Turbine blade design method and device, electronic equipment and storage medium

Abstract

The invention provides a turbine blade design method and device, electronic equipment and a storage medium, and belongs to the technical field of turbine machinery design. The method comprises the steps that design working conditions are obtained, at least one expansion stage is determined according to the design working conditions, pneumatic calculation is conducted on any expansion stage based on the expansion stage, pneumatic parameters are generated, the pneumatic parameters comprise pneumatic efficiency, the pneumatic parameters meeting a first preset condition are screened out from the multiple pneumatic parameters according to the pneumatic efficiency, and the pneumatic parameters meeting the first preset condition are obtained. And according to the pneumatic parameters meeting the first preset condition, the turbine blade is designed. Therefore, the expansion stage is determined based on the design working condition, the pneumatic parameters meeting the first preset condition are obtained through pneumatic calculation, and the turbine blade is designed according to the pneumatic parameters meeting the first preset condition. The design of the turbine blade can be realized, and the axial flow turbine efficiency of S-CO2 is improved.

Description

Technical Field

[0001] The present application relates to the technical field of turbine machinery design, and in particular to a design method, device, electronic equipment and storage medium for turbine blades. Background Art

[0002] As the world's population and economic activities continue to increase, energy demand is also growing. As the cornerstone of modern society, the stable supply and efficient use of energy are crucial to maintaining sustainable economic development and improving people's living standards.

[0003] However, in the current energy structure, fossil energy is the most important energy source. In order to effectively cope with the energy crisis, converting fossil energy into electric energy has become an urgent need, and power cycle technology plays a vital role in this process.

[0004] In the related technologies, in the existing S-CO2 power cycle technology, the S-CO2 turbine is the core component in its cycle process, but its design faces many challenges. Due to the high pressure and high density of the S-CO2 working fluid itself, the size of the turbine blades is significantly lower than that of traditional steam turbines and steam turbines. In particular, the size of turbine blades of small power levels is further reduced, which brings great difficulties to the design of the blades. At the same time, due to the small size of the blades, the secondary flow loss is also significantly increased, resulting in reduced blade efficiency. Summary of the invention

[0005] The purpose of the embodiments of the present application is to provide a method, device, electronic device and storage medium for designing turbine blades, so as to realize the design of turbine blades and improve the efficiency of the axial flow turbine of S-CO2. The specific technical solution is as follows:

[0006] In a first aspect of an embodiment of the present application, a method for designing a turbine blade is first provided, the method comprising:

[0007] Obtain design operating conditions;

[0008] Determining at least one expansion stage according to the design operating conditions;

[0009] For any expansion stage, performing aerodynamic calculation based on the expansion stage to generate aerodynamic parameters, wherein the aerodynamic parameters include aerodynamic efficiency;

[0010] According to the aerodynamic efficiency, aerodynamic parameters satisfying a first preset condition are selected from the plurality of aerodynamic parameters;

[0011] The turbine blades are designed according to the aerodynamic parameters that meet the first preset condition.

[0012] In an optional embodiment, the aerodynamic parameters include a first parameter and a second parameter, and the aerodynamic calculation is performed based on the expansion stage to generate the aerodynamic parameters, and the aerodynamic parameters include aerodynamic efficiency, including:

[0013] According to the design operating conditions, at least one expansion stage reaction degree is set, and the expansion stage stagnation isentropic enthalpy drop, blade rotation speed and stationary blade speed coefficient are determined;

[0014] For any of the expansion stage reaction degrees, determining the stator blade outlet absolute airflow velocity based on the expansion stage reaction degree, the expansion stage stagnation isentropic enthalpy drop and the stator blade velocity coefficient;

[0015] Determining the relative airflow velocity at the stator blade outlet according to the absolute airflow velocity at the stator blade outlet and the blade rotation speed;

[0016] The first parameter includes the reaction degree of the expansion stage, the stagnation isentropic enthalpy drop of the expansion stage, the blade rotation speed, the absolute airflow speed at the stator blade outlet, and the relative airflow speed at the stator blade outlet;

[0017] Perform aerodynamic calculation according to the first parameter and the design operating condition to generate second parameters, where the second parameters include the aerodynamic efficiency.

[0018] In an optional embodiment, the aerodynamic calculation is performed according to the first parameter and the design operating condition to generate a second parameter, wherein the second parameter includes the aerodynamic efficiency, including:

[0019] acquiring the expansion stage reaction degree, the expansion stage stagnation isentropic enthalpy drop, the blade rotation speed, the stator blade outlet absolute airflow speed and the stator blade outlet relative airflow speed from the first parameter;

[0020] Determining a speed coefficient from the design operating conditions, wherein the speed coefficient includes a moving blade speed coefficient and a stationary blade speed coefficient;

[0021] Determine the relative airflow velocity at the moving blade outlet according to the relative airflow velocity at the stationary blade outlet, the reaction degree of the expansion stage, the moving blade velocity coefficient, and the stagnation isentropic enthalpy drop of the expansion stage;

[0022] Determine the absolute airflow velocity at the rotor blade outlet according to the relative airflow velocity at the rotor blade outlet and the blade rotation speed;

[0023] The aerodynamic efficiency is generated according to the stationary blade speed coefficient, the moving blade speed coefficient, the absolute airflow velocity at the stationary blade outlet, the stagnation isentropic enthalpy drop of the expansion stage, the relative airflow velocity at the moving blade outlet, and the absolute airflow velocity at the moving blade outlet;

[0024] The second parameters include the speed coefficient, the relative airflow speed at the rotor blade outlet, the absolute airflow speed at the rotor blade outlet, and the aerodynamic efficiency.

[0025] In an optional embodiment, the step of designing the turbine blades according to the aerodynamic parameters satisfying the first preset condition comprises:

[0026] A coordinate system is established with the main flow axis of the working fluid as the x-axis and the normal direction of the x-axis as the y-axis;

[0027] Defining the mid-camber equation and thickness equation of the turbine blade according to the coordinate system;

[0028] The turbine blade is designed according to the median arc equation, the thickness equation, the first parameter and the second parameter.

[0029] In an optional embodiment, the designing of the turbine blade according to the camber line equation, the thickness equation, the first parameter and the second parameter comprises:

[0030] According to the mid-arc equation, determining the inclination angle equation corresponding to the inclination angle at each point of the blade in the coordinate system;

[0031] Inputting the x value corresponding to each point of the blade into the thickness equation to determine the blade thickness corresponding to each point of the blade and the maximum thickness of the blade;

[0032] The turbine blade is designed according to the mid-arc line equation, the inclination angle equation, the blade thickness corresponding to each point on the blade, the maximum blade thickness, the first parameter and the second parameter.

[0033] In an optional embodiment, the designing of the turbine blade according to the camber line equation, the inclination angle equation, the blade thickness corresponding to each point of the blade, the maximum thickness of the blade, the first parameter and the second parameter comprises:

[0034] Determine the axial length and angle parameters of the blade according to the first parameter and the second parameter;

[0035] Inputting the first parameter, the blade thickness corresponding to each point of the blade, the second parameter, the blade axial length and the angle parameter into the inclination angle equation and the thickness equation to calculate the throat area of ​​the blade, thereby obtaining a first blade throat area;

[0036] When the throat area of ​​the first blade satisfies the second preset condition, the turbine blade profile is drawn in the coordinate system according to the blade thickness corresponding to each point of the blade, the maximum thickness of the blade, the mid-arc line equation, the first blade throat area, the blade axial length and the angle parameter to complete the turbine blade design.

[0037] In an optional embodiment, the method further comprises:

[0038] Obtain changing operating conditions;

[0039] Calculating according to the changed operating condition and the designed operating condition to generate a changed operating condition efficiency;

[0040] Based on the variable operating efficiency, the performance prediction of the turbine blades is completed.

[0041] In a second aspect of an embodiment of the present application, a device for designing a turbine blade is further provided, the device comprising:

[0042] Acquisition module, to obtain design working conditions;

[0043] An analysis module, determining at least one expansion stage according to the design operating conditions;

[0044] A processing module, for any expansion stage, performs aerodynamic calculation based on the expansion stage to generate aerodynamic parameters, wherein the aerodynamic parameters include aerodynamic efficiency;

[0045] A screening module, screening the aerodynamic parameters satisfying a first preset condition from the plurality of aerodynamic parameters according to the aerodynamic efficiency;

[0046] The design module designs the turbine blades according to the aerodynamic parameters that meet the first preset condition.

[0047] In a third aspect of the embodiments of the present application, there is further provided an electronic device, comprising a processor, a communication interface, a memory and a communication bus, wherein the processor, the communication interface and the memory communicate with each other via the communication bus;

[0048] Memory, used to store computer programs;

[0049] The processor is used to implement the turbine blade design method described in any one of the first aspects above when executing the program stored in the memory.

[0050] In a fourth aspect of an embodiment of the present application, a storage medium is further provided, wherein instructions are stored in the storage medium, and when the storage medium is run on a computer, the computer executes the turbine blade design method described in any one of the first aspects above.

[0051] In a fifth aspect of an embodiment of the present application, there is also provided a computer program product comprising instructions, which, when executed on a computer, enables the computer to execute the turbine blade design method described in any one of the first aspects above.

[0052] The above technical solution provided in the embodiment of the present application obtains the design operating conditions, determines at least one expansion stage according to the design operating conditions, performs aerodynamic calculations based on the expansion stage for any expansion stage, generates aerodynamic parameters, and the aerodynamic parameters include aerodynamic efficiency. According to the aerodynamic efficiency, aerodynamic parameters that meet the first preset condition are screened from multiple aerodynamic parameters, and the turbine blades are designed according to the aerodynamic parameters that meet the first preset condition. In this way, the expansion stage is determined based on the design operating conditions, and the aerodynamic parameters that meet the first preset condition are obtained through aerodynamic calculations, so that the turbine blades are designed according to the aerodynamic parameters that meet the first preset condition. The design of the turbine blades can be realized, and the efficiency of the axial flow turbine of S-CO2 can be improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0053] The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the present application and, together with the description, serve to explain the principles of the present application.

[0054] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, for ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative labor.

[0055] Figure 1 A schematic diagram of an implementation flow of a turbine blade design method provided in an embodiment of the present application;

[0056] Figure 2 A schematic diagram of an implementation flow of another data distribution rule recommendation method provided in an embodiment of the present application;

[0057] Figure 3 A schematic diagram of an implementation flow of a pneumatic calculation provided in an embodiment of the present application;

[0058] Figure 4 A schematic diagram of an implementation process for generating aerodynamic efficiency provided in an embodiment of the present application;

[0059] Figure 5 A schematic diagram of an implementation process of a turbine blade design provided in an embodiment of the present application;

[0060] Figure 6 A schematic diagram of an implementation process of another turbine blade design provided in an embodiment of the present application;

[0061] Figure 7 A schematic diagram of the structure of a turbine blade provided in an embodiment of the present application;

[0062] Figure 8 A schematic diagram of the structure of an axial flow turbine expansion stage provided in an embodiment of the present application;

[0063] Fig. 9 A schematic diagram of the structure of a turbine blade design device provided in an embodiment of the present application;

[0064] Fig.10 A schematic diagram of the structure of an electronic device provided in an embodiment of the present application. DETAILED DESCRIPTION

[0065] In order to make the purpose, technical solution and advantages of the embodiments of the present application clearer, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application.

[0066] The disclosure below provides many different embodiments or examples to realize the different structures of the present application. In order to simplify the disclosure of the present application, the parts and settings of specific examples are described in detail below. Of course, they are only examples, and the purpose is not to limit the present application. In addition, the present application can repeat reference numbers and / or letters in different examples. This repetition is for the purpose of simplification and clarity, and does not itself indicate the relationship between the various embodiments and / or settings discussed.

[0067] To facilitate understanding of the embodiments of the present application, further explanation will be given below with reference to specific embodiments in conjunction with the accompanying drawings. The embodiments do not constitute a limitation on the embodiments of the present application.

[0068] like Figure 1 FIG. 1 is a schematic diagram of an implementation flow of a method for designing a turbine blade provided in an embodiment of the present application. The method may specifically include the following steps:

[0069] S101, obtaining design operating conditions.

[0070] In the embodiment of the present application, the design operating condition is obtained. The design operating condition may be the optimal applicable condition of the turbine blade, and the design operating condition may include inlet temperature (such as 200°C, 300°C, 400°C, etc.), inlet pressure, inlet velocity, outlet pressure, flow rate and other information. The present application example does not limit this.

[0071] The above inlet temperature directly affects the physical properties of the working fluid S-CO2 (i.e., supercritical carbon dioxide), such as density, specific heat capacity, etc., and thus has a significant impact on the aerodynamic performance and thermal efficiency of the turbine blades. The inlet temperature values ​​include but are not limited to 200°C, 500°C, 600°C, etc., and this application example does not limit this.

[0072] The above-mentioned inlet pressure determines the compression state of the working fluid S-CO2 before entering the turbine, and is also an important factor affecting the design and performance of the turbine blades. In the S-CO2 cycle, the inlet pressure is usually higher to adapt to the physical properties of CO2 in the supercritical state. The inlet pressure includes but is not limited to 10MPa, 15MPa, 50MPa, etc., and this application example does not limit this.

[0073] The above-mentioned inlet velocity is the velocity of the working fluid S-CO2 at the inlet of the turbine blade, which reflects the magnitude of the kinetic energy and has a direct impact on the impact force and energy conversion efficiency of the turbine blade. The inlet velocity includes but is not limited to 30m / s, 40m / s, 60m / s, etc., and this application example does not limit this.

[0074] The above outlet pressure determines the expansion ratio and work capacity of the turbine blades. In the S-CO2 turbine, the outlet pressure is usually low to achieve effective expansion and energy release of the working fluid. The outlet pressure includes but is not limited to 2MPa, 4MPa, 10MPa, etc., and this application example does not limit this.

[0075] The above flow rate refers to the mass of the working fluid passing through the turbine per unit time. It directly affects the output power and efficiency of the turbine. The flow rate includes but is not limited to 15kg / s, 25kg / s, 35kg / s, etc., and this application example does not limit this.

[0076] S102, determining at least one expansion stage according to design operating conditions.

