-dimensional computational fluid dynamics (CFD) model adopts a single-channel model.

[0009] In an exemplary instance, the three-dimensional computational fluid dynamics (CFD) model adopts a full-cycle modeling method.

[0010] In an exemplary instance, the analysis of the aeroelastic response of the blades during the surge process includes: After the compressor enters surge, based on the unsteady aerodynamic force data on the blade surface, the aeroelastic response of the blades is analyzed. Through the forced vibration analysis, the dynamic aerodynamic force excitation borne by the blades during the surge process is calculated to determine whether there is a high-cycle fatigue risk; through the flutter analysis, the feedback effect of the aerodynamic force at different stages of the surge on the blades is evaluated, and the aerodynamic damping of the blades is calculated to determine whether flutter instability may occur.

[0011] In an exemplary instance, when performing the forced vibration analysis of the blades, the modal superposition method is used; the modal superposition method includes: The modal analysis of the blades is performed through the FEM model to extract the natural modal information of the blades; combining the unsteady aerodynamic force information obtained from the three-dimensional CFD calculation as the excitation input, the modal superposition method is used to calculate the vibration response of the blades under the action of the surge aerodynamic force.

[0012] In an exemplary instance, the key data includes: surge loop, blade surface pressure distribution, surge frequency.

[0013] In an exemplary instance, the unsteady aerodynamic force information on the blade surface includes: pressure distribution, aerodynamic force change.

[0014] The embodiment of the present application also provides a computer-readable storage medium storing computer-executable instructions for executing the method for realizing aeroelastic analysis of a compressor according to any one of the above.

[0015] Another embodiment of the present application provides a computer device, including a memory and a processor. Among them, the following instructions that can be executed by the processor are stored in the memory: steps for executing the method for realizing the aeroelastic analysis of the compressor described in any one of the above.

[0016] Another embodiment of the present application provides a device for realizing the aeroelastic analysis of the compressor, including: a first establishment module, a second establishment module, a third establishment module, a processing module, and an analysis module; among them, The first establishment module is used to establish a three-dimensional CFD model of the compressor; The second establishment module is used to establish a one-dimensional CFD model of the upstream and downstream pipelines of the compressor; The third establishment module is used for the FEM model of the compressor blades; The processing module is used to trigger surge using the one-dimensional CFD model, calculate the unsteady aerodynamic force information on the blade surface using the three-dimensional CFD model of the compressor, and use the unsteady aerodynamic force information as the input of the FEM model of the blade to extract the key data of the compressor; The analysis module is used to analyze the aeroelastic response of the blades during the surge process after the surge phenomenon occurs in the compressor, including forced vibration analysis and flutter analysis.

[0017] The method for realizing the aeroelastic analysis of the compressor provided by the embodiment of the present application is a method for aeroelastic analysis of the compressor based on one-dimensional combined with three-dimensional modeling, which greatly improves the analysis efficiency of the vibration characteristics of the blades under surge conditions. By optimizing the modeling process and reducing the calculation cost, the surge problem of the compressor is identified more quickly, and optimization is carried out in the design stage, improving the reliability and stability of the compressor.

[0018] Other features and advantages of the present application will be described below, and some of them will become obvious from the description of the specification, or be understood by implementing the present application. The objectives and other advantages of the present application can be achieved and obtained through the structures specifically pointed out in the specification, claims, and drawings. Description of the Drawings

[0019] The drawings are used to provide a further understanding of the technical solutions of the present application, and constitute a part of the specification. They are used together with the embodiments of the present application to explain the technical solutions of the present application, and do not constitute a limitation to the technical solutions of the present application.

