Heavy-duty gas turbine compressor aeroelasticity vibration structure coupling design method and system

Abstract

The application provides a heavy-duty gas turbine compressor aerodynamic strength vibration structure coupling design method and system. The method comprises the following steps: determining first flow-through parameters and first blade profile parameters of the compressor according to aerodynamic performance indexes; optimizing the first flow-through parameters and the first blade profile parameters of the compressor according to structural manufacturing and assembly indexes and the aerodynamic performance indexes, to obtain second flow-through parameters and second blade profile parameters of the compressor; optimizing blade root geometric parameters of the compressor according to strength vibration life indexes and the structural manufacturing and assembly indexes, and simultaneously designing and optimizing geometric parameters of a blade locking structure of the compressor, to obtain optimized blade root geometric parameters of the compressor and the geometric parameters of the blade locking structure; and designing the heavy-duty gas turbine compressor based on the second flow-through parameters and the second blade profile parameters. The technical scheme provided by the application improves the design efficiency, optimizes the performance balance, and reduces the design cost.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of compressor design, in particular to a heavy-duty gas turbine compressor aerodynamic strength vibration structure coupling design method and system. BACKGROUND

[0002] As a high-efficiency and clean energy conversion device, heavy-duty gas turbines play an extremely important role in the energy field. As one of the core components, the compressor is mainly responsible for compressing air to provide high-pressure air for the combustion chamber, thereby improving combustion efficiency and power generation efficiency. However, the design of the compressor faces many challenges. First, the compressor has large flow rate and multiple stages, making aerodynamic matching design extremely difficult. In order to meet the high-efficiency operation requirements of the gas turbine, the compressor needs to achieve efficient air compression in a complex aerodynamic environment while ensuring the stability and uniformity of the airflow. Secondly, the compressor blades are subjected to complex excitation sources during operation, including airflow excitation and mechanical vibration, which can easily cause resonance or flutter problems, and high requirements are placed on the strength and vibration characteristics of the blades. In addition, from the perspective of structural design, the compressor blades need to have good machinability and dismountability to meet the manufacturing and maintenance requirements, while also balancing cost and performance.

[0003] In the prior art, the design of the compressor usually involves multiple professional fields, including aerodynamic design, strength design and structural design. These design works are often carried out by different design teams, and the design requirements and emphases of each professional are different. For example, aerodynamic design mainly focuses on the efficiency and performance of air flow, strength design focuses on the strength and vibration characteristics of the blades, and structural design needs to consider the machinability, dismountability and cost of the blades. The design between each professional needs to be iterated repeatedly, and each iteration needs to re-evaluate and adjust the design scheme, which greatly prolongs the design cycle. In addition, due to the difficulty in balancing the requirements of each professional, the design scheme often cannot meet the requirements of aerodynamic performance, strength vibration life, machinability and dismountability, etc. at the same time, resulting in insufficient performance optimization and large resource consumption. These problems seriously restrict the design efficiency and performance improvement of heavy-duty gas turbine compressors, therefore, a new design method is urgently needed to solve these problems. SUMMARY

[0004] The present application provides a heavy-duty gas turbine compressor aerodynamic strength vibration structure coupling design method and system to at least solve the technical problem that the prior art seriously restricts the design efficiency and performance improvement of heavy-duty gas turbine compressors.

[0005] The first aspect embodiment of the present application provides a heavy-duty gas turbine compressor aerodynamic strength vibration structure coupling design method, which comprises:

[0006] Acquire design requirements of a heavy-duty gas turbine compressor, and decompose the design requirements into aerodynamic performance indexes, strength-vibration life indexes, and structure-manufacturing assembly indexes;

[0007] Determine first through-flow parameters and first blade profile parameters of the compressor according to the aerodynamic performance indexes and the strength-vibration life indexes and a preset aerodynamic-strength-vibration coupling design process;

[0008] Optimize the first through-flow parameters and first blade profile parameters according to the structure-manufacturing assembly indexes and the aerodynamic performance indexes and a preset aerodynamic-structure coupling design process, to obtain second through-flow parameters and second blade profile parameters of the compressor;

[0009] Optimize blade root geometry parameters of the compressor according to the strength-vibration life indexes and the structure-manufacturing assembly indexes and a preset strength-structure coupling design process, and simultaneously design and optimize geometry parameters of a blade locking structure of the compressor, to obtain optimized blade root geometry parameters and geometry parameters of the blade locking structure of the compressor;

[0010] Design the heavy-duty gas turbine compressor based on a hub ratio, an aspect ratio, flow passage coordinates, and a blade axial position in the second through-flow parameters, a blade number, a blade profile chord length, a blade profile thickness, an installation angle, and inlet-outlet geometric angles in the second blade profile parameters, the optimized blade root geometry parameters, and the geometry parameters of the blade locking structure.

[0011] The first through-flow parameters and the second through-flow parameters both include a hub ratio, an aspect ratio, flow passage coordinates, and a blade axial position.

[0012] The first blade profile parameters and the second blade profile parameters both include a blade number, a blade profile chord length, a blade profile thickness, an installation angle, and inlet-outlet geometric angles.

[0013] Preferably, the aerodynamic-strength-vibration coupling design process includes:

[0014] Determine a reasonable range of the first through-flow parameters and blade profile parameters of the compressor according to the aerodynamic performance indexes, the strength-vibration life indexes, and a preset through-flow design and vibration analysis coupling optimization chord length sub-process.

[0015] Determine a first blade number of the compressor according to the reasonable range of the first through-flow parameters and blade profile parameters of the compressor and a preset blade profile design, blade root design, and vibration analysis coupling optimization blade number sub-process.

[0016] Determine initial blade profile parameters of the compressor according to the reasonable range of the blade profile parameters of the compressor and a preset blade profile design and vibration analysis coupling optimization design blade profile geometry parameters sub-process, wherein the initial blade profile parameters include a blade profile chord length, a blade profile thickness, an installation angle, and inlet-outlet geometric angles.

[0017] According to the preset blade vibration and high-cycle fatigue life checking and optimization sub-process, it is judged whether the initial blade type parameters of the compressor meet the aerodynamic performance indicators and the strength vibration life indicators, if yes, the initial blade type parameters of the compressor are taken as the first blade type parameters of the compressor, otherwise, the initial blade type parameters of the compressor are optimized according to the preset blade type geometric parameter optimization sub-process until the initial blade type parameters of the compressor meet the aerodynamic performance indicators and the strength vibration life indicators.

[0018] Further, the preset through-flow design and vibration analysis coupled optimization chord length sub-process comprises:

[0019] Step F1: based on the aerodynamic performance indicators, through-flow design is carried out to determine the preliminary through-flow parameters of the compressor;

[0020] Step F2: based on the preliminary through-flow parameters of the compressor, blade preliminary modeling design is carried out to determine the reasonable range of blade type parameters of the compressor, wherein the reasonable range of blade type parameters comprises blade chord length;

[0021] Step F3: preliminary vibration / flutter analysis is carried out on the initial blade type formed by the reasonable range of blade type parameters to determine the vibration frequency avoidance rate margin of the key vibration mode of the initial blade type and the main excitation source and the flutter equivalent frequency margin of the key vibration mode;

[0022] Step F4: it is judged whether the absolute value of the difference between the vibration frequency avoidance rate margin of the key vibration mode of the initial blade type and the main excitation source and the vibration frequency avoidance rate margin in the strength vibration life indicators is less than or equal to a preset first difference threshold value, and whether the absolute value of the difference between the flutter equivalent frequency margin of the key vibration mode and the flutter equivalent frequency margin in the strength vibration life indicators is less than or equal to a preset first difference threshold value, if yes, the chord length is adjusted based on a preset chord length adjustment scheme, and returns to step F2, otherwise, the chord length of the initial blade type of the compressor is taken as the optimized chord length, the preliminary through-flow parameters are taken as the first through-flow parameters, and the blade type parameter range corresponding to the optimized chord length is taken as the reasonable range of blade type parameters.

[0023] Further, the preset blade type design, blade root design and vibration analysis coupled optimization blade number sub-process comprises:

[0024] Based on the first through-flow parameters, the reasonable range of blade type parameters and the blade root strength design requirements, a blade root preliminary design result is obtained, and based on the blade root preliminary design result, a range of initial blade numbers is obtained;

[0025] Vibration analysis is performed on the initial airfoil to evaluate the natural frequency of the key mode and the avoidance rate of the excitation source of the front and rear rows of blades. Then, based on the natural frequency of the key mode and the avoidance rate of the excitation source of the front and rear rows of blades, the adjustment amount of the number of front and rear rows of blades is determined to obtain the adjusted number of front and rear rows of blades of the compressor.

[0026] Based on the adjusted number of front and rear rows of blades, the initial airfoil of the compressor is analyzed for aerodynamic performance, and the aerodynamic performance analysis results are obtained.

[0027] The number of the first blades of the compressor is determined based on the aerodynamic performance analysis results and the preliminary blade root design results.

[0028] Furthermore, the preset blade profile design and vibration analysis coupled optimization design of blade profile geometric parameters sub-process includes:

[0029] Step A1: Based on the reasonable range of the compressor blade parameters, perform vibration / flutter analysis on the compressor blades and enter the preset blade geometry parameter optimization sub-process;

[0030] Step A2: Perform aerodynamic performance analysis based on the reasonable range of the compressor blade profile parameters to obtain the blade profile geometric parameter constraints for frequency tuning optimization of the compressor blades, and then enter the preset blade profile geometric parameter optimization sub-process.

[0031] Furthermore, the preset blade geometry parameter optimization sub-process includes:

[0032] Step B1: Adjust the key section airfoil parameters of the blade based on the airfoil geometry constraints and the aerodynamic performance indicators;

[0033] Step B2: Perform vibration / flutter check on the adjusted blades. If the strength vibration life index is not met, return to step B1; if it is met, proceed to step B3.

[0034] Step B3: Perform aerodynamic performance checks on the blade after adjusting the key section airfoil parameters, and determine whether the change in aerodynamic performance before and after adjustment is within the preset range. If so, update the initial airfoil parameters based on the adjusted key section airfoil parameters to obtain optimized initial airfoil parameters; otherwise, return to step B1.

[0035] Furthermore, the preset blade vibration and high-cycle fatigue life verification and optimization sub-process includes:

[0036] A three-dimensional model of the compressor blades is obtained based on the initial airfoil parameters of the compressor.

