CN115994411A - Method, device, apparatus and storage medium for airfoil blade design - Google Patents
Method, device, apparatus and storage medium for airfoil blade design Download PDFInfo
- Publication number
- CN115994411A CN115994411A CN202111211727.0A CN202111211727A CN115994411A CN 115994411 A CN115994411 A CN 115994411A CN 202111211727 A CN202111211727 A CN 202111211727A CN 115994411 A CN115994411 A CN 115994411A
- Authority
- CN
- China
- Prior art keywords
- wing
- cross
- section
- blade
- coordinate
- 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
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The application relates to the technical field of household appliances and discloses a method, a device, equipment and a storage medium for designing wing type blades. The method comprises the following steps: deriving a first contour point coordinate required for setting the cross section of the airfoil blade, wherein a first end point of the cross section of the airfoil blade is the origin of a coordinate system, and a second end point is on the transverse axis of the coordinate system; fitting is carried out according to the first contour point coordinates, and a distribution function related to the set parameters of the wing-shaped blade is obtained; obtaining a second contour point coordinate of the cross section of the wing-shaped blade to be designed according to the configuration value of the set parameter in the wing-shaped blade to be designed and the distribution function; and generating the cross section of the wing-shaped blade to be designed according to the second contour point coordinates, so that the wing-shaped blade corresponding to the product is obtained by carrying out data modeling according to the cross section of the wing-shaped blade to be designed, and the performance of the wing-shaped blade can be improved.
Description
Technical Field
The present application relates to the technical field of intelligent home appliances, for example, to a method, an apparatus, a device and a storage medium for designing airfoil type blades.
Background
In the product design development process of intelligent household appliances such as a smoke exhaust ventilator fan, a washing machine and the like, impeller blades are one of key parts. Its design and manufacturing performance directly determines the performance of the whole machine. The wing type blade is manufactured by imitating an airplane wing shape, has a streamline cross section, has the advantages of good strength, simplicity in installation, long service life and the like, and is widely applied to intelligent household appliances.
The unequal thickness is one of the geometric characteristics of the wing-shaped blade, and the aerodynamic characteristics of the wing-shaped blade directly influence the aerodynamic characteristics of the wing-shaped impeller. The relative thickness of the airfoil directly affects the drag (especially wave drag), the maximum lift coefficient, etc. of the non-uniform thickness blade. A non-uniform thickness blade is essentially a blade with an airfoil shape as cross-section. Currently, in the development of non-uniform thickness airfoil blade designs, blade sections are typically designed with reference to airfoil data. While airfoil data is typically derived from commercial software. Due to the limited variety of airfoils in software, the design of blade sections by developers is greatly limited. The method greatly limits the control of airfoil characteristics, such as relative camber, maximum camber position, blade thickness and other parameters, which cannot be flexibly changed according to the design requirements of users, and only the existing airfoil in software can be adopted.
It can be seen that the performance and flexibility of the wing type blade designed at present are still to be improved.
Disclosure of Invention
The following presents a simplified summary in order to provide a basic understanding of some aspects of the disclosed embodiments. This summary is not an extensive overview, and is intended to neither identify key/critical elements nor delineate the scope of such embodiments, but is intended as a prelude to the more detailed description that follows.
The embodiment of the disclosure provides a method, a device, equipment and a storage medium for designing an airfoil type blade, so as to solve the technical problem that the performance of the airfoil type blade needs to be improved.
In some embodiments, the method comprises:
deriving a first contour point coordinate required for setting the cross section of the airfoil blade, wherein a first end point of the cross section of the airfoil blade is the origin of a coordinate system, and a second end point is on the transverse axis of the coordinate system;
fitting is carried out according to the first contour point coordinates, and a distribution function related to the set parameters of the wing-shaped blade is obtained;
obtaining a second contour point coordinate of the cross section of the wing-shaped blade to be designed according to the configuration value of the set parameter in the wing-shaped blade to be designed and the distribution function;
and generating the cross section of the wing-shaped blade to be designed according to the second contour point coordinates, so that data modeling is carried out according to the cross section of the wing-shaped blade to be designed, and the wing-shaped blade corresponding to the product is obtained.
In some embodiments, the apparatus comprises:
the deriving module is configured to derive a first contour point coordinate required for setting the wing-shaped blade cross section, wherein a first end point of the wing-shaped blade cross section is an origin of a coordinate system, and a second end point is on a transverse axis of the coordinate system;
the fitting module is configured to fit according to the first contour point coordinates to obtain a distribution function related to the set parameters of the wing-shaped blade;
the profile determining module is configured to obtain a second profile point coordinate of the cross section of the wing-shaped blade to be designed according to the configuration value of the set parameter in the wing-shaped blade to be designed and the distribution function;
the graphic modeling module is configured to generate the cross section of the wing-shaped blade to be designed according to the second contour point coordinates, so that data modeling is performed according to the cross section of the wing-shaped blade to be designed, and the wing-shaped blade corresponding to the product is obtained.
