Turbine blade transplanting method and system

Abstract

The invention belongs to the technical field of turbines, and provides a transplanting method and system for turbine blades, and the method comprises the steps: dividing an original turbine blade into a plurality of blade sections; obtaining a layered meridian discrete point set and a layered meridian dimensionless arc length of the relative height of the blade section; calculating the blade profile discrete point set of the original blade revolution surface and the original axial coordinates of the feature points in the original flow channel, and calculating the new axial coordinates of the feature points in the new flow channel; obtaining a new blade profile rectangular coordinate data set of all blade sections in the new runner; and adopting the new blade profile rectangular coordinate data set of all the blade sections, and performing stretching through a skin method to obtain the blade profile under the new runner. The blade can be transplanted in different flow channels, and the characteristics of the blade can be kept basically unchanged before and after transplanting, so that the excellent blade can be repeatedly referred and inherited.

Description

Technical Field

[0001] The present invention belongs to the technical field of turbomachines and relates to a method and system for transplanting turbomachine blades. Background Technique

[0002] Blade design is a very crucial link in the aerodynamic design of turbomachines. Since blade design is closely related to the shape and size of the turbomachine flow passage, etc., the shapes and sizes of the flow passages of different turbomachine schemes are usually different, and excellent blades are difficult to be borrowed and inherited in different turbomachine schemes. Therefore, blade design is also one of the time-consuming links in the aerodynamic design of turbomachines.

[0003] Currently, when facing a new scheme for the aerodynamic design of turbomachines, it is often necessary to redesign the blades, which greatly increases the design cost and cycle. Summary of the Invention

[0004] In order to solve the technical problem that the design cycle and cost are greatly increased due to the need to redesign the blades during the aerodynamic design of turbomachines, the present invention discloses a method for transplanting turbomachine blades. This method can realize the transplantation of blades in different flow passages and keep their characteristics basically unchanged before and after transplantation, which enables excellent blades to be repeatedly borrowed and inherited. The method is used to transplant the original turbomachine blades from the original flow passage to the new flow passage, and includes the following steps: S1. Select a characteristic point on the original turbomachine blade as the transplantation reference, and divide the original turbomachine blade into multiple blade sections according to the blade profile complexity and relative height; S2. For each blade section, obtain the discrete point set of the stratified meridian at its relative height, and calculate the dimensionless arc length of the stratified meridian based on the discrete point set of the stratified meridian. Among them, the discrete point set of the stratified meridian includes the original discrete point set of the stratified meridian and the new discrete point set of the stratified meridian, and the dimensionless arc length of the stratified meridian includes the original dimensionless arc length of the stratified meridian and the new dimensionless arc length of the stratified meridian; S3. According to the original discrete point set of the stratified meridian of each blade section, obtain the discrete point set of the blade revolution surface profile of the original blade and the original axial coordinate of the characteristic point in the original flow passage; according to the turbomachine design requirements and the given position of the characteristic point in the new flow passage, obtain the new axial coordinate of the characteristic point in the new flow passage; S4. Through the discrete point set of the stratified meridian, the dimensionless arc length of the stratified meridian, the discrete point set of the blade revolution surface profile of the original blade, the original axial coordinate, and the new axial coordinate, obtain the new blade profile rectangular coordinate data set of all the blade sections in the new flow passage; S5. Adopt the new blade profile rectangular coordinate data set of all the blade sections, and perform stretching by the skinning method to obtain the blade profile under the new flow passage.

[0005] Further, in the above step S2, for each of the blade sections, obtaining a discrete point set of the stratified meridian line at the relative height where it is located, including: S21. Performing equal-arc-length encryption on the downstream channel line and the upstream channel line to obtain a plurality of encrypted point connection lines, wherein 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; S22. For each of the blade sections, selecting 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 where the blade section is located; S23. For each of the blade sections, extracting the coordinates of the points selected on all the encrypted point connection lines to obtain a discrete point set of the stratified meridian line.

[0006] Further, in the above step S2, calculating the dimensionless arc length of the stratified meridian line according to the discrete point set of the stratified meridian line, including: S24. Along the flow channel direction, defining the dimensionless arc length of the stratified meridian line of the first stratified meridian line discrete point in the discrete point set of the stratified meridian line as zero; S25. Calculating the dimensionless arc length of the stratified meridian line of the remaining stratified meridian line discrete points except the first stratified meridian line discrete point according to the dimensionless arc length of the previous stratified meridian line discrete point, the coordinates of the current stratified meridian line discrete point, and the coordinates of the previous stratified meridian line discrete point.