[0037] performing three-dimensional finite element analysis on the three-dimensional model of the blade based on the preset aerodynamic boundary condition to determine vibration characteristics and high-cycle fatigue life of the blade;

[0038] determining whether the vibration characteristics of the blade satisfy a vibration frequency avoidance rate index in the strength vibration life index and whether the high-cycle fatigue life of the blade is greater than a preset high-cycle fatigue cycle life index, and if the vibration characteristics of the blade satisfy the vibration frequency avoidance rate index and the high-cycle fatigue life of the blade is greater than the preset high-cycle fatigue cycle life index, taking the initial blade profile parameter of the compressor as a first blade profile parameter of the compressor, otherwise, entering a preset blade profile geometry parameter optimization sub-process.

[0039] Preferably, the preset aerodynamic structure coupling design process comprises:

[0040] performing axial space design to determine a blade axial position and a flow passage coordinate during through-flow design according to the structure manufacturing and assembly index;

[0041] performing circumferential space design to determine a planned number of blades of the compressor during blade profile design;

[0042] optimizing the first through-flow parameter and the first blade profile parameter according to the aerodynamic performance index, the blade axial position, the flow passage coordinate and the planned number of blades of the compressor to obtain a second through-flow parameter and a second blade profile parameter of the compressor.

[0043] Preferably, the preset strength structure coupling design process comprises:

[0044] Step D1: selecting a blade root type based on the second blade profile parameter to obtain a blade root type of the blade profile;

[0045] Step D2: performing two-dimensional section design of a blade root based on the second blade profile parameter, and then performing two-dimensional section strength evaluation of the blade root to obtain two-dimensional section parameters of the blade root of the blade profile;

[0046] Step D3: performing three-dimensional structure design of a blade root based on the second blade profile parameter, and then performing three-dimensional finite element static strength evaluation of the blade root to obtain three-dimensional structure parameters of the blade root of the blade profile;

[0047] Step D4: determining whether low-cycle fatigue life of the blade profile satisfies the strength vibration life index and whether the blade of the blade profile satisfies the structure manufacturing and assembly index based on the blade root type, the two-dimensional section parameters of the blade root of the blade profile and the three-dimensional structure parameters of the blade root of the blade profile, and if so, entering Step D5, otherwise, returning to Step D3;

[0048] Step D5: optimizing the blade root geometric parameters in the second blade type parameters based on the blade root type, the blade root two-dimensional section parameters of the blade type and the optimized three-dimensional structure parameters of the blade root, to obtain optimized blade root geometric parameters;

[0049] Step D6: designing a blade locking three-dimensional structure to obtain initial parameters of the blade locking structure;

[0050] Step D7: judging whether the strength and vibration life of the blade locking structure meets the strength and vibration life index and whether the blade locking structure meets the structure manufacturing and assembly index, if yes, taking the initial parameters of the blade locking structure as the geometric parameters of the blade locking structure, otherwise, returning to Step D6.

[0051] The second aspect embodiment of the application provides a heavy-duty gas turbine compressor aerodynamic strength and vibration structure coupling design system, comprising:

[0052] An acquisition module is configured to acquire design requirements of a heavy-duty gas turbine compressor and decompose the design requirements into an aerodynamic performance index, a strength and vibration life index and a structure manufacturing and assembly index;

[0053] A first determination module is configured to determine first through-flow parameters and first blade type parameters of the compressor according to the aerodynamic performance index, the strength and vibration life index and a preset aerodynamic strength and vibration coupling design process;

[0054] A second determination module is configured to optimize the first through-flow parameters and the first blade type parameters of the compressor according to the structure manufacturing and assembly index, the aerodynamic performance index and a preset aerodynamic structure coupling design process, to obtain second through-flow parameters and second blade type parameters of the compressor;

[0055] An optimization module is configured to optimize blade root geometric parameters of the compressor according to the strength and vibration life index, the structure manufacturing and assembly index and a preset strength and structure coupling design process, and to design and optimize geometric parameters of a blade locking structure of the compressor, to obtain optimized blade root geometric parameters and geometric parameters of the blade locking structure of the compressor;

[0056] A design module is configured to design the heavy-duty gas turbine compressor based on a hub ratio, an aspect ratio, flow channel coordinates and blade axial positions in the second through-flow parameters, a number of blades, blade chord length, blade thickness, installation angle, inlet and outlet geometric angle in the second blade type parameters, the optimized blade root geometric parameters and the geometric parameters of the blade locking structure;

[0057] The first through-flow parameters and the second through-flow parameters both include a hub ratio, an aspect ratio, flow channel coordinates and blade axial positions;

[0058] The first blade profile parameter and the second blade profile parameter each include: a number of blades, a blade profile chord length, a blade profile thickness, an installation angle, and an inlet-outlet geometric angle.

[0059] The embodiments of the present application provide at least the following beneficial effects:

[0060] The present application provides a heavy-duty gas turbine compressor aerodynamic strength vibration structure coupling design method and system, the method comprising: obtaining the design requirements of the heavy-duty gas turbine compressor, and decomposing the design requirements into aerodynamic performance indicators, strength vibration life indicators, and structure manufacturing and assembly indicators; determining first through-flow parameters and first blade profile parameters of the compressor according to the aerodynamic performance indicators, the strength vibration life indicators, and a preset aerodynamic strength vibration coupling design process; optimizing the first through-flow parameters and the first blade profile parameters according to the structure manufacturing and assembly indicators, the aerodynamic performance indicators, and a preset aerodynamic structure coupling design process, to obtain second through-flow parameters and second blade profile parameters of the compressor; optimizing the blade root geometry parameters of the compressor according to the strength vibration life indicators and the structure manufacturing and assembly indicators, and a preset strength structure coupling design process, and simultaneously designing and optimizing the geometry parameters of the compressor blade locking structure, to obtain the optimized blade root geometry parameters and the geometry parameters of the blade locking structure of the compressor; and designing the heavy-duty gas turbine compressor based on the hub ratio, the aspect ratio, the flow passage coordinates, and the blade axial position in the second through-flow parameters, the number of blades, the blade profile chord length, the blade profile thickness, the installation angle, and the inlet-outlet geometric angle in the second blade profile parameters, the optimized blade root geometry parameters, and the geometry parameters of the blade locking structure. The technical solution provided by the present application improves the design efficiency and optimizes the performance balance, while reducing the design cost.

[0061] Additional aspects and advantages of the present application will be made apparent by the following description and the accompanying drawings. BRIEF DESCRIPTION OF DRAWINGS

[0062] The above and / or additional aspects and advantages of the present application will become apparent and be readily understood from the following description, taken in conjunction with the accompanying drawings, in which:

[0063] Figure 1 A flowchart of a heavy-duty gas turbine compressor aerodynamic strength vibration structure coupling design method according to an embodiment of the present application is provided;

[0064] Figure 2 A flowchart of a compressor aerodynamic strength vibration structure coupling design overall process according to an embodiment of the present application is provided;

[0065] Figure 3A schematic diagram of a hierarchical relationship of a compressor aerodynamic strength-vibration structure coupling design process according to an embodiment of the present application is provided.

[0066] Figure 4 A flow chart of an aerodynamic strength-vibration coupling design process according to an embodiment of the present application is provided.

[0067] Figure 5 A flow chart of a through-flow design and vibration analysis coupling optimization chord length sub-process according to an embodiment of the present application is provided.

[0068] Figure 6 A flow chart of a blade type design, blade root design and vibration analysis coupling optimization blade number sub-process according to an embodiment of the present application is provided.

[0069] Figure 7 A flow chart of a blade type design and vibration analysis coupling optimization design blade type geometry parameter sub-process according to an embodiment of the present application is provided.

[0070] Figure 8 A flow chart of a blade type geometry parameter optimization sub-process according to an embodiment of the present application is provided.

[0071] Figure 9 A flow chart of a blade vibration and high-cycle fatigue life check optimization sub-process according to an embodiment of the present application is provided.

[0072] Figure 10 A flow chart of an aerodynamic structure coupling design process according to an embodiment of the present application is provided.

[0073] Figure 11 A flow chart of a strength structure coupling design process according to an embodiment of the present application is provided.

[0074] Figure 12 A schematic diagram of a preliminary check of machinability of a two-dimensional section of a dovetail type blade root of a compressor according to an embodiment of the present application is provided.

[0075] Figure 13 A schematic diagram of a check of dismountability of an axial blade root of a compressor according to an embodiment of the present application is provided.

[0076] Figure 14 A schematic diagram of a circumferential space design of a compressor according to an embodiment of the present application is provided.

[0077] Figure 15 A structural diagram of a heavy-duty gas turbine compressor aerodynamic strength-vibration structure coupling design system according to an embodiment of the present application is provided. DETAILED DESCRIPTION

[0078] Embodiments of the present application are described below in detail with reference to the accompanying drawings, wherein the same or similar components or components having the same or similar functions are denoted by the same or similar reference numerals throughout the drawings. The embodiments described below by reference to the drawings are exemplary and are intended to explain the present application, and cannot be understood as a limitation of the present application.

[0079] The aerodynamic strength vibration structure coupling design method and system of the heavy-duty gas turbine compressor provided by the present application, the method comprises: obtaining the design requirements of the heavy-duty gas turbine compressor, and decomposing the design requirements into aerodynamic performance indicators, strength vibration life indicators and structure manufacturing and assembly indicators; determining the first through-flow parameters and the first blade profile parameters of the compressor according to the aerodynamic performance indicators, the strength vibration life indicators and a preset aerodynamic strength vibration coupling design process; optimizing the first through-flow parameters and the first blade profile parameters according to the structure manufacturing and assembly indicators, the aerodynamic performance indicators and a preset aerodynamic structure coupling design process to obtain the second through-flow parameters and the second blade profile parameters of the compressor; optimizing the blade root geometry parameters of the compressor according to the strength vibration life indicators and the structure manufacturing and assembly indicators and a preset strength structure coupling design process, and simultaneously designing and optimizing the geometry parameters of the blade locking structure of the compressor to obtain the optimized blade root geometry parameters and the geometry parameters of the blade locking structure of the compressor; and designing the heavy-duty gas turbine compressor based on the hub ratio, the aspect ratio, the flow passage coordinates and the blade axial position in the second through-flow parameters, the blade number, the blade profile chord length, the blade profile thickness, the installation angle, the inlet and outlet geometric angle in the second blade profile parameters, the optimized blade root geometry parameters and the geometry parameters of the blade locking structure. The technical solution provided by the present application improves the design efficiency and optimizes the performance balance, and reduces the design cost.

[0080] The aerodynamic strength vibration structure coupling design method and system of the heavy-duty gas turbine compressor of the embodiments of the present application are described below with reference to the accompanying drawings.