In some embodiments, the apparatus for airfoil blade design includes a processor and a memory storing program instructions, the processor being configured, when executing the program instructions, to perform the above-described method for airfoil blade design.
In some embodiments, the apparatus comprises a device for airfoil blade design as described above.
In some embodiments, the storage medium stores program instructions that, when executed, perform the above-described method for airfoil blade design.
The method, the device, the equipment and the storage medium for designing the airfoil blade provided by the embodiment of the disclosure can realize the following technical effects:
after the profile point data of the cross section of the wing-shaped blade is derived, fitting can be carried out according to the set parameters to obtain a distribution function related to the set parameters, so that the profile point data of the cross section of the wing-shaped blade to be designed can be obtained according to the configuration values of the set parameters required by design and the distribution function, data modeling can be carried out, and the wing-shaped blade corresponding to the product is designed, thus the wing-shaped blade with different set parameter values can be designed flexibly according to the product requirement, the performance of the wing-shaped blade is improved, the design flexibility is also increased, and the user experience is improved.
The foregoing general description and the following description are exemplary and explanatory only and are not restrictive of the application.
Drawings
One or more embodiments are illustrated by way of example and not limitation in the figures of the accompanying drawings, in which like references indicate similar elements, and in which like reference numerals refer to similar elements, and in which:
FIG. 1 is a flow diagram of a method for airfoil blade design provided by an embodiment of the present disclosure;
FIG. 2 is a schematic illustration of a cross-section of an airfoil vane provided by an embodiment of the present disclosure;
FIG. 3 is a schematic illustration of a airfoil vane cross-section in a coordinate system provided by an embodiment of the present disclosure;
FIG. 4 is a flow diagram of a method for airfoil blade design provided by an embodiment of the present disclosure;
FIG. 5 is a schematic structural view of a wing-type blade design device provided in an embodiment of the present disclosure;
FIG. 6 is a schematic structural view of a wing-type blade design device provided in an embodiment of the present disclosure.
Detailed Description
So that the manner in which the features and techniques of the disclosed embodiments can be understood in more detail, a more particular description of the embodiments of the disclosure, briefly summarized below, may be had by reference to the appended drawings, which are not intended to be limiting of the embodiments of the disclosure. In the following description of the technology, for purposes of explanation, numerous details are set forth in order to provide a thorough understanding of the disclosed embodiments. However, one or more embodiments may still be practiced without these details. In other instances, well-known structures and devices may be shown simplified in order to simplify the drawing.
The terms first, second and the like in the description and in the claims of the embodiments of the disclosure and in the above-described figures are used for distinguishing between similar objects and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used may be interchanged where appropriate in order to describe embodiments of the present disclosure. Furthermore, the terms "comprise" and "have," as well as any variations thereof, are intended to cover a non-exclusive inclusion.
The term "plurality" means two or more, unless otherwise indicated.
In the embodiment of the present disclosure, the character "/" indicates that the front and rear objects are an or relationship. For example, A/B represents: a or B.
The term "and/or" is an associative relationship that describes an object, meaning that there may be three relationships. For example, a and/or B, represent: a or B, or, A and B.
In the embodiment of the disclosure, the derived profile point data of the cross section of the wing-shaped blade can be fitted to obtain the distribution function related to the set parameters, so that the profile point data of the cross section of the wing-shaped blade to be designed can be obtained according to the configuration value of the set parameters required by the design and the distribution function, the limit of the number of wing types in software is broken through, and the profile types of the wing types are greatly increased. In addition, the data modeling can be performed according to the profile point data of the cross section of the wing-shaped blade to be designed, and the wing-shaped blade corresponding to the product is designed, so that the wing-shaped blade with different set parameter values can be designed flexibly according to the product requirements, the performance of the wing-shaped blade is improved, the design flexibility is also improved, and the user experience is improved.
Fig. 1 is a flow diagram of a method for airfoil blade design provided by an embodiment of the present disclosure.
Step 101: and deriving a first contour point coordinate required for setting the cross section of the airfoil blade, wherein a first end point of the cross section of the airfoil blade is set as an origin of a coordinate system, and a second end point is on a transverse axis of the coordinate system.
Basic data of the airfoil blade may be derived from some relevant software, such as: profile wing design software can derive profile point data required by setting the cross section of the wing-shaped blade of the aircraft, and a corresponding coordinate system is configured to obtain corresponding first profile point coordinates.
Fig. 2 is a schematic illustration of a cross-section of an airfoil vane provided by an embodiment of the present disclosure. As shown in fig. 2, the cross section of the wing-shaped blade is provided with a front edge point and a rear edge point, namely a first end point and a second end point, and a connecting line between the front edge point and the rear edge point is a chord line of the cross section of the wing-shaped blade and corresponds to the chord length b; and the connecting line of the middle point of the longitudinal height on the cross section of the wing-shaped blade is the camber line of the cross section of the wing-shaped blade. If the camber line is a straight line, the airfoil is a symmetrical airfoil blade, and the camber line and the chord line are coincident. If the camber line curve is the camber, the airfoil vane has a camber, and the magnitude of the camber f is represented by the magnitude of a longitudinal value corresponding to the highest point on the camber line.