[0077] In an embodiment of the present application, at least one expansion stage is determined according to the design operating conditions. The design operating conditions include key parameters such as inlet temperature, inlet pressure, inlet velocity, outlet pressure and flow rate. Among them, the determination of the expansion stage also needs to consider factors such as the physical properties of the working fluid S-CO2, the size limitations of the turbine, efficiency requirements, and the overall layout of the circulation system. In addition, the number of expansion stages will also affect the size and shape of the turbine blades. More expansion stages usually mean that more blades are needed to guide the flow of the working fluid and convert its kinetic energy, but this may also increase the complexity and manufacturing cost of the turbine. For example, the expansion stages can be 2, 8, 16, etc., and the examples of the present application are not limited to this.

[0078] For example, according to the design operating condition 1, the expansion stage can be determined to be 2; according to the design operating condition 2, the expansion stage can be determined to be 8.

[0079] S103, for any expansion stage, performing aerodynamic calculation based on the expansion stage to generate aerodynamic parameters, where the aerodynamic parameters include aerodynamic efficiency.

[0080] In the embodiment of the present application, for any expansion stage, aerodynamic calculation is performed based on the expansion stage to generate aerodynamic parameters, which include aerodynamic efficiency. The aerodynamic efficiency directly reflects the quality of turbine blade design and is crucial to improving the performance of the entire turbine system.

[0081] S104, selecting aerodynamic parameters that meet a first preset condition from a plurality of aerodynamic parameters according to the aerodynamic efficiency.

[0082] In an embodiment of the present application, aerodynamic parameters that meet the first preset condition are screened from multiple aerodynamic parameters based on aerodynamic efficiency, wherein the first preset condition may be that the aerodynamic efficiency reaches a certain level or is higher than the average level. By screening the aerodynamic parameters based on aerodynamic efficiency, a design solution that can meet the requirements of high-efficiency conversion can be found from a large number of aerodynamic parameters, providing strong support for the subsequent optimization design of turbine blades. During the screening process, mathematical methods such as comparison and sorting can be used to ensure that the optimal or suboptimal aerodynamic parameter combination is finally selected, and this application example does not limit this.

[0083] For example, the first preset condition may be that the aerodynamic efficiency is greater than 60%, then aerodynamic parameters with aerodynamic efficiency greater than 60% are screened out from multiple aerodynamic parameters; the first preset condition may also be that the aerodynamic efficiency is greater than 50%, then aerodynamic parameters with aerodynamic efficiency greater than 50% are screened out from multiple aerodynamic parameters.

[0084] S105, designing turbine blades according to aerodynamic parameters that meet the first preset condition.

[0085] In an embodiment of the present application, the turbine blades are designed based on aerodynamic parameters that meet the first preset condition. During the turbine blade design process, it is necessary to fully utilize the results of aerodynamic calculations to ensure that the blades can guide the airflow to flow efficiently and stably while reducing energy loss and frictional resistance. The present application example is not limited to this.

[0086] For example, the first preset condition is that the aerodynamic efficiency is greater than 60%, and the turbine blades are designed according to the aerodynamic parameters with the aerodynamic efficiency being greater than 60%.

[0087] Through the above description of the technical solution provided by the embodiment of the present application, the design operating conditions are obtained, at least one expansion stage is determined according to the design operating conditions, and for any expansion stage, aerodynamic calculation is performed based on the expansion stage to generate aerodynamic parameters, the aerodynamic parameters including aerodynamic efficiency, and aerodynamic parameters that meet the first preset conditions are screened from multiple aerodynamic parameters according to the aerodynamic efficiency, and the turbine blades are designed according to the aerodynamic parameters that meet the first preset conditions. In this way, the expansion stage is determined based on the design operating conditions, and the aerodynamic parameters that meet the first preset conditions are obtained through aerodynamic calculation, so that the turbine blades are designed according to the aerodynamic parameters that meet the first preset conditions. The design of the turbine blades can be realized, and the axial flow turbine efficiency of S-CO2 can be improved.

[0088] like Figure 2 FIG. 1 is a schematic diagram of an implementation flow of another data distribution rule recommendation method provided in an embodiment of the present application, which may specifically include the following contents:

[0089] S201, obtaining design operating conditions.

[0090] In the embodiment of the present application, this step is similar to the above-mentioned step S101, and the embodiment of the present application will not be described one by one here.

[0091] S202, determining at least one expansion stage according to design operating conditions.

[0092] In an embodiment of the present application, at least one expansion stage is determined according to the design operating conditions. The design operating conditions include key parameters such as inlet temperature, inlet pressure, inlet velocity, outlet pressure and flow rate. Among them, the determination of the expansion stage also needs to consider factors such as the physical properties of the working fluid S-CO2, the size limitations of the turbine, efficiency requirements, and the overall layout of the circulation system. In addition, the number of expansion stages will also affect the size and shape of the turbine blades. More expansion stages usually mean that more blades are needed to guide the flow of the working fluid and convert its kinetic energy, but it may also increase the complexity and manufacturing cost of the turbine. In the design of the S-CO2 turbine, since S-CO2 has the characteristics of high constant pressure specific heat and energy density, reasonable expansion stage distribution can effectively improve the cycle efficiency. Therefore, when determining the number of expansion stages, the principle of enthalpy drop distribution is usually combined to ensure that the working fluid in each expansion stage can fully expand and release enough energy.

[0093] For example, the restriction of the local ideal Mach number Ma≤0.75 at the blade outlet can be used to perform reasonable enthalpy drop distribution and select a suitable expansion stage. For example, the expansion stages can be 2, 8, 16, etc., and this application example does not limit this.

[0094] S203, for any expansion stage, setting at least one expansion stage reaction degree according to the design operating conditions, and determining the expansion stage stagnation isentropic enthalpy drop, blade rotation speed and stationary blade speed coefficient.

[0095] In an embodiment of the present application, for any expansion stage, at least one expansion stage reaction degree is set according to the design operating conditions, and the expansion stage stagnation isentropic enthalpy drop, blade rotation speed and stationary blade speed coefficient are determined.

[0096] The above expansion stage reaction is a parameter used to measure the expansion degree of airflow on the moving blades in the turbine, that is, the ratio of the enthalpy drop of the moving blades to the total enthalpy drop. It reflects the degree of expansion of the airflow in the blade channel. The selection of reaction has a great influence on the performance of the turbine, including efficiency, stability and axial thrust. By setting at least one expansion stage reaction according to the design operating conditions, the blade with the best performance can be obtained by setting at least one expansion stage reaction.

[0097] The above expansion stage stagnation isentropic enthalpy drop refers to the maximum energy that can be released by the airflow from the inlet to the outlet under isentropic conditions (i.e., no heat exchange and friction loss) in a certain expansion stage of the turbine. It is used to measure the work capacity of the turbine stage.

[0098] The blade rotation speed refers to the linear velocity or angular velocity of the turbine blade during rotation. The blade rotation speed directly affects the dynamic pressure drop on the blade, the flow state of the airflow, and the stress distribution of the blade.

[0099] The above-mentioned stator blade speed coefficient is used to reflect the quality of the stator blade design and the speed loss of the airflow when passing through the stator blade (i.e., fixed blade). In turbine design, optimizing the stator blade speed coefficient can reduce speed loss and improve turbine efficiency. The speed coefficient reflects the speed loss in the moving blade or stator blade.

[0100] The isentropic enthalpy drop of the moving blades mentioned above refers to the maximum energy that can be released by the airflow from the inlet to the outlet in the moving blade channel under isentropic conditions.

