CN-115962147-B - Impeller design method and device, and storage medium

CN115962147BCN 115962147 BCN115962147 BCN 115962147BCN-115962147-B

Abstract

The disclosure provides an impeller design method and device and a storage medium, and relates to the field of mechanical equipment design. The impeller design method comprises the steps of determining an impeller runner of an axial flow pump and two-dimensional airfoil initial parameters matched with the impeller runner according to an axial flow pump design target, generating a two-dimensional blade bone line by utilizing the two-dimensional airfoil initial parameters and a blade inlet and outlet speed triangle, adding a first control point between a blade root of a blade inlet side and a blade tip of the blade inlet side to determine the shape of the blade inlet side, adding a second control point between the blade root of a blade outlet side and the blade tip of the blade outlet side to determine the shape of the blade outlet side, superposing thickness distribution information of the blade on the blade bone line to obtain two-dimensional molded lines of all sections of the blade, and carrying out coordinate conversion on the two-dimensional molded lines of all sections of the blade to obtain three-dimensional blade coordinates of all sections of the blade, so as to obtain a three-dimensional model of the blade.

Inventors

HUANG JIANHUA
ZHOU KANG
ZHAO BIN

Assignees

江苏徐工工程机械研究院有限公司

Dates

Publication Date: 20260505
Application Date: 20220809

Claims (15)

1. An impeller design method performed by an impeller design apparatus, comprising: determining an impeller flow channel of the axial flow pump and two-dimensional airfoil initial parameters matched with the impeller flow channel according to an axial flow pump design target; generating a two-dimensional blade bone line by using the two-dimensional airfoil initial parameters and the blade inlet and outlet speed triangle; Adding a first control point between a blade root of a blade inlet side and a blade tip of the blade inlet side to determine the shape of the blade inlet side, and adding a second control point between a blade root of a blade outlet side and a blade tip of the blade outlet side to determine the shape of the blade outlet side; Superposing the thickness distribution information of the blade on a blade bone line to obtain two-dimensional molded lines of all sections of the blade; converting coordinates of two-dimensional molded lines of each section of the blade to obtain three-dimensional blade coordinates of each section of the blade, thereby obtaining a three-dimensional model of the blade; Wherein adding a first control point between a blade root of a blade inlet edge and a blade tip of the blade inlet edge to determine a shape of the blade inlet edge comprises: According to the blade tip control point of the blade inlet edge , , ) Blade root control point of the inlet edge of the blade , , ) And the first control point , , ) Constructing a corresponding first parabola, wherein parameters of the first control point Satisfy the following requirements ; The shape of the inlet edge of the blade is determined using the first parabola.
2. The method of claim 1, wherein generating a two-dimensional blade bone line using the two-dimensional airfoil initial parameter and a blade exit velocity triangle comprises: according to the two-dimensional airfoil initial parameters determining the blade and diameter as On the cross section intersection line of (2) Coordinates of individual points Coordinates in a three-dimensional cylindrical coordinate system, wherein the diameter is Is the section from the hub to the rim The cross-section of the steel plate is the same as the cross-section of the steel plate, , Is the total number of sections from the hub to the rim; Generating a first tangent to an initial two-dimensional airfoil bone line included in the two-dimensional airfoil initial parameter at an entry point of the blade, and generating a second tangent to the initial two-dimensional airfoil bone line at an exit point of the blade; selecting a first intermediate control point on the first tangent line Selecting a second intermediate control point on the second tangent line ; Using the first intermediate control point, the second intermediate control point, the first end point of the blade And a second end point Constructing a first control point matrix of the initial two-dimensional airfoil bone line; And constructing a two-dimensional blade bone line by using a preset curve according to the first control point matrix of the two-dimensional airfoil bone line.
3. The method of claim 2, wherein, The blade has a diameter of On the cross section intersection line of (2) Coordinates of individual points The coordinates in the three-dimensional cylindrical coordinate system are: Wherein, the For the initial two-dimensional airfoil bone line coordinates, For the coordinates of the start point of the blade, For the angle of the blade inlet origin in the three-dimensional cylindrical coordinate system, Is the first The radial distance of the points from each other, Is the first The angle of the individual points in the three-dimensional cylindrical coordinate system, And placing an angle for the blade.
4. The method of claim 2, wherein, The angle of the first tangent line is The angle of the second tangent is ; The first intermediate control point and the second intermediate control point satisfy:
5. the method of claim 4, wherein, The first control point matrix is: 。
6. the method of claim 2, further comprising: A preset number is arranged between the first intermediate control point and the second intermediate control point Third intermediate control point Wherein And (2) and ; Constructing a second control point matrix of the initial two-dimensional airfoil bone line by using the first intermediate control point, the second intermediate control point, the first end point and the second end point of the blade and the preset number of third intermediate control points; and constructing a two-dimensional blade bone line by using a preset curve according to the second control point matrix of the two-dimensional airfoil bone line.
7. The method of claim 6, wherein, The second control point matrix is: 。
8. The method of claim 2, wherein, The preset curve is a Bezier curve.
9. The method of claim 1, wherein, The first parabola is as follows: Wherein, the - 。
10. The method of claim 1, wherein adding a second control point between a blade root of a blade exit edge and a blade tip of the blade exit edge to determine a shape of the blade exit edge comprises: According to the blade tip control point of said blade outlet edge , , ) Blade root control point of said blade outlet edge , , ) And the second control point # , , ) Constructing a corresponding second parabola; the shape of the exit edge of the blade is determined using the second parabola.
11. The method of claim 10, wherein, Parameters of the second control point The method meets the following conditions: 。
12. the method of claim 11, wherein, The second parabola is as follows: Wherein, the - 。
13. An impeller design apparatus comprising: A first processing module configured to determine an impeller flow path of an axial flow pump and two-dimensional airfoil initial parameters matching the impeller flow path according to an axial flow pump design objective; The second processing module is configured to generate a two-dimensional blade bone line by using the two-dimensional airfoil initial parameters and the blade inlet and outlet speed triangle; A third processing module configured to add a first control point between a blade root of a blade inlet side and a blade tip of the blade inlet side to determine a shape of the blade inlet side, and add a second control point between a blade root of a blade outlet side and a blade tip of the blade outlet side to determine a shape of the blade outlet side, wherein the first control point is based on the blade tip control point of the blade inlet side , , ) Blade root control point of the inlet edge of the blade , , ) And the first control point , , ) Constructing a corresponding first parabola, wherein parameters of the first control point Satisfy the following requirements Determining the shape of the inlet edge of the blade using the first parabola; A fourth processing module configured to superimpose thickness distribution information of the blade on a blade skeleton line to obtain a two-dimensional molded line of each section of the blade; And the fifth processing module is configured to perform coordinate transformation on the two-dimensional molded lines of each section of the blade to obtain three-dimensional blade coordinates of each section of the blade, so as to obtain a three-dimensional model of the blade.
14. An impeller design apparatus comprising: A memory configured to store instructions; A processor coupled to the memory, the processor configured to perform the method of any of claims 1-12 based on instructions stored by the memory.
15. A non-transitory computer readable storage medium storing computer instructions which, when executed by a processor, implement the method of any one of claims 1-12.