The designer can derive the data of the wing-shaped blade which is relatively close from some related software according to the size and shape characteristics of the wing-shaped blade in the product, namely, derive the profile point data of the cross section of the wing-shaped blade, and then establish a corresponding coordinate system, wherein the first end point of the cross section of the wing-shaped blade is set as the origin of the coordinate system, and the second end point is on the transverse axis of the coordinate system. And obtaining the first contour point coordinates corresponding to the derived contour point data in the established coordinate system.
FIG. 3 is a schematic illustration of a airfoil blade cross-section in a coordinate system provided by an embodiment of the present disclosure. As shown in fig. 3, the profile point a (x u ,y u ) Lower contour point B (x l ,y l ). Of course, the chord length b, and thus x, is the transverse axis coordinate of the coordinate system,
the magnitude of the camber f is expressed by the longitudinal coordinates of the highest point on the middle arc, while the relative camber
Corresponding maximum camber position->
The camber line of the cross section of the airfoil blade is a connecting line of the midpoints of the longitudinal heights, so that the longitudinal coordinates of the camber line are as follows: />
. Thickness y of airfoil c Is the difference between the longitudinal coordinate value of the upper profile point A and the longitudinal coordinate value of the lower profile point B of the airfoil. Therefore, the thickness of the airfoil can be expressed as: />
The maximum thickness on the airfoil is denoted +.>
Thus (S)>
Step 102: fitting is carried out according to the first contour point coordinates, and a distribution function related to the set parameters of the wing-shaped blade is obtained.
And obtaining a first contour point coordinate, namely performing data fitting through matlab, excel and other software to obtain a distribution function related to the set parameters of the wing-type blade. In the embodiment of the disclosure, the setting parameters include: relative camber of
Maximum bend position->
Maximum thickness->
One, two or more of the following.
In some embodiments, deriving the distribution function related to the set parameter of the airfoil vane comprises: after the chord length b of the chord line of the cross section of the wing-shaped blade is determined, performing fourth-order function fitting according to the first contour point coordinates to obtain a first distribution function related to the thickness of the wing profile of the cross section of the wing-shaped blade, which is shown in a formula (1);
wherein x is the horizontal axis coordinate of the coordinate system,
is the maximum thickness of the wing type blade; m, n, p, q, l, t is a constant associated with setting airfoil blades.
For example: setting the airfoil blade as an NACA23015 airfoil blade, and performing fourth-order function fitting on the first profile point coordinates to obtain a first distribution function related to the airfoil profile thickness of the airfoil blade cross section:
of course, the values of m, n, p, q, l, t are different for the set airfoil blades. Also, in some embodiments, a third, fourth, fifth, sixth, etc. order function fit is performed.
In some embodiments, the relative camber may also be obtained
Maximum camber position +.>
A related second distribution function, namely a first coordinate (0, 0) of the relative chord length b of the first end point in the coordinate system and a second coordinate (1, 0) of the relative chord length b of the second end point in the coordinate system are determined; then, according to the first coordinate and the second coordinate, parabolic fitting is carried out on the camber line of the cross section of the wing-shaped blade, and the relative camber ++of the camber line shown in the formula (2) and the cross section of the wing-shaped blade is obtained>
Maximum camber position +.>
A related second distribution function;
wherein the magnitude of the camber f of the wing-type blade cross section is expressed by the longitudinal coordinate y of the highest point on the middle arc line, and the relative camber
The coordinate x of the transverse axis corresponding to the maximum camber f Maximum camber position->
Wing type bladeThe mean camber line of the cross section is a parabola, and the vertex of the parabola is used
Is a boundary point and is divided into two sections, wherein +.>
When the first coordinate (0, 0) of the parabola is known, and the vertex of the parabola +.>
According to the parabolic mathematical expression +.>
But->
At the same time, according to the second coordinate (1, 0), and parabolic vertex +.>
According to the parabolic mathematical expression +.>
Step 103: and obtaining a second contour point coordinate of the cross section of the airfoil blade to be designed according to the configuration value of the set parameter in the airfoil blade to be designed and the distribution function.
And obtaining a contour point coordinate formula shown in formula (3) according to a camber line obtained by connecting the longitudinal height midpoints of the wing-shaped blade cross sections.
Wherein y is u Longitudinal seating for upper profile points in airfoil blade cross-sectionScale, y l Is the longitudinal coordinate value of the lower contour point in the cross section of the wing type blade.
And then, substituting the configuration values, the first distribution function and the second distribution function of the set parameters in the airfoil blade to be designed into a formula (3) to obtain the second contour point coordinates of the cross section of the airfoil blade to be designed.
And obtaining a series of coordinates through software such as matlab, excel and the like, and obtaining the coordinates of the second contour point of the cross section of the wing type blade to be designed.