[0020] Figure 1 It is a schematic flowchart of the method for realizing the aeroelastic analysis of the compressor in the embodiment of the present application; Figure 2 It is a schematic diagram of the principle of the process for realizing the aeroelastic analysis of the compressor in the embodiment of the present application; Figure 3 It is a schematic diagram of the composition structure of a typical compressor in the embodiment of the present application; Figure 4(a) is a schematic diagram of a single-channel three-dimensional CFD calculation model of the combined compressor shown in the embodiment of the present application; Figure 3 Figure 4(b) is a schematic diagram of a CFD model when performing flutter analysis on the stator S1 of the combined compressor shown in the embodiment of the present application; Figure 3 Figure 4(c) is a schematic diagram of another CFD model when performing flutter analysis on the stator S1 of the combined compressor shown in the embodiment of the present application; Figure 3 Figure 5 is a schematic diagram of a one-dimensional / three-dimensional coupling model in the embodiment of the present application; Figure 6 is a schematic diagram of the surge dynamic process in the embodiment of the present application; Figure 7 is a schematic diagram of the composition structure of the device for realizing the aeroelastic analysis of the compressor in the embodiment of the present application. Detailed implementation manners

[0021] To make the objectives, technical solutions and advantages of the present application clearer and more understandable, the embodiments of the present application will be described in detail below with reference to the accompanying drawings. It should be noted that, without conflict, the embodiments and features in the embodiments of the present application can be combined with each other arbitrarily.

[0022] To facilitate the understanding of the present application, the present application will be described more comprehensively below with reference to the relevant accompanying drawings. Embodiments of the present application are shown in the accompanying drawings. However, the present application can be implemented in many different forms and is not limited to the embodiments described herein. On the contrary, these embodiments are provided to make the disclosure of the present application more thorough and comprehensive.

[0023] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by those skilled in the technical field to which the present application belongs. The terms used in the specification of the present application herein are only for the purpose of describing specific embodiments and are not intended to limit the present application.

[0024] It can be understood that the terms "first" and "second" used in the present application are only for descriptive purposes and cannot be construed as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, features defined with "first" and "second" may explicitly or implicitly include at least one of such features. In the description of the present application, "a plurality of" means at least two, such as two, three, etc., unless otherwise specifically defined.

[0025] ​​​It can be understood that for the "connection" in the following embodiments, if there is a transfer of electrical signals or data between the connected circuits, modules, units, etc., it should be understood as "electrical connection", "communication connection", etc.

[0026] As used herein, the singular forms "a", "an" and "the" may also include the plural forms unless the context clearly dictates otherwise. It should also be understood that the terms "comprise / include" or "have" etc. specify the presence of the stated features, wholes, steps, operations, components, parts or combinations thereof, but do not preclude the possibility of the presence or addition of one or more other features, wholes, steps, operations, components, parts or combinations thereof. At the same time, the term "and / or" used in this specification includes any and all combinations of the related listed items.

[0027] The aeroelastic problems of a compressor involve the interaction between fluid and solid. Especially under unstable operating conditions, the complex unsteady three-dimensional characteristics of the air flow will affect the vibration modes of the blades. To accurately capture these flow field characteristics, decoupling methods and fluid-structure interaction methods are usually used for aeroelastic analysis. Both of these methods rely on three-dimensional numerical simulation of the flow field around the blades to obtain the aerodynamic forces acting on the blades. However, when analyzing the aeroelastic problems during the surge process, the surge characteristics of the compressor are affected by the characteristics of the entire compression system. Therefore, it is necessary to model the pipes and cavities upstream and downstream of the compressor during numerical simulation. Considering the complex structure of the compression system, the computational cost of three-dimensional modeling of the entire system is huge. Moreover, re-modeling is required for each design iteration and it cannot be carried out quickly during the design stage.

[0028] Due to the high time cost of numerical simulation of surge, there is relatively little research on the aeroelastic problems of compressors under surge conditions in academia and engineering applications. Compared with the high-frequency compressor flow instability characteristics such as rotating stall or rotating instability, surge shows an obvious low-frequency large-scale phenomenon. The frequency of the former is of the same order as the compressor speed, and the duration of a complete characteristic is generally in the millisecond level, while the period of surge is generally in the second level. Therefore, under the same conditions, the computational cost of numerical simulation for a surge cycle increases greatly. Taking the commonly used three-dimensional numerical simulation method in current academia and engineering - unsteady Reynolds-averaged method (URANS) as an example, the calculation time is generally in the order of several months or even up to a year. This time cost greatly limits the analysis and evaluation of the surge resistance of compressor blades during the design stage.

