CN114330063A - Blade tip deflection calculation method and device of blade, electronic equipment and storage medium - Google Patents
Blade tip deflection calculation method and device of blade, electronic equipment and storage medium Download PDFInfo
- Publication number
- CN114330063A CN114330063A CN202111649432.1A CN202111649432A CN114330063A CN 114330063 A CN114330063 A CN 114330063A CN 202111649432 A CN202111649432 A CN 202111649432A CN 114330063 A CN114330063 A CN 114330063A
- Authority
- CN
- China
- Prior art keywords
- blade
- tip deflection
- deflection
- tip
- determining
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Landscapes
- Wind Motors (AREA)
Abstract
The embodiment of the disclosure provides a method and a device for calculating blade tip deflection of a blade, electronic equipment and a storage medium, wherein the method comprises the following steps: determining a first tip deflection of the blade based on a first set of deflections for different sections of the blade; determining a second tip deflection of the blade based on a second set of deformations of different cross sections of the blade, the second set of deformations determined based on the first set of deformations; determining a target tip deflection based on a difference between the first tip deflection and the second tip deflection. By the method for calculating the deflection of the blade tip of the blade, the efficiency and the precision of calculating the stress and deformation conditions of the wind turbine blade in the operation process can be effectively improved, so that the blade is more reasonable in design, and the working efficiency is obviously improved.
Description
Technical Field
The embodiment of the disclosure relates to the technical field of data calculation, in particular to a method and a device for calculating blade tip deflection of a blade, electronic equipment and a storage medium.
Background
With the development of wind power technology, the diameter of a wind wheel is larger and larger, the traditional experience method is no longer suitable for mechanical analysis of the blades of a large-scale wind driven generator, and the accurate calculation of the aerodynamic performance and the stress state of the blades in a real working state is more and more important.
The conventional wind power blade has a large wind wheel diameter, and the sizes of the blade tip and the rear edge of the blade are very small, so that the grid quantity of flow field division is very large, the requirement on computer equipment is high during flow field analysis, and the calculation time is long; the structural layering and the load of the blade are complex, and the grid division is difficult; the transmission quantity of load data between the flow field and the structure is large; the deformation of the blade is large, so that the flow field grid is difficult to reconstruct; due to the difference of grid division, the blade boundary in the flow field grid and the blade in the structural grid cannot be completely consistent, and the load and deformation interpolation are difficult. Therefore, the traditional fluid-solid coupling analysis method is not suitable for rapid design and iteration of large-size wind generating sets.
Disclosure of Invention
In view of the above problems in the prior art, the embodiments of the present disclosure provide a method and an apparatus for calculating blade tip deflection of a blade, an electronic device, and a storage medium, so as to solve the problem of low efficiency in calculating the stress and deformation of a wind turbine blade during operation due to an over-large fan.
In order to solve the above problems, the technical solution provided by the embodiments of the present disclosure is: a method of calculating tip deflection of a blade, the method comprising:
determining a first tip deflection of the blade based on a first set of deflections for different sections of the blade;
determining a second tip deflection of the blade based on a second set of deformations of different cross sections of the blade, the second set of deformations determined based on the first set of deformations;
determining a target tip deflection based on a difference between the first tip deflection and the second tip deflection.
Further, the first set of deformation amounts is obtained by:
determining a first aerodynamic load of the blade based on the first three-dimensional model of the blade and the characteristic parameters of the fan;
obtaining the first set of deformation quantities based on the first finite element model of the blade and the first aerodynamic load data.
Further, the determining a first aerodynamic load of the blade based on the first three-dimensional model of the blade, the characteristic parameters of the wind turbine, comprises:
establishing a first three-dimensional model based on a first profile parameter of the blade in a predetermined coordinate system;
establishing a first simulation model of the blade based on the first three-dimensional model and the characteristic parameters of the wind turbine,
setting boundary conditions of the blade, mapping the boundary conditions into the first simulation model, and determining the first aerodynamic load data.
Further, the first finite element model is established by:
and establishing the first finite element model based on the first three-dimensional model and the structural layering information of the blade.
Further, the second set of deformations is determined by:
obtaining a second three-dimensional model of the blade based on the first set of deformations;
determining a second aerodynamic load of the blade based on the second three-dimensional model and the characteristic parameters of the fan;
determining the second set of deformation amounts based on a second finite element model of the blade and the second aerodynamic load data.