Step 104: and generating the cross section of the wing-shaped blade to be designed according to the second contour point coordinates, so that data modeling is carried out according to the cross section of the wing-shaped blade to be designed, and the wing-shaped blade corresponding to the product is obtained.
And generating a cross section of the wing-shaped blade to be designed according to the second contour point coordinates, and then carrying out data modeling according to the cross section of the wing-shaped blade to be designed to obtain the wing-shaped blade corresponding to the product. The data modeling may include manual modeling, or, alternatively, coordinate translation modeling. For example: based on the cross section of the wing-shaped blade to be designed, after the bending angle is determined, coordinates of contour points of the cross section of each blade after changing parameters can be obtained rapidly through coordinate transformation, then stored data are imported into three-dimensional drawing software, for example, solidWorks software, a cross section figure of the wing-shaped blade after bending can be generated, then the cross section figure can be stretched, a wing-shaped blade model with a set bending angle and a set bending radius is formed, and accordingly the wing-shaped blade corresponding to the product is obtained.
In this way, the configuration values of the setting parameters are continuously adjusted, for example: adjusting relative camber
Maximum bend position->
Maximum thickness->
One, two or more of the above-mentioned materials can obtain different wing type blade cross sections to be designed so as to design the wing type blade with better performance.
Therefore, in the embodiment of the disclosure, after the profile point data of the cross section of the wing-shaped blade is derived, fitting can be performed according to the set parameters to obtain the distribution function related to the set parameters, so that the profile point data of the cross section of the wing-shaped blade to be designed can be obtained according to the configuration values of the set parameters required by the design and the distribution function, and data modeling can be performed to design the wing-shaped blade corresponding to the product.
The following sets of operational flows into specific embodiments illustrating the process provided by embodiments of the present disclosure for airfoil blade design.
In this embodiment, the airfoil blade is set as a NACA23015 airfoil blade, and fourth-order function fitting is performed on the first contour point coordinates.
Fig. 4 is a flow chart of a method for airfoil blade design provided by an embodiment of the present disclosure. With reference to fig. 4, the process for airfoil blade design includes:
step 401: and deriving profile data of points required by the cross section of the NACA23015 airfoil blade from profile airfoil design software, and obtaining corresponding first profile point coordinates in a configured coordinate system.
In the coordinate system, the first end point of the cross section of the wing-shaped blade is set as the origin of the coordinate system, and the second end point is arranged on the transverse axis of the coordinate system.
Step 402: determining the chord length b of the chord line of the cross section of the wing-shaped blade; and performing fourth-order function fitting according to the first contour point coordinates to obtain a first distribution function related to the wing profile thickness of the cross section of the wing-shaped blade shown in the formula (4).
Step 403: a first coordinate (0, 0) of the relative chord length b of the first end point in the coordinate system and a second coordinate (1, 0) of the relative chord length b of the second end point in the coordinate system are determined.
Step 404: parabolic fitting is carried out on the camber line of the cross section of the wing-shaped blade according to the first coordinate and the second coordinate, so that the relative camber of the camber line and the cross section of the wing-shaped blade shown in the formula (2) is obtained
Maximum camber position +.>
And an associated second distribution function.
Wherein the magnitude of the camber f of the wing-type blade cross section is expressed by the longitudinal coordinate y of the highest point on the middle arc line, and the relative camber
The coordinate x of the transverse axis corresponding to the maximum camber f Maximum camber position->
Step 405: and obtaining a contour point coordinate formula shown in formula (3) according to a camber line obtained by connecting the longitudinal height midpoints of the wing-shaped blade cross sections.
Wherein y is u Is the longitudinal coordinate value of the upper contour point in the cross section of the wing-type blade, y l Is the longitudinal coordinate value of the lower contour point in the cross section of the wing type blade.
Step 406: substituting the configuration value, the first distribution function and the second distribution function of the set parameters in the airfoil blade to be designed into the formula (3) to obtain the second contour point coordinates of the cross section of the airfoil blade to be designed.
For example: and obtaining a second contour point coordinate of the cross section of the wing-shaped blade to be designed in Matlab software.
Step 407: and carrying out coordinate transformation on the coordinates of the second contour point of the cross section of the wing-shaped blade to be designed according to the set bending angle to obtain the coordinates of the contour point of each blade cross section after the parameters are changed.
Step 408: in SolidWorks software, contour point coordinates are imported to generate a curved wing-shaped blade cross-section graph.
Step 409: and stretching the cross section graph to form the wing-shaped blade model with the bending angle and the bending radius.
In the embodiment, the profile point data of the cross section of the wing type blade is obtained by fitting the derived profile point data of the cross section of the wing type blade in Matlab software, so that a distribution function related to the set parameters is obtained, and the profile point data of the cross section of the wing type blade to be designed can be obtained according to the configuration value of the set parameters required by the design and the distribution function, thereby breaking through the limitation of the number of wing types in the software and greatly increasing the profile types of the wing type blade. In addition, the data modeling can be performed according to the profile point data of the cross section of the wing-shaped blade to be designed, and the wing-shaped blade corresponding to the product is designed, so that the wing-shaped blade with different set parameter values can be designed flexibly according to the product requirements, the performance of the wing-shaped blade is improved, the design flexibility is also improved, and the user experience is improved.
