Blade stacking method and system

Abstract

The invention belongs to the technical field of turbines, and provides a blade stacking method and system.The method comprises the steps that a reference blade of turbine blades is designed through a linear stacking method; intercepting the reference blade according to the relative height of the flow channel to obtain a plurality of initial rotary blade profiles, rotating each initial rotary blade profile around a rotating shaft of the turbine, and enabling the stacking center of the initial rotary blade profile to penetrate through a circumferential stacking line to obtain a new rotary blade profile; axially stacking all the new rotary blade profiles according to axial stacking lines to obtain stacked blade profiles; and adopting all the stacked blade profiles, and stretching through a skin method to obtain the blade profile. According to the method, stacking is conducted on the basis of the rotating surface blade profiles of the relative height, the blade profiles in the annular flow surface can be kept unchanged in the stacking process, the throat area of the blades can be kept unchanged, and the precision of flow control of the blade stacking design can be improved.

Description

Technical Field

[0001] The present invention belongs to the technical field of turbomachines, 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 link in blade design. Currently, most blade stackings are axially and circumferentially stacked based on equal-height airfoils. However, according to the three-dimensional flow theory, the flow of fluid in a turbomachine can be basically considered as annular rotating surface flow. Therefore, the stacking design based on equal-height airfoils deviates from the flow characteristics to a certain extent, resulting in a reduction in the stacking control accuracy and causing changes in the throat area to affect the matching result. Summary of the Invention

[0003] In order to solve the technical problems such as the deviation from the flow characteristics caused by axially and circumferentially stacking based on equal-height airfoils, resulting in a reduction in the stacking control accuracy and causing changes in the throat area to affect the matching result, the present invention discloses a blade stacking method, which includes the following steps: S1. Design a reference blade of the turbomachine blade by a straight stacking method; S2. Intercept a plurality of initial rotating airfoils from the reference blade according to the relative height of the flow passage, and rotate each initial rotating airfoil around the rotation axis of the turbomachine so that the stacking center of the initial rotating airfoil passes through the circumferential stacking line to obtain a new rotating airfoil; S3. Axially stack all the new rotating airfoils respectively according to the axial stacking line to obtain stacked airfoils; S4. Use all the stacked airfoils and stretch them by a skinning method to obtain the blade profile.

[0004] Further, in the above step S1, designing a reference blade of the turbomachine blade by a straight stacking method includes: S11. Design a plurality of reference airfoils for the turbomachine blade at different heights; S12. Select characteristic points on each reference airfoil as stacking centers; S13. Stack all the stacking centers onto the radial line passing through the rotation center of the turbomachine, and perform skinning and stretching after straight stacking to form a reference blade.

[0005] Further, in the above step S3, axially stacking all the new rotating airfoils respectively according to the axial stacking line to obtain stacked airfoils includes: S31. For each new rotating airfoil, obtain a discrete point set of the stratified meridian at the relative height of the flow passage where it is located, and calculate the dimensionless arc length of the stratified meridian based on the discrete point set of the stratified meridian; S32. Stack the stacking centers of all the new rotary blade profiles on the axial stacking line according to the stratified meridian discrete point set, the dimensionless arc length of the stratified meridian, and the new rotary blade profile discrete point set to obtain a stacked blade profile.

[0006] Further, in the above step S31, for each of the new rotary blade profiles, obtaining the stratified meridian discrete point set of the relative height of the flow channel where it is located includes: S311. Perform equal-arc-length encryption on the downstream channel line and the upstream channel line to obtain multiple encrypted point connection lines, where one end of the encrypted point connection line is a downstream channel encrypted discrete point and the other end is an upstream channel encrypted discrete point; S312. For each of the encrypted point connection lines, select a point on each of the encrypted point connection lines such that the ratio of the length from the point to the downstream channel encrypted discrete point to the length of the encrypted point connection line is equal to the relative height of the flow channel where the new rotary blade profile is located; S313. For each of the encrypted point connection lines, extract the coordinates of all the selected points on the encrypted point connection lines to obtain the stratified meridian discrete point set.

[0007] Further, in the above step S31, calculating the dimensionless arc length of the stratified meridian according to the stratified meridian discrete point set includes: S314. Along the flow channel direction, define the dimensionless arc length of the stratified meridian of the first stratified meridian discrete point in the stratified meridian discrete point set as zero; S315. Calculate the dimensionless arc length of the stratified meridian of the remaining stratified meridian discrete points except the first stratified meridian discrete point according to the dimensionless arc length of the previous stratified meridian discrete point, the coordinates of the current stratified meridian discrete point, and the coordinates of the previous stratified meridian discrete point.

[0008] Even further, in the above step S315, 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 stratified meridian of the remaining stratified meridian discrete points except the first stratified meridian discrete point, where Ms i is the dimensionless arc length of the i-th stratified meridian discrete point, Ms i-1 is the dimensionless arc length of the (i - 1)-th stratified meridian discrete point, (Mx i ,Mz iare the coordinates of the i-th discrete point of the stratified meridian in the X and Z directions, (Mx i-1 , Mz i-1 ) are the coordinates of the (i - 1)-th discrete point of the stratified meridian in the X and Z directions, and i is an integer greater than or equal to 2.

[0009] Further, in the above step S32, according to the set of discrete points of the stratified meridian, the dimensionless arc length of the stratified meridian, and the set of discrete points of the new rotary blade profile, stacking the stacking centers of all the new rotary blade profiles on the axial stacking line to obtain a stacked blade profile, including: S321. Obtain the intersection points of the circumferential stacking line and each set of discrete points of the stratified meridian in the meridional plane projection, use the axial coordinates of the intersection points as the axial coordinates of the circumferential stacking center, obtain the intersection points of the axial stacking line and each set of discrete points of the stratified meridian in the meridional plane projection, and use the axial coordinates of the intersection points as the axial coordinates of the axial stacking center; S322. According to each set of discrete points of the stratified meridian, the dimensionless arc length of the stratified meridian, and the set of discrete points of the new rotary blade profile, obtain the dimensionless blade profile data set of the new rotary blade profile and the dimensionless axial coordinates of the circumferential stacking center; S323. According to the set of discrete points of the stratified meridian and the dimensionless arc length of the stratified meridian, using the axial coordinates of the axial stacking center as the interpolation points, interpolate the X coordinates of the set of discrete points of the stratified meridian and the dimensionless arc length of the stratified meridian to obtain the dimensionless axial coordinates of the axial stacking center; S324. According to the set of discrete points of the stratified meridian, the dimensionless arc length of the stratified meridian, the dimensionless axial coordinates of the circumferential stacking center, the dimensionless axial coordinates of the axial stacking center, and the dimensionless blade profile data set of the new rotary blade profile, calculate to obtain the dimensionless blade profile data set of the stacked blade profile and the right-angle coordinate data set of the discrete points of the stacked blade profile.

[0010] Even further, in the above step S322, according to each set of discrete points of the stratified meridian, the dimensionless arc length of the stratified meridian, and the set of discrete points of the new rotary blade profile, obtaining the dimensionless blade profile data set of the new rotary blade profile and the dimensionless axial coordinates of the circumferential stacking center includes: S3221. According to each set of discrete points of the stratified meridian and the dimensionless arc length of the stratified meridian, using the X coordinates in the set of discrete points of the new rotary blade profile as the interpolation points, obtain the dimensionless axial coordinates of the dimensionless blade profile data set of the new rotary blade profile; S3222. Perform atan2 function calculation on the set of discrete points 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; S3223. Based on the stratified meridian discrete point set and the dimensionless arc length of the stratified meridian, using the axial coordinate of the circumferential stacking center as the interpolation point, interpolate the X-direction coordinate of the stratified meridian discrete point set and the dimensionless arc length of the stratified meridian to obtain the dimensionless axial coordinate of the circumferential stacking center.

[0011] Furthermore, in the above step S324, based on the stratified meridian discrete point set, the dimensionless arc length of the stratified meridian, the dimensionless axial coordinate of the circumferential stacking center, the dimensionless axial coordinate of the axial stacking center, and the dimensionless blade profile data set of the new rotating blade profile, calculate the dimensionless blade profile data set of the stacked blade profile and the right-angle coordinate data set of the discrete points of the stacked blade profile, including: S3241. Translate the dimensionless blade profile data set of the new rotating blade profile according to the difference between the dimensionless axial coordinate of the circumferential stacking center and the dimensionless axial coordinate of the axial stacking center to obtain the dimensionless blade profile data set of the stacked blade profile; S3242. Based on the stratified meridian discrete point set and the dimensionless arc length of the stratified meridian, using the dimensionless axial coordinate of the dimensionless blade profile data set of the stacked blade profile as the interpolation point, interpolate the dimensionless arc length of the stratified meridian and the X-direction coordinate of the stratified meridian discrete point set to obtain the X-direction right-angle coordinate of the discrete points of the stacked blade profile; S3243. Based on the stratified meridian discrete point set, using the X-direction right-angle coordinate of the discrete points of the stacked blade profile as the interpolation point, obtain the perpendicular distance from the discrete points of the stacked blade profile to the axis of rotation of the turbomachine; S3244. Based on the perpendicular distance from the discrete points of the stacked blade profile to the axis of rotation of the turbomachine and the dimensionless blade profile data set of the stacked blade profile, calculate the Y-direction right-angle coordinate and the Z-direction right-angle coordinate of the discrete points of the stacked blade profile through the sine function and the cosine function respectively.

[0012] The embodiment of the present invention also provides a blade stacking system, including a reference blade design module, a new rotating blade profile acquisition module, a stacked blade profile acquisition module, and a blade profile generation module.

[0013] Among them, the reference blade design module is used to design the reference blade of the turbomachine blade by the straight-line stacking method; The new rotating blade profile acquisition module is used to intercept the reference blade according to the relative height of the flow passage to obtain a plurality of initial rotating blade profiles, and rotate each of the initial rotating blade profiles around the axis of rotation of the turbomachine so that the stacking center of the initial rotating blade profile passes through the circumferential stacking line to obtain a new rotating blade profile; The stacked blade profile acquisition module is used to axially stack all the new rotating blade profiles according to the axial stacking line to obtain a stacked blade profile; The blade profile generation module is used to stretch the blade profile by using all the stacked blade profiles through the skin method to obtain the blade profile.

[0014] Compared with the prior art, the method of the present invention can keep the blade profile in the annular flow surface unchanged and the blade throat area unchanged during the stacking process, and improve the accuracy of the blade stacking design for flow control. Brief Description of the Drawings

[0015] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following will briefly introduce the drawings required in the embodiments. Obviously, the drawings in the following description are only some embodiments of the present application. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0016] Figure 1 It is a flowchart of the blade stacking method disclosed in the embodiment of the present invention; Figure 2 It is a schematic diagram of the relative height stratified meridian disclosed in the embodiment of the present invention; Figure 3 It is a schematic diagram of obtaining the initial rotary blade profile by intercepting the reference blade disclosed in the embodiment of the present invention; Figure 4 It is a schematic diagram of circumferential stacking disclosed in the embodiment of the present invention; Figure 5 It is a schematic diagram of axial stacking disclosed in the embodiment of the present invention; Figure 6 It is an architecture diagram of the blade stacking system disclosed in the embodiment of the present invention; Among them, 601 is the reference blade design module; 602 is the new rotary blade profile acquisition module; 603 is the stacked blade profile acquisition module; 604 is the blade profile generation module. Detailed Embodiments

[0017] The following will describe the embodiments of the present application in detail with reference to the drawings.

[0018] The following specific examples illustrate the implementation manners of the present application. Those skilled in the art can easily understand other advantages and effects of the present application from the content disclosed in this specification. Obviously, the described embodiments are only 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 implementation manners. Various details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, without conflict, the following embodiments and the features of the embodiments can be combined with each other. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present application without creative efforts belong to the scope of protection of the present application.

[0019] An embodiment of the present invention discloses a blade stacking method. Refer to Figures 1 to 6 as shown, the method includes the following steps: S1. Design a reference blade of a turbomachine blade by a straight stacking method; S2. Intercept a plurality of initial rotary airfoils from the reference blade according to the relative height of the flow passage. Rotate each of the initial rotary airfoils around the rotation axis of the turbomachine so that the stacking center of the initial rotary airfoil passes through the circumferential stacking line to obtain a new rotary airfoil; S3. Axially stack all the new rotary airfoils respectively according to the axial stacking line to obtain a stacked airfoil; S4. Adopt all the stacked airfoils and perform stretching by a skin method to obtain the blade profile.

[0020] Further, in the above step S1, designing a reference blade of a turbomachine blade by a straight stacking method includes: S11. Design a plurality of reference airfoils for the turbomachine blade at different heights. Among them, the number of reference airfoils can be set to 3 - 5. When implementing the present invention, designing reference airfoils for the turbomachine blade at different heights can be done in ways such as equal height, relative height, conical surface height, etc.; S12. Select a characteristic point as the stacking center on each of the reference airfoils. Among them, the stacking center can be any one of the leading edge point of the blade, the trailing edge point of the blade, the centroid point of the blade, and the maximum thickness point of the blade; S13. Stack all the stacking centers onto a radial line passing through the rotation center of the turbomachine. After straight stacking, perform skin stretching to form a reference blade.

[0021] Further, in the above step S2, when intercepting the initial rotary airfoil from the reference blade, generally the number of initial rotary airfoils is related to the airfoil complexity. The number of initial rotary airfoils is directly proportional to the airfoil complexity and is usually not less than 5, including the initial rotary airfoils at two relative heights of 0% and 100%. Among them, intercepting the initial rotary airfoil according to the relative height is as Figure 3As shown. The blade profile complexity includes any one or more of the blade camber, twist angle, thickness, width, surface roughness, and geometric shape, and the relative height is the longitudinal position from the blade root to the blade tip. Specifically, a stratified meridian can be formed according to the discrete point set of the stratified meridian of each reference blade, and each stratified meridian is rotated around the turbine rotation axis to form a blade revolution surface; multiple initial revolution blade profiles are obtained by intercepting all the blade revolution surfaces on the reference blade, and at the same time, the discrete point set of the initial revolution blade profile in the rectangular coordinate can be extracted; according to the discrete point set of the blade profile on the blade revolution surface, the coordinates of the characteristic points in the flow passage are obtained. When obtaining a new revolution blade profile, the new revolution blade profile is discretized to obtain the discrete point set of the new revolution blade profile (X1 n ,Y1 n ,Z1 n ).

[0022] Further, in the above step S3, axially stacking all the new revolution blade profiles according to the axial stacking line to obtain a stacked blade profile includes: S31. For each of the new revolution blade profiles, obtain the discrete point set of the stratified meridian at the relative height of the flow passage where it is located (Mx i ,Mz i ), and calculate the dimensionless arc length Ms of the stratified meridian based on the discrete point set of the stratified meridian i ; S32. According to the discrete point set of the stratified meridian (Mx i ,Mz i ), the dimensionless arc length Ms of the stratified meridian i and the discrete point set of the new revolution blade profile (X1 n ,Y1 n ,Z1 n ), stack the stacking centers of all the new revolution blade profiles on the axial stacking line to obtain a stacked blade profile.

[0023] Further, in the above step S31, obtaining the discrete point set of the stratified meridian at the relative height of the flow passage where it is located (Mx i ,Mz i ) includes: S311. Perform equal-arc-length encryption on the downstream flow passage line and the upstream flow passage line to obtain multiple encrypted point connection lines. Among them, one end of the encrypted point connection line is a downstream flow passage encrypted discrete point, and the other end is an upstream flow passage encrypted discrete point. Specifically, in implementation, the upstream flow passage line and the downstream flow passage line of the flow passage line can be respectively subjected to equal-arc-length encryption, and the number of encrypted points on the upstream flow passage line and the downstream flow passage line is equal. The discrete point of the stratified meridian of the downstream flow passage line in the encrypted point connection line is represented as A i , and the discrete point of the stratified meridian of the upstream flow passage line is represented as B i , and the number of encrypted point connection lines is not less than 1000.

[0024] S312. For each of the encrypted point connections, select a point on each of the encrypted point connections such that the ratio of the length from the point to the downstream channel encrypted discrete points to the length of the encrypted point connection is equal to the relative height of the channel where the new rotating blade profile is located. Specifically, during implementation, the points selected on each encrypted point connection can be represented by M i , such that A i M i 's length to A i B i 's length ratio is equal to the relative height value h of the blade cross-section.

[0025] S313. For each of the encrypted point connections, extract the coordinates of all the selected points on the encrypted point connections to obtain a set of stratified meridian discrete points. The set of stratified meridian discrete points can be represented as (Mx i , Mz i ). (Mx i , Mz i ) respectively represent the coordinates of the i-th stratified meridian discrete point in the X direction and the Z direction in the channel. Among them, i takes values of 1, 2, 3, ……, m, and m is an integer ≥ 1000.

[0026] Furthermore, in the above step S31, calculating the non-dimensional arc length of the stratified meridian based on the set of stratified meridian discrete points includes: S314. Along the channel direction, define the non-dimensional arc length of the stratified meridian of the first stratified meridian discrete point in the set of stratified meridian discrete points as zero; S315. Based on the non-dimensional arc length of the previous stratified meridian discrete point, the coordinates of the current stratified meridian discrete point, and the coordinates of the previous stratified meridian discrete point, calculate the non-dimensional arc length of the stratified meridian of the remaining stratified meridian discrete points except the first one.

[0027] Even further, in the above step S315, 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 non-dimensional arc length of the stratified meridian of the remaining stratified meridian discrete points except the first one. Among them, Ms i is the non-dimensional arc length of the i-th stratified meridian discrete point, and Ms i-1is the dimensionless arc length of the stratified meridian for the (i - 1)-th discrete point of the stratified meridian, (Mx i , Mz i ) are the coordinates of the i-th discrete point of the stratified meridian in the X and Z directions respectively, (Mx i-1 , Mz i-1 ) are the coordinates of the (i - 1)-th discrete point of the stratified meridian in the X and Z directions respectively, and i is an integer greater than or equal to 2.

[0028] Further, in the above step S32, according to the set of discrete points of the stratified meridian (Mx i , Mz i ), the dimensionless arc length Ms of the stratified meridian i and the set of discrete points of the new blade profile (X1 n , Y1 n , Z1 n ), stacking the stacking centers of all the new blade profiles on the axial stacking line to obtain a stacked blade profile, including: S321. Obtain the intersection points of the circumferential stacking line and the projection of each set of discrete points of the stratified meridian (Mx i , Mz i ) on the meridian plane, take the axial coordinate of the intersection point as the axial coordinate T1x of the circumferential stacking center, obtain the intersection points of the axial stacking line and the projection of each set of discrete points of the stratified meridian (Mx i , Mz i ) on the meridian plane, and take the axial coordinate of the intersection point as the axial coordinate T2x of the axial stacking center; S322. According to each set of discrete points of the stratified meridian (Mx i , Mz i ), the dimensionless arc length Ms of the stratified meridian i and the set of discrete points of the new blade profile (X1 n , Y1 n , Z1 n ), obtain the dimensionless blade profile data set (F1 n , G1 n ) of the new blade profile and the dimensionless axial coordinate Q1 of the circumferential stacking center; S323. According to the set of discrete points of the stratified meridian (Mx i , Mz i ) and the dimensionless arc length of the stratified meridian, using the axial coordinate T2x of the axial stacking center as the interpolation point, interpolate the X-direction coordinate Mx of the set of discrete points of the stratified meridian i and the dimensionless arc length Ms of the stratified meridian i to obtain the dimensionless axial coordinate Q2 of the axial stacking center; S324. According to the set of discrete points of the stratified meridian (Mxi ,Mz i ), the dimensionless arc length Ms of the stratified 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 dataset of the new rotating blade profile (F1 n ,G1 n ), and calculate the dimensionless blade profile dataset of the stacked blade profile (F2 n ,G2 n ) and the rectangular coordinate dataset of the discrete points of the stacked blade profile (X2 n ,Y2 n ,Z2 n ).

[0029] Furthermore, in the above step S322, according to each of the stratified meridian discrete point sets (Mx i ,Mz i ), the dimensionless arc length Ms of the stratified meridian i and the new rotating blade profile discrete point set (X1 n ,Y1 n ,Z1 n ), obtain the dimensionless blade profile dataset of the new rotating blade profile (F1 n ,G1 n ), and the dimensionless axial coordinate Q1 of the circumferential stacking center, including: S3221. According to each of the stratified meridian discrete point sets (Mx i ,Mz i ) and the dimensionless arc length Ms of the stratified meridian i , using the X - coordinate X1 in the new rotating blade profile discrete point set (X1 n ,Y1 n ,Z1 n ) as the interpolation point, obtain the dimensionless axial coordinate F1 of the dimensionless blade profile dataset of the new rotating blade profile n . In the present invention, the dimensionless axial coordinate is also the X - direction coordinate (i.e., the axial coordinate of the turbomachine). During implementation, according to M1x in the stratified meridian discrete point set n i and the dimensionless arc length M1s of the stratified meridian i n , using X1 in the rotating blade profile discrete point set as the interpolation point, obtain the dimensionless axial coordinate F1 n ; S3222. Perform atan2 function calculation on the new rotating blade profile discrete point set (X1 n ,Y1 n ,Z1 n ), and obtain the dimensionless lateral coordinate G1 of the dimensionless blade profile dataset of the new rotating blade profile​​n In the present invention, the dimensionless transverse coordinate is also the Y-direction (i.e., the transverse direction of the turbomachine) coordinate. During implementation, according to the Y-direction coordinate Y1 in the discrete point set of the rotating blade profile n and the Z-direction coordinate Z1 n , the atan2 function is calculated to obtain G1 n , that is, G1 n =atan2(Y1 n , Z1 n ); S3223. According to the discrete point set of the stratified meridian (Mx i , Mz i ) and the dimensionless arc length Ms of the stratified meridian i , with the circumferential stacking center axial coordinate T1x as the interpolation point, interpolate the X-direction coordinate Mx of the discrete point set of the stratified meridian i and the dimensionless arc length Ms of the stratified meridian i to obtain the dimensionless axial coordinate Q1 of the circumferential stacking center.

[0030] Furthermore, in the above step S324, according to the discrete point set of the stratified meridian (Mx i , Mz i ), the dimensionless arc length Ms of the stratified 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 rotating blade profile (F1 n , G1 n ), calculate to obtain the dimensionless blade profile data set of the stacked blade profile (F2 n , G2 n ) and the rectangular coordinate data set of the discrete points of the stacked blade profile (X2 n , Y2 n , Z2 n ), including: 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 dimensionless blade profile data set of the new rotating blade profile (F1 n , G1 n ) to obtain the dimensionless blade profile data set of the stacked blade profile; specifically, through the formula F2 n =F1 n +Q2-Q1, G2 n =G1 n calculate the dimensionless blade profile 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, G2n is the dimensionless transverse coordinate of the nth dimensionless blade profile data of the stacked blade profile.

[0031] S3242. Based on the stratified meridian discrete point set (Mx i , Mz i ), the stratified meridian dimensionless arc length Ms i , using the dimensionless blade profile data set of the stacked blade profile (F2 n , G2 n ) as the interpolation points, interpolate the stratified meridian dimensionless arc length Ms n and the X-direction coordinate Mx of the stratified meridian discrete point set i to calculate the X-direction rectangular coordinate X2 of the discrete points of the stacked blade profile i ; n S3243. Based on the stratified meridian discrete point set (Mx i , Mz i ), using the X-direction rectangular coordinate X2 of the discrete points of the stacked blade profile n as the interpolation point, obtain the perpendicular distance from the discrete points of the stacked blade profile to the rotation axis of the turbomachine; S3244. Based on the perpendicular distance from the discrete points of the stacked blade profile to the rotation axis of the turbomachine and the dimensionless blade profile data set of the stacked blade profile (F2 n , G2 n ), calculate the Y-direction rectangular coordinate Y2 n and the Z-direction rectangular coordinate Z2 n of the discrete points of the stacked blade profile through the sine function and the cosine function respectively.

[0032] The specific processes of the above steps S3241 - S3244 are as follows: According to each dimensionless blade profile data set of the stacked blade profile (F2 n , G2 n ), the stratified meridian dimensionless arc length M1s i , calculate the rectangular coordinate data set of the discrete points of the stacked blade profile (X2 n , Y2 n , Z2 n ), where X2 n , Y2 n , Z2 n are the coordinates of the nth discrete point of the stacked blade profile in the X direction, Y direction, and Z direction respectively. Among them, X2 n can be calculated in the following way: Using F2 n as the interpolation point, interpolate the array (Ms i , Mx i ) to calculate X2 n . Y2n and Z2 n can be calculated in the following way: taking X2 n as the interpolation point, interpolating the array (Mx i , Mz i ) to obtain the vertical distance R2 from the nth discrete point of the stacked blade profile to the axis of rotation of the turbomachine n , and then calculating Y2 n = cos(G1 n ) * R2 n , Z2 n = sin(G1 n ) * R2 n .

[0033] Compared with the prior art, the method of the present invention can keep the blade profile in the annular flow surface unchanged and the blade throat area unchanged during the stacking process, and improve the accuracy of the blade stacking design for flow control.

[0034] Based on the same inventive concept, an embodiment of the present invention also provides a blade stacking system as described in the following embodiments. Since the principle of the blade stacking system for solving problems 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 described again. Hereinafter, the term "unit" or "module" may be a combination of software and / or hardware that can achieve a predetermined function. Although the devices described in the following embodiments are preferably implemented in software, implementation in hardware, or a combination of software and hardware is also possible and contemplated.

[0035] Figure 6 is a structural block diagram of a blade stacking system applicable to a turbomachine disclosed in an embodiment of the present invention. As Figure 6 shown, the system includes a reference blade design module 601, a new rotating blade profile acquisition module 602, a stacked blade profile acquisition module 603, and a blade profile generation module 604. The following describes this structure.

[0036] Among them, the reference blade design module 601 is used to design the reference blade of the turbomachine blade by the straight stacking method; The new rotating blade profile acquisition module 602 is used to intercept a plurality of initial rotating blade profiles from the reference blade according to the relative height of the flow passage, and rotate each of the initial rotating blade profiles around the axis of rotation of the turbomachine so that the stacking center of the initial rotating blade profile passes through the circumferential stacking line to obtain a new rotating blade profile; The stacked blade profile acquisition module 603 is used to axially stack all the new rotating blade profiles according to the axial stacking line to obtain a stacked blade profile; The blade profile generation module 604 is configured to stretch and obtain the blade profile by using all the stacked airfoils through the skinning method.

[0037] In this embodiment, a computer device is provided, including a memory, a processor, and a computer program stored on the memory and executable on the processor. When the processor executes the computer program, the above-mentioned arbitrary blade stacking method is implemented.

[0038] Specifically, the computer device may be a computer terminal, a server, or a similar computing device.

[0039] In this embodiment, a computer-readable storage medium is provided, and the computer-readable storage medium stores a computer program for executing the above-mentioned arbitrary blade stacking method.

[0040] Specifically, the computer-readable storage medium includes permanent and non-permanent, removable and non-removable media, and information storage can be implemented by any method or technology. The information may 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 technologies, compact disc read-only memory (CD-ROM), digital versatile disc (DVD) or other optical storage, magnetic cassette tapes, magnetic disk storage or other magnetic storage devices, or any other non-transmission medium that can be used to store information accessible by a computing device. As defined herein, computer-readable storage media do not include transitory computer-readable media, such as modulated data signals and carrier waves.

[0041] Obviously, those skilled in the art should understand that the above-mentioned modules or steps of the embodiments of the present invention can be implemented by a general-purpose computing device. They can be concentrated on a single computing device or distributed on a network composed of multiple computing devices. Optionally, they can be implemented by program codes executable by the computing device, so that they can be stored in a storage device and executed by the computing device. And in some cases, the steps shown or described can be executed in a different order than here, or they can be separately fabricated into individual integrated circuit modules, or multiple modules or steps among them can be fabricated into a single integrated circuit module to implement. Thus, the embodiments of the present invention are not limited to any specific combination of hardware and software.

[0042] The above are only the preferred embodiments of the present invention and are not intended to limit the present invention. For those skilled in the art, various modifications and variations can be made to the embodiments of the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. A blade stacking method, characterized in that, For the stacking design of turbine blades, the method includes: Designing a reference blade of the turbine blade by a straight stacking method; Intercepting a plurality of initial rotary airfoils from the reference blade according to the relative height of the flow passage, and rotating each of the initial rotary airfoils around the rotation axis of the turbine so that the stacking center of the initial rotary airfoil passes through the circumferential stacking line to obtain a new rotary airfoil; Axially stacking all the new rotary airfoils respectively according to the axial stacking line to obtain a stacked airfoil; Adopting all the stacked airfoils and stretching them by a skinning method to obtain the blade profile.

2. The blade stacking method according to claim 1, wherein Designing a reference blade of the turbine blade by a straight stacking method, including: Designing a plurality of reference airfoils for the turbine blade at different heights; Selecting characteristic points on each of the reference airfoils as stacking centers; Stacking all the stacking centers onto a radial line passing through the rotation center of the turbine and performing skinning stretching to form a reference blade.

3. The blade stacking method according to claim 1, wherein Axially stacking all the new rotary airfoils respectively according to the axial stacking line to obtain a stacked airfoil, including: For each of the new rotary airfoils, obtaining a discrete point set of the stratified meridian at the relative height of the flow passage where it is located, and calculating the dimensionless arc length of the stratified meridian according to the discrete point set of the stratified meridian; According to the discrete point set of the stratified meridian, the dimensionless arc length of the stratified meridian and the discrete point set of the new rotary airfoil, stacking the stacking centers of all the new rotary airfoils on the axial stacking line to obtain a stacked airfoil.

4. The blade stacking method according to claim 3, wherein For each of the new rotary airfoils, obtaining a discrete point set of the stratified meridian at the relative height of the flow passage where it is located, including: Performing equal-arc-length encryption on the downstream flow passage line and the upstream flow passage line to obtain a plurality of encrypted point connection lines, wherein one end of each encrypted point connection line is a downstream flow passage encrypted discrete point and the other end is an upstream flow passage encrypted discrete point; For each of the encrypted point connection lines, selecting a point on each of the encrypted point connection lines such that the ratio of the length between the point and the downstream flow passage encrypted discrete point to the length of the encrypted point connection line is equal to the relative height of the flow passage where the new rotary airfoil is located; For each of the encrypted point connection lines, extracting the coordinates of all the points selected on the encrypted point connection lines to obtain a discrete point set of the stratified meridian.

5. The blade stacking method according to claim 3, characterized in that, Calculating the dimensionless arc length of the stratified meridian according to the discrete point set of the stratified meridian, including: Along the flow passage direction, defining the dimensionless arc length of the stratified meridian of the first stratified meridian discrete point in the discrete point set of the stratified meridian as zero; Calculating the dimensionless arc length of the remaining stratified meridian discrete points except the first stratified meridian discrete point according to the dimensionless arc length of the previous stratified meridian discrete point, the coordinates of the current stratified meridian discrete point and the coordinates of the previous stratified meridian discrete point.

6. The blade stacking method according to claim 5, wherein 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 stratified meridian discrete points except the first stratified meridian discrete point, where Ms i is the dimensionless arc length of the i-th stratified meridian discrete point, Ms i-1 is the dimensionless arc length of the (i - 1)-th stratified meridian discrete point, (Mx i , Mz i ) are the coordinates of the i-th stratified meridian discrete point in the X and Z directions respectively, (Mx i-1 , Mz i-1 ) are the coordinates of the (i - 1)-th stratified meridian discrete point in the X and Z directions respectively, and i is an integer greater than or equal to 2.

7. The blade stacking method according to claim 3, wherein According to the discrete point set of the stratified meridian, the dimensionless arc length of the stratified meridian and the discrete point set of the new rotary airfoil, stacking the stacking centers of all the new rotary airfoils on the axial stacking line to obtain a stacked airfoil, including: Obtain the intersection points of the circumferential stacking line and the discrete point sets of each of the stratified meridians on the meridional plane projection, take the axial coordinates of the intersection points as the axial coordinates of the circumferential stacking center, obtain the intersection points of the axial stacking line and the discrete point sets of each of the stratified meridians on the meridional plane projection, and take the axial coordinates of the intersection points as the axial coordinates of the axial stacking center; Obtain the dimensionless airfoil data set of the new rotating airfoil and the dimensionless axial coordinates of the circumferential stacking center according to each of the discrete point sets of the stratified meridians, the dimensionless arc length of the stratified meridian, and the discrete point set of the new rotating airfoil; According to the discrete point set of the stratified meridian and the dimensionless arc length of the stratified meridian, taking the axial coordinates of the axial stacking center as the interpolation points, interpolate the X-direction coordinates of the discrete point set of the stratified meridian and the dimensionless arc length of the stratified meridian to obtain the dimensionless axial coordinates of the axial stacking center; Calculate the dimensionless airfoil data set of the stacked airfoil and the right-angle coordinate data set of the discrete points of the stacked airfoil according to the discrete point set of the stratified meridian, the dimensionless arc length of the stratified meridian, the dimensionless axial coordinates of the circumferential stacking center, the dimensionless axial coordinates of the axial stacking center, and the dimensionless airfoil data set of the new rotating airfoil.

8. The blade stacking method according to claim 7, wherein, Obtain the dimensionless airfoil data set of the new rotating airfoil and the dimensionless axial coordinates of the circumferential stacking center according to each of the discrete point sets of the stratified meridians, the dimensionless arc length of the stratified meridian, and the discrete point set of the new rotating airfoil, including: According to each of the discrete point sets of the stratified meridians and the dimensionless arc length of the stratified meridian, taking the X-direction coordinates in the discrete point set of the new rotating airfoil as the interpolation points, obtain the dimensionless axial coordinates of the dimensionless airfoil data set of the new rotating airfoil; Perform atan2 function calculation on the discrete point set of the new rotating airfoil to obtain the dimensionless lateral coordinates of the dimensionless airfoil data set of the new rotating airfoil; According to the discrete point set of the stratified meridian and the dimensionless arc length of the stratified meridian, taking the axial coordinates of the circumferential stacking center as the interpolation points, interpolate the X-direction coordinates of the discrete point set of the stratified meridian and the dimensionless arc length of the stratified meridian to obtain the dimensionless axial coordinates of the circumferential stacking center.

9. The blade stacking method according to claim 7, wherein Calculate the dimensionless airfoil data set of the stacked airfoil and the right-angle coordinate data set of the discrete points of the stacked airfoil according to the discrete point set of the stratified meridian, the dimensionless arc length of the stratified meridian, the dimensionless axial coordinates of the circumferential stacking center, the dimensionless axial coordinates of the axial stacking center, and the dimensionless airfoil data set of the new rotating airfoil, including: Translate the dimensionless airfoil data set of the new rotating airfoil according to the difference between the dimensionless axial coordinates of the circumferential stacking center and the dimensionless axial coordinates of the axial stacking center to obtain the dimensionless airfoil data set of the stacked airfoil; According to the discrete point set of the stratified meridian and the dimensionless arc length of the stratified meridian, taking the dimensionless axial coordinates of the dimensionless airfoil data set of the stacked airfoil as the interpolation points, interpolate the dimensionless arc length of the stratified meridian and the X-direction coordinates of the discrete point set of the stratified meridian to obtain the X-direction right-angle coordinates of the discrete points of the stacked airfoil; According to the set of discrete points of the hierarchical meridian, using the X-direction rectangular coordinates of the discrete points of the stacked blade profile as interpolation points, the vertical distance from the discrete points of the stacked blade profile to the rotation axis of the turbomachine is obtained; According to the vertical distance from the discrete points of the stacked blade profile to the rotation axis of the turbomachine and the dimensionless blade profile data set of the stacked blade profile, the Y-direction rectangular coordinates and Z-direction rectangular coordinates of the discrete points of the stacked blade profile are calculated respectively through the sine function and the cosine function.

10. A blade stacking system, characterized in that, Including: A reference blade design module, which is used to design the reference blade of the turbomachine blade by the straight stacking method; A new rotary blade profile acquisition module, which is used to intercept a plurality of initial rotary blade profiles from the reference blade according to the relative height of the flow passage, and rotate each of the initial rotary blade profiles around the rotation axis of the turbomachine so that the stacking center of the initial rotary blade profile passes through the circumferential stacking line to obtain a new rotary blade profile; A stacked blade profile acquisition module, which is used to perform axial stacking on all the new rotary blade profiles respectively according to the axial stacking line to obtain a stacked blade profile; A blade outer shape generation module, which is used to adopt all the stacked blade profiles and perform stretching through the skinning method to generate the blade outer shape.

Images