CN114491868A - Rapid design method for multi-wing centrifugal fan wing-shaped blade impeller - Google Patents
Rapid design method for multi-wing centrifugal fan wing-shaped blade impeller Download PDFInfo
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- CN114491868A CN114491868A CN202210133596.7A CN202210133596A CN114491868A CN 114491868 A CN114491868 A CN 114491868A CN 202210133596 A CN202210133596 A CN 202210133596A CN 114491868 A CN114491868 A CN 114491868A
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/17—Mechanical parametric or variational design
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/30—Vanes
Abstract
The invention discloses a method for quickly designing a multi-wing centrifugal fan wing-shaped blade impeller, and belongs to the technical field of household appliances. The method includes determining an airfoil mean camber line equation: selecting a mean camber line of an original blade as a mean camber line of the airfoil profile, and acquiring a mean camber line equation of the airfoil profile; determining an airfoil thickness distribution equation: determining an included angle theta between each oblique line perpendicular to the tangential direction and each abscissa of each point on the mean camber line of the airfoil profile; determining a scaling factor; determining the thickness of the airfoil corresponding to each point on the camber line of the airfoil; calculating coordinates of upper and lower wing surfaces of the wing-shaped blade according to the thickness and the included angle theta of each point on the camber line of the wing-shaped blade, and connecting the coordinates to obtain the wing-shaped blade; and obtaining an airfoil impeller model by using a single airfoil blade along the circumferential array of the rotation center of the impeller. The design method of the invention directly adds different wing profiles on the camber line of the original blade, reserves the inlet and outlet mounting angles of the original blade, can directly generate the impeller, and improves the design efficiency and accuracy of the wing-profile blade impeller.
Description
Technical Field
The invention relates to the technical field of household appliances, in particular to a method for quickly designing a multi-wing centrifugal fan wing-shaped blade impeller.
Background
The multi-wing centrifugal fan is widely applied to the fields of air conditioners, range hoods and the like due to the characteristics of small overall size, high pressure coefficient, large flow coefficient and the like, but has the problems of large internal flow loss, low efficiency, large noise and the like. The multi-wing centrifugal fan mainly comprises a volute, an impeller and a collector, wherein the impeller is used as a main power component and has great influence on the aerodynamic performance and noise of the multi-wing centrifugal fan.
The multi-wing centrifugal fan blade is often a single-arc or double-arc blade with equal thickness, and has the problems of large blade inlet impact and serious flow separation of flow channels between blades. In recent years, bionic airfoils or aviation airfoils are applied to multi-airfoil centrifugal fan blade design more and more generally by utilizing the characteristics of good airfoil flow dividing effect, low impact loss, difficult separation of flow and the like.
The conventional method for designing the airfoil profile comprises manual modeling and computer software modeling, wherein the manual modeling method is adopted, if points are taken too few, the airfoil profile blade cannot be in smooth transition and is far away from the original airfoil profile, and if more points are taken, a large amount of time is consumed and errors are easily caused due to manual modeling, so that the design efficiency is too low; the method of modeling by means of computer software is more efficient than manual modeling, but the existing method of modeling by means of computer software firstly designs the airfoil blades and then assembles the blades in the impeller according to the designed inlet and outlet mounting angles, so that the design of the impeller cannot be completed while the airfoil blades are generated.
Disclosure of Invention
The invention aims to overcome the problems in the prior art and provides a method for quickly designing an airfoil-shaped blade impeller of a multi-airfoil centrifugal fan.
The invention provides a method for quickly designing a wing-shaped blade impeller of a multi-wing centrifugal fan, which comprises the following steps of:
determining an airfoil mean camber line equation for the airfoil blade: selecting a mean camber line of an original blade as a mean camber line of the airfoil, keeping the placing position of the mean camber line of the airfoil consistent with that of an actual impeller, and fitting to obtain a mean camber line equation of the airfoil;
determining a thickness distribution equation of the selected airfoil profile:
determining an included angle theta between each oblique line perpendicular to the tangential direction and each abscissa of each point on the mean camber line of the airfoil profile;
obtaining a scaling coefficient according to the relation between the arc length of the camber line of the original blade and the length of the selected camber line of the airfoil; determining the airfoil thickness corresponding to each point on the camber line of the airfoil according to the scaling relationship and the thickness distribution equation from the front edge to the tail edge of the airfoil blade;
calculating the coordinates of the upper airfoil surface and the lower airfoil surface of the airfoil blade according to the thickness and the included angle theta of each point on the obtained camber line of the airfoil, and connecting the coordinates to obtain the airfoil blade;
and obtaining an airfoil impeller model by using a single airfoil blade along the circumferential array of the rotation center of the impeller.
Preferably, the method for determining the camber line equation of the airfoil is as follows: and taking a plurality of points on the airfoil mean camber line to obtain coordinates of the points, and carrying out nonlinear curve fitting on the mean camber line by using a least square method according to the coordinates of the points to obtain an airfoil mean camber line equation.
Preferably, the method for determining the thickness distribution equation of the airfoil is as follows: and determining the relation between the upper wing surface and the lower wing surface of the airfoil blade and the camber line of the airfoil, and performing nonlinear curve fitting on the relation by using a least square method to obtain a thickness distribution equation of the airfoil.
Preferably, the included angle θ between the oblique line perpendicular to the tangential direction and the abscissa of each point on the camber line of the airfoil is determined as follows: and (3) deriving an equation of the camber line of the wing profile to obtain the tangential direction of each point on the camber line of the wing profile, calculating the slope of a slash perpendicular to the tangential direction of each point on the camber line of the wing profile, and then solving the included angle theta between the slash and a horizontal coordinate by a trigonometric function relation.
Compared with the prior art, the invention has the beneficial effects that:
according to the method for quickly designing the wing-shaped blade impeller of the multi-wing centrifugal fan, different wing shapes are directly added to the camber line of the original blade, the inlet and outlet installation angles of the original blade are reserved, the impeller can be directly generated, the trouble that the installation angle of the wing-shaped blade on the impeller needs to be determined again after the wing-shaped blade is designed is avoided, and the design efficiency and accuracy of the wing-shaped blade impeller are improved.
In the method for quickly designing the wing-shaped blade impeller of the multi-wing centrifugal fan, the camber line of the original blade can be any curve, the added wing can be any wing, and the two wings of the wing can be designed independently, so that the method is suitable for quickly designing wing-shaped blade impellers of various wings and improves the design efficiency of the wing-shaped blade impeller.
Drawings
Fig. 1 is a schematic design flow diagram provided in the embodiment of the present disclosure.
FIG. 2 is a raw blade camber line provided by an embodiment of the present disclosure.
Fig. 3 is a schematic illustration of a NACA0008 airfoil employed by embodiments of the present disclosure.
FIG. 4 is a schematic diagram illustrating coordinate point calculation of upper and lower airfoils according to an embodiment of the disclosure.
FIG. 5 is a schematic view of an airfoil blade provided in accordance with an embodiment of the present disclosure.
FIG. 6 is a schematic view of an airfoil vane wheel provided by embodiments of the present disclosure.
Detailed Description
Detailed description of the preferred embodimentsthe following detailed description of the present invention will be made with reference to the accompanying drawings 1-6, although it should be understood that the scope of the present invention is not limited to the specific embodiments. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.
The invention provides a method for quickly designing a wing-shaped blade impeller of a multi-wing centrifugal fan, which comprises the following steps of:
determining an airfoil mean camber line equation for the airfoil blade: selecting a mean camber line of an original blade as a mean camber line of the airfoil, keeping the placing position of the mean camber line of the airfoil consistent with that of an actual impeller, and fitting to obtain a mean camber line equation of the airfoil;
determining a thickness distribution equation of the selected airfoil profile:
determining an included angle theta between each oblique line perpendicular to the tangential direction and each abscissa of each point on the mean camber line of the airfoil profile;
obtaining a scaling coefficient according to the relation between the arc length of the camber line of the original blade and the length of the selected camber line of the airfoil; determining the airfoil thickness corresponding to each point on the camber line of the airfoil according to the scaling relationship and the thickness distribution equation from the front edge to the tail edge of the airfoil blade;
calculating the coordinates of the upper airfoil surface and the lower airfoil surface of the airfoil blade according to the thickness and the included angle theta of each point on the obtained camber line of the airfoil, and connecting the coordinates to obtain the airfoil blade;
and obtaining an airfoil impeller model by using a single airfoil blade along the circumferential array of the rotation center of the impeller.
Further, the method for determining the camber line equation of the airfoil is as follows: and taking a plurality of points on the airfoil mean camber line to obtain coordinates of the points, and carrying out nonlinear curve fitting on the mean camber line by using a least square method according to the coordinates of the points to obtain an airfoil mean camber line equation.
Further, the method for determining the thickness distribution equation of the airfoil is as follows: and determining the relation between the upper wing surface and the lower wing surface of the airfoil blade and the camber line of the airfoil, and performing nonlinear curve fitting on the relation by using a least square method to obtain a thickness distribution equation of the airfoil.
Further, the method for determining the included angle θ between the oblique line perpendicular to the tangential direction and the abscissa of each point on the camber line of the airfoil is as follows: and (3) deriving an equation of the camber line of the wing profile to obtain the tangential direction of each point on the camber line of the wing profile, calculating the slope of a slash perpendicular to the tangential direction of each point on the camber line of the wing profile, and then solving the included angle theta between the slash and a horizontal coordinate by a trigonometric function relation.
Fig. 1 is a schematic flow chart of a rapid design method for an airfoil blade of a multi-blade centrifugal fan according to this embodiment.
Fig. 2 shows the mean camber line of the original blade, which refers to the non-airfoil blade currently used in the impeller, and the arrangement position of the mean camber line of the original blade is consistent with that of the actual impeller. And selecting the mean camber line of the original blade as the mean camber line of the airfoil, and taking a point on the mean camber line of the airfoil to obtain the coordinate of the point. The airfoil mean camber line equation is obtained by least squares fitting based on the coordinates of the points, and the equation form is a polynomial selected in this embodiment. In order to improve the fitting precision, the airfoil mean camber line is divided into an upper part and a lower part. The airfoil mean camber line equation is as follows:
in the equation, x is the abscissa in the mean arc coordinate system, and y is the ordinate in the mean arc coordinate system.
FIG. 3 is a NACA0008 airfoil derived by the Profile airfoil design software, which is added to the original blade camber line to create an airfoil blade. The profile derived profile default leading edge is at point (0,0) and the trailing edge is at point (100, 0). And carrying out nonlinear fitting on the upper wing surface of the wing profile by adopting a least square method to obtain a thickness distribution equation of the wing profile, wherein the equation is as follows:
x in the equationaIs the abscissa, y, in the airfoil coordinate systemaIs the ordinate in the airfoil coordinate system.
The slope of each point on the camber line of the airfoil can be obtained by deriving the equation of the camber line of the airfoil, the slope represents the tangential direction of each point on the camber line of the airfoil, and the derivative equation is as follows:
the product of the slopes of the two mutually perpendicular oblique lines is-1, so that the slope of the oblique line perpendicular to the tangential direction at each point on the camber line of the airfoil profile can be obtained, and then the corresponding angle theta is obtained by a trigonometric function relation. Referring to FIG. 4, the coordinates of points on the pressure surface and the suction surface of the airfoil blade can be calculated from the obtained angle θ according to the following equations. X in the equationuIs the upper airfoil abscissa, y, in the mean camber line coordinate systemuIs the upper airfoil surface ordinate in the mean camber line coordinate system; x is the number ofdIs the lower airfoil abscissa, y, in the mean camber line coordinate systemdIs the lower airfoil longitudinal coordinate in the mean camber line coordinate system.
And (4) storing the coordinates of the points, and importing the coordinates into three-dimensional drawing software, such as SolidWorks, so that a single airfoil blade can be generated. As shown in fig. 5. The airfoil impeller model can be obtained by circumferentially arraying the single airfoil blades along the rotation center of the impeller, as shown in fig. 6.
In this embodiment, after the camber line of the original blade is determined, as long as the thickness distribution of the airfoil is known, the airfoil can be quickly added to the camber line of the original blade, so as to obtain the two-dimensional profile of the airfoil blade. The thickness distribution of the airfoil profile can be conveniently obtained by airfoil design software. The method has the advantages that the wing profiles are directly added to the camber lines of the original blades, the inlet and outlet installation angles of the original blades are reserved, meanwhile, different wing profiles are added conveniently, and the design efficiency and accuracy of the wing profile blades are improved.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (4)
1. A method for quickly designing an airfoil-shaped blade impeller of a multi-blade centrifugal fan is characterized by comprising the following steps of:
determining an airfoil mean camber line equation for the airfoil blade: selecting a mean camber line of an original blade as a mean camber line of the airfoil, keeping the placing position of the mean camber line of the airfoil consistent with that of an actual impeller, and fitting to obtain a mean camber line equation of the airfoil;
determining a thickness distribution equation of the selected airfoil profile:
determining an included angle theta between each oblique line perpendicular to the tangential direction and each abscissa of each point on the mean camber line of the airfoil profile;
obtaining a scaling coefficient according to the relation between the arc length of the camber line of the original blade and the length of the selected camber line of the airfoil; determining the airfoil thickness corresponding to each point on the camber line of the airfoil according to the scaling relationship and the thickness distribution equation from the front edge to the tail edge of the airfoil blade;
calculating the coordinates of the upper airfoil surface and the lower airfoil surface of the airfoil blade according to the thickness and the included angle theta of each point on the obtained camber line of the airfoil, and connecting the coordinates to obtain the airfoil blade;
and obtaining an airfoil impeller model by using a single airfoil blade along the circumferential array of the rotation center of the impeller.
2. The method for rapidly designing the airfoil blade impeller of the multi-blade centrifugal fan as claimed in claim 1, wherein the determination method of the airfoil mean camber line equation is as follows: and taking a plurality of points on the airfoil mean camber line to obtain coordinates of the points, and carrying out nonlinear curve fitting on the mean camber line by using a least square method according to the coordinates of the points to obtain an airfoil mean camber line equation.
3. The method for rapidly designing the airfoil blade impeller of the multi-airfoil centrifugal fan according to claim 1, wherein the method for determining the thickness distribution equation of the airfoil is as follows: and determining the relation between the upper wing surface and the lower wing surface of the airfoil blade and the camber line of the airfoil, and performing nonlinear curve fitting on the relation by using a least square method to obtain a thickness distribution equation of the airfoil.
4. The method for rapidly designing the airfoil blade impeller of the multi-blade centrifugal fan as claimed in claim 1, wherein the method for determining the included angle θ between the oblique line perpendicular to the tangential direction and the abscissa of each point on the camber line of the airfoil is as follows: and (3) deriving an equation of the camber line of the wing profile to obtain the tangential direction of each point on the camber line of the wing profile, calculating the slope of a slash perpendicular to the tangential direction of each point on the camber line of the wing profile, and then solving the included angle theta between the slash and a horizontal coordinate by a trigonometric function relation.
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106640757A (en) * | 2016-11-24 | 2017-05-10 | 西安交通大学 | Multi-blades centrifugal fan and group design method thereof |
| CN111120401A (en) * | 2020-01-07 | 2020-05-08 | 中国计量大学 | Multi-wing centrifugal ventilator blade design method based on NACA wing profile |
| CN113309736A (en) * | 2021-07-09 | 2021-08-27 | 杭州老板电器股份有限公司 | Blade, impeller, centrifugal fan, range hood and blade design method |
| JP2021139316A (en) * | 2020-03-03 | 2021-09-16 | 株式会社酉島製作所 | Blade design method of turbo machine |
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- 2022-02-14 CN CN202210133596.7A patent/CN114491868B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106640757A (en) * | 2016-11-24 | 2017-05-10 | 西安交通大学 | Multi-blades centrifugal fan and group design method thereof |
| CN111120401A (en) * | 2020-01-07 | 2020-05-08 | 中国计量大学 | Multi-wing centrifugal ventilator blade design method based on NACA wing profile |
| JP2021139316A (en) * | 2020-03-03 | 2021-09-16 | 株式会社酉島製作所 | Blade design method of turbo machine |
| CN113309736A (en) * | 2021-07-09 | 2021-08-27 | 杭州老板电器股份有限公司 | Blade, impeller, centrifugal fan, range hood and blade design method |
Non-Patent Citations (2)
| Title |
|---|
| 梁之博;季俊生;黎本锋;刘晓燕;: "翼型蜗舌技术在多翼离心风机中的应用", 电器, no. 1 * |
| 艾子健;秦国良;陈雪飞;林静祥;: "翼型叶片精确参数化建模的研究及应用", 流体机械, no. 08 * |
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