[0101] Among them, the stagnation isentropic enthalpy drop of the expansion stage can be obtained by calling the physical property library through the blade inlet and outlet parameters.

[0102] The isentropic enthalpy drop of the moving blade can be calculated according to the following isentropic enthalpy drop formula of the moving blade:

[0103]

[0104] in, is the isentropic enthalpy drop of the expansion stage, Ω is the reaction degree of the expansion stage, Δh 2s is the isentropic enthalpy drop of the moving blade.

[0105] The blade rotation speed and the stationary blade speed coefficient can be set according to the design operating conditions.

[0106] For example, according to the design operating conditions, 10 expansion stage reaction degrees are set, and the corresponding blade rotation speed and stationary blade speed coefficient are determined. The physical property library is called using the import and export parameters to obtain the stagnation isentropic enthalpy drop of the expansion stage, and the isentropic enthalpy drop of the moving blade is calculated according to the isentropic enthalpy drop formula of the moving blade.

[0107] S204, for any expansion stage reaction degree, determine the absolute airflow velocity at the stator blade outlet based on the expansion stage reaction degree, the expansion stage stagnation isentropic enthalpy drop and the stator blade velocity coefficient.

[0108] Further, in the embodiment of the present application, for any expansion stage reaction degree, the absolute airflow velocity at the stator blade outlet is determined based on the expansion stage reaction degree, the expansion stage stagnation isentropic enthalpy drop and the stator blade velocity coefficient, and the absolute airflow velocity at the stator blade outlet can be calculated by the following formula for the absolute airflow velocity at the stator blade outlet:

[0109]

[0110] Among them, Ω is the expansion stage reaction degree, is the stagnation isentropic enthalpy drop of the expansion stage, is the stationary blade velocity coefficient, c1 is the absolute airflow velocity at the stationary blade outlet.

[0111] S205, determining the relative airflow velocity at the stator blade outlet according to the absolute airflow velocity at the stator blade outlet and the blade rotation speed.

[0112] In an embodiment of the present application, the relative airflow velocity at the stator blade outlet is determined based on the absolute airflow velocity at the stator blade outlet and the blade rotation speed.

[0113] The specific method of determining the relative airflow velocity at the stator blade outlet based on the absolute airflow velocity at the stator blade outlet and the blade rotation speed can be obtained through the following steps.

[0114] Step 1: Set the rotation speed, hub diameter and average blade height of the moving blade according to the design operating conditions, and then calculate the blade rotation speed according to the following blade rotation speed formula:

[0115]

[0116] Among them, u is the blade rotation speed, N is the rotation speed, D is the hub diameter, and L2 is the average blade height of the moving blade.

[0117] Step 2, set the absolute airflow angle at the stator blade outlet according to the design working conditions, and determine the relative airflow velocity at the stator blade outlet according to the absolute airflow velocity at the stator blade outlet, the blade rotation speed, and the absolute airflow angle at the stator blade outlet. The relative airflow velocity at the stator blade outlet can be calculated using the following formula for the relative airflow velocity at the stator blade outlet:

[0118]

[0119] Among them, c 11 is the absolute airflow velocity at the stator blade outlet, u1 is the blade rotation speed, α1 is the absolute airflow angle at the stator blade outlet, and w1 is the relative airflow velocity at the stator blade outlet.

[0120] S206, the first parameters include the reaction degree of the expansion stage, the stagnation isentropic enthalpy drop of the expansion stage, the blade rotation speed, the absolute airflow speed at the stator blade outlet, and the relative airflow speed at the stator blade outlet.

[0121] In the embodiment of the present application, the first parameter includes the reaction degree of the expansion stage, the stagnation isentropic enthalpy drop of the expansion stage, the blade rotation speed, the absolute airflow velocity at the stator blade outlet and the relative airflow velocity at the stator blade outlet, and the example of the present application is not limited to this.

[0122] S207, performing aerodynamic calculation according to the first parameter and the design operating condition to generate a second parameter, where the second parameter includes aerodynamic efficiency, and the aerodynamic parameter includes the first parameter and the second parameter.

[0123] In an embodiment of the present application, aerodynamic calculation is performed based on the first parameter and the design operating conditions to generate the second parameter, the second parameter includes the aerodynamic efficiency, and the aerodynamic parameters include the first parameter and the second parameter.

[0124] For example, aerodynamic calculations are performed based on the expansion stage reaction degree, expansion stage stagnation isentropic enthalpy drop, blade rotation speed, absolute airflow velocity at the stator blade outlet, relative airflow velocity at the stator blade outlet, and design operating conditions included in the first parameter to generate aerodynamic efficiency.

[0125] How to perform aerodynamic calculation based on the first parameter and the design working conditions to generate the second parameter, the second parameter includes aerodynamic efficiency, for details, please refer to Figure 3 As shown in the method. Figure 3 As shown, it is a schematic diagram of an implementation process of a pneumatic calculation provided in an embodiment of the present application, which may specifically include the following steps:

[0126] S301, obtaining the expansion stage reaction degree, the expansion stage stagnation isentropic enthalpy drop, the blade rotation speed, the absolute airflow speed at the stator blade outlet, and the relative airflow speed at the stator blade outlet from the first parameter.

[0127] In an embodiment of the present application, the expansion stage reaction degree, the expansion stage stagnation isentropic enthalpy drop, the blade rotation speed, the absolute airflow velocity at the stator blade outlet and the relative airflow velocity at the stator blade outlet are obtained from the first parameter for aerodynamic calculation.

[0128] S302, determining a speed coefficient from design operating conditions, where the speed coefficient includes a moving blade speed coefficient and a stationary blade speed coefficient.

[0129] In an embodiment of the present application, the speed coefficient is determined from the design operating conditions, and the speed coefficient includes the moving blade speed coefficient and the stationary blade speed coefficient, wherein the speed coefficient is used to reflect the quality of the blade (stationary blade and moving blade) design and the speed loss of the airflow when passing through the blade (stationary blade and moving blade).

[0130] S303, determining the relative airflow velocity at the moving blade outlet according to the relative airflow velocity at the stationary blade outlet, the reaction degree of the expansion stage, the moving blade velocity coefficient, and the stagnation isentropic enthalpy drop of the expansion stage.

[0131] In the embodiment of the present application, the relative airflow velocity at the moving blade outlet is determined according to the relative airflow velocity at the stationary blade outlet, the reaction degree of the expansion stage, the moving blade velocity coefficient, and the stagnation isentropic enthalpy drop of the expansion stage. The relative airflow velocity at the moving blade outlet reflects the relative velocity of the airflow at the moving blade outlet.

[0132] The specific method of determining the relative airflow velocity at the moving blade outlet according to the relative airflow velocity at the stationary blade outlet, the reaction degree of the expansion stage, the moving blade velocity coefficient and the stagnation isentropic enthalpy drop of the expansion stage can be obtained through the following steps.

[0133] Step 1, determining the relative airflow angle at the stator blade outlet according to the absolute airflow velocity at the stator blade outlet, the relative airflow velocity at the stator blade outlet and the absolute airflow angle at the stator blade outlet.

[0134] The relative airflow angle at the stator blade outlet can be calculated using the following formula:

[0135]

[0136] Among them, c 12 is the absolute airflow velocity at the stator blade outlet, w 11 is the relative airflow velocity at the stator blade outlet, α 11 is the absolute airflow angle at the stator blade outlet, and β2 is the relative airflow angle at the stator blade outlet.