Description

Impeller design method and device, and storage medium Technical Field The disclosure relates to the field of mechanical equipment design, and in particular relates to an impeller design method and device and a storage medium. Background The axial flow pump has the characteristics of large flow, energy conservation, high efficiency, relatively low lift and the like, and is widely applied to the fields of municipal water supply and drainage, agricultural irrigation, water regulation engineering and the like. The axial flow pump impeller is a core overcurrent component which influences the performance of the axial flow pump, and the design of the axial flow pump impeller directly determines the performance of the axial flow pump. For the design of axial flow pump impeller, because the design is limited by the defect of space bending and twisting impeller geometric expression capability, the fixed airfoil is mainly adopted to design the blades at present. For example, in the design method of the axial flow pump impeller based on the Confucius wing profile, the axial flow pump impeller is designed by utilizing the parameters of the blade grid density, the axial surface speed, the rotation component speed, the chord laying angle, the wing profile camber and the thickness. Disclosure of Invention The inventors have noted that in the related art, the blades are designed using a fixed airfoil, and then mounted to the impeller flow passage at a mounting angle. The method only carries out quantitative analysis on part of design parameters, so that the geometric diversity of the blades is insufficient, and an optimal scheme is difficult to obtain when the axial flow pump impeller is optimally designed. Accordingly, the present disclosure provides an impeller design scheme, in which the blade shape design is directly performed according to the control point of the blade shape, so that an optimal scheme is obtained when the axial flow pump impeller is optimally designed. According to a first aspect of the embodiment of the present disclosure, an impeller design method is provided, which is executed by an impeller design device, and includes determining an impeller runner of an axial flow pump and a two-dimensional airfoil initial parameter matched with the impeller runner according to an axial flow pump design target, generating a two-dimensional blade skeleton line by using the two-dimensional airfoil initial parameter and a blade inlet and outlet speed triangle, adding a first control point between a blade root of a blade inlet side and a blade tip of the blade inlet side to determine a shape of the blade inlet side, adding a second control point between a blade root of a blade outlet side and a blade tip of the blade outlet side to determine a shape of the blade outlet side, superposing thickness distribution information of the blade on the blade skeleton line to obtain a two-dimensional molded line of each section of the blade, and performing coordinate conversion on the two-dimensional molded line of each section of the blade to obtain three-dimensional blade coordinates of each section of the blade, thereby obtaining a three-dimensional model of the blade. In some embodiments, generating a two-dimensional blade bone line by using the two-dimensional airfoil initial parameters and a blade inlet and outlet speed triangle comprises determining coordinates of a coordinate Pi of an ith point on an intersection line of the blade and a cross section with a diameter of D j in a three-dimensional cylindrical coordinate system according to the two-dimensional airfoil initial parameters, wherein the cross section with the diameter of D j is a jth cross section from a hub to a rim, 1≤j≤n, n is a total number of cross sections from the hub to the rim, generating a first tangent line of an initial two-dimensional airfoil bone line included in the two-dimensional airfoil initial parameters at an inlet point of the blade, generating a second tangent line of the initial two-dimensional airfoil bone line at an outlet point of the blade, selecting a first intermediate control point P1' (θ ' 1, m1 ') on the first tangent line, selecting a second intermediate control point P2 θ ' 2, m2 ') on the second tangent line, and constructing a two-dimensional airfoil bone line according to the two-dimensional airfoil bone line by using the first intermediate control point, the second intermediate control point, the first endpoint P1' (θ 25, m 1) and the second endpoint P2' (θ 2) of the blade. In some embodiments, the coordinates Pi of the ith point on the intersection of the blade and the cross-section of diameter D j in the three-dimensional cylindrical coordinate system are: Pi=(Ri,(lx-x0)*sinβLi+(ly-y0)*cosβLi,θi+θ0) Wherein, (lx, ly) is an initial two-dimensional airfoil bone line coordinate, (x 0, y 0) is a blade start point coordinate, θ 0 is an angle of a blade inlet start point under a three-dimensional cylindrical coordinate system, R