According to the above procedure for airfoil blade design, a device for airfoil blade design can be constructed.
Fig. 5 is a schematic structural view of a wing-type blade design device according to an embodiment of the present disclosure. As shown in fig. 5, the blade design apparatus for an airfoil type includes: the derivation module 510, the fitting module 520, the contour determination module 530, and the graphical modeling module 540.
The deriving module 510 is configured to derive a first contour point coordinate required for setting the airfoil blade cross section, wherein a first end point of the airfoil blade cross section is set as an origin of the coordinate system and a second end point is on a horizontal axis of the coordinate system.
The fitting module 520 is configured to perform fitting according to the first contour point coordinates, so as to obtain a distribution function related to the set parameters of the airfoil vane.
The profile determination module 530 is configured to obtain a second profile point coordinate of the cross section of the airfoil vane to be designed according to the configuration value of the set parameter in the airfoil vane to be designed and the distribution function.
The graph modeling module 540 is configured to generate a cross section of the airfoil blade to be designed according to the second contour point coordinates, so that data modeling is performed according to the cross section of the airfoil blade to be designed to obtain the airfoil blade corresponding to the product.
In some embodiments, the fitting module 520 includes:
a first determining unit configured to determine a chord length b of a chord line of the cross section of the airfoil type blade.
The first fitting unit is configured to perform fourth-order function fitting according to the first contour point coordinates to obtain a first distribution function related to the thickness of the wing profile of the cross section of the wing type blade shown in the formula (1);
wherein x is the horizontal axis coordinate of the coordinate system,
c is the maximum thickness of the wing type blade, the relative thickness +.>
m, n, p, q, l, t is a constant associated with setting airfoil blades.
In some embodiments, the fitting module 520 includes:
a second determination unit configured to determine a first coordinate (0, 0) of a relative chord length b of the first end point in the coordinate system, and a second coordinate (1, 0) of a relative chord length b of the second end point in the coordinate system;
a second fitting unit configured to perform parabolic fitting on the camber line of the airfoil-shaped blade cross section according to the first coordinate and the second coordinate to obtain a relative camber of the camber line and the airfoil-shaped blade cross section shown in formula (2)
Maximum camber position +.>
A related second distribution function;
wherein the magnitude of the camber f of the wing-type blade cross section is expressed by the longitudinal coordinate y of the highest point on the middle arc line, and the relative camber
The coordinate x of the transverse axis corresponding to the maximum camber f Maximum camber position->
In some embodiments, the contour determination module 530 includes:
the formula determining unit is configured to obtain a contour point coordinate formula shown in formula (3) according to a mean camber line obtained by connecting the midpoints of the longitudinal heights of the cross sections of the wing-shaped blades;
substituting the configuration values, the first distribution function and the second distribution function of the parameters set in the wing-shaped blade to be designed into the formula (3) to obtain second contour point coordinates of the cross section of the wing-shaped blade to be designed;
wherein y is u Is the longitudinal coordinate value of the upper contour point in the cross section of the wing-type blade, y l Is the longitudinal coordinate value of the lower contour point in the cross section of the wing type blade.
Therefore, in this embodiment, after the profile point data of the cross section of the wing-shaped blade is derived, the wing-shaped blade design device can perform fitting according to the set parameters to obtain a distribution function related to the set parameters, so that the profile point data of the cross section of the wing-shaped blade to be designed can be obtained according to the configuration values of the set parameters required by the design and the distribution function, and the profile point data of the cross section of the wing-shaped blade to be designed can be subjected to data modeling to design the wing-shaped blade corresponding to the product, thus the wing-shaped blade with different set parameter values can be designed flexibly according to the product requirements, the performance of the wing-shaped blade is improved, the flexibility of the design is also increased, and the user experience is improved.
An embodiment of the present disclosure provides an apparatus for airfoil vane design, the structure of which is shown in fig. 6, comprising:
a processor (processor) 1000 and a memory (memory) 1001, and may also include a communication interface (Communication Interface) 1002 and a bus 1003. The processor 1000, the communication interface 1002, and the memory 1001 may communicate with each other via the bus 1003. The communication interface 1002 may be used for information transfer. The processor 1000 may call logic instructions in the memory 1001 to perform the method for airfoil blade design of the above-described embodiments.
Further, the logic instructions in the memory 1001 described above may be implemented in the form of software functional units and may be stored in a computer readable storage medium when sold or used as a stand alone product.
The memory 1001 is used as a computer readable storage medium for storing a software program and a computer executable program, such as program instructions/modules corresponding to the methods in the embodiments of the present disclosure. The processor 1000 performs functional applications as well as data processing by running program instructions/modules stored in the memory 1001, i.e. implements the method for airfoil blade design in the method embodiments described above.