Further, the second finite element model is established by:
and establishing the second finite element model based on the second three-dimensional model and the structural layering information of the blade.
Further, said determining a tip target deflection based on a difference between said first tip deflection and said second tip deflection comprises:
if the difference value is smaller than a preset threshold value, determining that the first blade tip deflection is the target blade tip deflection;
if the difference is greater than a preset threshold, reconstructing the first three-dimensional model of the blade until the difference is less than the preset threshold.
Embodiments of the present disclosure also provide an apparatus for calculating a tip deflection of a blade, the apparatus including:
a first determination module for determining a first tip deflection of the blade based on a first set of deformations of different sections of the blade;
a second determination module for determining a second tip deflection of the blade based on a second set of deformations of different cross sections of the blade, the second set of deformations being determined based on the first set of deformations;
and the difference value module is used for determining the target deflection of the blade tip based on the difference value between the first deflection of the blade tip and the second deflection of the blade tip.
Embodiments of the present disclosure also provide an electronic device, at least including a memory and a processor, where the memory stores a computer program thereon, and the processor implements the steps of the method for calculating blade tip deflection of a blade according to the embodiments of the present disclosure when executing the computer program on the memory.
Embodiments of the present disclosure also provide a storage medium having a computer program stored thereon, where the computer program is executed by a processor to implement the steps of the method for calculating blade tip deflection of a blade according to the embodiments of the present disclosure.
The beneficial effects of this disclosed embodiment lie in: the method for calculating the blade tip deflection of the blade can effectively improve the efficiency and the precision of calculating the stress and deformation conditions of the wind turbine blade in the operation process, so that the blade design is more efficient and accurate.
Drawings
Fig. 1 is a schematic flow chart of a method for calculating a blade tip deflection of a blade according to an embodiment of the present disclosure;
FIG. 2 is a schematic view of a blade airfoil assembly provided in accordance with an embodiment of the present disclosure;
FIG. 3 is a schematic view of a pre-curved, chord length of a blade according to an embodiment of the present disclosure;
FIG. 4 is a schematic view of a blade layer structure provided by an embodiment of the present disclosure
FIG. 5 is a schematic cross-sectional view of a blade according to an embodiment of the present disclosure;
fig. 6 is a schematic diagram of a hardware structure of an electronic device according to an embodiment of the present disclosure;
fig. 7 is a schematic view of a device for calculating blade tip deflection of a blade according to an embodiment of the present disclosure.
Detailed Description
Various aspects and features of the present application are described herein with reference to the drawings.
It will be understood that various modifications may be made to the embodiments of the present application. Accordingly, the foregoing description should not be construed as limiting, but merely as exemplifications of embodiments. Those skilled in the art will envision other modifications within the scope and spirit of the application.
The accompanying drawings, which are incorporated in and constitute a part of the specification, illustrate embodiments of the application and, together with a general description of the application given above and the detailed description of the embodiments given below, serve to explain the principles of the application.
These and other characteristics of the present application will become apparent from the following description of preferred forms of embodiment, given as non-limiting examples, with reference to the attached drawings.
It is also to be understood that although the present application has been described with reference to some specific examples, those skilled in the art are able to ascertain many other equivalents to the practice of the present application.
The above and other aspects, features and advantages of the present application will become more apparent in view of the following detailed description when taken in conjunction with the accompanying drawings.
Specific embodiments of the present application are described hereinafter with reference to the accompanying drawings; however, it is to be understood that the disclosed embodiments are merely exemplary of the application, which can be embodied in various forms. Well-known and/or repeated functions and constructions are not described in detail to avoid obscuring the application of unnecessary or unnecessary detail. Therefore, specific structural and functional details disclosed herein are not to be interpreted as limiting, but merely as a basis for the claims and as a representative basis for teaching one skilled in the art to variously employ the present application in virtually any appropriately detailed structure.
The specification may use the phrases "in one embodiment," "in another embodiment," "in yet another embodiment," or "in other embodiments," which may each refer to one or more of the same or different embodiments in accordance with the application.
