Blade stacking method and system

Abstract

The present invention belongs to the technical field of impellers and provides a blade stacking method and system, the method comprising designing a reference blade of an impeller blade by a linear stacking method; obtaining a plurality of initial rotating blade profiles by cutting the reference blade according to the relative height of the flow channel, rotating each of the initial rotating blade profiles around the impeller rotation axis so that the stacking center of the initial rotating blade profile passes through the circumferential stacking line to obtain a new rotating blade profile; axially stacking all the new rotating blade profiles according to the axial stacking line to obtain a stacked blade profile; and using all the stacked blade profiles, stretching them by a skinning method to obtain a blade shape. The method of the present invention stacks the rotating surface blade profiles based on the relative height, which can keep the blade profile within the annular flow surface and the blade throat area unchanged during the stacking process, thereby improving the accuracy of the blade stacking design for flow control.

Description

Technical Field

[0001] The invention belongs to the technical field of impellers and relates to a blade stacking method and system. Background Art

[0002] Blade stacking design is an important means of blade flow control and a key step in blade design. Currently, most blade stacking is based on axial and circumferential stacking of uniform-height blades. However, according to ternary flow theory, fluid flow within a turbine can be considered essentially a toroidal surface of revolution flow. Therefore, stacking designs based on uniform-height blades deviate from flow characteristics, resulting in reduced stacking control accuracy and changes in throat area, affecting matching results. Summary of the Invention

[0003] In order to solve the technical problems that axial and circumferential stacking based on constant-height blade profiles causes a certain deviation from flow characteristics, resulting in reduced stacking control accuracy and changes in throat area that affect matching results, the present invention discloses a blade stacking method, which includes the following steps:

[0004] S1. Design a reference blade for a turbine blade by using a linear stacking method;

[0005] S2. Cutting the reference blades according to the relative height of the flow channel to obtain a plurality of initial rotating blade profiles, rotating each of the initial rotating blade profiles around the impeller rotation axis so that the stacking center of the initial rotating blade profile passes through the circumferential stacking line to obtain a new rotating blade profile;

[0006] S3. Axially stacking all the new rotary blade profiles according to the axial stacking line to obtain a stacked blade profile;

[0007] S4. Using all the stacked blade profiles, stretching is performed by a skinning method to obtain a blade shape.

[0008] Furthermore, in the above step S1, designing a reference blade of the impeller blade by a linear stacking method includes:

[0009] S11. Design multiple reference blade profiles for the impeller blades at different heights;

[0010] S12, selecting a characteristic point on each of the reference blade profiles as a stacking center;

[0011] S13, stacking all the stacking centers onto a radial line passing through the rotation center of the impeller, and performing skin stretching after linear stacking to form a reference blade.

[0012] Furthermore, in the above step S3, all the new rotary blade profiles are axially stacked according to the axial stacking line to obtain the stacked blade profile, including:

[0013] S31. For each of the new rotary blade profiles, obtain a discrete point set of the layered meridian at a relative height of the flow passage where the blade profile is located, and calculate the dimensionless arc length of the layered meridian based on the discrete point set of the layered meridian;

[0014] S32. Based on the layered meridian discrete point set, the layered meridian dimensionless arc length, and the new rotation blade profile discrete point set, stacking centers of all the new rotation blade profiles on an axial stacking line to obtain a stacked blade profile.

[0015] Furthermore, in the above step S31, for each of the new rotary blade profiles, a discrete set of layered meridian points at a relative height of the flow passage in which the blade profile is located is obtained, including:

[0016] S311, performing equal arc length encryption on the lower flow channel line and the upper flow channel line to obtain a plurality of encrypted point connection lines, wherein one end of the encrypted point connection line is an encrypted discrete point of the lower flow channel, and the other end is an encrypted discrete point of the upper flow channel;

[0017] S312. For each of the encrypted point lines, select a point on each of the encrypted point lines so that the ratio of the length of the point to the encrypted discrete points of the lower flow channel to the length of the encrypted point line is equal to the relative height of the flow channel where the new rotary blade profile is located;

[0018] S313. For each of the encrypted point lines, extract the coordinates of the points selected on all the encrypted point lines to obtain a layered meridian discrete point set.

[0019] Furthermore, in the above step S31, the dimensionless arc length of the layered meridian is calculated based on the discrete point set of the layered meridian, including:

[0020] S314, along the flow channel direction, defining the dimensionless arc length of the first stratification meridian discrete point in the stratification meridian discrete point set as zero;

[0021] S315. Calculate the dimensionless arc lengths of the layer meridians of the remaining layer meridian discrete points except the first layer meridian discrete point based on the dimensionless arc length of the previous layer meridian discrete point, the coordinates of the current layer meridian discrete point, and the coordinates of the previous layer meridian discrete point.

[0022] Furthermore, in the above step S315, according to the formula:

[0023] Ms i =Ms i-1 +((Mx i -Mx i-1 ) 2 +(Mz i -Mz i-1 ) 2 )0.5 / Mz i Calculate the dimensionless arc length of the layer meridian of the remaining layer meridian discrete points except the first layer meridian discrete point, where Ms i is the dimensionless arc length of the stratification meridian of the ith stratification meridian discrete point, Ms i-1 is the dimensionless arc length of the layer meridian at the i-1th layer meridian discrete point, (Mx i ,Mz i ) are the coordinates of the discrete points of the i-th layer meridian in the X and Z directions, (Mx i-1 ,Mz i-1 ) are the coordinates of the i-1th layer meridian discrete point in the X and Z directions, respectively, and i is an integer ≥ 2.

[0024] Furthermore, in the above step S32, based on the layered meridian discrete point set, the layered meridian dimensionless arc length and the new rotation blade profile discrete point set, the stacking centers of all the new rotation blade profiles are stacked on the axial stacking line to obtain the stacked blade profile, including:

[0025] S321. Obtain an intersection point between the circumferential stacking line and each of the discrete point sets of the layered meridians on the meridian plane projection, and use the axial coordinate of the intersection point as the axial coordinate of the circumferential stacking center. Obtain an intersection point between the axial stacking line and each of the discrete point sets of the layered meridians on the meridian plane projection, and use the axial coordinate of the intersection point as the axial coordinate of the axial stacking center.

[0026] S322. Obtain a dimensionless blade profile data set of a new rotating blade profile and a dimensionless axial coordinate of a circumferential stacking center according to each of the layered meridian discrete point sets, the layered meridian dimensionless arc lengths, and the new rotating blade profile discrete point set;

[0027] S323: Based on the discrete point set of the layered meridian and the dimensionless arc length of the layered meridian, the axial coordinate of the axial stacking center is used as an interpolation point, and the X-coordinate of the discrete point set of the layered meridian and the dimensionless arc length of the layered meridian are interpolated to obtain the dimensionless axial coordinate of the axial stacking center;

[0028] S324. Calculate the stacked blade profile dimensionless blade profile data set and the stacked blade profile discrete point rectangular coordinate data set based on the layered meridian discrete point set, the layered meridian dimensionless arc length, the circumferential stacking center dimensionless axial coordinate, the axial stacking center dimensionless axial coordinate, and the new rotating blade profile dimensionless blade profile data set.

[0029] Furthermore, in the above step S322, according to each of the layered meridian discrete point sets, the layered meridian dimensionless arc lengths, and the new rotating blade profile discrete point set, a new rotating blade profile dimensionless blade profile data set and a dimensionless axial coordinate of the circumferential stacking center are obtained, including:

[0030] S3221. According to each of the layered meridian discrete point sets and the layered meridian dimensionless arc lengths, using the X-axis coordinates in the new rotary blade profile discrete point set as interpolation points, obtain the dimensionless axial coordinates of the dimensionless blade profile data set of the new rotary blade profile;

[0031] S3222. Perform atan2 function calculation on the discrete point set of the new rotary blade profile to obtain the dimensionless transverse coordinates of the dimensionless blade profile data set of the new rotary blade profile;

[0032] S3223. Based on the layered meridian discrete point set and the layered meridian dimensionless arc length, the circumferential stacking center axial coordinate is used as an interpolation point, and the X-direction coordinate of the layered meridian discrete point set and the layered meridian dimensionless arc length are interpolated to obtain the circumferential stacking center dimensionless axial coordinate.

[0033] Furthermore, in the above step S324, the stacked blade profile dimensionless blade profile dataset and the stacked blade profile discrete point rectangular coordinate dataset are calculated based on the layered meridian discrete point set, the layered meridian dimensionless arc length, the circumferential stacking center dimensionless axial coordinate, the axial stacking center dimensionless axial coordinate, and the new rotating blade profile dimensionless blade profile dataset, including:

[0034] S3241. According to the difference between the dimensionless axial coordinate of the circumferential stacking center and the dimensionless axial coordinate of the axial stacking center, translate the new rotating blade profile dimensionless blade profile dataset to obtain a stacked blade profile dimensionless blade profile dataset;

[0035] S3242: Based on the layered meridian discrete point set and the layered meridian dimensionless arc length, the dimensionless axial coordinates of the stacked blade profile dimensionless blade profile data set are used as interpolation points, and the layered meridian dimensionless arc lengths and the X-direction coordinates of the layered meridian discrete point set are interpolated to obtain the X-direction rectangular coordinates of the stacked blade profile discrete points.

[0036] S3243. Based on the layered meridian discrete point set, using the X-axis rectangular coordinates of the stacked blade discrete points as interpolation points, obtain the vertical distances of the stacked blade discrete points from the impeller rotation axis;

[0037] S3244. According to the vertical distance between the stacked blade profile discrete point and the impeller rotation axis and the stacked blade profile dimensionless blade profile data set, the Y-direction rectangular coordinate and the Z-direction rectangular coordinate of the stacked blade profile discrete point are calculated by using the sine function and the cosine function respectively.

[0038] An embodiment of the present invention further provides a blade stacking system, comprising a reference blade design module, a new rotation blade profile acquisition module, a stacked blade profile acquisition module, and a blade shape generation module.

[0039] Wherein, the reference blade design module is used to design the reference blade of the impeller blade by a linear stacking method;

[0040] The new rotating blade profile acquisition module is used to obtain a plurality of initial rotating blade profiles by intercepting the reference blade according to the relative height of the flow channel, and rotate each of the initial rotating blade profiles around the impeller rotation axis so that the stacking center of the initial rotating blade profile passes through the circumferential stacking line to obtain a new rotating blade profile;

[0041] The stacked blade profile acquisition module is used to perform axial stacking on all the new rotary blade profiles according to the axial stacking line to obtain a stacked blade profile;

[0042] The blade shape generating module is used to adopt all the stacked blade profiles and to obtain the blade shape by stretching through a skinning method.

[0043] Compared with the prior art, the method of the present invention can keep the blade profile within the annular flow surface and the blade throat area unchanged during the stacking process, thereby improving the accuracy of flow control in the blade stacking design. BRIEF DESCRIPTION OF THE DRAWINGS

[0044] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following briefly introduces the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0045] Figure 1 This is a flow chart of a blade stacking method disclosed in an embodiment of the present invention;

[0046] Figure 2 A schematic diagram of the relative altitude layered meridian disclosed in an embodiment of the present invention;

[0047] Figure 3 A schematic diagram of an initial rotation blade profile obtained by cutting a reference blade according to an embodiment of the present invention;

[0048] Figure 4 A schematic diagram of circumferential stacking disclosed in an embodiment of the present invention;

[0049] Figure 5 This is a schematic diagram of axial stacking disclosed in an embodiment of the present invention;

[0050] Figure 6 This is an architectural diagram of a blade stacking system disclosed in an embodiment of the present invention;

[0051] Among them, 601 is a reference blade design module; 602 is a new rotation blade profile acquisition module; 603 is a stacked blade profile acquisition module; and 604 is a blade shape generation module. DETAILED DESCRIPTION

[0052] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0053] The following describes the embodiments of the present application through specific examples, and those skilled in the art can easily understand other advantages and effects of the present application from the contents disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The present application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, in the absence of conflict, the features of the following embodiments and embodiments can be combined with each other. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without making creative work are within the scope of protection of this application.

[0054] The embodiment of the present invention discloses a blade stacking method, see Figures 1 to 6 As shown, the method includes the following steps:

[0055] S1. Design a reference blade for a turbine blade by using a linear stacking method;

[0056] S2. Cutting the reference blades according to the relative height of the flow channel to obtain a plurality of initial rotating blade profiles, rotating each of the initial rotating blade profiles around the impeller rotation axis so that the stacking center of the initial rotating blade profile passes through the circumferential stacking line to obtain a new rotating blade profile;

[0057] S3. Axially stacking all the new rotary blade profiles according to the axial stacking line to obtain a stacked blade profile;

[0058] S4. Using all the stacked blade profiles, stretching is performed by a skinning method to obtain a blade shape.

[0059] Furthermore, in the above step S1, designing a reference blade of the impeller blade by a linear stacking method includes:

[0060] S11. Designing a plurality of reference blade profiles for the impeller blades at different heights, wherein the number of reference blade profiles may be 3 to 5. When the present invention is implemented, the reference blade profiles may be designed at different heights for the impeller blades, such as by equal height, relative height, or cone height.

[0061] S12. Selecting a characteristic point on each reference blade profile as a stacking center, wherein the stacking center may be selected from any one of a blade leading edge point, a blade trailing edge point, a blade centroid point, and a blade maximum thickness point;

[0062] S13, stacking all the stacking centers onto a radial line passing through the rotation center of the impeller, and performing skin stretching after linear stacking to form a reference blade.

[0063] Furthermore, in the above step S2, when the reference blade is intercepted to obtain the initial rotating blade profile, the number of the initial rotating blade profiles is usually related to the blade profile complexity. The number of the initial rotating blade profiles is proportional to the blade profile complexity, and is usually not less than 5, including the initial rotating blade profiles of two relative heights of 0% and 100%. The initial rotating blade profile is intercepted according to the relative height as follows: Figure 3 As shown. The complexity of the blade profile includes any one or more of the curvature, twist angle, thickness, width, surface roughness and geometric shape of the blade, and the relative height is the longitudinal position from the root of the blade to the top of the blade. Specifically, a layered meridian can be formed based on the layered meridian discrete point set of each reference blade, and each layered meridian can be rotated around the impeller rotation axis to form a blade rotation surface; all blade rotation surfaces are used to intercept the reference blade to obtain multiple initial rotation blade profiles, and the initial rotation blade profile discrete point set in rectangular coordinates can be extracted at the same time; based on the blade rotation surface blade profile discrete point set, the coordinates of the feature points in the flow channel are obtained. When a new rotation blade profile is obtained, the new rotation blade profile is discretized to obtain a new rotation blade profile discrete point set (X1 n ,Y1 n ,Z1 n ).

[0064] Furthermore, in the above step S3, all the new rotary blade profiles are axially stacked according to the axial stacking line to obtain the stacked blade profile, including:

[0065] S31, for each new rotary blade, obtain the layered meridian discrete point set (Mx i ,Mz i ), calculate the dimensionless arc length Ms of the layered meridian based on the layered meridian discrete point set i ;

[0066] S32, according to the layered meridian discrete point set (Mx i ,Mz i), the dimensionless arc length Ms of the layer meridian i and the new rotating blade discrete point set (X1 n ,Y1 n ,Z1 n ), the stacking centers of all the new rotating blade profiles are stacked on the axial stacking line to obtain a stacked blade profile.

[0067] Furthermore, in the above step S31, the discrete point set of the layered meridian at the relative height of the flow channel (Mx i ,Mz i ),include:

[0068] S311. Perform equal arc length encryption on the lower flow line and the upper flow line to obtain multiple encrypted point lines, wherein one end of the encrypted point line is the lower flow encrypted discrete point, and the other end is the upper flow encrypted discrete point. In specific implementation, the upper flow line and the lower flow line can be encrypted with equal arc length respectively, and the number of encrypted points of the upper flow line and the lower flow line is equal. The layered meridian discrete point of the lower flow line in the encrypted point line is represented by A i The discrete points of the stratified meridian of the upper flow line are represented by B i , the number of encrypted point connections is not less than 1000.

[0069] S312. For each of the encrypted point lines, select a point on each of the encrypted point lines so that the ratio of the length of the point to the encrypted discrete point of the lower flow channel to the length of the encrypted point line is equal to the relative height of the flow channel where the new rotary blade is located. In specific implementation, the points selected on each of the encrypted point lines can be represented by M i Indicates that A i M i The length of A i B i The ratio of the lengths is equal to the relative height h of the blade section.

[0070] S313: For each of the encrypted point lines, extract the coordinates of the points selected on all the encrypted point lines to obtain a layered meridian discrete point set. The layered meridian discrete point set can be expressed as (Mx i ,Mz i ). (Mx i ,Mz i ) represent the coordinates of the i-th layer meridian discrete point in the flow channel in the X direction and the Z direction, respectively. Where i is 1, 2, 3, ..., m, and m is an integer ≥ 1000.

[0071] Furthermore, in the above step S31, the dimensionless arc length of the layered meridian is calculated based on the discrete point set of the layered meridian, including:

[0072] S314, along the flow channel direction, defining the dimensionless arc length of the first stratification meridian discrete point in the stratification meridian discrete point set as zero;

[0073] S315. Calculate the dimensionless arc lengths of the layer meridians of the remaining layer meridian discrete points except the first layer meridian discrete point based on the dimensionless arc length of the previous layer meridian discrete point, the coordinates of the current layer meridian discrete point, and the coordinates of the previous layer meridian discrete point.

[0074] Furthermore, in the above step S315, according to the formula:

[0075] Ms i =Ms i-1 +((Mx i -Mx i-1 ) 2 +(Mz i -Mz i-1 ) 2 ) 0.5 / Mz i Calculate the dimensionless arc length of the layer meridian of the remaining layer meridian discrete points except the first layer meridian discrete point, where Ms i is the dimensionless arc length of the stratification meridian of the ith stratification meridian discrete point, Ms i-1 is the dimensionless arc length of the layer meridian at the i-1th layer meridian discrete point, (Mx i ,Mz i ) are the coordinates of the discrete points of the i-th layer meridian in the X and Z directions, (Mx i-1 ,Mz i-1 ) are the coordinates of the i-1th layer meridian discrete point in the X and Z directions, respectively, and i is an integer ≥ 2.

[0076] Furthermore, in the above step S32, according to the layered meridian discrete point set (Mx i ,Mz i ), the dimensionless arc length Ms of the layer meridian i and the new rotating blade discrete point set (X1 n ,Y1 n ,Z1 n ), stacking the stacking centers of all the new rotary blade profiles on the axial stacking line to obtain a stacked blade profile, including:

[0077] S321, obtain the circumferential stacking line and each layered meridian discrete point set (Mx i ,Mz i) on the meridian plane projection, the axial coordinate of the intersection is used as the axial coordinate of the circumferential stacking center T1x, and the axial stacking line and each of the layered meridian discrete point sets (Mx i ,Mz i ) on the meridian plane projection, and taking the axial coordinate of the intersection point as the axial coordinate T2x of the axial stacking center;

[0078] S322, according to each of the layered meridian discrete point sets (Mx i ,Mz i ), the dimensionless arc length Ms of the layer meridian i and the new rotating blade discrete point set (X1 n ,Y1 n ,Z1 n ), obtain the new rotating blade dimensionless blade data set (F1 n ,G1 n ) and the dimensionless axial coordinate Q1 of the circumferential stacking center;

[0079] S323, according to the layered meridian discrete point set (Mx i ,Mz i ) and the dimensionless arc length of the stratified meridian, and taking the axial coordinate T2x of the axial stacking center as the interpolation point, the X-direction coordinate Mx of the discrete point set of the stratified meridian is obtained. i and the dimensionless arc length of the layer meridian Ms i Perform interpolation to obtain the dimensionless axial coordinate Q2 of the axial stacking center;

[0080] S324, according to the layered meridian discrete point set (Mx i ,Mz i ), the dimensionless arc length Ms of the layer meridian i , the dimensionless axial coordinate Q1 of the circumferential stacking center, the dimensionless axial coordinate Q2 of the axial stacking center and the dimensionless blade profile data set of the new rotary blade profile (F1 n ,G1 n ), the dimensionless blade data set of the stacked blade is calculated (F2 n ,G2 n ) and the stacked leaf-shaped discrete point rectangular coordinate data set (X2 n ,Y2 n ,Z2 n ).

[0081] Furthermore, in the above step S322, according to each of the layered meridian discrete point sets (Mx i ,Mz i ), the dimensionless arc length Ms of the layer meridian i and the new rotating blade discrete point set (X1n ,Y1 n ,Z1 n ), obtain the new rotating blade dimensionless blade data set (F1 n ,G1 n ) and the dimensionless axial coordinate Q1 of the circumferential stacking center, including:

[0082] S3221, according to each of the layered meridian discrete point sets (Mx i ,Mz i ) and the dimensionless arc length Ms of the layer meridian i , with the new rotating blade discrete point set (X1 n ,Y1 n ,Z1 n ) X-coordinate X1 n As the interpolation point, the dimensionless axial coordinate F1 of the dimensionless blade data set of the new rotating blade is obtained n The dimensionless axial coordinate in the present invention is also the X-direction coordinate (i.e., the axial coordinate of the impeller). In implementation, according to the M1x of the discrete points of the layered meridian i and the dimensionless arc length of the layer meridian M1s i , with X1 as the discrete point of the rotating blade n As the interpolation point, the dimensionless axial coordinate F1 is obtained n ;

[0083] S3222, the new rotary blade discrete point set (X1 n ,Y1 n ,Z1 n ) Perform atan2 function calculation to obtain the dimensionless transverse coordinate G1 of the dimensionless blade data set of the new rotating blade n The dimensionless horizontal coordinate in the present invention is also the Y-axis (ie, the horizontal direction of the impeller) coordinate. In implementation, according to the Y-axis coordinate Y1 of the rotating blade discrete point set n and Z-axis coordinate Z1 n , calculate G1 using atan2 function n , that is, G1 n =atan2(Y1 n , Z1 n );

[0084] S3223, according to the layered meridian discrete point set (Mx i ,Mz i ) and the dimensionless arc length Ms of the layer meridian i , using the axial coordinate T1x of the circumferential stack center as the interpolation point, the X-direction coordinate Mx of the layered meridian discrete point set i and the dimensionless arc length of the layer meridian Msi Interpolation is performed to obtain the dimensionless axial coordinate Q1 of the circumferential stacking center.

[0085] Furthermore, in the above step S324, according to the layered meridian discrete point set (Mx i ,Mz i ), the dimensionless arc length Ms of the layer meridian i , the dimensionless axial coordinate Q1 of the circumferential stacking center, the dimensionless axial coordinate Q2 of the axial stacking center and the dimensionless blade profile data set of the new rotary blade profile (F1 n ,G1 n ), the dimensionless blade data set of the stacked blade is calculated (F2 n ,G2 n ) and the stacked leaf-shaped discrete point rectangular coordinate data set (X2 n ,Y2 n ,Z2 n ),include:

[0086] S3241, according to the difference between the dimensionless axial coordinate Q1 of the circumferential stacking center and the dimensionless axial coordinate Q2 of the axial stacking center, translate the new rotary blade profile dimensionless blade profile data set (F1 n ,G1 n ), the dimensionless blade profile data set of the stacked blade is obtained; specifically, by formula F2 n =F1 n +Q2-Q1,G2 n =G1 n Calculate the dimensionless blade data set of the stacked blade profile (F2 n ,G2 n ), where F2 n is the dimensionless axial coordinate of the nth dimensionless blade profile data of the stacked blade profile, G2 n It is the dimensionless horizontal coordinate of the nth dimensionless blade profile data of the stacked blade profile.

[0087] S3242, according to the layered meridian discrete point set (Mx i ,Mz i ), the dimensionless arc length Ms of the layer meridian i , with the dimensionless blade profile dataset (F2 n ,G2 n ) in F2 n is the interpolation point, the dimensionless arc length Ms of the layer meridian i and the X-direction coordinate Mx of the discrete point set of the layered meridian i Interpolation is performed to calculate the X-axis rectangular coordinate X2 of the stacked leaf discrete point n ;

[0088] S3243, according to the layered meridian discrete point set (Mx i ,Mz i ), with the X-direction rectangular coordinate X2 of the stacked blade discrete point n As the interpolation point, the vertical distance between the discrete point of the stacked blade profile and the impeller rotation axis is obtained;

[0089] S3244, according to the vertical distance of the stacked blade profile discrete point from the impeller rotation axis and the stacked blade profile dimensionless blade profile data set (F2 n ,G2 n ), the Y-direction rectangular coordinates Y2 of the stacked blade discrete points are calculated by sine function and cosine function respectively. n and the Z-axis rectangular coordinate Z2 n .

[0090] The specific process of the above steps S3241-S3244 is as follows: According to each of the stacked blade dimensionless blade data sets (F2 n ,G2 n ), dimensionless arc length of the layer meridian M1s i Calculate the rectangular coordinate data set of the stacked leaf discrete points (X2 n ,Y2 n ,Z2 n ), where X2 n ,Y2 n ,Z2 n are the coordinates of the nth discrete point of the stacked leaf in the X, Y, and Z directions respectively. n It can be calculated as follows: n is the interpolation point, the array (Ms i , Mx i ) to interpolate and calculate X2 n Y2 n and Z2 n It can be calculated as follows: n For interpolation points, the array (Mx i , Mz i ) is interpolated to obtain the vertical distance R2 between the nth discrete point of the stacked blade and the impeller rotation axis n , and then calculate Y2 through the function n =cos(G1 n )*R2 n , Z2 n =sin(G1 n )* R2 n .

[0091] Compared with the prior art, the method of the present invention can keep the blade profile within the annular flow surface and the blade throat area unchanged during the stacking process, thereby improving the accuracy of flow control in the blade stacking design.

[0092] Based on the same inventive concept, a blade stacking system is also provided in an embodiment of the present invention, as described in the following embodiments. Since the principle of solving the problem by the blade stacking system is similar to the blade stacking method disclosed in the above embodiments, the implementation of the blade stacking system can refer to the implementation of the blade stacking method, and the repeated parts will not be repeated. As used below, the term "unit" or "module" can be a combination of software and / or hardware that implements a predetermined function. Although the device described in the following embodiments is preferably implemented in software, the implementation of hardware, or a combination of software and hardware, is also possible and conceived.

[0093] Figure 6 This is a structural block diagram of a blade stacking system applicable to an impeller according to an embodiment of the present invention. Figure 6 As shown, the system includes a reference blade design module 601, a new rotation blade profile acquisition module 602, a stacked blade profile acquisition module 603 and a blade shape generation module 604. The structure is described below.

[0094] The reference blade design module 601 is used to design the reference blade of the impeller blade by using the linear stacking method;

[0095] The new rotating blade profile acquisition module 602 is configured to obtain a plurality of initial rotating blade profiles by intercepting the reference blade according to the relative height of the flow channel, and rotate each of the initial rotating blade profiles around the impeller rotation axis so that the stacking center of the initial rotating blade profile passes through the circumferential stacking line to obtain a new rotating blade profile;

[0096] The stacked blade profile acquisition module 603 is used to perform axial stacking on all the new rotary blade profiles according to the axial stacking line to obtain a stacked blade profile;

[0097] The blade shape generating module 604 is used to obtain the blade shape by using all the stacked blade profiles and stretching them through a skinning method.

[0098] In this embodiment, a computer device is provided, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor implements any of the above-mentioned blade stacking methods when executing the computer program.

[0099] Specifically, the computer device may be a computer terminal, a server or a similar computing device.

[0100] In this embodiment, a computer-readable storage medium is provided, wherein the computer-readable storage medium stores a computer program for executing any of the above-mentioned blade stacking methods.

[0101] Specifically, computer-readable storage media include permanent and non-permanent, removable and non-removable media that can be used to store information by any method or technology. The information can be computer-readable instructions, data structures, program modules or other data. Examples of computer-readable storage media include, but are not limited to, phase change memory (PRAM), static random access memory (SRAM), dynamic random access memory (DRAM), other types of random access memory (RAM), read-only memory (ROM), electrically erasable programmable read-only memory (EEPROM), flash memory or other memory technology, compact disc read-only memory (CD-ROM), digital versatile disc (DVD) or other optical storage, magnetic cassettes, tape disk storage or other magnetic storage devices or any other non-transmission media that can be used to store information that can be accessed by a computing device. As defined herein, computer-readable storage media does not include transitory media such as modulated data signals and carrier waves.

[0102] Obviously, those skilled in the art should understand that the various modules or steps of the above-mentioned embodiments of the present invention can be implemented using a general-purpose computing device, they can be concentrated on a single computing device, or distributed across a network composed of multiple computing devices. Alternatively, they can be implemented using program code executable by the computing device, so that they can be stored in a storage device and executed by the computing device. In some cases, the steps shown or described can be performed in a different order than herein, or they can be made into separate integrated circuit modules, or multiple modules or steps can be made into a single integrated circuit module for implementation. Thus, the embodiments of the present invention are not limited to any specific combination of hardware and software.

[0103] The foregoing description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Those skilled in the art will readily appreciate that various modifications and variations of the present invention are possible. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention are intended to be within the scope of protection of the present invention.

Claims

1. A blade stacking method, characterized in that: For performing stacking design on a turbine blade, the method comprises: Designing a reference blade for an impeller blade by a linear stacking method includes: designing a plurality of reference blade profiles at different heights for the impeller blade; selecting a characteristic point on each of the reference blade profiles as a stacking center; stacking all of the stacking centers onto a radial line passing through the center of rotation of the impeller, and performing skin stretching to form a reference blade; The reference blade is cut according to the relative height of the flow channel to obtain a plurality of initial rotating blade profiles, and each of the initial rotating blade profiles is rotated around the impeller rotation axis so that the stacking center of the initial rotating blade profile passes through the circumferential stacking line to obtain a new rotating blade profile; Axially stacking all the new rotating blade profiles according to the axial stacking line to obtain a stacked blade profile, including: for each new rotating blade profile, obtaining a layered meridian discrete point set at a relative height of the flow channel in which the blade profile is located, and calculating a layered meridian dimensionless arc length based on the layered meridian discrete point set; and stacking the stacking centers of all the new rotating blade profiles on the axial stacking line according to the layered meridian discrete point set, the layered meridian dimensionless arc length, and the new rotating blade profile discrete point set to obtain a stacked blade profile; All the stacked blade profiles are used to obtain the blade shape by stretching through a skinning method.

2. The blade stacking method according to claim 1, characterized in that: For each of the new rotary blade profiles, a discrete set of layered meridian points at relative heights of the flow passage in which the blade profile is located is obtained, including: Perform equal arc length encryption on the lower flow channel line and the upper flow channel line to obtain multiple encrypted point connection lines, wherein one end of the encrypted point connection line is the encrypted discrete point of the lower flow channel, and the other end is the encrypted discrete point of the upper flow channel; For each of the encrypted point lines, select a point on each of the encrypted point lines so that the ratio of the length of the point to the encrypted discrete points of the lower flow channel to the length of the encrypted point line is equal to the relative height of the flow channel where the new rotary blade profile is located; For each of the encrypted point lines, the coordinates of the points selected on all the encrypted point lines are extracted to obtain a layered meridian discrete point set.

3. The blade stacking method according to claim 1, characterized in that: Calculating the dimensionless arc length of the layered meridian according to the layered meridian discrete point set includes: Along the flow channel direction, defining the dimensionless arc length of the first stratification meridian discrete point in the stratification meridian discrete point set as zero; The dimensionless arc lengths of the layer meridians of the remaining layer meridian discrete points except the first layer meridian discrete point are calculated according to the dimensionless arc length of the layer meridian of the previous layer meridian discrete point, the coordinates of the current layer meridian discrete point and the coordinates of the previous layer meridian discrete point.

4. The blade stacking method according to claim 3, characterized in that: According to the formula Ms i =Ms i-1 +((Mx i -Mx i-1 ) 2 +(Mz i -Mz i-1 ) 2 ) 0.5 / Mz i Calculate the dimensionless arc length of the layer meridian of the remaining layer meridian discrete points except the first layer meridian discrete point, where Ms i is the dimensionless arc length of the stratification meridian of the ith stratification meridian discrete point, Ms i-1 is the dimensionless arc length of the layer meridian at the i-1th layer meridian discrete point, (Mx i ,Mz i ) are the coordinates of the discrete points of the i-th layer meridian in the X and Z directions, (Mx i-1 ,Mz i-1 ) are the coordinates of the i-1th layer meridian discrete point in the X and Z directions, respectively, and i is an integer ≥ 2.

5. The blade stacking method according to claim 1, characterized in that: According to the layered meridian discrete point set, the layered meridian dimensionless arc length and the new rotation blade profile discrete point set, the stacking centers of all the new rotation blade profiles are stacked on the axial stacking line to obtain the stacked blade profile, including: Obtaining the intersection of the circumferential stacking line and each of the discrete point sets of the layered meridian on the meridian plane projection, and using the axial coordinate of the intersection as the axial coordinate of the circumferential stacking center; obtaining the intersection of the axial stacking line and each of the discrete point sets of the layered meridian on the meridian plane projection, and using the axial coordinate of the intersection as the axial coordinate of the axial stacking center; Obtaining a new rotating blade profile dimensionless blade profile data set and a dimensionless axial coordinate of a circumferential stacking center according to each of the layered meridian discrete point sets, the layered meridian dimensionless arc lengths, and the new rotating blade profile discrete point set; According to the layered meridian discrete point set and the layered meridian dimensionless arc length, the axial coordinate of the axial stacking center is used as an interpolation point, and the X-axis coordinate of the layered meridian discrete point set and the layered meridian dimensionless arc length are interpolated to obtain the dimensionless axial coordinate of the axial stacking center; According to the layered meridian discrete point set, the layered meridian dimensionless arc length, the circumferential stacking center dimensionless axial coordinate, the axial stacking center dimensionless axial coordinate and the new rotating blade profile dimensionless blade profile data set, the stacked blade profile dimensionless blade profile data set and the stacked blade profile discrete point rectangular coordinate data set are calculated.

6. The blade stacking method according to claim 5, characterized in that: According to each of the layered meridian discrete point sets, the layered meridian dimensionless arc lengths, and the new rotating blade profile discrete point set, a new rotating blade profile dimensionless blade profile data set and a dimensionless axial coordinate of a circumferential stacking center are obtained, including: According to each of the layered meridian discrete point sets and the layered meridian dimensionless arc length, the dimensionless axial coordinates of the dimensionless blade profile data set of the new rotating blade profile are obtained by using the X-axis coordinates in the new rotating blade profile discrete point set as interpolation points; Performing atan2 function calculation on the discrete point set of the new rotating blade profile to obtain the dimensionless transverse coordinates of the dimensionless blade profile data set of the new rotating blade profile; According to the layered meridian discrete point set and the layered meridian dimensionless arc length, the circumferential stacking center dimensionless axial coordinate is interpolated on the X-direction coordinate of the layered meridian discrete point set and the layered meridian dimensionless arc length with the circumferential stacking center axial coordinate as an interpolation point.

7. The blade stacking method according to claim 5, characterized in that: According to the layered meridian discrete point set, the layered meridian dimensionless arc length, the circumferential stacking center dimensionless axial coordinate, the axial stacking center dimensionless axial coordinate, and the new rotary blade profile dimensionless blade profile data set, a stacked blade profile dimensionless blade profile data set and a stacked blade profile discrete point rectangular coordinate data set are calculated, including: translating the new rotating blade profile dimensionless blade profile dataset according to a difference between the dimensionless axial coordinate of the circumferential stacking center and the dimensionless axial coordinate of the axial stacking center to obtain a stacked blade profile dimensionless blade profile dataset; According to the layered meridian discrete point set and the layered meridian dimensionless arc length, the dimensionless axial coordinate of the stacked blade profile dimensionless blade profile data set is used as an interpolation point, and the layered meridian dimensionless arc length and the X-direction coordinate of the layered meridian discrete point set are interpolated to obtain the X-direction rectangular coordinate of the stacked blade profile discrete point; According to the layered meridian discrete point set, the X-axis rectangular coordinates of the stacked blade discrete points are used as interpolation points to obtain the vertical distances of the stacked blade discrete points from the impeller rotation axis; According to the vertical distance between the stacked blade profile discrete point and the impeller rotation axis and the stacked blade profile dimensionless blade profile data set, the Y-direction rectangular coordinate and the Z-direction rectangular coordinate of the stacked blade profile discrete point are calculated by sine function and cosine function respectively.

8. A blade stacking system, characterized in that: include: A reference blade design module is used to design a reference blade for an impeller blade by a linear stacking method, including: designing a plurality of reference blade profiles at different heights for the impeller blade; selecting a characteristic point on each of the reference blade profiles as a stacking center; stacking all of the stacking centers onto a radial line passing through the impeller rotation center, and performing skin stretching to form a reference blade; a new rotating blade profile acquisition module, configured to obtain a plurality of initial rotating blade profiles by intercepting the reference blade according to the relative height of the flow channel, and to rotate each of the initial rotating blade profiles around the impeller rotation axis so that the stacking center of the initial rotating blade profile passes through a circumferential stacking line to obtain a new rotating blade profile; A stacked blade profile acquisition module is configured to perform axial stacking on all the new rotating blade profiles according to an axial stacking line to obtain a stacked blade profile, comprising: obtaining, for each new rotating blade profile, a discrete point set of layered meridians at a relative height of the flow channel in which the new rotating blade profile is located, and calculating a dimensionless arc length of the layered meridians according to the discrete point set of layered meridians; and stacking the stacking centers of all the new rotating blade profiles on the axial stacking line according to the discrete point set of layered meridians, the dimensionless arc length of the layered meridians, and the discrete point set of the new rotating blade profile to obtain a stacked blade profile; The blade shape generation module is used to adopt all the stacked blade profiles and stretch them through the skinning method to obtain the blade shape.

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