[0137] Step 2, determining the ideal relative airflow velocity at the moving blade outlet according to the reaction degree of the expansion stage, the stagnation isentropic enthalpy drop of the expansion stage and the relative airflow velocity at the stationary blade outlet.

[0138] The ideal relative airflow velocity at the moving blade outlet can be calculated using the following formula for the ideal relative airflow velocity at the moving blade outlet:

[0139]

[0140] Among them, Ω1 is the reaction degree of the expansion stage, is the isentropic enthalpy drop of the expansion stage, w 12 is the relative airflow velocity at the stationary blade outlet, w 2s It is the ideal relative airflow velocity at the moving blade outlet.

[0141] Step 3, setting the moving blade velocity coefficient according to the design operating conditions, and determining the actual relative airflow velocity at the moving blade outlet according to the moving blade velocity coefficient and the ideal relative airflow velocity at the moving blade outlet.

[0142] The actual relative airflow velocity at the moving blade outlet can be calculated using the following formula for the actual relative airflow velocity at the moving blade outlet:

[0143] w2=θ*w 22s

[0144] Where θ is the blade speed coefficient, w 22s is the ideal relative airflow velocity at the moving blade outlet, and w2 is the actual relative airflow velocity at the moving blade outlet.

[0145] S304, determining the absolute airflow velocity at the rotor blade outlet according to the relative airflow velocity at the rotor blade outlet and the blade rotation speed.

[0146] In the embodiment of the present application, the blade outlet angle is determined according to the design working conditions, and the absolute airflow velocity at the blade outlet is determined according to the blade outlet angle, the relative airflow velocity at the blade outlet, and the blade rotation speed. The absolute airflow velocity at the blade outlet can be calculated by the following formula for the absolute airflow velocity at the blade outlet:

[0147]

[0148] Where β2 is the blade outlet angle, w 22 is the relative airflow velocity at the moving blade outlet. μ3 is the blade rotation speed, and c2 is the absolute airflow velocity at the moving blade outlet.

[0149] S305, generating aerodynamic efficiency according to the stationary blade speed coefficient, the moving blade speed coefficient, the absolute airflow velocity at the stationary blade outlet, the stagnation isentropic enthalpy drop of the expansion stage, the relative airflow velocity at the moving blade outlet, and the absolute airflow velocity at the moving blade outlet.

[0150] In an embodiment of the present application, aerodynamic efficiency is generated based on the stationary blade speed coefficient, the moving blade speed coefficient, the absolute airflow velocity at the stationary blade outlet, the stagnation isentropic enthalpy drop of the expansion stage, the relative airflow velocity at the moving blade outlet and the absolute airflow velocity at the moving blade outlet.

[0151] How to generate aerodynamic efficiency based on the stationary blade speed coefficient, the moving blade speed coefficient, the absolute airflow velocity at the stationary blade outlet, the expansion stage stagnation isentropic enthalpy drop, the relative airflow velocity at the moving blade outlet and the absolute airflow velocity at the moving blade outlet can be specifically referred to as follows: Figure 4 As shown in the method. Figure 4 As shown, it is a schematic diagram of an implementation process of generating aerodynamic efficiency provided by an embodiment of the present application, which may specifically include the following steps:

[0152] S401, determining a moving blade loss according to an ideal relative airflow velocity at a moving blade outlet and an actual relative airflow velocity at a moving blade outlet.

[0153] In the embodiment of the present application, the moving blade loss can be calculated according to the following moving blade loss function formula:

[0154]

[0155] where w 23s is the ideal relative airflow velocity at the rotor blade outlet, w 23 is the actual relative airflow velocity at the rotor blade outlet, Δh 2ξ Loss of moving blades.

[0156] S402, determining a moving blade loss coefficient according to a moving blade loss function and an expansion stage stagnation isentropic enthalpy drop.

[0157] In the embodiment of the present application, the moving blade loss coefficient can be calculated according to the following moving blade loss coefficient formula:

[0158]

[0159] in, is the moving blade loss function, is the stagnation isentropic enthalpy drop of the expansion stage, and ζ2 is the moving blade loss coefficient.

[0160] S403, determining the residual speed loss according to the absolute airflow velocity at the rotor blade outlet.

[0161] In the embodiment of the present application, the residual speed loss can be calculated according to the following residual speed loss formula:

[0162]

[0163] Among them, c 21 is the absolute airflow velocity at the rotor blade outlet, Residual speed loss.

[0164] S404, determining a residual velocity loss coefficient according to the residual velocity loss and the isentropic enthalpy drop of the expansion stage stagnation.

[0165] In the embodiment of the present application, the residual speed loss coefficient can be calculated according to the following residual speed loss coefficient formula:

[0166]

[0167] Where Δh c21 is the residual speed loss, is the isentropic enthalpy drop of the expansion stage, ζ c2 is the residual speed loss coefficient.

[0168] S405, determining the ideal absolute airflow velocity at the stator blade outlet according to the expansion stage reaction degree and the expansion stage stagnation isentropic enthalpy drop.

[0169] In the embodiment of the present application, the ideal absolute airflow velocity at the stator blade outlet can be calculated by the following ideal absolute airflow velocity formula at the stator blade outlet:

[0170]

[0171] Among them, Ω5 is the expansion stage reaction degree, is the isentropic enthalpy drop of the expansion stage, c 1s It is the ideal absolute air flow velocity at the stator blade outlet.

[0172] S406, determining the stator blade loss according to the ideal absolute airflow velocity at the stator blade outlet and the absolute airflow velocity at the stator blade outlet.

[0173] In the embodiment of the present application, the stator blade loss can be calculated according to the following stator blade loss formula:

[0174]

[0175] Among them, c 19s is the ideal absolute airflow velocity at the stator blade outlet, c 19 is the absolute airflow velocity at the stator blade outlet, Δh 1ξ The loss of stationary blades.

[0176] S407, determining a stationary blade loss coefficient according to the stationary blade loss and the expansion stage stagnation isentropic enthalpy drop.

[0177] In the embodiment of the present application, the stationary blade loss coefficient can be calculated by the following stationary blade loss coefficient formula:

[0178]

[0179] Where Δh 11ξ is the stationary blade loss, is the stagnation isentropic enthalpy drop of the expansion stage, and ζ1 is the stationary blade loss coefficient.

[0180] S408, determining the aerodynamic efficiency according to the stationary blade loss coefficient, the moving blade loss coefficient, and the residual speed loss coefficient.

[0181] In the embodiment of the present application, the aerodynamic efficiency can be calculated according to the following aerodynamic efficiency formula:

[0182] η=1-ζ 10 -ζ 20 -ζ c20

[0183] Among them, 10 is the stationary blade loss coefficient, ζ20 is the moving blade loss coefficient, ζ c20 is the residual speed loss factor, η is the aerodynamic efficiency

[0184] S306, the second parameters include the velocity coefficient, the relative airflow velocity at the rotor blade outlet, the absolute airflow velocity at the rotor blade outlet, and the aerodynamic efficiency.

[0185] In the embodiment of the present application, the second parameter includes the velocity coefficient, the relative airflow velocity at the rotor blade outlet, the absolute airflow velocity at the rotor blade outlet and the aerodynamic efficiency.

[0186] S208, selecting aerodynamic parameters that meet a first preset condition from a plurality of aerodynamic parameters according to the aerodynamic efficiency.

[0187] In an embodiment of the present application, aerodynamic parameters that meet the first preset condition are screened from multiple aerodynamic parameters based on aerodynamic efficiency, wherein the first preset condition may be that the aerodynamic efficiency reaches a certain level or is higher than the average level. By screening the aerodynamic parameters based on aerodynamic efficiency, a design solution that can meet the requirements of high-efficiency conversion can be found from a large number of aerodynamic parameters, providing support for the subsequent optimization design of turbine blades. In the screening process, mathematical methods such as comparison and sorting can be used to ensure that the optimal or suboptimal aerodynamic parameter combination is finally selected, and this application example does not limit this.

[0188] For example, the first preset condition is that the aerodynamic efficiency is greater than 50%, and aerodynamic parameters with aerodynamic efficiency greater than 50% are screened from multiple aerodynamic parameters.

[0189] S209, establishing a coordinate system with the main flow axis of the working fluid as the x-axis and the normal direction of the x-axis as the y-axis.

[0190] In the embodiment of the present application, a coordinate system is established with the main flow axis of the working fluid as the x-axis and the normal direction of the x-axis as the y-axis, which provides a basic framework for the subsequent definition and design of the blade profile.

[0191] S210, defining the mid-arc equation and thickness equation of the turbine blade according to the coordinate system.

[0192] In the embodiment of the present application, the camber equation and thickness equation of the turbine blade are defined according to the coordinate system, wherein the camber equation describes the centerline shape of the blade profile, and the thickness equation defines the thickness of the blade at various positions.

[0193] S211, designing the turbine blade according to the mid-arc equation, the thickness equation, the first parameter and the second parameter.

[0194] In the embodiment of the present application, the turbine blade is designed based on the mid-arc equation, the thickness equation, the first parameter and the second parameter.

[0195] As for how to design the turbine blade according to the mid-arc equation, thickness equation, first parameter and second parameter, please refer to the following. Figure 5 As shown in the method. Figure 5 FIG. 1 is a schematic diagram of an implementation process of a turbine blade design provided in an embodiment of the present application, which may specifically include the following steps:

[0196] S501, determining the inclination angle equation corresponding to the inclination angle at each point of the blade in the coordinate system according to the mid-arc equation.

[0197] In the embodiment of the present application, the inclination angle equation corresponding to the inclination angle at each point of the blade in the coordinate system is determined according to the mid-arc equation. The inclination angle at each point on the mid-arc of the blade can be determined according to the inclination angle equation, and the mid-arc equation and the inclination angle equation satisfy the corresponding relationship between the integral and the derivative, that is, when the mid-arc equation is y1=f1(x), the inclination angle equation corresponding to each point on the arc is y2=f2(x), and the mid-arc equation and the inclination angle equation satisfy the relationship y2=atan(f1(x)).

[0198] S502, inputting the x value corresponding to each point of the blade into the thickness equation to determine the blade thickness corresponding to each point of the blade and the maximum thickness of the blade.

[0199] In the embodiment of the present application, the x value corresponding to each point of the blade is input into the thickness equation to determine the blade thickness corresponding to each point of the blade and the maximum thickness of the blade.

[0200] S503, designing the turbine blade according to the mid-arc equation, the inclination angle equation, the blade thickness corresponding to each point of the blade, the maximum thickness of the blade, the first parameter and the second parameter.

[0201] In an embodiment of the present application, the turbine blade is designed based on the mid-arc line equation, the inclination angle equation, the blade thickness corresponding to each point on the blade, the maximum thickness of the blade, the first parameter and the second parameter.

[0202] The turbine blade is designed according to the mid-arc equation, the inclination equation, the blade thickness corresponding to each point of the blade, the maximum thickness of the blade, the first parameter and the second parameter. For details, please refer to the following Figure 6 As shown in the method. Figure 6 FIG. 1 is a schematic diagram of an implementation process of another turbine blade design provided in an embodiment of the present application, which may specifically include the following steps:

[0203] S601, determining the axial length and angle parameters of the blade according to the first parameter and the second parameter.

[0204] In the embodiment of the present application, the axial length and angle parameters of the blade are determined according to the first parameter and the second parameter. Figure 7 As shown in the figure, B is the axial length of the blade, and the inlet angle β1 and the outlet angle β2 are angle parameters, which are generally matched with the airflow angle to ensure that the airflow can pass through the blade smoothly.

[0205] S602, input the first parameter, the blade thickness corresponding to each point of the blade, the second parameter, the axial length of the blade and the angle parameter into the inclination angle equation and the thickness equation to calculate the throat area of ​​the blade to obtain the first blade throat area.

[0206] In the embodiment of the present application, the first parameter, the blade thickness corresponding to each point of the blade, the second parameter, the blade axial length and the angle parameter are input into the inclination equation and the thickness equation to calculate the throat area of ​​the blade to obtain the first blade throat area. Among them, the inclination equation describes the shape of the blade center arc line (i.e., the center line of the blade profile line),

[0207] S603, when the throat area of ​​the first blade meets the second preset condition, the turbine blade profile is drawn in the coordinate system according to the blade thickness corresponding to each point of the blade, the maximum thickness of the blade, the mid-arc line equation, the throat area of ​​the first blade, the axial length of the blade and the angle parameters, to complete the turbine blade design.

[0208] In the embodiment of the present application, when the throat area of ​​the first blade satisfies the second preset condition, the turbine blade profile is drawn in the coordinate system according to the blade thickness corresponding to each point of the blade, the maximum thickness of the blade, the mid-camber equation, the throat area of ​​the first blade, the axial length of the blade and the angle parameter, and the turbine blade design is completed. The shape and thickness of the blade profile are determined by the mid-camber equation and the thickness equation.

[0209] The second preset condition may be whether the flow area and the blade throat area meet a certain error (e.g., the error is within 10 mm). 2 , 15mm 2 , 20mm 2 The flow area is calculated by the blade outlet velocity and the required flow rate obtained by aerodynamic calculation, and the blade throat area is the blade throat area obtained by iteration.

[0210] like Figure 7 As shown, tmax is the maximum thickness of the blade, the dotted line in the figure is the curve corresponding to the mid-arc equation, and B is the axial length of the blade.

[0211] In addition, after drawing the blade profile, the blade needs to be further optimized and verified to ensure that it meets the performance and manufacturing requirements, including adjusting the axial length, leading and trailing edge thickness, maximum thickness, number of blades and other parameters of the blade, as well as using a suitable pressure loss model to calculate and verify the total pressure loss coefficient of the blade.

[0212] For example, the total pressure loss coefficient (y1) can be obtained by aerodynamic calculation, and compared with the total pressure loss coefficient (y2) obtained by using a suitable pressure loss model (such as KO model, AG model, etc.) to remove the leakage loss. If the error between the two is within an acceptable range, it can be considered that the blade design meets the aerodynamic calculation results. Otherwise, it is necessary to adjust the parameters such as the blade axial length, the leading and trailing edge thickness, the maximum blade thickness, the number of blades, etc. to redesign the blade. If it is still impossible to design a blade that meets the error requirements, it is necessary to further adjust the static blade speed coefficient and the moving blade speed coefficient to re-perform the above calculation process.

[0213] In addition, the performance of turbine blades can also be predicted. Specifically, the performance of turbine blades can be predicted through the following steps:

[0214] Step 1: Obtain changing operating conditions.

[0215] In the embodiment of the present application, the changed operating condition is obtained. The changed operating condition may be the inlet temperature, inlet pressure, inlet speed, outlet pressure, etc. corresponding to the new scene when the designed turbine blade is applied to the new scene.

[0216] Step 2: Calculate based on the changed operating conditions and the design operating conditions to generate the changed operating efficiency.

[0217] In the embodiment of the present application, the static blade speed coefficient corresponding to the variable working condition and the design working condition is consistent with the static blade speed coefficient. The reaction degree and the corresponding flow rate are obtained under the variable working condition, and then the blade performance is calculated with reference to the above-mentioned aerodynamic calculation process to obtain the efficiency under the variable working condition (variable working condition efficiency).

[0218] The reaction degree under variable operating conditions can be calculated using the formula for the speed ratio under variable operating conditions (Xa) and the speed ratio under design operating conditions (Xad), where Xa and Xad represent the ratio of the blade rotation speed to the ideal expansion speed under the respective operating conditions;

[0219] The reaction degree under variable working conditions can be calculated according to the following variable working condition reaction degree formula:

[0220] Ω1′=f(Xa,Ω1)

[0221] Among them, Ω1' is the reaction degree under variable working conditions, Ω1 is the reaction degree under design working conditions, and Xa is the speed ratio under variable working conditions.

[0222] Step 3: Complete the performance prediction of turbine blades based on the efficiency under variable operating conditions.

[0223] In the embodiment of the present application, the performance change of the turbine blade under the variable operating condition is analyzed by comparing the efficiency under the variable operating condition with the efficiency under the design operating condition, and the performance prediction of the turbine blade is completed, wherein a turbine blade performance prediction report can be written based on the calculation results. The report may include key parameters, calculation results, performance evaluation and improvement suggestions under the variable operating condition. The report may also include charts and curves to intuitively show the performance change trend of the turbine blade under the variable operating condition, which is not limited in the example of the present application.

[0224] In order to facilitate understanding of the design method of turbine blades provided in the embodiment of the present application, Figure 8 As shown, it is a structural schematic diagram of an axial flow turbine expansion stage provided in an embodiment of the present application.

[0225] Figure 8 As shown in the figure: 0 is the stationary blade inlet, which is the first stop for gas to enter the turbine expansion stage. This design is directly related to whether the gas can smoothly enter the next stage of flow

[0226] 1 is the stationary blade outlet / moving blade inlet, where the gas completes the initial acceleration and direction adjustment in the stationary blade and is ready to enter the moving blade for further energy conversion.

[0227] 2 is the moving blade outlet, where the gas completes the expansion process in the moving blade, and its speed and direction change significantly, and finally flows out of the current turbine expansion stage to complete energy release (or enters the next turbine expansion stage to expand and do work again).

[0228] a1 or a2 is the absolute airflow angle, which is used to describe the absolute movement direction of the gas in the turbine blades (moving blades or stationary blades) and is one of the important indicators for evaluating the gas flow state and turbine performance.

[0229] β1 or β2 is the relative airflow angle, which is used to describe the direction of gas movement relative to the turbine blades (moving blades or stationary blades). It is crucial for optimizing blade design and improving turbine efficiency.

[0230] c1 or c2 is the absolute speed, which is used to describe the actual movement speed of the gas in the turbine blades (moving blades or stationary blades). Its size and direction directly affect the work capacity and efficiency of the turbine blades.

[0231] w1 or w2 is the relative speed, which is used to describe the speed of gas relative to the turbine blades (moving blades or stationary blades).

[0232] u is the blade rotation speed, that is, the linear speed or angular speed of the turbine blade during rotation. The blade rotation speed directly affects the dynamic pressure drop on the blade, the flow state of the airflow, and the stress distribution of the blade.

[0233] Corresponding to the above method embodiment, the present application embodiment also provides a design device for turbine blades, such as Fig. 9 As shown, the device may include an acquisition module 901, an analysis module 902, a processing module 903, a screening module 904, and a design module 805.

[0234] Acquisition module 901, acquiring design working conditions;

[0235] An analysis module 902 determines at least one expansion stage according to design operating conditions;

[0236] A processing module 903 performs aerodynamic calculation based on the expansion stage for any expansion stage to generate aerodynamic parameters, wherein the aerodynamic parameters include aerodynamic efficiency;

[0237] A screening module 904, screening aerodynamic parameters satisfying a first preset condition from a plurality of aerodynamic parameters according to the aerodynamic efficiency;

[0238] The design module 905 designs the turbine blades according to the aerodynamic parameters that meet the first preset condition.

[0239] The present application also provides an electronic device, such as Fig.10 As shown, it includes a processor 1001, a communication interface 1002, a memory 1003 and a communication bus 1004, wherein the processor 1001, the communication interface 1002, and the memory 1003 communicate with each other through the communication bus 1004, and the memory 1003 is used to store computer programs;

[0240] In one embodiment of the present application, the processor 1001, when used to execute the program stored in the memory 1003, implements the following steps:

[0241] The design operating conditions are obtained, and at least one expansion stage is determined according to the design operating conditions. For any expansion stage, aerodynamic calculations are performed based on the expansion stage to generate aerodynamic parameters, wherein the aerodynamic parameters include aerodynamic efficiency. According to the aerodynamic efficiency, aerodynamic parameters that meet a first preset condition are screened from multiple aerodynamic parameters, and turbine blades are designed according to the aerodynamic parameters that meet the first preset condition.

[0242] The communication bus mentioned in the above electronic device can be a Peripheral Component Interconnect (PCI) bus or an Extended Industry Standard Architecture (EISA) bus, etc. The communication bus can be divided into an address bus, a data bus, a control bus, etc. For ease of representation, only one thick line is used in the figure, but it does not mean that there is only one bus or one type of bus.

[0243] The communication interface is used for communication between the above electronic device and other devices.

[0244] The memory may include a random access memory (RAM) or a non-volatile memory, such as at least one disk memory. Optionally, the memory may also be at least one storage device located away from the aforementioned processor.

[0245] The above-mentioned processor can be a general-purpose processor, including a central processing unit (CPU), a network processor (NP), etc.; it can also be a digital signal processor (DSP), an application specific integrated circuit (ASIC), a field programmable gate array (FPGA) or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components.

[0246] In another embodiment provided in the present application, a storage medium is also provided, in which instructions are stored. When the storage medium is run on a computer, the computer executes the turbine blade design method described in any of the above embodiments.

[0247] In another embodiment provided in the present application, a computer program product including instructions is also provided, which, when executed on a computer, enables the computer to execute the turbine blade design method described in any one of the above embodiments.

[0248] In the above embodiments, it can be implemented in whole or in part by software, hardware, firmware or any combination thereof. When implemented using software, it can be implemented in whole or in part in the form of a computer program product. The computer program product includes one or more computer instructions. When the computer program instructions are loaded and executed on a computer, the process or function described in the embodiment of the present application is generated in whole or in part. The computer may be a general-purpose computer, a special-purpose computer, a computer network, or other programmable device. The computer instructions may be stored in a storage medium, or transmitted from one storage medium to another storage medium, for example, the computer instructions may be transmitted from a website site, a computer, a server or a data center by wired (e.g., coaxial cable, optical fiber, digital subscriber line (DSL)) or wireless (e.g., infrared, wireless, microwave, etc.) mode to another website site, computer, server or data center. The storage medium may be any available medium that a computer can access or a data storage device such as a server or a data center that includes one or more available media integrations. The available medium may be a magnetic medium, (e.g., a floppy disk, a hard disk, a tape), an optical medium (e.g., a DVD), or a semiconductor medium (e.g., a solid-state drive Solid State Disk (SSD)), etc.

[0249] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "comprise a ..." do not exclude the existence of other identical elements in the process, method, article or device including the elements.

[0250] Each embodiment in this specification is described in a related manner, and the same or similar parts between the embodiments can be referred to each other, and each embodiment focuses on the differences from other embodiments. In particular, for the system embodiment, since it is basically similar to the method embodiment, the description is relatively simple, and the relevant parts can be referred to the partial description of the method embodiment.

[0251] The above description is only a preferred embodiment of the present application and is not intended to limit the protection scope of the present application. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application are included in the protection scope of the present application.

Claims

1. A method for designing a turbine blade, characterized in that: The method comprises: Obtain design operating conditions; Determining at least one expansion stage according to the design operating conditions; For any expansion stage, performing aerodynamic calculation based on the expansion stage to generate aerodynamic parameters, wherein the aerodynamic parameters include aerodynamic efficiency; According to the aerodynamic efficiency, aerodynamic parameters satisfying a first preset condition are selected from the plurality of aerodynamic parameters; The turbine blades are designed according to the aerodynamic parameters that meet the first preset condition.

2. The method according to claim 1, characterized in that The aerodynamic parameters include a first parameter and a second parameter. The aerodynamic calculation is performed based on the expansion stage to generate the aerodynamic parameters. The aerodynamic parameters include aerodynamic efficiency, including: According to the design operating conditions, at least one expansion stage reaction degree is set, and the expansion stage stagnation isentropic enthalpy drop, blade rotation speed and stationary blade speed coefficient are determined; For any of the expansion stage reaction degrees, determining the stator blade outlet absolute airflow velocity based on the expansion stage reaction degree, the expansion stage stagnation isentropic enthalpy drop and the stator blade velocity coefficient; Determining the relative airflow velocity at the stator blade outlet according to the absolute airflow velocity at the stator blade outlet and the blade rotation speed; The first parameter includes the reaction degree of the expansion stage, the stagnation isentropic enthalpy drop of the expansion stage, the blade rotation speed, the absolute airflow speed at the stator blade outlet, and the relative airflow speed at the stator blade outlet; Perform aerodynamic calculation according to the first parameter and the design operating condition to generate second parameters, where the second parameters include the aerodynamic efficiency.

3. The method according to claim 2, characterized in that The performing of aerodynamic calculation according to the first parameter and the design operating condition to generate a second parameter, wherein the second parameter includes the aerodynamic efficiency, comprises: Obtaining the expansion stage reaction degree, the expansion stage stagnation isentropic enthalpy drop, the blade rotation speed, the stator blade outlet absolute airflow speed and the stator blade outlet relative airflow speed from the first parameter; Determining a speed coefficient from the design operating conditions, wherein the speed coefficient includes a moving blade speed coefficient and a stationary blade speed coefficient; Determine the relative airflow velocity at the moving blade outlet according to the relative airflow velocity at the stationary blade outlet, the reaction degree of the expansion stage, the moving blade velocity coefficient, and the stagnation isentropic enthalpy drop of the expansion stage; Determine the absolute airflow velocity at the rotor blade outlet according to the relative airflow velocity at the rotor blade outlet and the blade rotation speed; The aerodynamic efficiency is generated according to the stationary blade speed coefficient, the moving blade speed coefficient, the absolute airflow velocity at the stationary blade outlet, the stagnation isentropic enthalpy drop of the expansion stage, the relative airflow velocity at the moving blade outlet, and the absolute airflow velocity at the moving blade outlet; The second parameters include the speed coefficient, the relative airflow speed at the rotor blade outlet, the absolute airflow speed at the rotor blade outlet, and the aerodynamic efficiency.

4. The method according to claim 3, characterized in that The step of designing the turbine blades according to the aerodynamic parameters satisfying the first preset condition comprises: A coordinate system is established with the main flow axis of the working fluid as the x-axis and the normal direction of the x-axis as the y-axis; Defining the mid-camber equation and thickness equation of the turbine blade according to the coordinate system; The turbine blade is designed according to the median arc equation, the thickness equation, the first parameter and the second parameter.

5. The method according to claim 4, characterized in that The step of designing a turbine blade according to the mid-camber equation, the thickness equation, the first parameter and the second parameter comprises: According to the mid-arc equation, determining the inclination angle equation corresponding to the inclination angle at each point of the blade in the coordinate system; Inputting the x value corresponding to each point of the blade into the thickness equation to determine the blade thickness corresponding to each point of the blade and the maximum thickness of the blade; The turbine blade is designed according to the mid-arc line equation, the inclination angle equation, the blade thickness corresponding to each point on the blade, the maximum blade thickness, the first parameter and the second parameter.

6. The method according to claim 5, characterized in that The step of designing a turbine blade according to the mid-camber equation, the inclination angle equation, the blade thickness corresponding to each point of the blade, the maximum blade thickness, the first parameter and the second parameter comprises: Determine the axial length and angle parameters of the blade according to the first parameter and the second parameter; Inputting the first parameter, the blade thickness corresponding to each point of the blade, the second parameter, the blade axial length and the angle parameter into the inclination angle equation and the thickness equation to calculate the throat area of ​​the blade, thereby obtaining a first blade throat area; When the throat area of ​​the first blade satisfies the second preset condition, the turbine blade profile is drawn in the coordinate system according to the blade thickness corresponding to each point of the blade, the maximum thickness of the blade, the mid-arc line equation, the first blade throat area, the blade axial length and the angle parameter to complete the turbine blade design.

7. The method according to claim 1, characterized in that The method further comprises: Obtain changing operating conditions; Calculating according to the changed operating condition and the designed operating condition to generate a changed operating condition efficiency; Based on the variable operating efficiency, the performance prediction of the turbine blades is completed.

8. A design device for turbine blades, characterized in that: The device comprises: Acquisition module, to obtain design working conditions; An analysis module, determining at least one expansion stage according to the design operating conditions; A processing module, for any expansion stage, performs aerodynamic calculation based on the expansion stage to generate aerodynamic parameters, wherein the aerodynamic parameters include aerodynamic efficiency; A screening module, screening the aerodynamic parameters satisfying a first preset condition from the plurality of aerodynamic parameters according to the aerodynamic efficiency; The design module designs the turbine blades according to the aerodynamic parameters that meet the first preset condition.

9. An electronic device, characterized in that: It includes a processor, a communication interface, a memory and a communication bus, wherein the processor, the communication interface and the memory communicate with each other through the communication bus; Memory, used to store computer programs; A processor, for implementing any of the methods described in claims 1-7 when executing a program stored in a memory.

10. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores a computer program, and when the computer program is executed by a processor, the method according to any one of claims 1 to 7 is implemented.

Images