With the development of wind power technology, when a wind power blade works, mutual coupling action between fluid and solid exists, and in order to calculate the stress state and deformation condition of the designed wind power blade more accurately, fluid-solid coupling analysis of the blade is required. At present, the fluid-solid coupling research on the blades in China is relatively weak, and the comprehensive research on the system is not developed, so that the main reason is that the traditional fluid-solid coupling analysis method is not suitable for large-size wind generating sets and mainly shows the following aspects: the diameter of a wind wheel is large, the sizes of the blade tip and the rear edge of a blade are small, so that the grid quantity of flow field division is large, the requirement on computer equipment is high during flow field analysis, and the calculation time is long; secondly, structural layering and loads of the blades are complex, and grid division is difficult; thirdly, the transmission quantity of load data between the flow field and the structure is large; fourthly, the deformation of the blades is large, so that the flow field grid is difficult to reconstruct; and fifthly, due to the difference of grid division, the blade boundary in the flow field grid and the blade in the structural grid cannot be completely consistent, so that the load and deformation interpolation are difficult. Therefore, the stress and deformation conditions of the wind turbine blade in the operation process are difficult to calculate, and the blade design is more difficult.
In order to solve the technical problem, the embodiment of the disclosure provides a method for calculating blade tip deflection of a blade, which can solve the problem that the stress and deformation of a wind turbine blade in the operation process cannot be calculated due to an overlarge existing fan.
The embodiment of the first aspect of the disclosure provides a method for calculating blade tip deflection of a blade, which can be applied to equipment such as an intelligent terminal, and the method can improve the precision of calculating the stress and deformation conditions of the wind turbine blade in the operation process, so that the blade design is more reasonable, and the working efficiency is obviously improved. Fig. 1 shows a schematic flow chart of a method for calculating blade tip deflection of a blade according to an embodiment of the present disclosure, which mainly includes steps S101 to S103:
s101, determining first blade tip deflection of the blade based on the first deformation set of different sections of the blade.
The first set of deformation amounts may include flap deformation amounts, lag deformation amounts, torsional deformation amounts, and the like of different cross sections of the entire blade. The specific setting can be carried out according to the actual situation.
In some embodiments, the first set of deformations is obtained by:
and S11, determining the first aerodynamic load of the blade based on the first three-dimensional model of the blade and the characteristic parameters of the fan.
In some embodiments, the first three-dimensional model mainly refers to a three-dimensional model created by using current three-dimensional coordinate points of the fan blade, and may also be an original three-dimensional model of the fan blade. The setting can be carried out according to the actual situation.
In some embodiments, determining the first aerodynamic load comprises the steps of:
step 1: a first three-dimensional model is created in a predetermined coordinate system (the current three-dimensional coordinate system of the fan blade) based on first profile parameters of the blade.
The first shape parameter of the blade may be an original shape parameter of the blade, and may include one or more of chord length, twist angle, pre-bending, thickness, and pitch axis position information of the blade. The specific parameters of the blade can be set according to actual conditions, and the parameters are only used for reference.
In some embodiments, the blade chord length refers primarily to the linear distance between the tip and tail ends of the airfoil of the fan blade, as shown in FIG. 2 at A1.
In some embodiments, the blade twist angle mainly refers to a twist angle of a chord length coordinate system of the airfoil at different section positions of the fan blade relative to a blade root coordinate system.
In some embodiments, blade pre-bending refers primarily to the distance that the tip of the fan blade is offset from the pitch axis when the blade is unloaded. As shown at B2 in fig. 3.
In some embodiments, the thickness of the blade refers primarily to the maximum thickness of the windward and leeward sides of the blade airfoil. As shown at a2 in fig. 2.
In some embodiments, the pitch axis position line information mainly refers to a rotation axis when the blade pitches, and is a straight line. As shown by line B1 in fig. 3.
In some embodiments, the characteristic parameters of the wind turbine may include a pitch angle, an attack angle, and the like of the blade, and may be set according to actual conditions.
In some embodiments, the Pitch Angle (Pitch Angle) of a wind turbine blade, also referred to as the Pitch Angle, refers primarily to the Angle of the blade tip airfoil chord line from the plane of rotation.
In some embodiments, the Angle of attack (Angle of attack) of a wind turbine blade refers primarily to the Angle of the chord of the airfoil (i.e., the cross-section of the blade) of the blade from the relative wind.
Step 2: and establishing a first simulation model of the blade based on the first three-dimensional model and the characteristic parameters of the fan.