The memory 1001 may include a storage program area and a storage data area, wherein the storage program area may store an operating system, at least one application program required for functions; the storage data area may store data created according to the use of the terminal device, etc. In addition, the memory 1001 may include a high-speed random access memory, and may also include a nonvolatile memory.
Embodiments of the present disclosure provide a design apparatus for an airfoil type blade, comprising: a processor and a memory storing program instructions, the processor being configured to execute a method for airfoil blade design when executing the program instructions.
Embodiments of the present disclosure provide an apparatus comprising an airfoil blade design device as described above.
The disclosed embodiments provide a storage medium storing program instructions that, when executed, perform the above-described method for airfoil blade design.
The disclosed embodiments provide a computer program product comprising a computer program stored on a computer readable storage medium, the computer program comprising program instructions which, when executed by a computer, cause the computer to perform the above-described method for airfoil blade design.
The storage medium may be a transitory computer readable storage medium or a non-transitory computer readable storage medium.
Embodiments of the present disclosure may be embodied in a software product stored on a storage medium, including one or more instructions for causing a computer device (which may be a personal computer, a server, or a network device, etc.) to perform all or part of the steps of a method according to embodiments of the present disclosure. And the aforementioned storage medium may be a non-transitory storage medium including: a plurality of media capable of storing program codes, such as a usb disk, a removable hard disk, a Read-Only Memory (ROM), a random access Memory (RAM, random Access Memory), a magnetic disk, or an optical disk, or a transitory storage medium.
The above description and the drawings illustrate embodiments of the disclosure sufficiently to enable those skilled in the art to practice them. Other embodiments may involve structural, logical, electrical, process, and other changes. The embodiments represent only possible variations. Individual components and functions are optional unless explicitly required, and the sequence of operations may vary. Portions and features of some embodiments may be included in, or substituted for, those of others. The scope of the embodiments of the present disclosure encompasses the full ambit of the claims, as well as all available equivalents of the claims. When used in this application, although the terms "first," "second," etc. may be used herein to describe various elements, these elements should not be limited by these terms. These terms are only used to distinguish one element from another element. For example, a first element could be termed a second element, and, similarly, a second element could be termed a first element, without changing the meaning of the description, so long as all occurrences of the "first element" are renamed consistently and all occurrences of the "second element" are renamed consistently. The first element and the second element are both elements, but may not be the same element. Moreover, the terminology used in the present application is for the purpose of describing embodiments only and is not intended to limit the claims. As used in the description of the embodiments and the claims, the singular forms "a," "an," and "the" (the) are intended to include the plural forms as well, unless the context clearly indicates otherwise. Similarly, the term "and/or" as used in this application is meant to encompass any and all possible combinations of one or more of the associated listed. Furthermore, when used in this application, the terms "comprises," "comprising," and/or "includes," and variations thereof, mean that the stated features, integers, steps, operations, elements, and/or components are present, but that the presence or addition of one or more other features, integers, steps, operations, elements, components, and/or groups thereof is not precluded. Without further limitation, an element defined by the phrase "comprising one …" does not exclude the presence of other like elements in a process, method or apparatus comprising such elements. In this context, each embodiment may be described with emphasis on the differences from the other embodiments, and the same similar parts between the embodiments may be referred to each other. For the methods, products, etc. disclosed in the embodiments, if they correspond to the method sections disclosed in the embodiments, the description of the method sections may be referred to for relevance.
Those of skill in the art will appreciate that the various illustrative elements and algorithm steps described in connection with the embodiments disclosed herein may be implemented as electronic hardware, or combinations of computer software and electronic hardware. Whether such functionality is implemented as hardware or software depends upon the particular application and design constraints imposed on the solution. The skilled artisan may use different methods for each particular application to achieve the described functionality, but such implementation should not be considered to be beyond the scope of the embodiments of the present disclosure. It will be clearly understood by those skilled in the art that, for convenience and brevity of description, specific working procedures of the above-described systems, apparatuses and units may refer to corresponding procedures in the foregoing method embodiments, which are not repeated herein.
In the embodiments disclosed herein, the disclosed methods, articles of manufacture (including but not limited to devices, apparatuses, etc.) may be practiced in other ways. For example, the apparatus embodiments described above are merely illustrative, and for example, the division of the units may be merely a logical function division, and there may be additional divisions when actually implemented, for example, multiple units or components may be combined or integrated into another system, or some features may be omitted, or not performed. In addition, the coupling or direct coupling or communication connection shown or discussed with each other may be through some interface, device or unit indirect coupling or communication connection, which may be in electrical, mechanical or other form. The units described as separate units may or may not be physically separate, and units shown as units may or may not be physical units, may be located in one place, or may be distributed on a plurality of network units. Some or all of the units may be selected according to actual needs to implement the present embodiment. In addition, each functional unit in the embodiments of the present disclosure may be integrated in one processing unit, or each unit may exist alone physically, or two or more units may be integrated in one unit.
The flowcharts and block diagrams in the figures illustrate the architecture, functionality, and operation of possible implementations of systems, methods and computer program products according to embodiments of the present disclosure. In this regard, each block in the flowchart or block diagrams may represent a module, segment, or portion of code, which comprises one or more executable instructions for implementing the specified logical function(s). In some alternative implementations, the functions noted in the block may occur out of the order noted in the figures. For example, two blocks shown in succession may, in fact, be executed substantially concurrently, or the blocks may sometimes be executed in the reverse order, depending upon the functionality involved. In the description corresponding to the flowcharts and block diagrams in the figures, operations or steps corresponding to different blocks may also occur in different orders than that disclosed in the description, and sometimes no specific order exists between different operations or steps. For example, two consecutive operations or steps may actually be performed substantially in parallel, they may sometimes be performed in reverse order, which may be dependent on the functions involved. Each block of the block diagrams and/or flowchart illustration, and combinations of blocks in the block diagrams and/or flowchart illustration, can be implemented by special purpose hardware-based systems that perform the specified functions or acts, or combinations of special purpose hardware and computer instructions.
Claims (11)
1. A method for airfoil blade design, comprising:
deriving a first contour point coordinate required for setting the cross section of the airfoil blade, wherein a first end point of the cross section of the airfoil blade is the origin of a coordinate system, and a second end point is on the transverse axis of the coordinate system;
fitting is carried out according to the first contour point coordinates, and a distribution function related to the set parameters of the wing-shaped blade is obtained;
obtaining a second contour point coordinate of the cross section of the wing-shaped blade to be designed according to the configuration value of the set parameter in the wing-shaped blade to be designed and the distribution function;
and generating the cross section of the wing-shaped blade to be designed according to the second contour point coordinates, so that data modeling is carried out according to the cross section of the wing-shaped blade to be designed, and the wing-shaped blade corresponding to the product is obtained.
2. The method of claim 1, wherein the deriving a distribution function related to a set parameter of the airfoil vane comprises:
determining the chord length b of the chord line of the cross section of the wing-shaped blade;
performing fourth-order function fitting according to the first contour point coordinates to obtain a first distribution function related to the wing profile thickness of the cross section of the wing type blade, which is shown in formula (1);
wherein x is the horizontal axis coordinate of the coordinate system,
is the maximum thickness of the wing type blade; m, n, p, q, l, t is a constant associated with the set airfoil vane.
3. The method of claim 2, wherein the deriving a distribution function related to the set parameter of the airfoil vane comprises:
determining a first coordinate (0, 0) of the first end point in the coordinate system relative to the chord length b, and a second coordinate (1, 0) of the second end point in the coordinate system relative to the chord length b;
parabolic fitting is carried out on the camber line of the cross section of the wing-shaped blade according to the first coordinate and the second coordinate, so that the relative camber of the camber line and the cross section of the wing-shaped blade shown in formula (2) is obtained
Position at maximum camber
A related second distribution function;
wherein the magnitude of the camber f of the wing-type blade cross section is expressed by the longitudinal coordinate y of the highest point on the middle arc line, and the relative camber
The coordinate x of the transverse axis corresponding to the maximum camber f Maximum camber position->
4. A method according to claim 3, wherein said deriving second profile point coordinates of the airfoil vane cross-section to be designed comprises:
obtaining a contour point coordinate formula shown in formula (3) according to the camber line obtained by connecting the midpoints of the longitudinal heights of the cross sections of the wing-shaped blades;
substituting the first distribution function and the second distribution function into the formula (3) according to the configuration value of the set parameters in the wing-shaped blade to be designed to obtain a second contour point coordinate of the cross section of the wing-shaped blade to be designed;
wherein y is u Is the longitudinal coordinate value of the upper contour point in the cross section of the wing-type blade, y l Is the longitudinal coordinate value of the lower contour point in the cross section of the wing type blade.
5. An apparatus for airfoil blade design, comprising:
the deriving module is configured to derive a first contour point coordinate required for setting the wing-shaped blade cross section, wherein a first end point of the wing-shaped blade cross section is an origin of a coordinate system, and a second end point is on a transverse axis of the coordinate system;
the fitting module is configured to fit according to the first contour point coordinates to obtain a distribution function related to the set parameters of the wing-shaped blade;
the profile determining module is configured to obtain a second profile point coordinate of the cross section of the wing-shaped blade to be designed according to the configuration value of the set parameter in the wing-shaped blade to be designed and the distribution function;
the graphic modeling module is configured to generate the cross section of the wing-shaped blade to be designed according to the second contour point coordinates, so that data modeling is performed according to the cross section of the wing-shaped blade to be designed, and the wing-shaped blade corresponding to the product is obtained.
6. The apparatus of claim 5, wherein the fitting module comprises:
a first determining unit configured to determine a chord length b of a chord line of the cross section of the airfoil type blade;
the first fitting unit is configured to perform fourth-order function fitting according to the first contour point coordinates to obtain a first distribution function related to the airfoil profile thickness of the cross section of the airfoil blade, which is shown in formula (1);
wherein x is the horizontal axis coordinate of the coordinate system,
is the maximum thickness of the wing type blade, the relative thickness +.>
m, n, p, q, l, t is a constant associated with the set airfoil vane.
7. The apparatus of claim 6, wherein the fitting module comprises:
a second determining unit configured to determine a first coordinate (0, 0) of the first end point in the coordinate system with respect to the chord length b, and a second coordinate (1, 0) of the second end point in the coordinate system with respect to the chord length b;
a second fitting unit configured to perform parabolic fitting on a camber line of the airfoil-shaped blade cross section according to the first coordinate and the second coordinate, to obtain a relative camber of the camber line and the airfoil-shaped blade cross section shown in formula (2)
Maximum camber position +.>
A related second distribution function;
wherein the magnitude of the camber f of the airfoil-shaped blade cross section is expressed by the longitudinal coordinate y of the highest point on the middle arc lineShowing relative camber
The coordinate x of the transverse axis corresponding to the maximum camber f Maximum camber position->
8. The apparatus of claim 7, wherein the profile determination module comprises:
the formula determining unit is configured to obtain a contour point coordinate formula shown in formula (3) according to the camber line obtained by connecting the midpoints of the longitudinal heights of the cross sections of the wing-shaped blades;
substituting the first distribution function and the second distribution function into the formula (3) according to the configuration value of the set parameter in the wing-shaped blade to be designed to obtain a second contour point coordinate of the cross section of the wing-shaped blade to be designed;
wherein y is u Is the longitudinal coordinate value of the upper contour point in the cross section of the wing-type blade, y l Is the longitudinal coordinate value of the lower contour point in the cross section of the wing type blade.
9. An apparatus for airfoil blade design, the apparatus comprising a processor and a memory storing program instructions, wherein the processor is configured, when executing the program instructions, to perform the method for airfoil blade design of any of claims 1 to 4.
10. An apparatus, comprising: an apparatus for airfoil blade design as claimed in claim 5 or 9.
11. A storage medium storing program instructions which, when executed, perform a method for airfoil blade design according to any one of claims 1 to 4.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111211727.0A CN115994411A (en) | 2021-10-18 | 2021-10-18 | Method, device, apparatus and storage medium for airfoil blade design |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111211727.0A CN115994411A (en) | 2021-10-18 | 2021-10-18 | Method, device, apparatus and storage medium for airfoil blade design |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115994411A true CN115994411A (en) | 2023-04-21 |
Family
ID=85992811
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111211727.0A Pending CN115994411A (en) | 2021-10-18 | 2021-10-18 | Method, device, apparatus and storage medium for airfoil blade design |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115994411A (en) |
-
2021
- 2021-10-18 CN CN202111211727.0A patent/CN115994411A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110727995B (en) | Blade shape construction method, blade, and computer device | |
| US10002209B2 (en) | Method for modelling a part, in particular a blading | |
| Koini et al. | A software tool for parametric design of turbomachinery blades | |
| CN110008653A (en) | A kind of aviation centrifugal pump blade profile optimum design method | |
| JP6708995B2 (en) | Blade design method and blade for axial flow fluid machine | |
| CN109598081B (en) | Radial-flow turbine pneumatic optimization method based on data dimension reduction and multi-two-dimensional flow surface | |
| US10387611B2 (en) | Method for modeling a blade of a non-ducted propeller | |
| JP2016525756A (en) | How to model a non-streamlined propeller blade | |
| CN110750855B (en) | Volute molded line design method under shape sizing limitation | |
| CN106126791A (en) | A kind of hypersonic wing aerodynamic force/heat analysis method considering geometrical uncertainty | |
| CN113408044B (en) | Multi-rotor unmanned aerial vehicle blade optimization design method | |
| CN113569360B (en) | Method for designing flutter-resistant airfoil cluster of wind turbine blade | |
| CN109492234B (en) | Improved fluid-solid coupling interpolation method | |
| CN108268672A (en) | Aerofoil fan, design aerofoil fan three dimendional blade method and computer equipment | |
| CN106874526B (en) | Method and device for generating production coordinates of turbine blades | |
| CN115481511A (en) | Centrifugal impeller multi-working-condition local configuration pneumatic optimization method and device based on FFD | |
| CN108038259A (en) | Method based on curvature generation Pneumatic component shape | |
| CN112487570B (en) | Centrifugal compressor splitter blade shape optimization method based on free deformation technology | |
| CN115994411A (en) | Method, device, apparatus and storage medium for airfoil blade design | |
| Safari et al. | A novel combination of adaptive tools for turbomachinery airfoil shape optimization using a real-coded genetic algorithm | |
| CN110348575A (en) | A kind of impeller reverse engineering approach based on genetic algorithm | |
| RU2672990C1 (en) | Turbomachine component with non-axisymmetric surface | |
| CN115935525A (en) | Method, device and equipment for designing airfoil blade | |
| Marx et al. | A machine learning based approach of performance estimation for high-pressure compressor airfoils | |
| CN113051688B (en) | Blade profile shape geometry calculation method, device and equipment |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication |