CN114048567A - Vane intersecting line of impeller machine, design method of vane, and vane of impeller machine - Google Patents

Vane intersecting line of impeller machine, design method of vane, and vane of impeller machine Download PDF

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CN114048567A
CN114048567A CN202111351330.1A CN202111351330A CN114048567A CN 114048567 A CN114048567 A CN 114048567A CN 202111351330 A CN202111351330 A CN 202111351330A CN 114048567 A CN114048567 A CN 114048567A
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blade
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outer ring
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周康
黄建华
宋高垒
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Jiangsu XCMG Construction Machinery Institute Co Ltd
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Jiangsu XCMG Construction Machinery Institute Co Ltd
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Abstract

The invention discloses a design method of a blade intersecting line of impeller machinery, which comprises the steps of determining a two-dimensional blade outer ring molded line of a blade according to a two-dimensional blade outer ring skeleton line, and determining the intersecting line of the blade and an outer ring according to the blade outer ring molded line and inner surface parameters of the outer ring; calculating a three-dimensional blade outer ring skeleton line corresponding to the two-dimensional blade outer ring skeleton line on the inner surface of the outer ring according to the two-dimensional blade outer ring skeleton line and the inner surface parameters of the outer ring; determining a projection vector according to the three-dimensional blade outer ring skeleton line, determining a projection plane according to the projection vector, and projecting the three-dimensional blade outer ring skeleton line on the projection plane; a projection point set of the three-dimensional blade outer ring skeleton line on a projection plane is taken to determine a two-dimensional blade inner ring skeleton line; and determining a two-dimensional blade inner ring profile of the blade according to the determined two-dimensional blade inner ring skeleton line, and determining the intersection line of the blade and the inner ring according to the two-dimensional blade inner ring profile, the parameters of the projection surface and the outer surface parameters of the inner ring.

Description

Vane intersecting line of impeller machine, design method of vane, and vane of impeller machine
Technical Field
The invention relates to the field of impeller machinery, in particular to a blade intersecting line of the impeller machinery, a design method of the blade and the blade of the impeller machinery.
Background
Turbomachines are widely used in engineering applications, including fans, torque converters, water pumps, compressors, etc. The impeller machine generally comprises a blade cascade, an outer ring positioned on the outer side of the blade cascade and an inner ring positioned on the inner side of the blade cascade, wherein the blade cascade comprises a plurality of blades which are periodically arranged around a rotating shaft, the inner ring comprises a front disc and an outer ring comprises a rear disc, a channel formed by the blade cascade, the front disc and the rear disc forms a flow channel for fluid to flow, and the mutual conversion of mechanical energy and fluid kinetic energy is realized through the interaction of the blade cascade and fluid. The blades of the blade cascade are core components of the impeller machinery, and the performance of the impeller machinery is directly influenced by the quality of the design of the blades. The shape of the blade is greatly different according to different application occasions, and comprises a two-dimensional straight plate blade, a non-uniform thickness three-dimensional twisted blade and the like. The patent application with Chinese patent application number 201310028487.X provides an airfoil represented by an analytic function and a generation method thereof, wherein a single ring surface of the airfoil is represented by upper and lower profile analytic functions. The patent application of the Chinese patent application number 201710523249.4 discloses a multi-wing centrifugal fan blade, wherein the inlet end curve of the blade profile is a logarithmic spiral line, and the outlet end profile is an arc line. The Chinese patent application No. 201510036723.1 discloses a method for constructing a two-dimensional blade profile of a hydraulic torque converter based on a Bezier curve, and discloses that a two-dimensional blade profile of an inner ring of a pump impeller blade is constructed by using the Bezier curve through a given circle of the hydraulic torque converter, and then the two-dimensional blade profile is constructed by using the two-dimensional blade profile to construct the thickness distribution of the blade, so that the two-dimensional blade profile is obtained. The Chinese patent application No. 201510036723.1 discloses a method for constructing a two-dimensional blade profile of a hydraulic torque converter based on a Bezier curve, and discloses that a two-dimensional blade profile of an inner ring of a pump impeller blade is constructed by using the Bezier curve through a given circle of the hydraulic torque converter, and then the two-dimensional blade profile is constructed by using the two-dimensional blade profile to construct the thickness distribution of the blade, so that the two-dimensional blade profile is obtained. The Chinese patent application No. 201410220625.9 discloses a vane model of a hydraulic torque converter based on a Confucius-fusi type line, which discloses that a two-dimensional vane inner ring molded line and a two-dimensional vane outer ring molded line of a unit vane are constructed through the Confucius-fusi type line, then a three-dimensional vane inner ring curve and a three-dimensional vane outer ring curve are constructed according to parameters of a given circulation circle, and finally the vane model is formed.
Disclosure of Invention
The invention aims to provide a design method of a blade intersecting line of an impeller machine, which can be used for constructing a proper blade intersecting line of the impeller machine, thereby being beneficial to ensuring the adaptability, diversity, flexibility and good manufacturability of the blade.
The invention discloses a method for designing a blade intersecting line of impeller machinery, wherein the impeller machinery comprises an outer ring, an inner ring positioned on the inner side of the outer ring and blades connected between the outer surface of the inner ring and the inner surface of the outer ring, and the method for designing the blade intersecting line of the impeller machinery comprises the following steps:
giving two-dimensional blade outer ring bone line, inner surface parameters of the outer ring and outer surface parameters of the inner ring;
determining a two-dimensional blade outer ring molded line of the blade according to the two-dimensional blade outer ring skeleton line, and determining an intersecting line of the blade and the outer ring according to the two-dimensional blade outer ring molded line and the inner surface parameter of the outer ring;
calculating a three-dimensional blade outer ring skeleton line corresponding to the two-dimensional blade outer ring skeleton line on the inner surface of the outer ring according to the two-dimensional blade outer ring skeleton line and the inner surface parameters of the outer ring;
determining a projection vector according to the three-dimensional blade outer ring skeleton line, determining a projection plane according to the projection vector, and projecting the three-dimensional blade outer ring skeleton line on the projection plane;
a point set is taken from the projection of the three-dimensional blade outer ring skeleton line on the projection plane, a two-dimensional initial blade inner ring skeleton line is determined according to the taken point set, and the two-dimensional initial blade inner ring skeleton line is rotated and/or translated on the projection plane to obtain a two-dimensional blade inner ring skeleton line;
determining a two-dimensional blade inner ring molded line of the blade according to the determined two-dimensional blade inner ring skeleton line, and determining an intersection line of the blade and the inner ring according to the two-dimensional blade inner ring molded line, the parameters of the projection surface and the outer surface parameters of the inner ring.
In some embodiments, determining a projection vector from the three-dimensional outer blade ring skeleton line comprises:
determining an extreme point of the three-dimensional blade outer ring skeleton line, connecting a starting point and an end point of the three-dimensional blade outer ring skeleton line to obtain a first line segment, and drawing a first straight line which is perpendicular to the connecting line and intersects with the first point through the extreme point;
radius r is made through the extreme point in a plane perpendicular to the first line1A first circle of radius r passing through the first point in a plane perpendicular to the first line2Second circle of (1), wherein r1Less than r2And r is1And r2And the length of each line segment is less than half of the length of the first line segment, a second point is taken in the first circle, a third point is taken in the second circle, and a vector obtained by connecting the second point and the third point is determined as the projection vector.
In some embodiments, let the extreme point coordinate be (x)M，yM，zM) Let the coordinates of the first point be (x)H，yH，zH) Connecting the extreme point and the first point to obtain a first vector, and setting the space coordinate of the first vector as (V)x，Vy，Vz) Let the coordinates of the second point be (x)1，y1，z1) Let the coordinate of the third point be (x)2，y2，z2) Wherein:
Figure BDA0003354351460000031
Figure BDA0003354351460000032
y1∈(yM-r1，yM+r1)，x2∈(xH-r2，xH+r2)，y2∈(yH-r2，yH+r2)。
in some embodiments, determining a projection vector from the three-dimensional outer blade ring skeleton line comprises:
determining an extreme point of the three-dimensional blade outer ring skeleton line, connecting a starting point and an end point of the three-dimensional blade outer ring skeleton line to obtain a first line segment, and drawing a first straight line which is perpendicular to the connecting line and intersects with the first point through the extreme point;
and passing the extreme point to make a second straight line towards a deflection angle alpha on one side of the first straight line in a plane determined by the first straight line and the first line segment, and to make a third straight line towards a deflection angle beta on one side of the first straight line in a plane perpendicular to the plane determined by the first straight line and the first line segment, wherein the second straight line and the first line segment are intersected at a fourth point, the extreme point and the fourth point are connected to obtain a second vector, a third vector is obtained according to the third straight line, and the projection vector is equal to the vector sum of the second vector and the third vector.
In some embodiments, let a coordinate of a point of the two-dimensional initial blade inner ring skeleton line in a rectangular coordinate system on the projection plane be (x)0，y0) And the two-dimensional blade inner ring bone line obtained after rotation and/or translation comprises:
when the two-dimensional initial blade inner ring skeleton line is rotated by a rotation angle θ, the coordinates of the point of the two-dimensional blade inner ring skeleton line are (x, y), and the values of x and y are obtained by the following formula:
Figure BDA0003354351460000041
when the two-dimensional initial blade inner ring skeleton line is translated, (Δ x, Δ y) is the translation amount, the coordinates of the obtained two-dimensional blade inner ring skeleton line point are (x, y), and the values of x and y are obtained by the following formula: [ x ] of0，y0]+[Δx，Δy]；
When the two-dimensional initial blade inner ring skeleton line is rotated and translated again, the rotation angle is θ, and (Δ x, Δ y) is the translation amount, the coordinates of the obtained two-dimensional blade inner ring skeleton line point are (x, y), and the values of x and y are obtained by the following formula:
Figure BDA0003354351460000042
in some embodiments, the two-dimensional blade outer ring bone line is a bezier curve.
The invention discloses a method for designing a blade of an impeller machine in a second aspect, which comprises a method for designing a blade intersecting line of any impeller machine.
In some embodiments, further comprising: and sweeping the intersecting line of the blade and the inner ring and the intersecting line of the blade and the outer ring by using a straight line to obtain the blade of the impeller machine.
The third aspect of the invention discloses a blade of impeller machinery, which is designed by applying the design method of the blade of impeller machinery.
In some embodiments, the impeller machine blades comprise blades of an impeller of a torque converter, the outer ring comprises an impeller casing, and the inner ring comprises an impeller guide ring; or the blades of the impeller machine comprise blades of a turbine of a hydrodynamic torque converter, the outer ring comprises a turbine casing, and the inner ring comprises a turbine guide ring
According to the design method of the blade intersecting line of the impeller machine, the three-dimensional blade outer ring intersecting line is calculated by utilizing the two-dimensional blade outer ring intersecting line, then the two-dimensional initial blade inner ring intersecting line is determined by utilizing the projection after the three-dimensional blade outer ring intersecting line is projected by finding the proper projection vector, and the two-dimensional blade inner ring intersecting line is obtained after the two-dimensional initial blade inner ring intersecting line is rotated and/or translated on the projection plane.
Other features of the present invention and advantages thereof will become apparent from the following detailed description of exemplary embodiments thereof, which proceeds with reference to the accompanying drawings.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the invention without limiting the invention. In the drawings:
FIG. 1 is a flow chart of a method of designing a bucket intersection line of a turbomachinery of an embodiment of the present invention;
FIG. 2 is a schematic view of a portion of another embodiment of the present invention;
FIG. 3 is a schematic diagram of a projection vector determined by a method for designing a blade intersecting line of a turbo machine according to still another embodiment of the present invention;
FIG. 4 is a schematic diagram of a projection vector determined by a method for designing a blade intersecting line of a turbo machine according to still another embodiment of the present invention;
FIG. 5 is a schematic view of a three-dimensional blade outer ring skeleton line projected on a projection plane according to a method for designing a blade intersecting line of an impeller machine according to still another embodiment of the present invention;
FIG. 6 is a schematic view of a two-dimensional blade inner ring skeleton line obtained from a two-dimensional initial blade inner ring skeleton line according to a method for designing a blade intersection line of an impeller machine according to still another embodiment of the present invention;
FIG. 7 is a schematic view of a two-dimensional blade inner ring contour obtained from a two-dimensional blade inner ring contour according to a method for designing a blade intersecting line of an impeller machine according to still another embodiment of the present invention;
fig. 8 is a schematic view of the intersection line between the blade and the outer ring and the intersection line between the blade and the inner ring obtained by the method for designing the intersection line between the blade and the inner ring of the turbo machine according to the further embodiment of the present invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The relative arrangement of the components and steps, the numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any particular value should be construed as merely illustrative, and not limiting. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.
For ease of description, spatially relative terms, such as "over", "above", "on", "upper surface", "over", and the like, may be used herein to describe one element or feature's spatial relationship to another element or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if a device in the figures is turned over, devices described as "above" or "on" other devices or configurations would then be oriented "below" or "under" the other devices or configurations. Thus, the exemplary term "above" may include both an orientation of "above" and "below". The device may be otherwise variously oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
As shown in fig. 2, the impeller machinery includes an outer ring 1, an inner ring 5 located inside the outer ring 1, and blades connected between an outer surface of the inner ring 5 and an inner surface of the outer ring 1, the blades include a blade outer ring 2, a blade inner ring 6, a blade leading edge 4, and a blade trailing edge 8, the blade outer ring 2 is an outer surface of the blade located radially outside, that is, an intersecting surface of the blade and the outer ring 1, and an outer contour of the blade outer ring 2, that is, a intersecting line of the blade and the outer ring 1, as shown in fig. 8, is a first intersecting line 190. The vane inner ring 6 is the inner surface of the vane located at the radial inner side, namely the intersection surface of the vane and the inner ring 5, and the outer contour of the vane inner ring 6 is the intersection line of the vane and the inner ring 5, such as a second intersection line 120 shown in fig. 8.
The impeller machine of the embodiment comprises a fan, a hydraulic torque converter, a water pump, a gas compressor and the like. When the impeller machine is a torque converter, and when the blades shown in fig. 2 are impeller blades, the outer ring 1 is an impeller casing, the inner ring 5 is an impeller guide ring, and fluid enters from the inlet 3 on the side of the leading edge 4 of the blade, and flows out from the outlet 7 on the side of the trailing edge 8 of the blade into the turbine under the centrifugal action of the blades of the impeller. The direction Z shown in fig. 2 indicates the direction of the rotation axis of the pump wheel, and the direction R indicates the radial direction of the pump wheel.
The method for designing the blade intersecting line of the impeller machinery comprises the following steps:
the two-dimensional blade outer ring bone line, the inner surface parameter of the outer ring and the outer surface parameter of the inner ring are given.
The two-dimensional blade outer ring skeleton line can adopt an empirical skeleton line type according to the prior experience, and can also be constructed by a Bezier curve.
And determining a two-dimensional blade outer ring molded line of the blade according to the two-dimensional blade outer ring skeleton line, and determining an intersecting line of the blade and the outer ring 1 according to the blade outer ring molded line and the inner surface parameters of the outer ring 1.
The inner surface parameters of the outer ring 1 include parameter information such as the shape, angle, size distribution, etc. of the inner surface. After obtaining two-dimensional blade outer ring molded lines, mapping the two-dimensional blade outer ring molded lines to three dimensions according to inner surface parameters, so as to obtain intersecting lines of blades and an outer ring, wherein one embodiment can refer to the step of constructing a three-dimensional blade inner ring curve according to the inner ring molded lines of the blades in the patent application of chinese patent application No. 201410220625.9, another embodiment can further include projecting the two-dimensional blade outer ring molded lines as three-dimensional blade outer ring molded lines, and then performing inverse operation of projection on the two-dimensional blade outer ring molded lines according to the inner surface parameters to obtain three-dimensional blade outer ring molded lines, another embodiment can further include expanding the two-dimensional blade outer ring molded lines as three-dimensional blade outer ring molded lines when the inner surface of the outer ring is expanded into a plane, and reversely curling the plane where the two-dimensional blade outer ring molded lines are located into the inner surface of the outer ring according to the inner surface parameters, and obtaining the three-dimensional blade outer ring molded line by the two-dimensional blade outer ring molded line. During mapping, the relative position relationship between the plane where the two-dimensional outer ring molded line is located and the inner surface of the outer ring 1 can be obtained through empirical design.
After a two-dimensional blade outer ring skeleton line is obtained, a two-dimensional blade outer ring molded line can be obtained by constructing blade thickness distribution and superposing the thickness distribution on the two-dimensional blade outer ring skeleton line.
In this embodiment, reference may be made to an embodiment of constructing an inner ring profile of a vane of a pump impeller in chinese patent application No. 201510036723.1, reference may be made to method steps of constructing a unit vane profile in the embodiment of this patent application for constructing a two-dimensional vane outer ring profile of the present embodiment, reference may be made to method steps of constructing a vane thickness distribution and superimposing the thickness distribution on a vane profile in the embodiment of this patent application for determining a two-dimensional vane outer ring profile of a vane according to the two-dimensional vane outer ring profile, and obtaining a two-dimensional profile of the vane.
And calculating a three-dimensional blade outer ring skeleton line corresponding to the two-dimensional blade outer ring skeleton line on the inner surface of the outer ring according to the two-dimensional blade outer ring skeleton line and the inner surface parameters of the outer ring. The principle of the implementation mode of obtaining the three-dimensional blade outer ring skeleton line according to the two-dimensional blade outer ring skeleton line and the inner surface parameters of the outer ring 1 to determine the intersecting line of the blade and the outer ring 1 is the same as that of the implementation mode.
Determining a projection vector according to the three-dimensional blade outer ring skeleton line, determining a projection plane according to the projection vector, and projecting the three-dimensional blade outer ring skeleton line on the projection plane. And (3) taking a point set of the projection of the three-dimensional blade outer ring skeleton line on the projection plane, determining a two-dimensional initial blade inner ring skeleton line according to the taken point set, and rotating and/or translating the two-dimensional initial blade inner ring skeleton line on the projection plane to obtain the two-dimensional blade inner ring skeleton line.
As shown in fig. 3, 4 and 5, after the three-dimensional blade outer ring skeleton line is obtained, a suitable projection vector 92 and a projection plane 94 are determined for the three-dimensional blade outer ring skeleton line 91, so that a two-dimensional outer ring skeleton line projection 93 of the three-dimensional blade outer ring skeleton line 91 on the projection plane 94 can be obtained. Then, a set of points can be selected by using the projection to manufacture a two-dimensional initial blade inner ring skeleton line 11, and the two-dimensional initial blade inner ring skeleton line is rotated and/or translated on the projection surface to obtain the two-dimensional blade inner ring skeleton line. The angle of rotation may or may not be 0, and the amount of translation may or may not be 0. A part of the projection of the three-dimensional blade outer ring skeleton line on the projection plane can be directly used as a two-dimensional initial blade inner ring skeleton line, or a part of point set can be adopted in the projection, and then a curve is constructed by adopting an interpolation method to be used as the two-dimensional initial blade inner ring skeleton line.
In the embodiment shown in fig. 6, the rotation angle of the two-dimensional initial blade inner ring skeleton line is 0, and the translation amount of the translation is 0, so as to obtain a first two-dimensional blade inner ring skeleton line 11; the rotation angle of the two-dimensional initial blade inner ring skeleton line is not 0, and a second two-dimensional blade inner ring skeleton line 12 is obtained after the translation amount of the translation is 0; the rotation angle of the two-dimensional initial blade inner ring skeleton line is 0, and a third two-dimensional blade inner ring skeleton line 13 is obtained after the translation amount of the translation is not 0; the rotation angle of the two-dimensional initial blade inner ring skeleton line is not 0, and a fourth two-dimensional blade inner ring skeleton line 14 is obtained after the translation amount of the translation is not 0.
And determining a two-dimensional blade inner ring profile of the blade according to the determined two-dimensional blade inner ring skeleton line, and determining the intersection line of the blade and the inner ring according to the two-dimensional blade inner ring profile, the parameters of the projection surface and the outer surface parameters of the inner ring. The method for determining the two-dimensional blade inner ring profile of the blade according to the two-dimensional blade outer ring profile is similar to the method for determining the two-dimensional blade outer ring profile of the blade according to the two-dimensional blade inner ring profile, and the method for determining the intersection line of the blade and the inner ring according to the two-dimensional blade inner ring profile is similar to the method for determining the intersection line of the blade and the outer ring according to the blade outer ring profile.
As shown in fig. 7, when the two-dimensional blade inner ring skeleton line is the first two-dimensional blade inner ring skeleton line 11, the first two-dimensional blade inner ring molded line 21 is obtained; when the two-dimensional blade inner ring skeleton line is the second two-dimensional blade inner ring skeleton line 12, a second two-dimensional blade inner ring molded line 22 is obtained; when the two-dimensional blade inner ring skeleton line is a third two-dimensional blade inner ring skeleton line 13, a third two-dimensional blade inner ring molded line 23 is obtained; when the two-dimensional blade inner ring skeleton line is the fourth two-dimensional blade inner ring skeleton line 14, the fourth two-dimensional blade inner ring molded line 24 is obtained.
The two-dimensional blade outer ring skeleton line is used for calculating the three-dimensional blade outer ring skeleton line, then the two-dimensional initial blade inner ring skeleton line is determined by finding out a proper projection vector projection for the three-dimensional blade outer ring skeleton line, and the two-dimensional blade inner ring skeleton line is obtained after the two-dimensional initial blade inner ring skeleton line rotates and/or translates on a projection plane.
As shown in FIG. 3, in some embodiments, determining a projection vector from the three-dimensional blade outer ring skeleton line comprises:
determining an extreme point of a three-dimensional blade outer ring skeleton line, connecting a starting point and an end point of the three-dimensional blade outer ring skeleton line to obtain a first line segment, and making a first straight line which is perpendicular to the connecting line and intersects with the first point through the extreme point; for the embodiment shown in fig. 3, point M is AN extreme point, points a and N are the starting point and the ending point of the three-dimensional blade outer ring skeleton line, line segment AN is the first line segment, point H is the first point, and straight line MH is the first straight line.
The radius of the over-extreme point in a plane perpendicular to the first straight line is r1A first point in a plane perpendicular to the first straight line has a radius r2Second circle of (1), wherein r1Less than r2And r is1And r2And the length of the first line segment is less than half of the length of the first line segment, a second point is taken in the first circle, a third point is taken in the second circle, and a vector obtained by connecting the second point and the third point is determined as a projection vector. For the embodiment shown in fig. 3, the s1 circle is a first circle, the s2 circle is a second circle, the M 'point is a second point, the H' point is a third point, and the vector M 'H' is the resulting projection vector. The projection vector is vertical to the projection plane, and the projection plane can be obtained according to the projection vector. The projection vector obtained by the embodiment is beneficial to enabling the projection of the obtained three-dimensional blade outer ring skeleton line to better and more completely map the three-dimensional blade outer ring skeleton line, so that the obtained two-dimensional blade inner ring skeleton line can be better coordinated with the two-dimensional blade outer ring skeleton line, and a more suitable intersecting line of the blade and the inner ring is obtained.
As shown in FIG. 3, in some embodiments, let the extreme point coordinate be (x)M，yM，zM) Let the coordinate of the first point be (x)H，yH，zH) Connecting the extreme point and the first point to obtain a first vector, and setting the space coordinate of the first vector as (V)x，Vy，Vz) Let the coordinate of the second point be (x)1，y1，z1) Let the coordinate of the third point be (x)2，y2，z2) Wherein:
Figure BDA0003354351460000101
Figure BDA0003354351460000102
y1∈(yM-r1，yM+r1)，x2∈(xH-r2，xH+r2)，y2∈(yH-r2，yH+r2). The coordinates of the projection vector of the present embodiment are determined by the above equation.
As shown in FIG. 4, in some embodiments, determining a projection vector from the three-dimensional blade outer ring skeleton line comprises:
determining an extreme point of a three-dimensional blade outer ring skeleton line, connecting a starting point and an end point of the three-dimensional blade outer ring skeleton line to obtain a first line segment, and making a first straight line which is perpendicular to the connecting line and intersects with the first point through the extreme point; for the embodiment shown in fig. 4, point M is AN extreme point, points a and N are the starting point and the ending point of the three-dimensional blade outer ring skeleton line, line segment AN is the first line segment, point H is the first point, and straight line MH is the first straight line.
And the extreme point is crossed to a plane determined by the first straight line and the first line segment to form a second straight line towards a deflection angle alpha on one side of the first straight line, and a plane perpendicular to the plane determined by the first straight line and the first line segment (the plane is a first straight line) is crossed to a first straight line to form a third straight line towards a deflection angle beta on one side of the first straight line, the second straight line and the first line segment are crossed at a fourth point, the extreme point and the fourth point are connected to obtain a second vector, a third vector is obtained according to the third straight line, and the projection vector is equal to the vector sum of the second vector and the third vector. For the embodiment shown in fig. 4, point K is the fourth point, point J is the fifth point, vector MK is the second vector, vector MJ is the third vector, and the sum of vector MK and vector MJ is the projection vector.
In some embodiments, let the coordinate of the two-dimensional initial blade inner ring bone line point in the rectangular coordinate system on the projection plane be (x)0，y0) And the two-dimensional blade inner ring bone line obtained after rotation and/or translation comprises:
when the two-dimensional initial blade inner ring skeleton line is rotated by a rotation angle θ, the coordinates of the point of the two-dimensional blade inner ring skeleton line are (x, y), and the values of x and y are obtained by the following formula:
Figure BDA0003354351460000111
that is, the 1X 2 matrix result obtained by the expression corresponds to (x, y), x,And y respectively takes the numerical value in the matrix result.
When the two-dimensional initial blade inner ring skeleton line is translated, (Δ x, Δ y) is the translation amount, the coordinates of the obtained two-dimensional blade inner ring skeleton line point are (x, y), and the values of x and y are obtained by the following formula: [ x ] of0，y0]+[Δx，Δy]；
When the two-dimensional initial blade inner ring skeleton line is rotated and translated again, the rotation angle is θ, and (Δ x, Δ y) is the translation amount, the coordinates of the obtained two-dimensional blade inner ring skeleton line point are (x, y), and the values of x and y are obtained by the following formula:
Figure BDA0003354351460000112
in some embodiments, the two-dimensional blade outer ring bone line is a bezier curve.
In some embodiments, a method for designing a blade of an impeller machine, and a method for designing a blade intersecting line of the impeller machine are also disclosed.
In some embodiments, the method of designing a blade of an impeller machine further comprises: and sweeping the intersection line of the blade and the inner ring and the intersection line of the blade and the outer ring by using a straight line to obtain the blade of the impeller machine. The method comprises the following steps of dividing the intersecting line of a blade and an inner ring and the intersecting line of the blade and an outer ring into equal parts, and then connecting the corresponding points of the intersecting line of the blade and the inner ring and the intersecting line of the blade and the outer ring to obtain the outer contour of the blade.
In some embodiments, the blade of the impeller machine is designed by applying the design method of the blade of the impeller machine.
In some embodiments, the impeller of the impeller machine comprises a blade of an impeller of a hydraulic torque converter, the hydraulic torque converter comprises an impeller, a turbine and a guide wheel, wherein the impeller comprises an impeller shell, an impeller guide ring and a blade connected between the impeller shell and the impeller guide ring, the outer ring comprises the impeller shell, and the inner ring comprises the impeller guide ring; or the blades of the impeller machine include blades of a turbine of a torque converter, the outer ring includes a turbine casing, and the inner ring includes a turbine guide ring. Thus, the inner surface parameters of the outer ring and the outer surface parameters of the inner ring may be given by giving the parameters of the torus of the torque converter.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention and not to limit it; although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art will understand that: modifications to the specific embodiments of the invention or equivalent substitutions for parts of the technical features may be made; without departing from the spirit of the present invention, it is intended to cover all aspects of the invention as defined by the appended claims.

Claims (10)

1. A method for designing a blade intersection line of an impeller machine, wherein the impeller machine comprises an outer ring, an inner ring positioned on the inner side of the outer ring and blades connected between the outer surface of the inner ring and the inner surface of the outer ring, and the method for designing the blade intersection line of the impeller machine comprises the following steps:
giving two-dimensional blade outer ring bone line, inner surface parameters of the outer ring and outer surface parameters of the inner ring;
determining a two-dimensional blade outer ring molded line of the blade according to the two-dimensional blade outer ring skeleton line, and determining an intersecting line of the blade and the outer ring according to the two-dimensional blade outer ring molded line and the inner surface parameter of the outer ring;
calculating a three-dimensional blade outer ring skeleton line corresponding to the two-dimensional blade outer ring skeleton line on the inner surface of the outer ring according to the two-dimensional blade outer ring skeleton line and the inner surface parameters of the outer ring;
determining a projection vector according to the three-dimensional blade outer ring skeleton line, determining a projection plane according to the projection vector, and projecting the three-dimensional blade outer ring skeleton line on the projection plane;
a point set is taken from the projection of the three-dimensional blade outer ring skeleton line on the projection plane, a two-dimensional initial blade inner ring skeleton line is determined according to the taken point set, and the two-dimensional initial blade inner ring skeleton line is rotated and/or translated on the projection plane to obtain a two-dimensional blade inner ring skeleton line;
determining a two-dimensional blade inner ring molded line of the blade according to the determined two-dimensional blade inner ring skeleton line, and determining an intersection line of the blade and the inner ring according to the two-dimensional blade inner ring molded line, the parameters of the projection surface and the outer surface parameters of the inner ring.
2. The method of designing a vane intersection line of a turbomachinery as recited in claim 1, wherein determining a projection vector from said three-dimensional vane outer ring skeleton line comprises:
determining an extreme point of the three-dimensional blade outer ring skeleton line, connecting a starting point and an end point of the three-dimensional blade outer ring skeleton line to obtain a first line segment, and drawing a first straight line which is perpendicular to the connecting line and intersects with the first point through the extreme point;
making a first circle with radius r1 through the extreme point in a plane perpendicular to the first line, and making a first circle with radius r through the first point in a plane perpendicular to the first line2Second circle of (1), wherein r1Less than r2And r is1And r2And the length of each line segment is less than half of the length of the first line segment, a second point is taken in the first circle, a third point is taken in the second circle, and a vector obtained by connecting the second point and the third point is determined as the projection vector.
3. The method of designing the intersecting line of the vanes of the turbomachinery as recited in claim 2, wherein the coordinate of said extreme point is (x)M，yM，zM) Let the coordinates of the first point be (x)H，yH，zH) Connecting the extreme point and the first point to obtain a first vector, and setting the space coordinate of the first vector as (V)x，Vy，Vz) Let the coordinates of the second point be (x)1，y1，z1) Let the coordinate of the third point be (x)2，y2，z2) Wherein:
Figure FDA0003354351450000021
Figure FDA0003354351450000022
x1∈(xM-r1，xM+r1)，
y1∈(yM-r1，yM+r1)，x2∈(xH-r2，xH+r2)，y2∈(yH-r2，yH+r2)。
4. the method of designing a vane intersection line of a turbomachinery as recited in claim 1, wherein determining a projection vector from said three-dimensional vane outer ring skeleton line comprises:
determining an extreme point of the three-dimensional blade outer ring skeleton line, connecting a starting point and an end point of the three-dimensional blade outer ring skeleton line to obtain a first line segment, and drawing a first straight line which is perpendicular to the connecting line and intersects with the first point through the extreme point;
and passing the extreme point to make a second straight line towards a deflection angle alpha on one side of the first straight line in a plane determined by the first straight line and the first line segment, and to make a third straight line towards a deflection angle beta on one side of the first straight line in a plane perpendicular to the plane determined by the first straight line and the first line segment, wherein the second straight line and the first line segment are intersected at a fourth point, the extreme point and the fourth point are connected to obtain a second vector, a third vector is obtained according to the third straight line, and the projection vector is equal to the vector sum of the second vector and the third vector.
5. The method of claim 1, wherein the coordinates of the points of the two-dimensional initial blade endoskeleton line in the rectangular coordinate system on the projection plane are (x)0，y0)，The rotation and/or translation to obtain the two-dimensional blade inner ring bone line comprises the following steps:
when the two-dimensional initial blade inner ring skeleton line is rotated by a rotation angle θ, the coordinates of the point of the two-dimensional blade inner ring skeleton line are (x, y), and the values of x and y are obtained by the following formula:
Figure FDA0003354351450000031
when the two-dimensional initial blade inner ring skeleton line is translated, (Δ x, Δ y) is the translation amount, the coordinates of the obtained two-dimensional blade inner ring skeleton line point are (x, y), and the values of x and y are obtained by the following formula: [ x ] of0，y0]+[Δx，Δy]；
When the two-dimensional initial blade inner ring skeleton line is rotated and translated again, the rotation angle is θ, and (Δ x, Δ y) is the translation amount, the coordinates of the obtained two-dimensional blade inner ring skeleton line point are (x, y), and the values of x and y are obtained by the following formula:
Figure FDA0003354351450000032
6. the method for designing the intersecting line of the blade of the turbomachinery as recited in any one of claims 1 to 5, wherein the two-dimensional blade outer circumferential skeleton line is a bezier curve.
7. A method for designing a blade of an impeller machine, comprising the method for designing the intersecting line of the blade of the impeller machine according to any one of claims 1 to 6.
8. The method of designing a vane for an impeller machine according to claim 7, further comprising: and sweeping the intersecting line of the blade and the inner ring and the intersecting line of the blade and the outer ring by using a straight line to obtain the blade of the impeller machine.
9. A vane for an impeller machine, characterized by comprising a design using the method for designing a vane for an impeller machine according to claim 7 or 8.
10. The turbomachine blade of claim 9, wherein said turbomachine blade comprises a blade of an impeller of a torque converter, said outer ring comprises an impeller casing, and said inner ring comprises an impeller guide ring; or the impeller machine blades comprise blades of a turbine of a hydrodynamic torque converter, the outer ring comprises a turbine casing, and the inner ring comprises a turbine guide ring.
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