And the first simulation model preferably adopts a flow field simulation analysis model. The specific simulation model can be set according to actual conditions.
And step 3: setting boundary conditions of the blade, mapping the boundary conditions into the first simulation model, and determining first aerodynamic load data.
In some embodiments, the boundary condition includes at least one of: the symmetric boundaries, periodic boundaries, velocity inlet information, pressure outlet information, and fixed wall position information of the blade. In actual operation, the data included in the boundary condition may be set according to actual conditions, which is not discussed herein.
In some embodiments, the symmetric boundaries of the blade refer primarily to the constraint mirror distribution of the blade model.
In some embodiments, the periodic boundaries of the blade mainly refer to the periodic symmetric distribution of the constraints of the blade model.
In some embodiments, velocity entry refers primarily to the most common entry boundary in flow field simulations when calculating incompressible flows, defining flow velocity and associated scalar properties at the entry boundary. With such boundary conditions, the inlet total pressure needs to be determined by calculation (by adjusting the inlet total pressure so that the inlet velocity meets the input value). Velocity inlet boundary conditions may be used for both incompressible flow and compressible flow.
In some implementations, the pressure inlet is used primarily to define the fluid pressure of the fluid domain inlet, as well as other flow-related scalar data (e.g., temperature, radiation, composition, etc.).
In some implementations, the solid-wall surface mainly refers to a solid boundary of the flow field simulation analysis model.
In some embodiments, taking the flow field simulation analysis model as an example of the first simulation model, the set blade boundary conditions are mapped into the flow field simulation analysis model, and the first aerodynamic load data of the blade is output through simulation calculation of the flow field simulation analysis model. The flow field simulation analysis model can be used for independently calculating the flow field of the fan and ensuring the accuracy of calculating the blade deformation set.
In some embodiments, the pneumatic load data is in the form of spanwise segmented loads, i.e. the first simulation model outputs the pneumatic load data in the form of spanwise segmented loads.
S12, a first set of deformation values is obtained based on the first finite element model of the blade and the first aerodynamic load data.
Wherein the first finite element model is established by: and establishing a first finite element model based on the first three-dimensional model and the structural layering information of the blade.
In some embodiments, the common blade is made of composite materials, so the structural ply information of the blade mainly refers to information such as the direction and thickness of the fiber cloth ply. As shown in FIG. 4, the blade has a number of plies.
In the embodiment, the first aerodynamic load data output by the first simulation module is mapped into the first finite element model, and the first set of deformation is obtained through calculation of the first finite element model.
The pneumatic load data are mapped to the simplified finite element model in the spanwise segmented load mode, so that the operation is simple and the loading is convenient.
In some embodiments, during a specific operation process, the first finite element model of the blade may be simplified into a beam unit structure with a pre-bending function, and the aerodynamic load data calculated by the loading flow field simulation analysis model may quickly and accurately calculate the deformation of the blade, including the deflection of the blade in the flapwise and flap directions and the torsional deformation of the blade (i.e. the flap deformation, the flapwise deformation and the torsional deformation of the entire blade).
Specifically, the set of deformation amounts output by the first finite element module is a set of deformation amounts of the whole blade, that is, deformation amounts of different sections of the blade. As shown in fig. 5, a blade may be divided into several sections, and the deformation amount of the section of each section is different (such as section (1), section (2), etc.), and the deformation amount of the section of the tip portion of the blade is the first tip deflection.
And S102, determining second blade tip deflection of the blade based on the second deformation amount set of different sections of the blade.
In some embodiments, the second set of deformations is determined based on the first set of deformations.
The second set of deformation amounts may include a flap deformation amount, a lag deformation amount, a torsional deformation amount, and the like of the entire blade. Can be specifically set according to actual conditions
The second set of deformations is determined by:
s21, obtaining a second three-dimensional model of the blade based on the first set of deformation quantities.
In some embodiments, the first profile parameter of the blade is modified based on the first set of deformations of the blade to obtain a second profile parameter of the blade, and the three-dimensional model of the blade is reconstructed based on the second profile parameter of the blade to obtain a second three-dimensional model of the blade.
And correcting one or more parameters in profile parameter information such as chord length, torsion angle, pre-bending and thickness of the blade according to the first deformation set of the blade to obtain a new profile parameter of the blade, namely a second profile parameter of the blade.
In some embodiments, as the profile data of the blade is modified, the three-dimensional coordinate points of the blade may also change, as may the creation of the second three-dimensional model based on the modified profile parameters of the blade in the predetermined coordinate system (the current three-dimensional coordinate system of the wind turbine blade).
In fact, in the actual operation process, the shape parameters of the blade are corrected through the blade deformation set obtained through calculation of the first finite element model, the three-dimensional model of the blade can be quickly reconstructed, and the operation is simple.
And S22, determining a second aerodynamic load of the blade based on the second three-dimensional model and the characteristic parameters of the fan.
In some embodiments, determining the second aerodynamic load comprises the steps of:
step 1: and establishing a second simulation model of the blade based on the second three-dimensional model and the characteristic parameters of the fan.
And the second simulation model preferably adopts a flow field simulation analysis model. The specific simulation model can be set according to actual conditions.
Step 2: second aerodynamic load data is determined based on the boundary conditions of the blade and mapping the boundary conditions into a second simulation model. Wherein, the concrete steps can be according to the step process.
S23, a second set of deformation values is determined based on the second finite element model of the blade and the second aerodynamic load data.
Wherein the second finite element model is established by: and establishing a second finite element model based on the second three-dimensional model and the structural layering information of the blade.
In this embodiment, the second aerodynamic load data output by the second simulation module is mapped into the second finite element model, and the second set of deformation amounts is calculated by the second finite element model.
And S103, determining the target deflection of the blade tip based on the difference value between the first deflection of the blade tip and the second deflection of the blade tip.
In some implementations, if the difference is less than a preset threshold, the first tip deflection is determined to be the tip target deflection, and if the difference is greater than the preset threshold, the three-dimensional model of the blade is reconstructed until the difference is less than the preset threshold.
The preset threshold may also be in the form of a percentage, a constant, etc., such as 2%, 20%. The specific threshold form can be set according to actual conditions.
The preset threshold may also be in the form of a percentage, a constant, etc., such as 2%, 20%. The specific threshold form can be set according to actual conditions.
In some embodiments, taking the preset threshold value as 20 as an example, if the difference between the first tip deflection and the second tip deflection is less than 20, the first tip deflection is the target tip deflection, and if the difference is greater than or equal to 20, the first three-dimensional model of the blade is reconstructed until the difference between the first tip deflection and the second tip deflection is less than the preset threshold value.
In some embodiments, taking the preset threshold as 2% as an example, if the deviation between the first tip deflection and the second tip deflection is less than 2%, the first tip deflection is the target tip deflection, and if the deviation is greater than or equal to 2%, the first three-dimensional model of the blade is reconstructed until the deviation between the first tip deflection and the second tip deflection is less than 2%.
In one embodiment, during actual operation, the step of reconstructing the first three-dimensional model of the blade and deriving the tip deflection may start a loop iteration as follows (N ═ 0, 1, 2 …):
step (1), according to the deformation amount set D of the bladeNModifying the first profile parameter of the blade, reconstructing a first three-dimensional model C of the bladeN；
Step (2), according to the reconstructed three-dimensional blade model CNEstablishing a flow field simulation analysis model according to the characteristic parameters of the fan, setting the same boundary conditions as the above, obtaining blade aerodynamic load data through simulation calculation, and outputting L in the form of spanwise segmented loadsN；
Step (3), load data L of the segments are processedNLoading the obtained data on a finite element model F0, and calculating to obtain a deformation set (flap deformation, shimmy deformation and torsional deformation) D of each section of the bladeNDetermining the corrected blade tip deflection DTN；
Step (4), judging the corrected blade tip deflection DTNThe last calculated blade tip deflection DTN-1Comparing, calculating deviation, and judging whether the deviation is smaller than a preset threshold value;
and (5) outputting DT if the deviation is smaller than a preset threshold valueNAnd ending the cycle;
and (6) if the deviation is larger than the preset threshold, returning to the step (1) to reconstruct the three-dimensional model of the blade until the deviation requirement in the step (5) is met.
In the embodiment of the disclosure, the deflection of the blade tip is used as the basis for calculating convergence, so that the deformation condition of the blade can be accurately calculated, and the operation is simple and convenient.
Moreover, compared with the traditional fluid-solid coupling analysis method, the method for calculating the deflection of the blade tip of the blade has the advantages that the blade grids in the flow field simulation analysis model and the structural analysis model do not need to be aligned, the operation is simpler and faster, and the efficiency and the precision of calculating the stress and the deformation of the wind turbine blade in the operation process can be more effectively improved through the method for calculating the deflection of the blade tip of the blade, so that the blade is more reasonable in design, and the working efficiency is obviously improved.
Fig. 6 shows a schematic diagram of a device for calculating the tip deflection of a blade according to an embodiment of the disclosure.
As shown in fig. 6, the apparatus for calculating the tip deflection of the blade includes:
a first determining module 201, configured to determine a first tip deflection of the blade based on a first set of deformation amounts of different cross sections of the blade;
a second determination module 202 for determining a second tip deflection of the blade based on a second set of deformations of different cross sections of the blade, the second set of deformations being determined based on the first set of deformations;
a difference module 203 for determining a target tip deflection based on a difference between the first tip deflection and the second tip deflection
By the method for calculating the deflection of the blade tip of the blade, the precision of calculating the stress and deformation conditions of the wind turbine blade in the operation process can be effectively improved, so that the blade is more reasonable in design, and the working efficiency is obviously improved.
An electronic device is provided in an embodiment of the third aspect of the present disclosure, and a schematic structural diagram of the electronic device is shown in fig. 7, where the electronic device at least includes a memory 302 and a processor 301, the memory 302 stores a computer program, and the processor 301, when executing the computer program on the memory 302, implements the method provided in any embodiment of the present disclosure. Illustratively, the electronic device computer program steps are as follows S31-S33:
s31, determining a first tip deflection for the blade based on the first set of deflections for different sections of the blade;
s32, determining a second blade tip deflection of the blade based on a second deformation set of different sections of the blade, wherein the second deformation set is determined based on the first deformation set;
s33, determining the target deflection of the blade tip based on the difference value between the first deflection of the blade tip and the second deflection of the blade tip
The processor, when executing the determined first set of deformations stored on the memory, specifically executes the following computer program:
determining a first aerodynamic load of the blade based on the first three-dimensional model of the blade and the characteristic parameters of the fan;
a first set of deformation values is obtained based on the first finite element model of the blade and the first aerodynamic load data.
The processor, in executing the first three-dimensional model of the blade, the characteristic parameters of the wind turbine stored on the memory, and in determining the first aerodynamic load of the blade, further executes the following computer program:
establishing a first three-dimensional model based on a first profile parameter of the blade in a predetermined coordinate system;
establishing a first simulation model of the blade based on the first three-dimensional model and the characteristic parameters of the fan,
setting boundary conditions of the blade, mapping the boundary conditions into the first simulation model, and determining first aerodynamic load data.
In some embodiments, the electronic device further comprises: an input device 303 and an output device 304;
the processor 301, the memory 302, the input means 303 and the output means 304 in the electronic device may be connected by a bus or other means.
The memory 302 is a non-transitory computer-readable storage medium that can be used to store software programs, computer-executable programs. The processor 301 executes various functional applications of the server and data processing by running software programs and instructions stored in the memory 302, namely, the method for calculating the blade tip deflection of the blade according to the above method embodiment is realized.
The memory 302 may include high speed random access memory and may also include non-transitory memory, such as at least one magnetic disk storage device, flash memory device, or other non-transitory solid state storage device.
In some embodiments, memory 302 optionally includes memory located remotely from processor 301, which may be connected to a terminal device via a network. Examples of such networks include, but are not limited to, the internet, intranets, local area networks, mobile communication networks, and combinations thereof.
The input device 303 may include receiving input numeric or character information and generating key signal inputs related to user settings and function controls of the electronic device.
The output means 304 may comprise a display device such as a display screen.
An embodiment of the fourth aspect of the present disclosure provides a storage medium, which is specifically a computer-readable medium, storing a computer program, which when executed by a processor implements the method provided by any embodiment of the present disclosure, including the following steps S41 to S43:
s41, determining a first blade tip deflection of the blade based on the first deformation set of different sections of the blade;
s42, determining a second blade tip deflection of the blade based on a second deformation set of different sections of the blade, wherein the second deformation set is determined based on the first deformation set;
and S43, determining the target deflection of the blade tip based on the difference value between the first deflection of the blade tip and the second deflection of the blade tip.
When the computer program is executed by the processor to determine the first set of deformations, the processor specifically executes the following steps:
determining a first aerodynamic load of the blade based on the first three-dimensional model of the blade and the characteristic parameters of the fan;
a first set of deformation values is obtained based on the first finite element model of the blade and the first aerodynamic load data.
When the computer program is executed by the processor based on the first three-dimensional model of the blade and the characteristic parameters of the fan to determine the first aerodynamic load of the blade, the processor specifically executes the following steps:
establishing a first three-dimensional model based on a first profile parameter of the blade in a predetermined coordinate system;
establishing a first simulation model of the blade based on the first three-dimensional model and the characteristic parameters of the fan,
setting boundary conditions of the blade, mapping the boundary conditions into the first simulation model, and determining first aerodynamic load data.
Optionally, the computer executable instruction, when executed by the computer processor, may be further used to implement a technical solution of the method for calculating the blade tip deflection of the blade provided in any embodiment of the present disclosure.
By the method for calculating the deflection of the blade tip of the blade, the precision of calculating the stress and deformation conditions of the wind turbine blade in the operation process can be effectively improved, so that the blade is more reasonable in design, and the working efficiency is obviously improved.
The device provided by the embodiment of the present disclosure can execute the processes and steps of the above method embodiments, and further has a functional module corresponding to the above method embodiments, which can execute corresponding operations, and has corresponding technical effects, and in order to avoid repetition, details are not repeated here.
The above embodiments are merely exemplary embodiments of the present disclosure, which is not intended to limit the present disclosure, and the scope of the present disclosure is defined by the claims. Various modifications and equivalents of the disclosure may occur to those skilled in the art within the spirit and scope of the disclosure, and such modifications and equivalents are considered to be within the scope of the disclosure.
Claims (10)
1. A method for calculating blade tip deflection of a blade, the method comprising:
determining a first tip deflection of the blade based on a first set of deflections for different sections of the blade;
determining a second tip deflection of the blade based on a second set of deformations of different cross sections of the blade, the second set of deformations determined based on the first set of deformations;
determining a target tip deflection based on a difference between the first tip deflection and the second tip deflection.
2. The method of calculating the tip deflection of a blade according to claim 1, wherein the first set of deformations is obtained by:
determining a first aerodynamic load of the blade based on the first three-dimensional model of the blade and the characteristic parameters of the fan;
obtaining the first set of deformation quantities based on the first finite element model of the blade and the first aerodynamic load data.
3. The method of calculating blade tip deflection for a blade of claim 2, wherein said determining a first aerodynamic load for said blade based on a first three-dimensional model of said blade, a characteristic parameter of a wind turbine, comprises:
establishing a first three-dimensional model based on a first profile parameter of the blade in a predetermined coordinate system;
establishing a first simulation model of the blade based on the first three-dimensional model and the characteristic parameters of the wind turbine,
setting boundary conditions of the blade, mapping the boundary conditions into the first simulation model, and determining the first aerodynamic load data.
4. A method of calculating the tip deflection of a blade according to claim 3, wherein said first finite element model is created by:
and establishing the first finite element model based on the first three-dimensional model and the structural layering information of the blade.
5. The method of calculating the tip deflection of a blade according to claim 1, wherein said second set of deformations is determined by:
obtaining a second three-dimensional model of the blade based on the first set of deformations;
determining a second aerodynamic load of the blade based on the second three-dimensional model and the characteristic parameters of the fan;
determining the second set of deformation amounts based on a second finite element model of the blade and the second aerodynamic load data.
6. The method of calculating blade tip deflection for a blade according to claim 5, wherein said second finite element model is created by:
and establishing the second finite element model based on the second three-dimensional model and the structural layering information of the blade.
7. The method of calculating the tip deflection of a blade of claim 2, wherein said determining a tip target deflection based on the difference between said first tip deflection and said second tip deflection comprises:
if the difference value is smaller than a preset threshold value, determining that the first blade tip deflection is the target blade tip deflection;
if the difference is greater than a preset threshold, reconstructing the first three-dimensional model of the blade until the difference is less than the preset threshold.
8. An apparatus for calculating tip deflection of a blade, the apparatus comprising:
a first determination module for determining a first tip deflection of the blade based on a first set of deformations of different sections of the blade;
a second determination module for determining a second tip deflection of the blade based on a second set of deformations of different cross sections of the blade, the second set of deformations being determined based on the first set of deformations;
and the difference value module is used for determining the target deflection of the blade tip based on the difference value between the first deflection of the blade tip and the second deflection of the blade tip.
9. An electronic device comprising at least a memory, a processor, a computer program being stored on said memory, characterized in that said processor, when executing the computer program on said memory, carries out the steps of the method of calculating the tip deflection of a blade according to any one of claims 1 to 7.
10. A storage medium storing a computer program, characterized in that the computer program, when being executed by a processor, realizes the steps of the method of calculating the tip deflection of a blade according to any one of claims 1 to 7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111649432.1A CN114330063A (en) | 2021-12-30 | 2021-12-30 | Blade tip deflection calculation method and device of blade, electronic equipment and storage medium |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111649432.1A CN114330063A (en) | 2021-12-30 | 2021-12-30 | Blade tip deflection calculation method and device of blade, electronic equipment and storage medium |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114330063A true CN114330063A (en) | 2022-04-12 |
Family
ID=81018464
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111649432.1A Pending CN114330063A (en) | 2021-12-30 | 2021-12-30 | Blade tip deflection calculation method and device of blade, electronic equipment and storage medium |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114330063A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116705483A (en) * | 2023-06-21 | 2023-09-05 | 正泰电气股份有限公司 | Method for optimizing strength of transformer oil tank |
-
2021
- 2021-12-30 CN CN202111649432.1A patent/CN114330063A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116705483A (en) * | 2023-06-21 | 2023-09-05 | 正泰电气股份有限公司 | Method for optimizing strength of transformer oil tank |
| CN116705483B (en) * | 2023-06-21 | 2024-03-22 | 正泰电气股份有限公司 | Method for optimizing strength of transformer oil tank |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109460566B (en) | Aerodynamic robust optimization design method for thick airfoil section on inner side of wind turbine blade | |
| US11441542B2 (en) | Operating a wind turbine using estimated wind speed while accounting for blade torsion | |
| AU2020100825A4 (en) | Method for evaluating aerodynamic performance of wind wheel of wind turbine based on three-factor fitting integral method | |
| CN109902384B (en) | Wind turbine flexible blade pretwisting design method based on aeroelastic model | |
| Johnson et al. | Wind turbine performance in controlled conditions: BEM modeling and comparison with experimental results | |
| Sale | HARP_Opt User’s Guide | |
| CN112031998A (en) | Wind turbine generator independent variable pitch control optimization method and system based on laser radar | |
| CN105787212A (en) | Method for designing wind turbine airfoil with aeroelastic deformation resistance | |
| CN114330063A (en) | Blade tip deflection calculation method and device of blade, electronic equipment and storage medium | |
| CN109409019A (en) | A kind of pre-bending optimization method of pneumatic equipment bladess aerodynamic configuration | |
| CN110630438B (en) | Control method and device for yaw system of wind generating set | |
| CN116822417B (en) | Wind turbine blade surface wind pressure analysis method | |
| Chen et al. | Design tool for aeroelastic analysis of wind turbine blades based on geometrically exact beam theory and lifting surface method | |
| CN109325274B (en) | Wind turbine wind wheel aerodynamic performance evaluation method based on three-factor fitting integration method | |
| CN110457800A (en) | Consider the trunnion axis blower wind speed power output translation method of machinery inertial | |
| CN114329813A (en) | Fan blade optimization design method based on Wilson model and particle swarm optimization | |
| CN116257958A (en) | Wind turbine blade model optimization method and device, electronic equipment and storage medium | |
| CN113353285B (en) | Method and system for determining rotor wing profile | |
| CN105260498B (en) | A kind of large size civil aircraft wing variable camber design method | |
| CN110781618B (en) | Fan blade optimization design method based on zigzag lightning strike and fatigue damage | |
| CN112948973B (en) | Wing stall flutter closed-loop control method for continuously variable camber trailing edge | |
| CN111898074B (en) | Airfoil aerodynamic coefficient calculation method and system | |
| CN113378330A (en) | Method for calculating effective wind sweeping radius of ultra-long flexible downwind wind turbine blade | |
| CN114676510A (en) | Method, device, equipment and medium for determining blade profile parameters of fan | |
| Fritz et al. | Validation of a BEM correction model for swept blades using experimental data |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |