CN114491868B - Quick design method for airfoil blade impeller of multi-wing centrifugal fan - Google Patents
Quick design method for airfoil blade impeller of multi-wing centrifugal fan Download PDFInfo
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- CN114491868B CN114491868B CN202210133596.7A CN202210133596A CN114491868B CN 114491868 B CN114491868 B CN 114491868B CN 202210133596 A CN202210133596 A CN 202210133596A CN 114491868 B CN114491868 B CN 114491868B
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- G—PHYSICS
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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
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Abstract
The invention discloses a rapid design method of a multi-wing centrifugal fan wing blade impeller, and belongs to the technical field of household appliances. The method includes determining an airfoil mean camber line equation: selecting a camber line of an original blade as a camber line of an airfoil, and obtaining a camber line equation of the airfoil; determining the thickness distribution equation of the airfoil: determining an included angle theta between oblique lines and horizontal coordinates of each point on the mean camber line of the airfoil profile, wherein the oblique lines are perpendicular to the tangential direction; determining a scaling factor; determining the thickness of the wing profile corresponding to each point on the camber line of the wing profile; according to the thickness and the included angle theta of each point on the camber line of the airfoil, the coordinates of the upper airfoil surface and the lower airfoil surface of the airfoil blade are calculated, and the coordinates are connected to obtain the airfoil blade; the airfoil impeller model is obtained by a circumferential array of individual airfoil blades along the center of rotation of the impeller. According to the design method, different wing profiles are directly added on the camber line of the original blade, so that the inlet and outlet mounting angles of the original blade are reserved, the impeller can be directly generated, and the design efficiency and accuracy of the wing profile blade impeller are improved.
Description
Technical Field
The invention relates to the technical field of household appliances, in particular to a rapid design method for a multi-wing centrifugal fan wing 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 also 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 aerodynamic performance and noise.
The blades of the multi-wing centrifugal fan are usually single-arc or double-arc equal-thickness blades, and have the problems of large impact of blade inlets and serious flow separation of flow channels among the blades. In recent years, the application of bionic airfoils or aviation airfoils in the design of multi-airfoil centrifugal fan blades has become more and more popular by utilizing the characteristics of good airfoil splitting effect, low impact loss, difficult flow separation and the like.
At present, the common method for designing the wing profile comprises manual modeling and computer software modeling, wherein the manual modeling method is adopted, if too few points are taken, the wing profile blade cannot be in smooth transition and is far from the original wing profile, and if more points are taken, a great deal of time is consumed and errors are very easy to occur due to manual modeling, so that the design efficiency is too low; compared with manual modeling, the method of modeling by means of computer software is more efficient, but at present, the existing method of modeling by means of computer software is to design airfoil blades firstly, then assemble the blades in the impeller according to the designed inlet and outlet mounting angles, and the design of the impeller can not be completed while generating the airfoil blades.
Disclosure of Invention
The invention aims to overcome the problems in the prior art and provides a rapid design method for a multi-wing centrifugal fan wing blade impeller.
The invention provides a rapid design method of a multi-wing centrifugal fan wing blade impeller, which comprises the following steps:
determining an airfoil camber line equation for an airfoil blade: selecting a camber line of an original blade as a camber line of an airfoil, keeping the placing position of the camber line of the airfoil consistent with that of an actual impeller, and fitting to obtain a camber line equation of the airfoil;
determining a thickness distribution equation of the selected airfoil:
determining an included angle theta between oblique lines and horizontal coordinates of each point on the mean camber line of the airfoil profile, wherein the oblique lines are perpendicular to the tangential direction;
obtaining a scaling factor according to the length relation between the camber line arc length of the original blade and the camber line of the selected airfoil; determining the thickness of the airfoil corresponding to each point on the camber line of the airfoil from the leading edge to the trailing edge of the airfoil according to the scaling relation and the thickness distribution equation;
according to the thickness and the included angle theta of each point on the camber line of the airfoil, the coordinates of the upper airfoil surface and the lower airfoil surface of the airfoil blade are calculated, and the coordinates are connected to obtain the airfoil blade;
the airfoil impeller model is obtained by a circumferential array of individual airfoil blades along the center of rotation of the impeller.
Preferably, the method for determining the camber line equation of the airfoil is specifically 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 specifically as follows: and determining the relation between the upper airfoil surface and the lower airfoil surface of the airfoil blade and the camber line of the airfoil, and performing nonlinear curve fitting on the upper airfoil surface and the lower airfoil surface of the airfoil blade by using a least square method to obtain a thickness distribution equation of the airfoil.
Preferably, the method for determining the included angle theta between the oblique line and the abscissa of each point on the mean camber line of the airfoil is specifically as follows: and deriving an airfoil mean camber line equation to obtain the tangential direction of each point on the airfoil mean camber line, calculating the slope of the inclined line of each point on the airfoil mean camber line perpendicular to the tangential direction, and then solving the included angle theta between the inclined line and the abscissa by a trigonometric function relation.
Compared with the prior art, the invention has the beneficial effects that:
the rapid design method of the airfoil blade impeller of the multi-airfoil centrifugal fan directly adds different airfoils on the camber line of the original blade, reserves the inlet and outlet mounting angles of the original blade, can directly generate the impeller, avoids the trouble of determining the mounting angles of the airfoil blades on the impeller again after the design of the airfoil blades is completed, and improves the design efficiency and accuracy of the airfoil blade impeller.
According to the rapid design method of the airfoil blade impeller of the multi-airfoil centrifugal fan, the camber line of the original blade can be any curve, the added airfoil can be any airfoil, and the two airfoils of the airfoil can be designed independently, so that the rapid design method is suitable for rapid design of airfoil blade impellers of various airfoils, and the design efficiency of the airfoil blade impeller is improved.
Drawings
Fig. 1 is a schematic diagram of a design flow provided in an embodiment of the disclosure.
FIG. 2 is an illustration of an original blade camber line provided by an embodiment of the present disclosure.
FIG. 3 is a schematic illustration of an NACA0008 airfoil employed in embodiments of the present disclosure.
FIG. 4 is a schematic illustration of coordinate point calculations for upper and lower airfoils in accordance with an embodiment of the present disclosure.
FIG. 5 is a schematic view of an airfoil blade provided by an embodiment of the present disclosure.
Fig. 6 is a schematic view of an airfoil vane wheel provided by an embodiment of the present disclosure.
Detailed Description
Specific embodiments of the present invention will be described in detail below with reference to fig. 1-6, but it should be understood that the scope of the invention is not limited by the specific embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The invention provides a rapid design method of a multi-wing centrifugal fan wing blade impeller, which comprises the following steps:
determining an airfoil camber line equation for an airfoil blade: selecting a camber line of an original blade as a camber line of an airfoil, keeping the placing position of the camber line of the airfoil consistent with that of an actual impeller, and fitting to obtain a camber line equation of the airfoil;
determining a thickness distribution equation of the selected airfoil:
determining an included angle theta between oblique lines and horizontal coordinates of each point on the mean camber line of the airfoil profile, wherein the oblique lines are perpendicular to the tangential direction;
obtaining a scaling factor according to the length relation between the camber line arc length of the original blade and the camber line of the selected airfoil; determining the thickness of the airfoil corresponding to each point on the camber line of the airfoil from the leading edge to the trailing edge of the airfoil according to the scaling relation and the thickness distribution equation;
according to the thickness and the included angle theta of each point on the camber line of the airfoil, the coordinates of the upper airfoil surface and the lower airfoil surface of the airfoil blade are calculated, and the coordinates are connected to obtain the airfoil blade;
the airfoil impeller model is obtained by a circumferential array of individual airfoil blades along the center of rotation of the impeller.
Further, the method for determining the camber line equation of the airfoil is specifically 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 specifically as follows: and determining the relation between the upper airfoil surface and the lower airfoil surface of the airfoil blade and the camber line of the airfoil, and performing nonlinear curve fitting on the upper airfoil surface and the lower airfoil surface of the airfoil blade by using a least square method to obtain a thickness distribution equation of the airfoil.
Further, the method for determining the included angle theta between the oblique line and the abscissa of each point on the mean camber line of the airfoil is specifically as follows: and deriving an airfoil mean camber line equation to obtain the tangential direction of each point on the airfoil mean camber line, calculating the slope of the inclined line of each point on the airfoil mean camber line perpendicular to the tangential direction, and then solving the included angle theta between the inclined line and the abscissa by a trigonometric function relation.
Fig. 1 is a flow chart of a rapid design method for a multi-wing centrifugal fan airfoil blade according to the present embodiment.
FIG. 2 shows the camber line of an original blade, wherein the original blade is a non-airfoil blade used for an impeller, and the placement position of the camber line of the original blade is consistent with that of an actual impeller. And selecting a camber line of the original blade as a camber line of the airfoil, and taking a point on the camber line of the airfoil to obtain the coordinates of the point. And obtaining an airfoil mean camber line equation by least square fitting according to the coordinates of the points, wherein the equation form selects a polynomial in the embodiment. In order to improve fitting accuracy, the mean camber line of the airfoil is divided into an upper part and a lower part. The airfoil camber line equation is as follows:
in the equation, x is the abscissa in the mean camber line coordinate system, and y is the ordinate in the mean camber line coordinate system.
FIG. 3 is a profile airfoil design software derived NACA0008 airfoil that was added to the original blade camber line to produce an airfoil blade. The airfoil derived from Profili defaults with leading edge at point (0, 0) and trailing edge at point (100, 0). And (3) performing nonlinear fitting on the upper airfoil surface of the airfoil by adopting a least square method to obtain a thickness distribution equation of the airfoil, wherein the equation is as follows:
x in the equation a Is the abscissa in the airfoil coordinate system, y a Is the ordinate in the airfoil coordinate system.
Deriving an airfoil mean camber line equation to obtain the slope of each point on the airfoil mean camber line, wherein the slope represents the tangential direction of each point on the airfoil mean camber line, and the derivative equation is as follows:
the slope product between two mutually perpendicular oblique lines is-1, so that the slope of the oblique line perpendicular to the tangential direction of each point on the middle arc line of the wing profile can be obtained, and then the corresponding angle theta is obtained by a trigonometric function relation. As shown in FIG. 4, coordinates of points on the pressure and suction sides of an airfoil blade may be calculated from the following equation based on the resulting angle θ. X in the equation u Is the abscissa of the upper airfoil in the mean camber line coordinate system, y u Is the ordinate of the upper airfoil in the mean camber line coordinate system; x is x d Is the abscissa of the lower airfoil in the mean camber line coordinate system, y d Is the ordinate of the lower airfoil in the mean camber line coordinate system.
The coordinates of the points are saved and imported into three-dimensional drawing software, such as SolidWorks, to generate a single airfoil blade. As shown in fig. 5. An airfoil impeller model is obtained by arranging individual airfoil blades circumferentially about the center of rotation of the impeller, as shown in fig. 6.
In this embodiment, after determining the camber line of the original blade, 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 to obtain the two-dimensional profile of the airfoil blade. The thickness profile of the airfoil may be conveniently obtained by airfoil design software. The method has the advantages that the wing profile is directly added on the camber line of the original blade, the inlet and outlet mounting angles of the original blade are reserved, meanwhile, the addition of different wing profiles is facilitated, and the design efficiency and accuracy of the wing profile blade are improved.
Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein 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 rapid design method for a multi-wing centrifugal fan wing blade impeller is characterized by comprising the following steps:
determining an airfoil camber line equation for an airfoil blade: selecting a camber line of an original blade as a camber line of an airfoil, keeping the placing position of the camber line of the airfoil consistent with that of an actual impeller, and fitting to obtain a camber line equation of the airfoil;
the original blades are non-airfoil blades used for the impeller, and the placement position of camber lines of the original blades is consistent with that of an actual impeller; selecting a camber line of an original blade as a camber line of an airfoil, and taking a point on the camber line of the airfoil to obtain a coordinate of the point; fitting the coordinates of the points by a least square method to obtain an airfoil mean camber line equation, and selecting a polynomial in the equation form; in order to improve fitting accuracy, the airfoil mean camber line is divided into an upper part and a lower part; the airfoil camber line equation is as follows:
in the equation, x is the abscissa in the mean camber line coordinate system, and y is the ordinate in the mean camber line coordinate system;
determining a thickness distribution equation of the selected airfoil:
leading out NACA0008 airfoil through profile airfoil design software, and adding the airfoil to an camber line of an original blade to generate an airfoil blade; the airfoil derived from Profili defaults with leading edge at point (0, 0) and trailing edge at point (100, 0); and (3) performing nonlinear fitting on the upper airfoil surface of the airfoil by adopting a least square method to obtain a thickness distribution equation of the airfoil, wherein the equation is as follows:
y a ＝1.72e -5 x a 3 +0.20x a +1.09 0＜x a ＜100
x in the equation a Is the abscissa in the airfoil coordinate system, y a Is the ordinate in the airfoil coordinate system;
determining an included angle theta between oblique lines and horizontal coordinates of each point on the mean camber line of the airfoil profile, wherein the oblique lines are perpendicular to the tangential direction;
obtaining a scaling factor according to the length relation between the camber line arc length of the original blade and the camber line of the selected airfoil; determining the thickness of the airfoil corresponding to each point on the camber line of the airfoil from the leading edge to the trailing edge of the airfoil according to the scaling relation and the thickness distribution equation;
according to the thickness and the included angle theta of each point on the camber line of the airfoil, the coordinates of the upper airfoil surface and the lower airfoil surface of the airfoil blade are calculated, and the coordinates are connected to obtain the airfoil blade;
the airfoil impeller model is obtained by a circumferential array of individual airfoil blades along the center of rotation of the impeller.
2. The rapid design method for airfoil blade impeller of multi-wing centrifugal fan according to claim 1, wherein the determination method of the airfoil camber line equation is specifically 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 rapid design method for airfoil blade impeller of multi-wing centrifugal fan according to claim 1, wherein the determination method of thickness distribution equation of the airfoil is specifically as follows: and determining the relation between the upper airfoil surface and the lower airfoil surface of the airfoil blade and the camber line of the airfoil, and performing nonlinear curve fitting on the upper airfoil surface and the lower airfoil surface of the airfoil blade by using a least square method to obtain a thickness distribution equation of the airfoil.
4. The method for quickly designing the airfoil vane wheel of the multi-wing centrifugal fan according to claim 1, wherein the method for determining the included angle theta between the oblique line and the horizontal coordinate of each point on the camber line of the airfoil, which is perpendicular to the tangential direction, is specifically as follows: and deriving an airfoil mean camber line equation to obtain the tangential direction of each point on the airfoil mean camber line, calculating the slope of the inclined line of each point on the airfoil mean camber line perpendicular to the tangential direction, and then solving the included angle theta between the inclined line and the abscissa by a trigonometric function relation.
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| 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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