[0029] To quickly analyze and evaluate aeroelastic problems under surge conditions and improve the analysis and evaluation capabilities of anti-surge capabilities, an embodiment of the present application provides a method for realizing aeroelastic analysis of a compressor. By combining three-dimensional computational fluid dynamics (CFD) modeling and one-dimensional system modeling, the flow field characteristics around the key blades of the compressor can be quickly obtained, thereby performing aeroelastic analysis. Combining Figure 1 and Figure 2 as shown, it may include: Step 100: Establish a three-dimensional CFD model of the compressor.

[0030] A compressor usually consists of one or more stages, and each stage includes a rotor (R1) and a stator (S1). According to the flow path direction, compressors can be divided into axial flow, centrifugal, or axial flow - centrifugal combined types. As Figure 3 shown, it shows the flow path structure of a combined compressor with one stage of axial flow and one stage of centrifugal, including: the first-stage axial flow rotor R1, the first-stage axial flow stator S1, the centrifugal impeller IMP, and the radial vane diffuser RD.

[0031] In the embodiment of the present application, for the core part of the compressor containing blades, three-dimensional CFD modeling is adopted. To reduce the computational amount of surge simulation, in the embodiment of the present application, a single-channel model can be adopted, that is, a single-channel model is used for surge simulation. Fig. 4(a) shows Figure 3 the single-channel three-dimensional CFD calculation model of the combined compressor in, that is to say, the three-dimensional CFD model does not perform a full circumferential modeling of the entire blade row, but only establishes a single blade flow path (single channel) and applies periodic boundary conditions to simulate the flow characteristics of the entire blade row. In the embodiment of the present application, the three-dimensional CFD model of the compressor is used to simulate the three-dimensional flow characteristics inside the compressor, especially the aerodynamic force changes under surge conditions. Through the three-dimensional CFD model, the unsteady aerodynamic force distribution on the blade surface can be accurately calculated, providing the necessary input data for subsequent blade forced vibration analysis, flutter analysis, and aeroelastic analysis.

[0032] In another embodiment, under specific working conditions, such as when it is necessary to analyze the blade flutter under specific working conditions, full circumferential modeling can be performed on the relevant blades, as shown in Fig. 4(b) and Fig. 4(c). That is to say, under specific working conditions, the three-dimensional CFD model adopts a full-cycle modeling method instead of a single-channel model. This means that the CFD simulation range expands from a single blade flow path to the entire blade row (360° modeling) to more accurately simulate the interaction between blades and flutter characteristics.

[0033] In an exemplary instance, the aeroelastic problems of a compressor generally include forced vibration of blades and blade flutter. The three-dimensional CFD models also vary. For the case of forced vibration of blades, the CFD model is the same as the model required for compressor surge simulation, that is, a single-channel model is sufficient. If blade flutter analysis is to be performed for specific operating conditions during the surge process, then full-annulus modeling of the corresponding blades is required. Figure 4(b) shows Figure 3 the CFD model for the stator S1 of the combined compressor during flutter analysis, and the specific implementation of the flutter analysis is introduced below.

[0034] Under surge conditions, the flow field characteristics of the compressor are complex. The three-dimensional CFD model established through step 100 accurately simulates the aerodynamic force distribution on the blade surface.

[0035] Step 101: Establish a one-dimensional CFD model of the upstream and downstream pipelines of the compressor.

[0036] In order to reduce the computational cost, in the embodiments of the present application, the upstream and downstream components are simplified into ideal pipeline and cavity structures for dimensionality reduction modeling, as Figure 5 shown. This model simplifies the complex three-dimensional structure into a one-dimensional pipeline by extracting key geometric parameters, and combines with the three-dimensional CFD model to form a one-dimensional combined three-dimensional hybrid simulation model. Through the method of the embodiments of the present application, the analysis speed of aeroelastic problems under surge conditions is significantly improved, and it helps with rapid iteration during the design phase. How to establish the one-dimensional CFD model of the upstream and downstream pipelines of the compressor does not limit the protection scope of the present application and will not be elaborated here. For example, reference can be made to the prior application with the invention name "A method and device for predicting the stable boundary of a compressor" (application number CN202310263302.7).

[0037] In the embodiments of the present application, the main role of the one-dimensional CFD model is to simulate the flow characteristics of the upstream and downstream pipelines and cavities, and analyze the dynamic behavior of the compressor under surge conditions from a system-level perspective. Through the one-dimensional CFD model, it helps to reduce the computational cost and couple with the three-dimensional CFD model to achieve a more complete surge simulation.

[0038] Through step 100 and step 101, as Figure 3 shown, a fluid domain model of the compressor is established, that is, an aerodynamic simulation model is established.

[0039] Surge not only affects the internal flow field of the compressor, but is also affected by the upstream and downstream pipelines and cavities. The one-dimensional CFD system model established through step 101 better expresses the dynamic coupling effect between the compressor and the upstream and downstream pipelines and cavities.

[0040] Step 102: Establish a finite element (FEM) model of the compressor blades.

[0041] The aeroelasticity problem involves the coupling of the fluid domain and the solid domain, and it is necessary to model the two separately. The fluid domain model has been established in Step 100 and Step 101, and Step 102 mainly focuses on modeling the solid domain. As Figure 3 shown, a solid domain simulation model is established through Step 102.

[0042] The embodiments of the present application aim to emphasize the simplification of the fluid domain modeling, and do not limit the modeling method of the solid domain. Any possible solid domain modeling method can be applied to the embodiments of the present application.

[0043] The FEM model of the blade established through Step 102 is used to analyze the vibration characteristics of the blade, accurately describe the interaction between the fluid and the structure (fluid-structure coupling), and evaluate the dynamic response of the blade under complex flow conditions such as surging.

[0044] Step 103: Use a one-dimensional CFD model to trigger surging, calculate the unsteady aerodynamic force information on the blade surface by a three-dimensional CFD model of the compressor, and use the unsteady aerodynamic force information as the input of the FEM model of the blade to extract the key data of the compressor.

[0045] In an exemplary instance, the unsteady aerodynamic force information on the blade surface may include but is not limited to, for example: pressure distribution, aerodynamic force change, etc.

[0046] In an exemplary instance, the key data may include but is not limited to, for example: surge loop, blade surface pressure distribution, surge frequency, etc.

[0047] Through Step 103, use a one-dimensional CFD model to trigger surging, and simulate the dynamic changes of the system-level flow rate and pressure. Use a three-dimensional CFD model to calculate the unsteady aerodynamic force information on the blade surface, and capture the unsteady aerodynamic force information such as the transient aerodynamic force distribution on the blade during surging. Use the unsteady aerodynamic force information as the input of the FEM model to analyze the actual load borne by the blade during surging and extract the key data of the compressor (such as surge loop, blade surface pressure distribution, aerodynamic force change, etc.).

[0048] In one embodiment, use a one-dimensional CFD model to apply surging trigger conditions (such as adjusting the valve opening) to drive the compressor into the surging state, record the flow rate, pressure, and surging cycle trajectory (i.e., surge loop (SurgeLoop)) at the inlet and outlet of the compressor to describe the macroscopic characteristics of surging; and calculate the unsteady aerodynamic force information on the blade surface by a three-dimensional CFD model to analyze the influence of surging on the blade; the unsteady aerodynamic force information (such as the change of pressure with time) is input into the FEM model of the blade to calculate the forced vibration, flutter stability, and fatigue risk of the blade.

[0049] In one embodiment, a one-dimensional CFD model is used to provide an overall background for the occurrence of surge, determine the triggering conditions of surge, the flow-pressure variation, and the main characteristics of surge. Through the FEM model of the blade, relying on the CFD calculation results obtained from the one-dimensional CFD model, the structural stability and lifespan of the blade are further analyzed. The three-dimensional CFD model serves as a bridge between the two, providing both local flow details for the one-dimensional CFD model and aerodynamic load inputs for the FEM model.

[0050] Figure 5 FIG. is a schematic diagram of the one-dimensional / three-dimensional coupling model in the embodiments of the present application. In one embodiment, by adjusting Figure 5 the valve opening degree in, the process of the compressor approaching surge can be simulated, and the variation process of each physical parameter can be obtained, obtaining the system-level parameters obtained by using the one-dimensional CFD model and the aerodynamic force parameters on the blade surface obtained by using the three-dimensional CFD model. In one embodiment, the relationship between the pressure ratio and the flow rate at the inlet and outlet of the compressor can be used as a judgment criterion. When a closed loop is formed in the pressure ratio-flow rate relationship diagram (such as Figure 6 the historical trajectory forms a circle in the compressor pressure ratio and flow rate relationship diagram shown), and when a stage with a negative flow rate appears, it indicates that the compressor has experienced surge. This closed loop is called the surge loop, indicating that the compressor has experienced a complete surge cycle. Figure 6 FIG. is the relationship curve between the flow rate (Q) and the pressure ratio (ΔP) during the compressor surge process, where the closed circular loop (surge loop) represents the periodic oscillation of the flow parameters of the compressor in the surge state. The part where the flow rate becomes negative indicates that during the surge process, the compressor experiences a reverse flow phenomenon, that is, high-pressure gas enters the compressor in the reverse direction, affecting the system stability. The size and shape of the closed loop reflect the severity of the surge, including the surge period, the range of flow rate fluctuations, the pressure change situation, etc.

[0051] Step 104: After the compressor experiences surge, analyze the aeroelastic response of the blade during the surge process, including forced vibration analysis and flutter analysis.

[0052] In step 104, after the compressor enters surge, based on the unsteady aerodynamic force data of the blade extracted in step 103, analyze the aeroelastic response of the blade. Through forced vibration analysis, calculate the dynamic aerodynamic force excitation borne by the blade during the surge process, and judge whether there is a risk of high-cycle fatigue (HCF); through flutter analysis, evaluate the feedback effect of the aerodynamic force at different stages of surge on the blade, calculate the aerodynamic damping of the blade, and judge whether flutter instability is likely to occur.

[0053] In an exemplary example, during the surge process, the pressure fluctuation on the blade surface is intense. Therefore, it is necessary to analyze the vibration response of the blade under the action of unsteady aerodynamic force, that is, forced vibration analysis, including: Extract the pressure data on the blade surface and input it into the solid domain simulation model. That is, the unsteady aerodynamic forces (such as the blade surface pressure distribution and aerodynamic loads) calculated by the three-dimensional CFD model are used as inputs and applied to the FEM model of the blade to analyze the forced vibration, flutter, and structural response of the blade, so as to calculate the dynamic deformation and stress distribution of the blade. In this way, through forced vibration analysis, it is possible to evaluate whether the blade will fail due to high-cycle fatigue and optimize the blade structure.

[0054] In one embodiment, different solid domain modeling methods also have an impact on the calculation speed. In an exemplary example, in order to reduce the computational amount, when performing forced vibration analysis of the blade, preferably, the modal superposition method is used. That is, first, the modal analysis of the blade is carried out by FEM to extract the inherent modal information (natural frequency and vibration mode) of the blade, and then the unsteady aerodynamic force information calculated by the three-dimensional CFD is combined as the excitation input, and the modal superposition method is used to calculate the vibration response of the blade under the surge aerodynamic force.

[0055] In an exemplary example, flutter is a self-excited vibration phenomenon that may cause the blade structure to be unstable. Especially in the reverse flow stage of surge, the aerodynamic environment of the blade is very different from the normal working condition. During surge, the compressor may experience a reverse flow phenomenon (i.e., the gas flows from the outlet to the inlet). At this time, the blade may flutter. Since flutter involves the interaction between blades, full circumferential modeling is required (as shown in Fig. 4(b)). By extracting the surge calculation results, the flow field data is obtained at a specific time point and input into the flutter analysis model to evaluate the stability of the blade.

[0056] In one embodiment, when the compressor experiences a reverse flow phenomenon, the internal aerodynamic characteristics are significantly different from the normal working condition. However, traditional compressor designs (including anti-flutter designs) usually only consider the forward flow. Therefore, in the reverse flow stage and other stages during surge, the blade may face the risk of flutter. Flutter is a vibration phenomenon in which all blades vibrate in a specific mode along the circumference, and the characteristic is that there is a fixed phase angle between adjacent blades. Since flutter involves the coordinated vibration of adjacent blades, the embodiment of the present application performs full circumferential modeling on the target blade row, as shown in Fig. 4(b) of the accompanying drawings.

[0057] The time scale of flutter is much smaller than the surge period. Therefore, when performing flutter analysis, the embodiment of the present application extracts the interface flow field information of a specific stage from the surge simulation calculation results and uses it as the boundary condition of the flutter analysis model. For example, in the model of Fig. 4(b), the flutter analysis uses a single-channel model plus a full circumferential axial stator (S1), and its model boundary is the R1 inlet and the RD outlet. In order to ensure the accuracy of the boundary conditions, the embodiment of the present application extracts the interface flow field information of the R1 inlet and the R outlet from the surge simulation calculation results (Fig. 4(a) of the accompanying drawings) and applies it to the flutter analysis model.

[0058] In addition, in the embodiments of the present application, the flutter analysis model may also only include the full - circumference axial - flow stator (S1), as shown in Fig. 4(c). In this case, the embodiments of the present application extract the flow - field information of the inlet - outlet interface of the single - channel axial - flow stator (S1) in the surge calculation result (Fig. 4(a)) and use it as the boundary condition of the full - circumference axial - flow stator (S1). In this way, the flutter characteristics are analyzed under different modeling methods, and an accurate assessment of the blade flutter risk is ensured.

[0059] Through step 103 and step 104, aerodynamic elastic analysis is realized, that is, the flow field of the required working conditions is obtained by using a one - dimensional and three - dimensional combined model, including: extracting the unsteady pressure constant on the blade surface, using the unsteady aerodynamic force information as the input of the blade's FEM model to analyze the vibration of the blade; and extracting the flow - field boundary information as needed to carry out further fluid - structure combination calculations.

[0060] Compared with the traditional full three - dimensional modeling and simulation method, the method for realizing the aerodynamic elastic analysis of a compressor provided by the embodiments of the present application, on the one hand, adopts one - dimensional combined with three - dimensional coupled modeling, greatly reducing the calculation cost, making the surge simulation faster and more accurate. The calculation efficiency is significantly improved. The traditional full three - dimensional modeling calculation time may be as long as several months, while the embodiments of the present application can complete the analysis within several weeks. On the other hand, the embodiments of the present application realize rapid iterative optimization of the blade design, improve the surge - resistance ability of the blade, especially suitable for rapid optimization in the design stage. And by simplifying the modeling, engineers can evaluate various design schemes faster and optimize the shape, material or structural parameters of the blade. On the one hand, through one - dimensional combined with three - dimensional hybrid modeling, the surge phenomena of multi - stage axial - flow, centrifugal or mixed compressors are accurately simulated, realizing the capture of deep surge, reverse flow and other unsteady flow characteristics, providing a reliable basis for the optimization of the compressor, especially suitable for complex surge working conditions.

[0061] The method for realizing the aerodynamic elastic analysis of a compressor provided by the embodiments of the present application is a compressor aerodynamic elastic analysis method based on one - dimensional combined with three - dimensional modeling, greatly improving the analysis efficiency of the blade vibration characteristics in the case of surge. By optimizing the modeling process and reducing the calculation cost, the surge problem of the compressor is identified more quickly and optimized in the design stage, improving the reliability and stability of the compressor.

[0062] On the one hand, in the method for realizing the aerodynamic elastic analysis of a compressor provided by the embodiments of the present application, the dimensionality reduction treatment is adopted for the compressor upstream and downstream pipeline cavity systems, and in a way of combining one - dimensional and three - dimensional models, such as Figure 5As shown, the flow field characteristics during the surge dynamic process are effectively obtained, and aeroelastic analysis is carried out based on these flow field characteristics, thereby reducing the computational complexity and ensuring the accuracy of surge analysis, providing reliable data support for the evaluation of blade vibration characteristics and stability. Combining Figure 6 It can be seen that a one-dimensional CFD model is used to perform dimensionality reduction processing on the upstream and downstream pipelines and cavities, avoiding high-computation three-dimensional modeling of the entire system, such as Figure 6 As shown, the surge process is intuitively demonstrated through the flow rate - pressure ratio curve (Q-ΔP curve). Through the coupling of the one-dimensional and three-dimensional CFD models, the unsteady aerodynamic force information inside the compressor during the surge process is effectively extracted, without directly performing three-dimensional modeling of the entire system, significantly reducing the computational amount. The surge circle data directly provides the flow characteristics of surge occurrence, providing input data for subsequent forced vibration analysis and flutter analysis of the blade, ensuring the accuracy of the calculation.

[0063] On the other hand, in the method for realizing compressor aeroelastic analysis provided by the embodiments of the present application, the aeroelastic analysis (blade vibration analysis) depends on the flow field information calculated by the one-dimensional combined with three-dimensional CFD simulation method. It should be noted that any method of extracting flow field information based on the one-dimensional combined with three-dimensional CFD method and using it as the input for aeroelastic analysis falls within the protection scope of the present application. This method is applicable to different compressor structures, improving the simulation efficiency while ensuring the calculation accuracy, enabling a more comprehensive study of the blade vibration problem under surge conditions.

[0064] In one aspect, in the method for realizing compressor aeroelastic analysis provided by the embodiments of the present application, there is no specific limitation on the modeling method of the solid domain, that is, any finite element method (FEM) applicable to blade structure modeling or other solid domain calculation methods can be used. In practical applications, different modeling methods can be selected according to the analysis requirements to adapt to the aeroelastic analysis requirements under different working conditions. This flexible modeling method makes the present invention have strong versatility and can be applicable to a variety of compressor design scenarios.

[0065] The present application also provides a computer-readable storage medium storing computer-executable instructions for executing the method for realizing compressor aeroelastic analysis described in any one of the above.

[0066] The present application further provides a computer device including a memory and a processor, wherein the memory stores the following instructions executable by the processor: for executing the steps of the method for realizing compressor aeroelastic analysis described in any one of the above.

[0067] Figure 7 It is a schematic diagram of the composition structure of the device for realizing compressor aeroelastic analysis in the embodiments of the present application, such asFigure 7 As shown, it may include: a first establishment module, a second establishment module, a third establishment module, a processing module, and an analysis module; wherein, The first establishment module is used to establish a three-dimensional CFD model of the compressor; The second establishment module is used to establish a one-dimensional CFD model of the upstream and downstream pipelines of the compressor; The third establishment module is used for the FEM model of the compressor blades; The processing module is used to trigger surge using the one-dimensional CFD model, calculate the unsteady aerodynamic force information on the blade surface using the three-dimensional CFD model of the compressor, and use the unsteady aerodynamic force information as the input of the FEM model of the blade to extract the key data of the compressor; The analysis module is used to analyze the aeroelastic response of the blades during surge after the compressor exhibits a surge phenomenon, including forced vibration analysis and flutter analysis.

[0068] In an exemplary instance, the third establishment module can be used to: perform modal analysis on the blades by FEM using the modal superposition method, extract modal information and input it into the calculation model, so as to obtain the FEM simulation model of the compressor blades.

[0069] In an exemplary instance, the processing module can be used to: apply surge trigger conditions (such as adjusting the valve opening) using the one-dimensional CFD model, drive the compressor into the surge state, record the inlet and outlet flow rates, pressures, and surge cycles of the compressor, and describe the macroscopic characteristics of surge; calculate the unsteady aerodynamic force information on the blade surface through the three-dimensional CFD model for analyzing the impact of surge on the blades; the unsteady aerodynamic force information is input into the FEM model of the blades for calculating the forced vibration, flutter stability, and fatigue risk of the blades.

[0070] In an exemplary instance, the analysis module can be used to: after the compressor enters surge, extract the unsteady aerodynamic force data of the blades and analyze the aeroelastic response of the blades: through forced vibration analysis, calculate the dynamic aerodynamic force excitation borne by the blades during surge, and judge whether there is a high-cycle fatigue (HCF) risk; through flutter analysis, evaluate the feedback effect of the aerodynamic force at different stages of surge on the blades, calculate the aerodynamic damping of the blades, and judge whether flutter instability is likely to occur.

[0071] The device for realizing aeroelastic analysis of a compressor provided by the embodiments of the present application is a method for aeroelastic analysis of a compressor based on one-dimensional combined with three-dimensional modeling, which greatly improves the analysis efficiency of the vibration characteristics of the blades under surge conditions. By optimizing the modeling process and reducing the calculation cost, the surge problem of the compressor is identified more quickly, and optimization is carried out in the design stage, improving the reliability and stability of the compressor.

[0072] Although the embodiments disclosed in this application are as above, the content described is only the embodiments adopted for the convenience of understanding this application and is not intended to limit this application. Any person skilled in the art within the scope of this application can make any modifications and changes in the form and details of the implementation without departing from the spirit and scope disclosed in this application. However, the scope of patent protection of this application shall still be subject to the scope defined by the appended claims.

Claims

1. A method for realizing the aeroelastic analysis of a compressor, characterized in that Including: Establishing a three-dimensional computational fluid dynamics (CFD) model of the compressor, a one-dimensional CFD model of the upstream and downstream pipelines of the compressor, and a finite element method (FEM) model of the compressor blades; Triggering surge using the one-dimensional CFD model, calculating the unsteady aerodynamic force information on the blade surface using the three-dimensional CFD model of the compressor, and using the unsteady aerodynamic force information as the input of the FEM model of the blade to extract the key data of the compressor; After the compressor exhibits a surge phenomenon, analyzing the aeroelastic response of the blades during the surge process, including forced vibration analysis and flutter analysis.

2. The method according to claim 1, wherein, The three-dimensional computational fluid dynamics (CFD) model adopts a single-channel model.

3. The method according to claim 1, wherein, The three-dimensional computational fluid dynamics (CFD) model adopts a full-cycle modeling method.

4. The method according to claim 1, wherein The analysis of the aeroelastic response of the blades during the surge process includes: After the compressor enters surge, based on the unsteady aerodynamic force data on the blade surface, analyzing the aeroelastic response of the blades; through the forced vibration analysis, calculating the dynamic aerodynamic force excitation borne by the blades during the surge process, and determining whether there is a high-cycle fatigue risk; through the flutter analysis, evaluating the feedback effect of the aerodynamic forces at different stages of surge on the blades, calculating the aerodynamic damping of the blades, and determining whether flutter instability may occur.

5. The method according to claim 4, wherein When performing the forced vibration analysis of the blades, the mode superposition method is used; The mode superposition method includes: Performing a modal analysis on the blades through the FEM model to extract the natural modal information of the blades; Combining the unsteady aerodynamic force information obtained from the three-dimensional CFD calculation as the excitation input, and using the mode superposition method to calculate the vibration response of the blades under the action of the surge aerodynamic forces.

6. The method according to any one of claims 1-4, wherein, The key data includes: surge loop, blade surface pressure distribution, surge frequency.

7. The method according to any one of claims 1-4, wherein, The unsteady aerodynamic force information on the blade surface includes: pressure distribution, aerodynamic force change.

8. A computer-readable storage medium storing computer-executable instructions for executing the method for realizing aeroelastic analysis of a compressor according to any one of claims 1-7.

9. A computer device, comprising a memory and a processor, wherein, Instructions executable by a processor are stored in the memory: for performing the steps of the method for realizing aeroelastic analysis of a compressor according to any one of claims 1-7.

10. An apparatus for realizing the aerodynamic elastic analysis of a compressor, characterized in that, Including: A first establishment module, a second establishment module, a third establishment module, a processing module, and an analysis module; wherein, The first establishment module is used for establishing a three-dimensional CFD model of the compressor; The second establishment module is used for establishing a one-dimensional CFD model of the upstream and downstream pipelines of the compressor; The third establishment module is used for the FEM model of the compressor blades; The processing module is used for triggering surge using the one-dimensional CFD model, calculating the unsteady aerodynamic force information on the blade surface using the three-dimensional CFD model of the compressor, and using the unsteady aerodynamic force information as the input of the FEM model of the blade to extract the key data of the compressor; The analysis module is used for analyzing the aeroelastic response of the blades during the surge process after the compressor exhibits a surge phenomenon, including forced vibration analysis and flutter analysis.

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