[0081] Embodiment one

[0082] Figure 1 A flow chart of the aerodynamic strength vibration structure coupling design method of the heavy-duty gas turbine compressor provided according to one embodiment of the present application is shown as Figure 1 The method comprises:

[0083] Step 1: obtaining the design requirements of the heavy-duty gas turbine compressor, and decomposing the design requirements into aerodynamic performance indicators, strength vibration life indicators and structure manufacturing and assembly indicators;

[0084] It should be noted that the aerodynamic performance indicators include: flow indicators, pressure ratio indicators, efficiency indicators and surge margin indicators, etc.

[0085] The strength vibration life index includes: strength reserve safety factor index, vibration frequency avoidance rate index, low cycle fatigue cycle life index, and high cycle fatigue cycle life index, etc.

[0086] The structure manufacturing assembly index includes: machinability of compressor parts, disassembly, etc.

[0087] It should be noted that, as Figure 2 The embodiment proposes a heavy-duty gas turbine compressor aerodynamic strength vibration structure coupling design method. Starting from the overall design requirements of the compressor, the aerodynamic design, strength vibration design and structure design are closely integrated to form a complete coupling design system. The design process first defines the design indicators of the compressor, such as flow rate, pressure ratio, efficiency, etc. Then, these indicators are decomposed into aerodynamic performance requirements, strength vibration life requirements and structure manufacturing assembly requirements, corresponding to aerodynamic design, strength vibration design and structure design respectively. In the coupling design process, the three sub-processes are coordinated with each other: aerodynamic strength vibration coupling design sub-process, strength structure coupling design sub-process and aerodynamic structure coupling design sub-process. Aerodynamic design and strength vibration design are carried out simultaneously, through optimizing the geometry and vibration characteristics of the blade, to ensure that the blade can meet the requirements of strength and vibration life while running efficiently. Strength design and structure design are carried out simultaneously to ensure the structural strength and machinability and disassembly of the blade. Aerodynamic design and structure design are carried out simultaneously to ensure that the aerodynamic performance of the blade matches the structure design. The core of this coupling design method is to break down the barriers between different professions in traditional design, and to achieve the improvement of design efficiency and the optimization of performance through collaborative optimization. For example, during the aerodynamic design stage, the design team can simultaneously carry out strength vibration evaluation, identify potential vibration problems in advance, and make optimization adjustments in the early design stage. This collaborative design method greatly reduces the number of design iterations, significantly shortens the design cycle, and improves the design efficiency.

[0088] The compressor aerodynamic strength vibration structure coupling design includes four levels, such as Figure 3The first level is a total flow of compressor aerodynamic strength-vibration coupling design. The second level includes three sub-flows, i.e., a compressor aerodynamic strength-vibration coupling design sub-flow, a compressor strength-structure coupling design sub-flow and a compressor aerodynamic-structure coupling design sub-flow. The third level is called in the compressor aerodynamic strength-vibration coupling design sub-flow and includes four sub-flows, i.e., a through-flow design and vibration analysis coupling optimization chord length sub-flow, a blade profile design, a blade root design and vibration analysis coupling optimization blade number sub-flow, a blade profile design and vibration analysis coupling optimization design blade profile geometric parameter sub-flow and a blade vibration and high-cycle fatigue life check optimization sub-flow. The fourth level is called in the blade profile design and vibration analysis coupling optimization design blade profile geometric parameter sub-flow and the blade vibration and high-cycle fatigue life check optimization sub-flow and is a blade profile geometric parameter optimization sub-flow. The three sub-flows of the second level are in parallel relationship. In actual execution process, the compressor aerodynamic strength-vibration coupling design sub-flow and the compressor aerodynamic-structure coupling design sub-flow are slightly earlier in time, and the compressor strength-structure coupling design sub-flow is slightly later in time. The three sub-flows of the third level are called in the compressor aerodynamic strength-vibration coupling design sub-flow, are sequentially developed according to the aerodynamic design process and are internally looped and iterated in the design iteration process. After the sub-flows are sequentially iterated and designed, the scheme is basically perfect, and in the case that there is no great change in design requirement, no large loop iteration is needed, and iteration time can be greatly saved.

[0089] Step 2: determining the first through-flow parameter and the first blade profile parameter of the compressor according to the aerodynamic performance index, the strength-vibration life index and a preset aerodynamic strength-vibration coupling design flow;

[0090] The first through-flow parameter and the second through-flow parameter each include a hub ratio, an aspect ratio, a flow passage coordinate and a blade axial position.

[0091] The first blade profile parameter and the second blade profile parameter each include a blade number, a blade profile chord length, a blade profile thickness, an installation angle and an inlet-outlet geometric angle. The blade profile thickness in the first blade profile parameter can be a blade profile maximum thickness or a range.

[0092] In the embodiment of the present disclosure, as shown in Figure 4 The aerodynamic strength-vibration coupling design flow includes:

[0093] 2.1 determining the first through-flow parameter and a reasonable range of blade profile parameter of the compressor according to the aerodynamic performance index, the strength-vibration life index and a preset through-flow design and vibration analysis coupling optimization chord length sub-flow;

[0094] It should be noted that the reasonable range of blade profile parameter includes a blade profile maximum thickness range.

[0095] 2.2 determining the first number of blades of the compressor according to a first throughflow parameter and a reasonable range of blade profile parameters of the compressor and a preset blade profile design, a blade root design and vibration analysis coupled optimization blade number sub-process;

[0096] It should be noted that, based on the flow index requirement, according to the design of the chord length or the aspect ratio parameter of the blade profile, the recommended range of the number of blades can be determined;

[0097] Based on the vibration avoidance rate index, the recommended adjustment amount of the number of blades can be determined according to the deviation of the blade vibration frequency and the excitation frequency. Further, the blade number scheme can be determined by comprehensively considering the aerodynamic index and the vibration index.

[0098] 2.3 determining the initial blade profile parameters of the compressor according to a reasonable range of blade profile parameters of the compressor and a preset blade profile design and vibration analysis coupled optimization design blade profile geometry parameter sub-process, wherein the initial blade profile parameters include: blade profile chord length, blade profile thickness, installation angle, inlet and outlet geometric angle;

[0099] 2.4 determining whether the initial blade profile parameters of the compressor meet the aerodynamic performance index and the strength vibration life index according to a preset blade vibration and high-cycle fatigue life check optimization sub-process, if yes, taking the initial blade profile parameters of the compressor as the first blade profile parameters of the compressor, otherwise, optimizing the initial blade profile parameters of the compressor according to a preset blade profile geometry parameter optimization sub-process until the initial blade profile parameters of the compressor meet the aerodynamic performance index and the strength vibration life index.

[0100] It should be noted that, as Figure 4As shown, the sub-process couples the aerodynamic design process and the strength vibration design process, ensuring that the blade meets the requirements of aerodynamic performance, strength, and vibration life. The aerodynamic design includes three steps: through-flow design, blade profile design, and aerodynamic performance analysis. In the through-flow design stage, the chord length and arrangement of the blade are optimized to improve the through-flow efficiency of the compressor. At the same time, the through-flow design and vibration analysis coupled optimization chord length sub-process is carried out simultaneously to optimize the chord length of the blade, ensuring that the blade does not resonate or flutter due to airflow excitation during operation. In the blade profile design stage, the geometric shape of the blade is optimized to further improve the aerodynamic performance. At the same time, the blade number coupled optimization blade profile design and vibration analysis sub-process, and the blade profile geometry coupled optimization design blade profile geometry sub-process are carried out simultaneously to determine the number of blades and optimize the blade profile. The determination of the number of blades needs to consider the aerodynamic performance and strength vibration characteristics, and too many or too few blades may affect the overall performance of the compressor and the strength of the blade root tenon slot and excitation source. In the aerodynamic performance analysis stage, the aerodynamic performance of the compressor is evaluated through accurate numerical simulation and experimental verification. At the same time, the blade vibration and high-cycle fatigue life check optimization sub-process is carried out simultaneously for final check and necessary optimization design. The goal of this stage is to ensure that the blade meets the requirements of aerodynamic performance, strength, and vibration life. Through this coupled design method, the aerodynamic design scheme and the strength vibration design scheme of the compressor can basically meet the requirements of aerodynamic performance and strength vibration. The final compressor strength vibration coupled design scheme not only improves the performance of the compressor, but also prolongs the service life of the blade.

[0101] Further, as shown in Figure 5 The preset through-flow design and vibration analysis coupled optimization chord length sub-process includes:

[0102] Step F1: Based on the aerodynamic performance indicators, carry out through-flow design to determine the preliminary through-flow parameters of the compressor;

[0103] Step F2: Based on the preliminary through-flow parameters of the compressor, carry out preliminary modeling design of the blade to determine the reasonable range of blade profile parameters, wherein the reasonable range of blade profile parameters includes blade chord length;

[0104] It should be noted that the reasonable range of blade profile parameters is a preliminary scheme of blade profile, including all parameters of the blade profile, such as chord length, thickness, geometric angle, etc.

[0105] Step F3: Perform preliminary vibration / flutter analysis on the initial blade profile constituted by the reasonable range of blade profile parameters to determine the vibration frequency avoidance rate margin of the key vibration mode of the initial blade profile and the main excitation source and the flutter equivalent frequency margin of the key vibration mode;

[0106] It should be noted that the key vibration mode generally refers to the bending vibration mode and the torsional vibration mode, and the main excitation source includes the excitation source caused by the number of tail traces of the support plate, the front and rear rows of blades, etc.

[0107] Step F4: determining whether the absolute value of the difference between the vibration frequency avoidance margin of the key vibration mode of the initial blade profile and the vibration frequency avoidance margin in the strength vibration life index and the absolute value of the difference between the flutter equivalent frequency margin of the key vibration mode and the flutter equivalent frequency margin in the strength vibration life index are less than or equal to a preset first difference threshold value, if yes, adjusting the chord length based on a preset chord length adjustment scheme and returning to step F2, otherwise, taking the chord length of the initial blade profile of the compressor as the optimized chord length, taking the preliminary throughflow parameter as the first throughflow parameter, and taking the blade profile parameter range corresponding to the optimized chord length as the blade profile parameter reasonable range.

[0108] It should be noted that the first difference threshold value can be ten percent.

[0109] It should be noted that, as shown in Figure 5 The sub-process mainly focuses on the vibration characteristic optimization in the throughflow design stage to ensure that the blade does not resonate or flutter due to airflow excitation during operation. In the throughflow design stage, the design team needs to optimize the chord length and arrangement of the blade to improve the throughflow efficiency of the compressor. At the same time, the throughflow vibration coupling design sub-process is carried out synchronously to optimize the chord length of the blade. The optimization of the chord length of the blade needs to consider the aerodynamic performance and vibration characteristics comprehensively, and too long or too short chord length may affect the vibration characteristics of the blade. In the process of optimizing the chord length of the blade, the design team needs to perform preliminary vibration / flutter analysis on the preliminary blade profile to evaluate the avoidance margin of the key vibration mode and the main excitation source and the flutter equivalent frequency margin. If the inherent frequency adjustment amount is large (> 10%), simply adjusting the thickness of the blade cannot meet the vibration and flutter requirements of the blade, and the chord length needs to be optimized. If the inherent frequency adjustment amount is small (< 10%), it indicates that the thickness of the blade can be adjusted to meet the vibration and flutter requirements of the blade in the subsequent blade design, and the chord length does not need to be optimized. Without the need to optimize the chord length, the reasonable range of the blade geometric parameters (such as the maximum thickness of the blade profile) is provided based on the preliminary vibration / flutter analysis results to the blade design step to guide the blade design. Through this coupling design method, the throughflow design scheme of the compressor can basically meet the requirements of aerodynamic performance and vibration characteristics. The finally obtained throughflow design scheme not only improves the throughflow efficiency of the compressor, but also effectively avoids the resonance or flutter problem of the blade in the running process due to airflow excitation. Moreover, the blade frequency adjustment requirement is considered in advance, which can reduce the difficulty of frequency adjustment design in the subsequent blade design process and improve the design efficiency.

[0110] Further, as shown in Figure 6As shown, the preset blade profile design, blade root design and vibration analysis coupled optimization blade number sub-process includes:

[0111] Based on the first through-flow parameter, the reasonable range of the blade profile parameter and the blade root strength design requirement, a preliminary blade root design result is obtained, and an initial blade number range is obtained based on the preliminary blade root design result;

[0112] It should be noted that the preliminary blade root design can be selected and designed according to the geometric size of the blade. As long as the blade root can envelope the blade and form a complete structure during initial design, it is acceptable.

[0113] For the axial installation of the blade root form, the more the blade number is, the more dense the circumferential blade will be, and then the space of the tenon and groove on the wheel disc will be smaller, and the centrifugal force of the blade that can be borne will be smaller. Therefore, under the condition that the size of the blade root is unchanged, the blade number cannot exceed a limit value, and the centrifugal force of the blade that can be borne by the wheel disc is responsible.

[0114] The initial blade profile is subjected to vibration analysis, the key vibration mode natural frequency of the initial blade profile and the avoidance rate of the front and rear row blade number excitation source are evaluated, and then the front and rear row blade number adjustment amount is determined based on the key vibration mode natural frequency and the avoidance rate of the front and rear row blade number excitation source, to obtain the adjusted front and rear row blade number of the compressor;

[0115] Based on the adjusted front and rear row blade number, the initial blade profile of the compressor is subjected to aerodynamic performance analysis to obtain an aerodynamic performance analysis result;

[0116] According to the aerodynamic performance analysis result and the preliminary blade root design result, the first blade number of the compressor is determined.

[0117] It should be noted that the aerodynamic computational fluid dynamics analysis is performed to evaluate the flow rate, pressure ratio and efficiency changes after the blade number adjustment, and whether the changes are too large to cause the aerodynamic index to be not met.

[0118] If the changes are not large after the analysis and the aerodynamic performance index can still be met, the blade number adjustment scheme is recognized;

[0119] If the aerodynamic performance is greatly reduced after the analysis and cannot meet the index requirement, no blade number adjustment is performed, or a compromise blade number adjustment scheme is selected.

[0120] It should be noted that, as Figure 6As shown, the sub-process mainly focuses on the strength and vibration optimization in the blade design stage, to ensure that the blade can meet the requirements of strength and vibration life while meeting the requirements of aerodynamic performance. In the blade design stage, the design team needs to optimize the geometry of the blade to further improve the aerodynamic performance. At the same time, the aerodynamic strength and vibration coupling design optimization sub-process is carried out synchronously to determine the number of blades and optimize the blade shape. The determination of the number of blades needs to consider the aerodynamic performance and vibration characteristics comprehensively, and too many or too few blades may affect the overall performance of the compressor, as well as the strength of the blade root tenon slot and the excitation source. The preliminary design of the blade root is mainly based on the two-dimensional profile design of the blade root and the average stress strength evaluation. Generally, the greater the number of blades, the greater the average stress of the tenon slot, so the recommended range of the number of blades can be provided based on the strength design requirements of the blade root and the preliminary design results of the blade root. In the process of optimizing the number of blades, the design team needs to carry out preliminary vibration analysis on the preliminary blade shape to evaluate the natural frequency of the key vibration mode and the avoidance rate of the excitation source of the front and rear rows of blades. By adjusting the number of blades to change the excitation source and increase the avoidance rate, the adjustment amount of the number of blades is obtained. According to the adjustment amount of the number of blades, the aerodynamic performance is analyzed to evaluate the change of the aerodynamic performance, and the number of blades is determined comprehensively according to the results of the aerodynamic performance, blade root design and blade vibration analysis, and is fed back to the blade shape design step to adjust the number of blades. Through this coupling design method, the blade shape design scheme of the compressor can basically meet the requirements of aerodynamic performance and strength and vibration. The final blade shape design scheme not only improves the aerodynamic performance of the compressor, but also prolongs the service life of the blade.

[0121] Further, as shown in Figure 7 The preset blade shape design and vibration analysis coupling optimization design blade shape geometry parameter sub-process includes:

[0122] Step A1: based on the reasonable range of blade shape parameters of the compressor, vibration / flutter analysis is carried out on the blades of the compressor, and the preset blade shape geometry parameter optimization sub-process is entered;

[0123] Step A2: based on the reasonable range of blade shape parameters of the compressor, aerodynamic performance analysis is carried out to obtain the blade frequency optimization blade shape geometry parameter constraint of the compressor, and then enter the preset blade shape geometry parameter optimization sub-process.

[0124] It should be noted that, as Figure 7As shown, the sub-process mainly focuses on the optimization of vibration characteristics in the blade profile design stage, ensuring that the blade meets the requirements of aerodynamic performance and vibration life. In the blade profile design stage, the design team needs to optimize the geometry of the blade to further improve the aerodynamic performance. At the same time, the blade vibration / flutter analysis is carried out synchronously to evaluate the natural frequency of the key vibration mode and the avoidance rate of the excitation source. If the blade vibration / flutter analysis result does not meet the blade vibration design requirement, the blade frequency adjustment optimization sub-process needs to be carried out. In the process of blade frequency adjustment optimization, the design team needs to evaluate the sensitivity of the blade thickness change to the aerodynamic performance according to the aerodynamic performance analysis result, and summarize the constraint range of the blade profile geometry parameter adjustment to provide the geometry parameter constraint for the blade frequency adjustment optimization. By adjusting the blade thickness and other blade profile geometry parameters, the vibration characteristics of the blade are optimized to ensure that the blade will not be damaged due to resonance or flutter in the running process. Through this coupled design method, the blade profile design scheme of the compressor can basically meet the requirements of aerodynamic performance and vibration life. The finally obtained blade profile design scheme not only improves the aerodynamic performance of the compressor, but also prolongs the service life of the blade.

[0125] Further, as shown in Figure 8 The preset blade profile geometry parameter optimization sub-process includes:

[0126] Step B1: adjusting the key section blade profile parameters of the blade based on the blade profile geometry parameter constraints and the aerodynamic performance indicators;

[0127] It should be noted that the key section can be a blade root, blade middle, blade tip section, or a 0%, 25%, 50%, 75, 100% span section, or any relative span blade profile section.

[0128] Step B2: performing vibration / flutter check on the adjusted blade, if the strength vibration life indicator is not met, returning to step B1, if met, entering step B3;

[0129] It should be noted that the blade vibration frequency avoidance rate needs to meet the avoidance rate requirement in the strength vibration life indicator;

[0130] Step B3: performing aerodynamic performance check on the blade after adjusting the key section blade profile parameters of the blade, judging whether the change value of the aerodynamic performance before and after adjustment is within the preset range, if yes, updating the initial blade profile parameters based on the adjusted key section blade profile parameters of the blade to obtain the optimized initial blade profile parameters, otherwise, returning to step B1.

[0131] It should be noted that the blade profile after adjusting the blade profile parameters is subjected to computational fluid dynamics (CFD) analysis to evaluate the changes of the aerodynamic performance parameters such as flow rate, pressure ratio and efficiency.

[0132] It should be noted that, as shown in Figure 8 The sub-process mainly focuses on the optimization of blade vibration characteristics, ensuring that the blade meets the requirements of aerodynamic performance and vibration life. In the blade vibration / flutter analysis stage, the design team needs to identify the key vibration modes of the blade, calculate the inherent frequency of the key vibration mode, and calculate the avoidance rate of the key excitation source. If the avoidance rate does not meet the blade vibration design requirements, the blade frequency adjustment optimization needs to be carried out. According to the adjustment constraints of the blade profile geometric parameters provided by the aerodynamic performance analysis results, the key cross-section blade profile parameters are adjusted according to the aerodynamic performance demand. The vibration / flutter of the blade after frequency adjustment is checked, and if it still does not meet the vibration requirements, continue to adjust. If the blade after frequency adjustment meets the blade vibration requirements, the aerodynamic performance is checked, and the influence of frequency adjustment on aerodynamic performance is evaluated. If the aerodynamic performance change is not within the allowable range, the blade profile is re-adjusted. If the aerodynamic performance change is within the allowable range, the blade frequency adjustment optimization scheme is determined, which meets the aerodynamic performance demand and the blade vibration design demand. Through this coupled design method, the blade design scheme of the compressor can basically meet the aerodynamic performance demand and the vibration life requirement. The final blade design scheme meets the aerodynamic performance demand and the blade vibration design demand.

[0133] Further, as shown in Figure 9 The preset blade vibration and high-cycle fatigue life checking and optimization sub-process includes:

[0134] Obtaining a three-dimensional model of the blade of the compressor based on the initial blade profile parameters of the compressor;

[0135] Performing three-dimensional finite element analysis on the three-dimensional model of the blade based on preset aerodynamic boundary conditions to determine the vibration characteristics and high-cycle fatigue life of the blade;

[0136] It should be noted that the preset aerodynamic boundary conditions include: blade surface aerodynamic force distribution, working (average) temperature, etc.

[0137] Determine whether the vibration characteristics of the blade meet the vibration frequency avoidance rate index in the strength vibration life index, and whether the high-cycle fatigue life of the blade is greater than the preset high-cycle fatigue cycle life index. If the vibration characteristics of the blade meet the vibration frequency avoidance rate index and the high-cycle fatigue life of the blade is greater than the preset high-cycle fatigue cycle life index, the initial blade profile parameters of the compressor are taken as the first blade profile parameters of the compressor, otherwise, enter the preset blade profile geometric parameter optimization sub-process.

[0138] It should be noted that, as shown in Figure 9As shown, this process is a key link in the coupling design of the compressor, aiming to ensure that the blades can withstand the vibration load in long-term operation while meeting the aerodynamic performance requirements, avoiding safety problems caused by fatigue failure. After the pre-iteration design, the compressor blade scheme can basically meet the aerodynamic performance requirements and blade vibration design requirements. At this time, the final check and necessary improvement stage is entered. First, the blade three-dimensional model is obtained by developing the blade root design according to the blade profile design. After the blade profile design is completed, aerodynamic performance analysis is carried out, and the aerodynamic boundary conditions are provided according to the results. This boundary condition is an important basis for subsequent vibration and fatigue life analysis. Next, based on the blade three-dimensional model, the aerodynamic boundary conditions and other constraint conditions are applied, and the three-dimensional finite element analysis of the blade is carried out. This analysis process needs to consider various working conditions of the blade in actual operation, including aerodynamic load, temperature field distribution and mechanical stress, etc. Through finite element analysis, the vibration characteristics of the blade can be accurately evaluated, including natural frequency, mode distribution and stress concentration area, etc. At the same time, the high-cycle fatigue life of the blade is evaluated. High-cycle fatigue life refers to the service life of the blade under high-frequency vibration load. This evaluation needs to consider many factors such as the fatigue characteristics of the material, the geometry of the blade and the vibration amplitude in actual operation. Through high-cycle fatigue life evaluation, the reliability of the blade in long-term operation can be determined, avoiding safety problems caused by fatigue failure. If the blade vibration and high-cycle fatigue life do not meet the requirements, the blade frequency adjustment optimization sub-process is entered to adjust the blade geometric parameters. If the blade vibration and high-cycle fatigue life meet the requirements, and the aerodynamic performance also meets the requirements, the coupling design scheme of the compressor aerodynamic strength vibration is completed. This scheme not only meets the aerodynamic performance requirements, but also ensures the reliability and safety of the blade in long-term operation. Through this coupling design method, the blade design scheme of the compressor can achieve the best balance between aerodynamic performance, strength and vibration life, providing guarantee for the efficient and stable operation of heavy-duty gas turbines. The core of this process is to ensure that the blade can withstand the vibration load in long-term operation while meeting the aerodynamic performance requirements through accurate finite element analysis and high-cycle fatigue life evaluation, combined with the optimization of aerodynamic performance and vibration characteristics.

[0139] Step 3: According to the structure manufacturing and assembly indicators and the aerodynamic performance indicators and the preset aerodynamic structure coupling design process, the first through-flow parameters and the first blade profile parameters are optimized to obtain the second through-flow parameters and the second blade profile parameters of the compressor;

[0140] In the embodiments of the present disclosure, as shown in the figure, the preset aerodynamic structure coupling design process includes: Figure 10

[0141] According to the structure manufacturing and assembly indicators, the axial space design is carried out to determine the blade axial position and flow passage coordinates during through-flow design; ​

[0142] It should be noted that the axial space is designed based on the meridian flow passage parameters of the through-flow design result, which are determined by the inlet / outlet diameter and the flow passage contraction / expansion angle obtained by the through-flow design.

[0143] In consideration of the blade assembly space, the axial distance of the front and rear stage blades cannot be too small; based on aerodynamic considerations, too large a blade axial distance will result in more aerodynamic losses, and a moderate blade axial position is determined by comprehensively considering both.

[0144] The circumferential space design is carried out when the blade profile is designed to determine the planned number of blades of the compressor;

[0145] The circumferential space design mainly designs the number of blades, and generally the more the number of blades, the more dense the blades will be in the circumferential direction, and the assembly will be relatively poor.

[0146] According to the aerodynamic performance index, the blade axial position, the flow passage coordinates and the planned number of blades of the compressor, the first through-flow parameters and the first blade profile parameters are optimized to obtain the second through-flow parameters and the second blade profile parameters of the compressor.

[0147] It should be noted that according to the axial space assembly requirement, the axial distance of the blades is appropriately increased in the through-flow design, thereby determining the through-flow meridian flow passage coordinates;

[0148] According to the circumferential space assembly requirement, the number of blades is appropriately reduced in the blade profile design, thereby determining the number of blades and the blade profile parameter scheme of the blade profile design.

[0149] It should be noted that, as shown in Figure 10 The sub-process aims to ensure the overall performance and reliability of the compressor through collaborative optimization of aerodynamic design and structural design. In the aerodynamic-structural coupling design sub-process, first, the through-flow design is performed, while the axial space design is simultaneously carried out to check whether the axial space between the front and rear rows of blades is sufficient. The axial space design is crucial for the structural performance of the compressor. If the axial space is insufficient, it may cause interference between the blades, affecting the normal operation of the compressor. Therefore, during the design process, the axial space needs to be accurately calculated to ensure sufficient clearance between the blades to avoid collision and wear during operation. In the blade profile design stage, the circumferential space design is simultaneously carried out to check whether the circumferential space of the same row of blades is sufficient. The circumferential space design is also important, as it not only affects the aerodynamic performance of the blades but also determines the structural strength and machinability of the blades. By optimizing the circumferential space, it can be ensured that the blades do not interfere with each other in the circumferential direction during operation, and it is convenient for machining and assembly. The core of the aerodynamic-structural coupling design sub-process lies in achieving the best balance between aerodynamic performance and structural performance through collaborative optimization. During the design process, the requirements of aerodynamic design and structural design need to be considered comprehensively to ensure consistency and coordination between the two.

[0150] Step 4: optimizing the blade root geometry parameters of the compressor according to the strength vibration life index, the structure manufacturing assembly index and the preset strength structure coupling design process, and designing and optimizing the geometry parameters of the blade locking structure of the compressor, to obtain the optimized blade root geometry parameters of the compressor and the geometry parameters of the blade locking structure of the compressor;

[0151] In the embodiments of the present disclosure, as shown in Figure 11 The preset strength structure coupling design process comprises the following steps:

[0152] Step D1: selecting a blade root type based on the second blade profile parameter, to obtain the blade root type of the blade profile;

[0153] It should be noted that for the compressor moving blade, the dovetail type blade root is usually axially installed for the front stage, and the dovetail type blade root or the T type blade root can be selected for the rear stage.

[0154] The factors such as the rotor structure and the processing and assembly cost can be comprehensively considered.

[0155] Step D2: designing a blade root two-dimensional section based on the second blade profile parameter, and then evaluating the strength of the blade root two-dimensional section, to obtain the blade root two-dimensional section parameter of the blade profile;

[0156] It should be noted that the blade root force bearing surface width, the blade root edge plate width, the blade root height, the force bearing surface wedge angle and the round corner radius of the blade root two-dimensional section.

[0157] Generally, the size parameters of the blade root have a general size according to the size of the blade profile, and the blade profile can be included to form a relatively complete structure. Generally, the preliminary blade profile size is designed according to the design habit.

[0158] Step D3: designing a blade root three-dimensional structure based on the second blade profile parameter, and then evaluating the static strength of the blade root three-dimensional finite element, to obtain the blade root three-dimensional structure parameter of the blade profile;

[0159] It should be noted that for the axially installed blade root, the blade root three-dimensional parameters include the blade root axial length and the blade root installation angle.

[0160] According to whether the blade can be designed to be enveloped, the blade root mortise and tenon strength level is optimized.

[0161] For the circumferentially installed blade root, the blade root three-dimensional parameters include the blade root circumferential width or the blade root two-side circumferential face included angle, the blade root installation angle and the like.

[0162] The leaf root circumferential width needs to envelope the blade; the leaf root two side circumferential surface included angle is related to the blade number n, and is generally 360 / n; the leaf root installation angle design also needs to envelope the blade, and then is optimized according to the strength level.

[0163] Step D4: judging whether the low-cycle fatigue life of the blade root of the blade type meets the strength vibration life index and whether the blade of the blade type meets the structural manufacturing assembly index based on the blade root type, the blade root two-dimensional section parameter of the blade type and the blade root three-dimensional structure parameter of the blade type, if yes, entering step D5, otherwise returning to step D3;

[0164] Step D5: optimizing the blade root geometric parameter in the second blade type parameter based on the blade root type, the blade root two-dimensional section parameter of the blade type and the optimized blade root three-dimensional structure parameter, to obtain the optimized blade root geometric parameter;

[0165] Step D6: designing a blade locking three-dimensional structure to obtain initial parameters of the blade locking structure;

[0166] It should be noted that the structure form to be designed and locked and the size corresponding to the structure form need to be designed.

[0167] Generally, the design is based on the machinability and dismountability, and the optimization is based on the strength requirement.

[0168] The structure form to be locked is various, and the specific size and size source cannot be comprehensively summarized.

[0169] Step D7: judging whether the strength life of the blade locking structure meets the strength vibration life index and whether the blade locking structure meets the structural manufacturing assembly index, if yes, taking the initial parameters of the blade locking structure as the geometric parameters of the blade locking structure, otherwise returning to step D6.

[0170] Step 5: designing the heavy-duty gas turbine compressor based on the hub ratio, the aspect ratio, the flow passage coordinates, the blade axial position in the second through-flow parameter, the blade number, the blade type chord length, the blade type thickness, the installation angle, the inlet and outlet geometric angle in the second blade type parameter, the optimized blade root geometric parameter and the geometric parameter of the blade locking structure;

[0171] It should be noted that, for example, Figure 11As shown, this sub-process couples the strength design process and the structure design process, ensuring that the blade meets the strength requirements while having good processability and dismountability. In the design of a compressor, the strength of the blade is one of the key factors to ensure its safe operation. The blade needs to withstand dynamic loads from airflow, mechanical stress, and thermal stress under high-temperature environment, and other complex working conditions. Therefore, the strength design needs to consider factors such as the mechanical properties of the material, the geometry of the blade, and the load distribution in actual operation. At the same time, the structure design needs to consider the processability and dismountability of the blade to meet the needs of manufacturing and maintenance. In the strength-structure coupling design sub-process, first, the blade root type selection and the blade root two-dimensional section design are carried out according to the blade geometry. The blade root is the key part connecting the blade and the disc, and its design needs to ensure sufficient strength and rigidity, while facilitating processing and assembly. After the blade root two-dimensional section design is completed, the blade root two-dimensional section strength evaluation is carried out to evaluate the stress distribution and strength characteristics of the blade root in the two-dimensional section. When carrying out the blade two-dimensional section strength evaluation, the blade root mortise two-dimensional section processability preliminary check and the blade root and locking dismountability preliminary check are carried out simultaneously. Next, the blade root three-dimensional structure design and the blade root three-dimensional finite element static strength evaluation are carried out. In the three-dimensional structure design, the three-dimensional stress state of the blade root in actual operation needs to be considered, and the strength and rigidity of the blade root are evaluated through finite element analysis. At the same time, when carrying out the blade root three-dimensional finite element static strength evaluation, the blade three-dimensional processability check and the blade dismountability check are carried out simultaneously. The purpose of the processability check is to ensure that the structure design of the blade root can be realized under the existing processing technology, avoiding processing difficulties caused by complex structure. The dismountability check is to ensure that the blade can be easily dismounted and installed during maintenance and replacement. After the blade root three-dimensional finite element static strength and low-cycle fatigue life evaluation is completed, the blade locking three-dimensional structure design and the blade locking structure strength life evaluation are carried out. The locking structure is a key component to ensure that the blade does not loosen during operation, and its design needs to ensure sufficient strength and reliability. At the same time, when carrying out the locking structure strength life evaluation, the locking structure processability check and the blade locking structure dismountability check are carried out simultaneously. The purpose of these checks is to ensure that the design of the locking structure not only meets the strength requirements, but also facilitates processing and maintenance. Through this strength-structure coupling design method, the blade design scheme of the compressor can achieve the best balance between strength and structure. The blade not only can withstand complex operating conditions, but also has good processability and dismountability, reducing the manufacturing cost and maintenance difficulty. This coupling design method provides important technical support for the design and operation of heavy-duty gas turbines, ensuring the efficient and stable operation of the compressor.

[0172] In the present embodiment, Figure 12A preliminary examination of the manufacturability of a two-dimensional section of a dovetail compressor blade root is shown. This examination is an important part of the strength-structure coupling design sub-process, aiming to ensure that the structural design of the blade root can be realized under existing machining processes. In the design of a compressor, the blade root is the key part connecting the blade and the disk, and its design needs to ensure sufficient strength and rigidity, while facilitating machining and assembly. Compressor blade roots are usually machined by milling process. During the machining process, if the thickness of the rim plate is too thin, deformation may occur, leading to reduced machining accuracy, so the thickness of the rim plate needs to be sufficient. For example, for a rim plate with no wedge angle, its thickness needs to meet Ha (the thickness of the compressor blade root rim plate with no wedge angle) ≥ 4mm. For a rim plate with a wedge angle, its thickness needs to meet Hb1 (the thickness of the compressor blade root rim plate edge with a wedge angle) ≥ 2mm, Hb2 (the thickness of the compressor blade root rim plate near the centerline with a wedge angle) ≥ 6mm. These size parameters are determined according to the machining process and material properties, to ensure that no deformation or fracture occurs during machining. The purpose of the manufacturability check is to identify potential machining problems in the design stage and avoid machining difficulties caused by complex structures. Through manufacturability checking, the geometry and size parameters of the blade root can be optimized to ensure that the blade root can be realized under existing machining processes. This check not only improves the machining efficiency of the blade root, but also reduces the machining cost, providing important technical support for the manufacture and operation of the compressor. In practical applications, manufacturability checking needs to be combined with specific machining processes and equipment. For example, in the milling process, factors such as tool size, machining path, and cutting parameters need to be considered. By optimizing these parameters, the machining quality and efficiency of the blade root can be further improved. Specifically:

[0173] 1. Tool selection: Select the appropriate size and shape of the tool to ensure that the tool can smoothly pass through the narrow part of the T-shaped slot, while avoiding machining interference caused by too large a tool.

[0174] 2. Machining path optimization: Optimize the machining path to ensure that the tool can smoothly pass through each part of the T-shaped slot during machining, avoiding machining errors caused by unreasonable path.

[0175] 3. Cutting parameter adjustment: Adjust the cutting speed, feed rate, and cutting depth according to the material properties and machining requirements to ensure that the cutting force and cutting heat during machining are within a controllable range, avoiding machining deformation caused by excessive cutting force or high cutting heat.

[0176] This processability check method provides important guarantee for the design and manufacture of the compressor, ensuring that the structure design of the blade root mortise meets the strength requirements and is convenient for processing and manufacturing. By optimizing the geometric shape and size parameters of the mortise, combined with specific processing technology and equipment, the processing quality and efficiency of the blade root mortise can be significantly improved, and the manufacturing cost can be reduced, providing support for the efficient and stable operation of heavy-duty gas turbines.

[0177] In this embodiment, Figure 13 A schematic diagram of the disassembly check of the compressor axial blade root is shown. This check is one of the important links in the strength structure coupling design sub-process, aiming to ensure that the structure design of the blade root can be conveniently installed and disassembled during actual assembly and maintenance. In the design of the compressor, the disassembly of the blade root is one of the key factors to ensure the efficient maintenance and replacement of the blades. The axial blade root usually needs to have enough installation space in the axial direction to ensure that the blades can be smoothly installed on the rotor and conveniently disassembled for maintenance or replacement when needed. During the check, attention should be paid to the geometric shape and size parameters of the blade root. For example, the axial installation blade root needs to have enough installation space in the axial direction, i.e. Lf (axial installation moving blade root upstream rotor slot axial length) > L (axial installation moving blade root axial length), or Lr (axial installation moving blade root downstream rotor slot axial length) > L. These size parameters are determined according to the structure and assembly requirements of the blades, ensuring that there will be no interference or installation difficulty problems during assembly. In practical applications, the disassembly check needs to be combined with specific assembly processes and equipment. For example, during assembly, the installation sequence of the blades, the use of assembly tools, and the positioning accuracy during assembly need to be considered. By optimizing these parameters, the assembly quality and efficiency of the blades can be further improved. Specifically:

[0178] 1. Installation sequence optimization: determine a reasonable blade installation sequence to ensure that there will be no interference or installation difficulty problems during installation.

[0179] 2. Assembly tool selection: select appropriate assembly tools to ensure smooth operation during installation and disassembly, avoiding assembly problems caused by inappropriate tools.

[0180] 3. Positioning accuracy adjustment: adjust the positioning accuracy during assembly according to the structure and assembly requirements of the blades to ensure that the blades can be accurately installed on the rotor.

[0181] In addition, the disassembly check also needs to consider maintenance requirements. For example, the structure design of the blade root needs to be convenient for maintenance personnel to check and repair, while ensuring that the blades or rotors are not damaged during maintenance. Through the disassembly check, it can be ensured that the structure design of the blade root meets the assembly requirements and is convenient for maintenance and replacement.

[0182] In this embodiment, Figure 14 A schematic diagram of the circumferential space design of a compressor is shown. In the design of a compressor, insufficient circumferential space can cause interference between blades and blades, and between blades and the cylinder, affecting the smooth flow of air flow, and even causing blade damage or compressor failure. Therefore, the design of the circumferential space needs to consider the aerodynamic performance, structural strength, and the feasibility of processing and assembly. First, the static blades of the inlet stage of the heavy gas turbine compressor are usually designed as adjustable static blades, which can optimize the aerodynamic performance of the compressor under different operating conditions. The adjustable static blades pass through the through holes on the compressor cylinder through the driving handle, and are coupled to the external driving mechanism to achieve the adjustment of the blade angle. Therefore, in the design process, it is necessary to ensure that the distance TT (the minimum circumferential distance between the through holes of the adjustable static blades of the compressor cylinder) is sufficient to meet the requirements of processing and assembly; when designing the circumferential space, the diameter of the compressor cylinder, the diameter D of the driving handle, and the number of blades need to be considered. These parameters jointly determine the minimum circumferential distance TT between the through holes. Specifically, the number of blades affects the design of the circumferential space. The more the number of blades, the smaller the distance between the through holes, so a reasonable balance needs to be made between the number of blades and the circumferential space. In the actual design process, the design of the circumferential space also needs to consider the operating conditions of the compressor. For example, under high load operating conditions, the blades may deform to a certain extent, so sufficient circumferential space needs to be reserved in the design to avoid interference between the blades. In addition, the design of the circumferential space also needs to consider the processing error and assembly error. In the processing process, there may be size deviations, so a certain tolerance needs to be reserved in the design to ensure that there is no interference in the processing and assembly process. The design of the circumferential space also needs to be closely coupled with the aerodynamic design and structural design. For example, in the aerodynamic design, the geometry and arrangement of the blades affect the flow characteristics of the air flow, which in turn affects the demand for circumferential space. In the structural design, the processability and dismountability of the blades also require sufficient circumferential space to ensure. In addition, the design of the circumferential space also needs to consider the convenience of maintenance and replacement. In actual operation, the static blades may need to be regularly maintained or replaced, so it is necessary to ensure that the distance between the through holes is large enough to facilitate the operation of the maintenance personnel. Reasonable design of the circumferential space not only can improve the operating efficiency and reliability of the compressor, but also can reduce the maintenance cost.

[0183] It should be noted that the heavy gas turbine compressor aerodynamic strength vibration structure coupling design method provided in this embodiment solves the problems of low design efficiency, insufficient performance optimization, and high cost in the prior art by coupling the aerodynamic design, strength vibration design, and structural design.

[0184] In summary, the heavy-duty gas turbine compressor aerodynamic strength vibration structure coupling design method proposed in this embodiment significantly improves design collaboration and efficiency, achieves multi-dimensional performance optimization and balance, reduces design cost and resource consumption, improves design accuracy and reliability, promotes industry technology progress and innovation, and enhances product market competitiveness.

[0185] Embodiment Two

[0186] Figure 15 A structural diagram of a heavy-duty gas turbine compressor aerodynamic strength vibration structure coupling design system according to an embodiment of the present application is shown in FIG. 1. The system includes: Figure 15

[0187] The acquisition module 100 is configured to acquire design requirements of the heavy-duty gas turbine compressor and decompose the design requirements into aerodynamic performance indicators, strength vibration life indicators, and structure manufacturing and assembly indicators.

[0188] The first determination module 200 is configured to determine first through-flow parameters and first blade profile parameters of the compressor according to the aerodynamic performance indicators, the strength vibration life indicators, and a preset aerodynamic strength vibration coupling design process.

[0189] The second determination module 300 is configured to optimize the first through-flow parameters and the first blade profile parameters of the compressor according to the structure manufacturing and assembly indicators, the aerodynamic performance indicators, and a preset aerodynamic structure coupling design process, to obtain second through-flow parameters and second blade profile parameters of the compressor.

[0190] The optimization module 400 is configured to optimize the blade root geometry parameters of the compressor according to the strength vibration life indicators, the structure manufacturing and assembly indicators, and a preset strength structure coupling design process, and simultaneously design and optimize the geometry parameters of the compressor blade locking structure, to obtain optimized blade root geometry parameters and geometry parameters of the blade locking structure of the compressor.

[0191] The design module 500 is configured to design the heavy-duty gas turbine compressor based on the hub ratio, aspect ratio, flow channel coordinates, and blade axial position in the second through-flow parameters, the blade number, blade profile chord length, blade profile thickness, installation angle, and inlet / outlet geometric angle in the second blade profile parameters, and the optimized blade root geometry parameters and geometry parameters of the blade locking structure.

[0192] The first through-flow parameters and the second through-flow parameters both include the hub ratio, aspect ratio, flow channel coordinates, and blade axial position.

[0193] The first blade profile parameters and the second blade profile parameters both include the blade number, blade profile chord length, blade profile thickness, installation angle, and inlet / outlet geometric angle. ​

[0194] In the embodiments of the present disclosure, the first determining module 200 is further configured to:

[0195] determine the first throughflow parameter and the reasonable range of the blade profile parameter of the compressor according to the aerodynamic performance index, the strength vibration life index, and a preset throughflow design and vibration analysis coupled optimization chord length sub-process;

[0196] determine the first number of blades of the compressor according to the first throughflow parameter and the reasonable range of the blade profile parameter of the compressor and a preset blade profile design, blade root design and vibration analysis coupled optimization blade number sub-process;

[0197] determine the initial blade profile parameter of the compressor according to the reasonable range of the blade profile parameter of the compressor and a preset blade profile design and vibration analysis coupled optimization design blade profile geometry parameter sub-process, wherein the initial blade profile parameter includes a blade profile chord length, a blade profile thickness, an installation angle, and an inlet / outlet geometry angle;

[0198] determine whether the initial blade profile parameter of the compressor meets the aerodynamic performance index and the strength vibration life index according to a preset blade vibration and high-cycle fatigue life checking optimization sub-process, if yes, take the initial blade profile parameter of the compressor as the first blade profile parameter of the compressor, otherwise, optimize the initial blade profile parameter of the compressor according to a preset blade profile geometry parameter optimization sub-process until the initial blade profile parameter of the compressor meets the aerodynamic performance index and the strength vibration life index.

[0199] Further, the first determining module 200 is further configured to:

[0200] Step F1: perform throughflow design based on the aerodynamic performance index to determine the preliminary throughflow parameter of the compressor;

[0201] Step F2: perform preliminary blade modeling design based on the preliminary throughflow parameter of the compressor to determine the reasonable range of the blade profile parameter of the compressor, wherein the reasonable range of the blade profile parameter includes a blade chord length;

[0202] Step F3: perform preliminary vibration / flutter analysis on the initial blade profile constituted by the reasonable range of the blade profile parameter to determine the vibration frequency avoidance rate margin of the key vibration mode of the initial blade profile and the main excitation source and the flutter equivalent frequency margin of the key vibration mode;

[0203] Step F4: determining whether the absolute value of the difference between the vibration frequency avoidance margin of the key vibration mode of the initial blade profile and the vibration frequency avoidance margin in the strength vibration life index and the absolute value of the difference between the flutter equivalent frequency margin of the key vibration mode and the flutter equivalent frequency margin in the strength vibration life index are less than or equal to a preset first difference threshold value, if yes, adjusting the chord length based on a preset chord length adjustment scheme and returning to step F2, otherwise, taking the chord length of the initial blade profile of the compressor as the optimized chord length, taking the preliminary throughflow parameter as the first throughflow parameter, and taking the blade profile parameter range corresponding to the optimized chord length as the blade profile parameter reasonable range.

[0204] Further, the first determination module 200 is further used for:

[0205] obtaining a blade root preliminary design result based on the first throughflow parameter, the blade profile parameter reasonable range and the blade root strength design requirement, and obtaining a range of initial blade numbers based on the blade root preliminary design result.

[0206] performing vibration analysis on the initial blade profile, evaluating the key vibration mode natural frequency of the initial blade profile and the avoidance rate of the front and rear row blade number excitation source, and then determining the front and rear row blade number adjustment amount based on the key vibration mode natural frequency and the avoidance rate of the front and rear row blade number excitation source to obtain the adjusted front and rear row blade number of the compressor.

[0207] performing aerodynamic performance analysis on the initial blade profile of the compressor based on the adjusted front and rear row blade number to obtain an aerodynamic performance analysis result.

[0208] determining the first blade number of the compressor according to the aerodynamic performance analysis result and the blade root preliminary design result.

[0209] Further, the first determination module 200 is further used for:

[0210] Step A1: performing vibration / flutter analysis on the blade of the compressor based on the blade profile parameter reasonable range of the compressor, and entering a preset blade profile geometric parameter optimization sub-process.

[0211] Step A2: performing aerodynamic performance analysis based on the blade profile parameter reasonable range of the compressor to obtain a blade frequency adjustment optimized blade profile geometric parameter constraint, and then entering the preset blade profile geometric parameter optimization sub-process.

[0212] Further, the first determination module 200 is further used for:

[0213] Step B1: adjusting the key cross-section blade profile parameter of the blade based on the blade profile geometric parameter constraint and the aerodynamic performance index.

[0214] Step B2: if the vibration / flicker check of the adjusted blade does not meet the strength vibration life index, return to step B1; if it meets, go to step B3;

[0215] Step B3: perform aerodynamic performance check on the blade after adjusting the key cross-section airfoil parameters of the blade, determine whether the aerodynamic performance change value before and after adjustment is within the preset range, if yes, update the initial airfoil parameters based on the adjusted key cross-section airfoil parameters of the blade to perform optimization, obtain the optimized initial airfoil parameters, otherwise, return to step B1.

[0216] Further, the first determination module 200 is further used for:

[0217] obtaining a three-dimensional model of the blade of the compressor based on the initial airfoil parameters of the compressor;

[0218] performing three-dimensional finite element analysis on the three-dimensional model of the blade based on the preset aerodynamic boundary condition, and determining the vibration characteristics and high-cycle fatigue life of the blade;

[0219] determining whether the vibration characteristics of the blade meet the vibration frequency avoidance rate index in the strength vibration life index, and whether the high-cycle fatigue life of the blade is greater than the preset high-cycle fatigue cycle life index, if the vibration characteristics of the blade meet the vibration frequency avoidance rate index and the high-cycle fatigue life of the blade is greater than the preset high-cycle fatigue cycle life index, taking the initial airfoil parameters of the compressor as the first airfoil parameters of the compressor, otherwise, entering a preset airfoil geometric parameter optimization sub-process.

[0220] In the embodiment of the present disclosure, the second determination module 300 is further used for:

[0221] determining the blade axial position and flow passage coordinates in the axial space design according to the structure manufacturing assembly index when conducting through-flow design;

[0222] determining the planned blade number of the compressor in the circumferential space design when conducting airfoil design;

[0223] optimizing the first through-flow parameters and the first airfoil parameters according to the aerodynamic performance index, the blade axial position, the flow passage coordinates and the planned blade number of the compressor, to obtain the second through-flow parameters and the second airfoil parameters of the compressor.

[0224] In the embodiment of the present disclosure, the optimization module 400 is further used for:

[0225] Step D1: selecting the blade root type based on the second airfoil parameters to obtain the blade root type of the airfoil;

[0226] Step D2: design a blade root two-dimensional section based on the second blade profile parameter, and then perform blade root two-dimensional section strength evaluation to obtain blade root two-dimensional section parameters of the blade profile;

[0227] Step D3: design a blade root three-dimensional structure based on the second blade profile parameter, and then perform blade root three-dimensional finite element static strength evaluation to obtain blade root three-dimensional structure parameters of the blade profile;

[0228] Step D4: determine whether the low-cycle fatigue life of the blade profile meets the strength vibration life index and whether the blade of the blade profile meets a structure manufacturing assembly index based on the blade root type, the blade root two-dimensional section parameters of the blade profile, and the blade root three-dimensional structure parameters of the blade profile, if yes, go to Step D5, otherwise, return to Step D3;

[0229] Step D5: optimize the blade root geometric parameters in the second blade profile parameter based on the blade root type, the blade root two-dimensional section parameters, and the optimized blade root three-dimensional structure parameters to obtain optimized blade root geometric parameters;

[0230] Step D6: design a blade locking three-dimensional structure to obtain initial parameters of the blade locking structure;

[0231] Step D7: determine whether the strength life of the blade locking structure meets the strength vibration life index and whether the blade locking structure meets a structure manufacturing assembly index, if yes, take the initial parameters of the blade locking structure as the geometric parameters of the blade locking structure, otherwise, return to Step D6.

[0232] In summary, the heavy-duty gas turbine compressor aerodynamic strength vibration structure coupling design system provided in the embodiment improves design efficiency, optimizes performance balance, and reduces design cost.

[0233] In the description of the present specification, the description of the terms "one embodiment", "some embodiments", "an example", "a specific example", or "some examples" and the like means that the specific features, structures, materials or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present application. In the present specification, the illustrative description of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any appropriate manner in any one or more embodiments or examples. In addition, the person skilled in the art can combine and combine the different embodiments or examples described in the present specification and the features of the different embodiments or examples without contradiction.

[0234] Any processes or methods described in the flow charts or otherwise described herein can be understood as representing modules, segments, or portions of code that include one or more executable instructions for implementing the specified logical functions or steps, and the preferred embodiments of the application include additional or fewer steps, in other orders, with other functionality, in implementations of these preferred embodiments of the application. Thus, any of the steps, options, aspects, components, etc. discussed herein can be included or deleted in other embodiments of the application, and yet still be deemed to fall within the scope of the present application.

[0235] Although the embodiments of the present application have been shown and described above, it should be understood by those ordinary skilled in the art that the above embodiments are exemplary and cannot be construed as limiting the present application, and those ordinary skilled in the art can make changes, modifications, replacements and variations to the above embodiments within the scope of the present application.

Claims

1. A method for aeroelastic vibration-structure coupling design of a heavy-duty gas turbine compressor, characterized in that, The method comprises: obtaining design requirements of a heavy-duty gas turbine compressor, and decomposing the design requirements into aerodynamic performance indexes, strength and vibration life indexes, and structure manufacturing and assembly indexes; determining first through-flow parameters and first blade profile parameters of the compressor according to the aerodynamic performance indexes and the strength and vibration life indexes and a preset aerodynamic strength and vibration coupling design process; optimizing the first through-flow parameters and first blade profile parameters according to the structure manufacturing and assembly indexes and the aerodynamic performance indexes and a preset aerodynamic structure coupling design process to obtain second through-flow parameters and second blade profile parameters of the compressor; optimizing a blade root geometry parameter of the compressor according to the strength and vibration life indexes and the structure manufacturing and assembly indexes and a preset strength and structure coupling design process, and simultaneously designing and optimizing a geometry parameter of a compressor blade locking structure to obtain an optimized blade root geometry parameter and the geometry parameter of the blade locking structure of the compressor; designing the heavy-duty gas turbine compressor based on the hub ratio, aspect ratio, flow passage coordinates and blade axial position in the second through-flow parameters, the blade number, blade profile chord length, blade profile thickness, installation angle and inlet and outlet geometry angle in the second blade profile parameters, the optimized blade root geometry parameter and the geometry parameter of the blade locking structure. The first through-flow parameters and the second through-flow parameters both comprise: hub ratio, aspect ratio, flow passage coordinates and blade axial position. The first blade profile parameters and the second blade profile parameters both comprise: blade number, blade profile chord length, blade profile thickness, installation angle and inlet and outlet geometry angle.

2. The method of claim 1, wherein, The aerodynamic strength and vibration coupling design process comprises: determining a reasonable range of the first through-flow parameters and blade profile parameters of the compressor according to the aerodynamic performance indexes, the strength and vibration life indexes and a preset through-flow design and vibration analysis coupling optimization chord length sub-process; determining a first blade number of the compressor according to the reasonable range of the first through-flow parameters and blade profile parameters of the compressor and a preset blade profile design, blade root design and vibration analysis coupling optimization blade number sub-process; determining initial blade profile parameters of the compressor according to the reasonable range of the blade profile parameters of the compressor and a preset blade profile design and vibration analysis coupling optimization design blade profile geometry parameter sub-process, wherein the initial blade profile parameters comprise: blade profile chord length, blade profile thickness, installation angle and inlet and outlet geometry angle; judging whether the initial blade profile parameters of the compressor satisfy the aerodynamic performance indexes and the strength and vibration life indexes according to a preset blade vibration and high-cycle fatigue life checking optimization sub-process, if yes, taking the initial blade profile parameters of the compressor as the first blade profile parameters of the compressor, otherwise, optimizing the initial blade profile parameters of the compressor according to a preset blade profile geometry parameter optimization sub-process until the initial blade profile parameters of the compressor satisfy the aerodynamic performance indexes and the strength and vibration life indexes.

3. The method of claim 2, wherein, The preset through-flow design and vibration analysis coupling optimization chord length sub-process comprises: Step F1: carrying out through-flow design based on the aerodynamic performance indexes to determine preliminary through-flow parameters of the compressor; Step F2: based on the preliminary through-flow parameters of the compressor, preliminary profile design of the blade is carried out to determine a reasonable range of profile parameters of the compressor, wherein the reasonable range of profile parameters comprises: chord length of the blade; Step F3: preliminary vibration / flexural vibration analysis is carried out on the initial profile constituted by the reasonable range of profile parameters to determine vibration frequency avoidance rate margin of a key mode of vibration of the initial profile and a main excitation source and flexural vibration equivalent frequency margin of the key mode of vibration; Step F4: it is judged whether the absolute value of the difference between the vibration frequency avoidance rate margin of the key mode of vibration of the initial profile and the vibration frequency avoidance rate margin in the strength vibration life index is less than or equal to a preset first difference threshold value and whether the absolute value of the difference between the flexural vibration equivalent frequency margin of the key mode of vibration and the flexural vibration equivalent frequency margin in the strength vibration life index is less than or equal to the preset first difference threshold value, if yes, chord length is adjusted based on a preset chord length adjustment scheme and step F2 is returned, otherwise, the chord length of the initial profile of the compressor is taken as the optimized chord length, the preliminary through-flow parameters are taken as the first through-flow parameters, and the profile parameter range corresponding to the optimized chord length is taken as the reasonable range of profile parameters.

4. The method of claim 2, wherein, The preset profile design, root design and vibration analysis coupled optimization blade number sub-process comprises: a root preliminary design result is obtained based on the first through-flow parameters, the reasonable range of profile parameters and root strength design requirements, and an initial blade number range is obtained based on the root preliminary design result; vibration analysis is carried out on the initial profile to evaluate the key mode of vibration natural frequency of the initial profile and avoidance rate of front and rear row blade number excitation sources, and then front and rear row blade number adjustment amount is determined based on the key mode of vibration natural frequency and the avoidance rate of the front and rear row blade number excitation sources to obtain adjusted front and rear row blade number of the compressor; aerodynamic performance analysis is carried out on the initial profile of the compressor based on the adjusted front and rear row blade number to obtain aerodynamic performance analysis result; the first blade number of the compressor is determined according to the aerodynamic performance analysis result and the root preliminary design result.

5. The method of claim 2, wherein, The preset profile design and vibration analysis coupled optimization profile geometric parameter sub-process comprises: Step A1: vibration / flexural vibration analysis is carried out on the blade of the compressor based on the reasonable range of profile parameters of the compressor, and a preset profile geometric parameter optimization sub-process is entered; Step A2: aerodynamic performance analysis is carried out based on the reasonable range of profile parameters of the compressor to obtain blade frequency modulation optimized profile geometric parameter constraint of the compressor, and then the preset profile geometric parameter optimization sub-process is entered.

6. The method of claim 5, wherein, The preset profile geometric parameter optimization sub-process comprises: Step B1: key cross-section profile parameters of the blade are adjusted based on the profile geometric parameter constraint and the aerodynamic performance index; Step B2: vibration / flexural vibration checking is carried out on the adjusted blade, if the strength vibration life index is not satisfied, step B1 is returned, and if it is satisfied, step B3 is entered; Step B3: checking aerodynamic performance of the blade after adjusting the key cross-section profile parameters of the blade, judging whether the change of the aerodynamic performance before and after the adjustment is within the preset range, if yes, updating the initial profile parameters based on the adjusted key cross-section profile parameters of the blade to perform optimization to obtain the optimized initial profile parameters, otherwise, returning to step B1.

7. The method of claim 2, wherein, The preset blade vibration and high-cycle fatigue life checking and optimization sub-process includes: obtaining a three-dimensional model of the blade of the compressor based on the initial profile parameters of the compressor; performing three-dimensional finite element analysis on the three-dimensional model of the blade based on preset aerodynamic boundary conditions to determine the vibration characteristics and high-cycle fatigue life of the blade; judging whether the vibration characteristics of the blade meet the vibration frequency avoidance rate index in the strength vibration life index and whether the high-cycle fatigue life of the blade is greater than the preset high-cycle fatigue cycle life index, if the vibration characteristics of the blade meet the vibration frequency avoidance rate index and the high-cycle fatigue life of the blade is greater than the preset high-cycle fatigue cycle life index, taking the initial profile parameters of the compressor as the first profile parameters of the compressor, otherwise, entering the preset profile geometric parameter optimization sub-process.

8. The method of claim 1, wherein, The preset aerodynamic structure coupling design process includes: determining the axial position of the blade and the flow passage coordinates during through-flow design according to the structure manufacturing and assembly index; determining the planned number of blades of the compressor during profile design to carry out circumferential space design; optimizing the first through-flow parameters and the first profile parameters according to the aerodynamic performance index, the axial position of the blade, the flow passage coordinates and the planned number of blades of the compressor to obtain the second through-flow parameters and the second profile parameters of the compressor.

9. The method of claim 1, wherein, The preset strength structure coupling design process includes: Step D1: selecting a blade root type based on the second profile parameters to obtain a blade root type of the profile; Step D2: designing a two-dimensional cross-section of the blade root based on the second profile parameters, and then performing two-dimensional cross-section strength evaluation of the blade root to obtain two-dimensional cross-section parameters of the blade root of the profile; Step D3: designing a three-dimensional structure of the blade root based on the second profile parameters, and then performing three-dimensional finite element static strength evaluation of the blade root to obtain three-dimensional structure parameters of the blade root of the profile; Step D4: judging whether the low-cycle fatigue life of the profile meets the strength vibration life index and whether the blade of the profile meets the structure manufacturing and assembly index based on the blade root type, the two-dimensional cross-section parameters of the blade root of the profile and the three-dimensional structure parameters of the blade root of the profile, if yes, entering step D5, otherwise, returning to step D3; Step D5: optimizing the blade root geometric parameters in the second profile parameters based on the blade root type, the two-dimensional cross-section parameters of the blade root of the profile and the optimized three-dimensional structure parameters of the blade root to obtain optimized blade root geometric parameters; Step D6: designing a three-dimensional structure of a blade locking to obtain initial parameters of the three-dimensional structure of the blade locking. Step D7: judging whether the strength life of the blade locking structure meets the strength vibration life index and whether the blade locking structure meets the structure manufacturing assembly index, if yes, taking the initial parameters of the blade locking structure as the geometric parameters of the blade locking structure, otherwise, returning to step D6.

10. A heavy-duty gas turbine engine compressor aero-structural vibration- coupling design system, characterized by, The system comprises: an acquisition module configured to acquire design requirements of a heavy-duty gas turbine compressor and decompose the design requirements into an aerodynamic performance index, a strength vibration life index and a structure manufacturing assembly index; a first determination module configured to determine first through-flow parameters and first blade profile parameters of the compressor according to the aerodynamic performance index, the strength vibration life index and a preset aerodynamic strength vibration coupling design process; a second determination module configured to optimize the first through-flow parameters and the first blade profile parameters of the compressor according to the structure manufacturing assembly index, the aerodynamic performance index and a preset aerodynamic structure coupling design process to obtain second through-flow parameters and second blade profile parameters of the compressor; an optimization module configured to optimize blade root geometric parameters of the compressor according to the strength vibration life index, the structure manufacturing assembly index and a preset strength structure coupling design process, and simultaneously design and optimize geometric parameters of a blade locking structure of the compressor to obtain optimized blade root geometric parameters and geometric parameters of the blade locking structure of the compressor; a design module configured to design the heavy-duty gas turbine compressor based on a hub ratio, an aspect ratio, a flow channel coordinate and a blade axial position in the second through-flow parameters, a blade number, a blade profile chord length, a blade profile thickness, an installation angle and an inlet-outlet geometric angle in the second blade profile parameters, the optimized blade root geometric parameters and the geometric parameters of the blade locking structure; wherein the first through-flow parameters and the second through-flow parameters each comprise the hub ratio, the aspect ratio, the flow channel coordinate and the blade axial position; the first blade profile parameters and the second blade profile parameters each comprise the blade number, the blade profile chord length, the blade profile thickness, the installation angle and the inlet-outlet geometric angle.

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