[0007] Even further, in the above step S22, 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 Calculating the dimensionless arc length of the stratified meridian line of the remaining stratified meridian line discrete points except the first stratified meridian line discrete point, where Ms i is the dimensionless arc length of the i-th stratified meridian line discrete point, Ms i-1 is the dimensionless arc length of the (i - 1)-th stratified meridian line discrete point, (Mx i ,Mz i ) are the coordinates of the i-th stratified meridian line discrete point, (Mx i-1 ,Mz i-1 ) are the coordinates of the (i - 1)-th stratified meridian line discrete point in the X direction and the Z direction respectively, and i is an integer greater than or equal to 2.

[0008] Further, in the above step S3, according to the original stratified meridian discrete point sets of each of the blade cross-sections, obtaining the original blade revolution surface profile discrete point set and the original axial coordinates of the characteristic points in the original flow passage includes: S31. Form the original stratified meridians according to the original stratified meridian discrete point sets of each of the blade cross-sections, and rotate each of the original stratified meridians around the rotary shaft of the turbomachine to form the original blade revolution surface; S32. Intercept the blades of the original turbomachine with all of the original blade revolution surfaces to obtain the original blade revolution surface profile discrete point set in rectangular coordinates; S33. According to the original blade revolution surface profile discrete point set, obtain the original axial coordinates of the characteristic points in the original flow passage.

[0009] Further, in the above step S4, through the stratified meridian discrete point sets, the dimensionless arc lengths of the stratified meridians, the original blade revolution surface profile discrete point set, the original axial coordinates, and the new axial coordinates, obtaining the new blade profile rectangular coordinate data sets of all of the blade cross-sections in the new flow passage includes: S41. Through the original stratified meridian discrete point sets, the dimensionless arc lengths of the original stratified meridians, the original blade revolution surface profile discrete point set, and the original axial coordinates, obtain the original blade dimensionless profile data sets and the original characteristic point dimensionless axial coordinates of each of the blade cross-sections by interpolation; S42. According to the new stratified meridian discrete point sets, the dimensionless arc lengths of the new stratified meridians, and the new axial coordinates, obtain the new characteristic point dimensionless axial coordinates of each of the blade cross-sections by interpolation; S43. According to the original characteristic point dimensionless axial coordinates, the new characteristic point dimensionless axial coordinates, the original blade dimensionless profile data sets, the new stratified meridian discrete point sets, and the dimensionless arc lengths of the new stratified meridians, obtain the new blade profile rectangular coordinate data sets of each of the blade cross-sections.

[0010] Even further, in the above step S41, through the original stratified meridian discrete point sets, the dimensionless arc lengths of the original stratified meridians, the original blade revolution surface profile discrete point set, and the original axial coordinates, obtaining the original blade dimensionless profile data sets and the original characteristic point dimensionless axial coordinates of each of the blade cross-sections by interpolation includes: S411. According to the original stratified meridian discrete point sets and the dimensionless arc lengths of the original stratified meridians, using the original blade revolution surface profile discrete point set as the interpolation points, obtain the dimensionless axial coordinates of the original blade dimensionless profile data sets; S412. Perform atan2 function calculations on the original blade revolution surface profile discrete point set to obtain the dimensionless transverse coordinates of the original blade dimensionless profile data sets.

[0011] S413. Based on the original stratified meridian discrete point set and the dimensionless arc length of the original stratified meridian, using the original axial coordinate as the interpolation point, obtain the dimensionless axial coordinates of the original characteristic points.

[0012] Further, the interpolation operation in step S42 is the same as steps S411 - S413 above, and thus will not be elaborated herein in the present invention.

[0013] Furthermore, in step S43 above, based on the dimensionless axial coordinates of the original characteristic points, the dimensionless axial coordinates of the new characteristic points, the dimensionless blade profile data set of the original blade, the new stratified meridian discrete point set, and the dimensionless arc length of the new stratified meridian, obtain the new blade profile rectangular coordinate data set for each blade section, including: S431. Translate the dimensionless blade profile data set of the original blade according to the difference between the dimensionless axial coordinates of the original characteristic points and the dimensionless axial coordinates of the new characteristic points to obtain the dimensionless blade profile data set of the new blade; S432. Based on the dimensionless arc length of the new stratified meridian and the new stratified meridian discrete point set, using the axial coordinate of the dimensionless blade profile data set of the new blade as the interpolation point, obtain the X - coordinate of the new blade profile rectangular coordinate data set of the blade section; S433. Based on the new stratified meridian discrete point set, using the X - coordinate of the new blade profile rectangular coordinate data set of the blade section as the interpolation point, obtain the vertical distance from the new blade profile discrete points of the blade section to the turbine rotation axis; S434. Based on the vertical distance from the new blade profile discrete points of the blade section to the turbine rotation axis and the dimensionless blade profile data set of the new blade, perform function calculations to obtain the Y - coordinate and Z - coordinate of the new blade profile rectangular coordinate data set of the blade section.

[0014] The embodiment of the present invention also provides a transplantation system for turbine blades, including a blade division module, a first calculation module, a second calculation module, a third calculation module, and a transplantation module.

[0015] Among them, the blade division module is used to select a characteristic point on the original turbine blade as the transplantation reference, and divide the original turbine blade into multiple blade sections according to the blade profile complexity and relative height; The first calculation module is used to, for each blade section, obtain the stratified meridian discrete point set at its corresponding relative height, and calculate the dimensionless arc length of the stratified meridian based on the stratified meridian discrete point set. Among them, the stratified meridian discrete point set includes the original stratified meridian discrete point set and the new stratified meridian discrete point set, and the dimensionless arc length of the stratified meridian includes the original dimensionless arc length of the stratified meridian and the new dimensionless arc length of the stratified meridian; The second calculation module is configured to obtain the discrete point set of the original blade rotating surface airfoil and the original axial coordinate of the feature point in the original flow channel according to the discrete point set of the original layered meridian of each blade section; obtain the new axial coordinate of the feature point in the new flow channel according to the design requirements of the turbomachine and the given position of the feature point in the new flow channel; The third calculation module is configured to obtain the new airfoil rectangular coordinate data set of all the blade sections in the new flow channel through the discrete point set of the layered meridian, the dimensionless arc length of the layered meridian, the discrete point set of the original blade rotating surface airfoil, the original axial coordinate, and the new axial coordinate; The transplantation module is configured to stretch by the skinning method using the new airfoil rectangular coordinate data set of all the blade sections to obtain the blade shape under the new flow channel.

[0016] Compared with the prior art, the beneficial effects that can be achieved by at least one of the above technical solutions adopted in the embodiments of the present specification at least include: The method for transplanting the turbomachine blade provided by the present invention enables the original turbomachine blade to be transplanted in different flow channels while keeping its characteristics basically unchanged. This enables excellent blade design results to be reused and inherited repeatedly in different turbomachines regardless of the shape and size of the flow channel, thereby greatly improving the reusability of the blade design results and the blade design efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required to be used in the embodiments will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments of the present application. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0018] Figure 1 It is a flowchart of the method for transplanting the turbomachine blade disclosed in the embodiments of the present invention; Figure 2 It is the flow line of the original flow channel and the position of the original turbomachine blade in the original flow channel disclosed in the embodiments of the present invention; Figure 3 It is the flow line of the new flow channel and the position of the original turbomachine blade transplanted into the new flow channel disclosed in the embodiments of the present invention; Figure 4 It is a schematic diagram of intercepting the blade section according to the relative height disclosed in the embodiments of the present invention; Figure 5 It is a comparison diagram of the isentropic Mach number on the blade surface before and after transplantation disclosed in the embodiments of the present invention; Figure 6 It is an architecture diagram of the turbomachine blade transplantation system disclosed in the embodiments of the present invention; Among them, 601 is the blade division module; 602 is the first calculation module; 603 is the second calculation module; 604 is the third calculation module; 605 is the transplantation module. Detailed implementation manners

[0019] The embodiments of the present application will be described in detail below with reference to the accompanying drawings.

[0020] The following uses specific specific examples to 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 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 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 in the present application without creative efforts belong to the scope protected by the present application.

[0021] An embodiment of the present invention discloses a method for transplanting a turbine blade. The method is used to transplant the original turbine blade from the original flow channel to a new flow channel. Refer to Figure 1 、 Figure 2 、 Figure 3 and Figure 4 as shown, and specifically includes the following steps: S1. Select a feature point on the original turbine blade as the transplantation reference, and divide the original turbine blade into multiple blade sections according to the blade profile complexity and relative height; S2. For each of the blade sections, obtain the discrete point set of the stratified meridian at its relative height, and calculate the dimensionless arc length of the stratified meridian based on the discrete point set of the stratified meridian. Among them, the discrete point set of the stratified meridian includes the original discrete point set of the stratified meridian and the new discrete point set of the stratified meridian, and the dimensionless arc length of the stratified meridian includes the original dimensionless arc length of the stratified meridian and the new dimensionless arc length of the stratified meridian; S3. According to the original discrete point set of the stratified meridian of each blade section, obtain the discrete point set of the original blade revolution surface profile and the original axial coordinate of the feature point in the original flow channel; according to the design requirements of the turbine and the given position of the feature point in the new flow channel, obtain the new axial coordinate T2x of the feature point in the new flow channel; S4. Through the discrete point set of the stratified meridian, the dimensionless arc length of the stratified meridian, the discrete point set of the original blade revolution surface profile, the original axial coordinate, and the new axial coordinate, obtain the new blade profile rectangular coordinate data set of all the blade sections in the new flow channel; S5. Adopt the new airfoil rectangular coordinate data set of all the blade sections, and obtain the blade profile under the new flow channel through stretching by the skin method.

[0022] Further, in the above step S1, the characteristic points include any one of the blade leading edge point, the blade trailing edge point, the blade centroid point, and the blade maximum thickness point. Generally speaking, the number of blade sections is related to the airfoil complexity, and the number of blade sections is directly proportional to the airfoil complexity, usually not less than 10, including blade sections at two relative heights of 0% and 100%. The schematic diagram of intercepting the blade section according to the relative height is as Figure 4 shown. The airfoil complexity includes any one or more of the blade camber, twist angle, thickness, width, surface roughness, and geometric shape. The relative height is the longitudinal position from the blade base to the blade top.

[0023] Further, in the above step S2, for each of the blade sections, obtain the stratified meridian discrete point set at its corresponding relative height, including: S21. Perform equal arc length encryption on the downstream flow channel line and the upstream flow channel line to obtain multiple encrypted point connection lines. Among them, one end of the encrypted point connection line is the downstream flow channel encrypted discrete point, and the other end is the upstream flow channel encrypted discrete point. Specifically, during implementation, equal arc length encryption can be performed on the upstream flow channel line and the downstream flow channel line of the original / new flow channel line, and the number of encrypted points on the upstream flow channel line and the downstream flow channel line is equal. The stratified meridian discrete points of the downstream flow channel line in the encrypted point connection line are represented as A i , and the stratified meridian discrete points of the upstream flow channel line are represented as B i , and the number of encrypted point connection lines is not less than 1000.

[0024] S22. For each of the blade sections, select a point on each of the encrypted point connection lines such that the ratio of the length from the point to the downstream flow channel encrypted discrete point to the length of the encrypted point connection line is equal to the relative height where the blade section is located. Specifically, during implementation, the points selected on each of the encrypted point connection lines can be represented by M i , such that the ratio of the length of A i M i to the length of A i B i is equal to the relative height value h where the blade section is located.

[0025] S23. For each of the blade sections, extract the coordinates of all the points selected on the encrypted point connection lines to obtain the stratified meridian discrete point set. Connect the points selected on all the encrypted point connection lines of each blade section to form the stratified meridian of the blade section, and its stratified meridian discrete point set can be represented as (Mx i , Mz i ). Among them, the original stratified meridian discrete point set can be represented as (M1x i, M1z i ), (M1x i , M1z i ) represent the X - coordinate and Z - coordinate of the i - th discrete point of the stratified meridian in the original flow channel respectively. The new set of discrete points of the stratified meridian can be expressed as (M2x i , M2z i ), (M2x i , M2z i ) represent the X - coordinate and Z - coordinate of the i - th discrete point of the stratified meridian in the new flow channel respectively, where i takes values 1, 2, 3, ……, m, m is an integer ≥ 1000, M1 represents the original flow channel, and M2 represents the new flow channel.

[0026] Furthermore, in the above step S2, calculating the dimensionless arc length of the stratified meridian based on the set of discrete points of the stratified meridian includes: S24. Along the flow - channel direction, define the dimensionless arc length of the stratified meridian of the first discrete point in the set of discrete points of the stratified meridian as zero.

[0027] S25. Calculate the dimensionless arc length of the stratified meridian of the remaining discrete points of the stratified meridian except the first discrete point of the stratified meridian based on the dimensionless arc length of the previous discrete point of the stratified meridian, the coordinates of the current discrete point of the stratified meridian, and the coordinates of the previous discrete point of the stratified meridian.

[0028] Even further, in the above step S22, 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 discrete points of the stratified meridian except the first discrete point of the stratified meridian, where Ms i is the dimensionless arc length of the i - th discrete point of the stratified meridian, Ms i-1 is the dimensionless arc length of 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, (Mx i-1 , Mz i-1 ) are the coordinates of the (i - 1) - th discrete point of the stratified meridian, and i is an integer ≥ 2.

[0029] Among them, the dimensionless arc length of the original stratified meridian M1s iIt can be expressed as: when i = 1, M1s i = 0; when i ≥ 2, M1s i = M1s i-1 + ((M1x i - M1x i-1 ) 2 + (M1z i - M1z i-1 ) 2 ) 0.5 / M1z i .

[0030] The dimensionless arc length of the new stratified meridian M2s i It can be expressed as: when i = 1, M2s i = 0; when i ≥ 2, M2s i = M2s i-1 + ((M2x i - M2x i-1 ) 2 + (M2z i - M2z i-1 ) 2 ) 0.5 / M2z i .

[0031] Furthermore, in the above step S3, according to the original stratified meridian discrete point set of each blade section, obtaining the original blade revolution surface profile discrete point set and the original axial coordinate of the characteristic point in the original flow channel includes: S31. Form the original stratified meridian according to the original stratified meridian discrete point set of each blade section, and rotate each original stratified meridian around the rotation axis of the turbomachine to form the original blade revolution surface.

[0032] S32. Use all the original blade revolution surfaces to intercept the original turbomachine blades to obtain the original blade revolution surface profile discrete point set in rectangular coordinates. The original blade revolution surface profile discrete point set can be expressed as (X1 n , Y1 n , Z1 n ), where n is the number of discrete points of the original blade revolution surface profile, and the value range is 1, 2, 3,..., q. X1 n is the coordinate of the nth discrete point of the original blade revolution surface profile in the X direction, Y1 n is the coordinate of the nth discrete point of the original blade revolution surface profile in the Y direction, and Z1 n is the coordinate of the nth discrete point of the original blade revolution surface profile in the Z direction.

[0033] S33. According to the original blade revolution surface profile discrete point set, obtain the original axial coordinate T1x of the characteristic point in the original flow channel.

[0034] Further, in the above step S4, based on the hierarchical meridian discrete point set, the dimensionless arc length of the hierarchical meridian, the discrete point set of the original blade revolution surface profile, the original axial coordinate, and the new axial coordinate, the new leaf profile rectangular coordinate data set of all the blade sections in the new flow channel is obtained, including: S41. Based on the original hierarchical meridian discrete point set, the dimensionless arc length of the original hierarchical meridian, the discrete point set of the original blade revolution surface profile, and the original axial coordinate, the original blade dimensionless profile data set of each blade section and the dimensionless axial coordinate Q1 of the original characteristic points are obtained by interpolation; S42. Based on the new hierarchical meridian discrete point set, the dimensionless arc length parameter of the new hierarchical meridian, and the new axial coordinate, the dimensionless axial coordinate Q2 of the new characteristic points of each blade section is obtained by interpolating discrete points; S43. Based on the dimensionless axial coordinate of the original characteristic points, the dimensionless axial coordinate of the new characteristic points, the original blade dimensionless profile data set, the new hierarchical meridian discrete point set, and the dimensionless arc length of the new hierarchical meridian, the new leaf profile rectangular coordinate data set of each blade section is obtained.

[0035] Furthermore, in the above step S41, based on the original hierarchical meridian discrete point set, the dimensionless arc length of the original hierarchical meridian, the discrete point set of the original blade revolution surface profile, and the original axial coordinate, the original blade dimensionless profile data set of each blade section and the dimensionless axial coordinate Q1 of the original characteristic points are obtained by interpolation, including: S411. Based on the original hierarchical meridian discrete point set and the dimensionless arc length of the original hierarchical meridian, taking the discrete point set of the original blade revolution surface profile as the interpolation points, the dimensionless axial coordinate F1 of the original blade dimensionless profile data set is obtained n , in the present invention, the dimensionless axial coordinate is also the X-direction (i.e., the axial direction of the turbomachine) coordinate. During implementation, according to M1x in the original hierarchical meridian discrete point set i and the dimensionless arc length parameter M1s of the original hierarchical meridian i , taking X1 in the discrete point set of the original blade revolution surface profile n as the interpolation points, the axial coordinate F1 of the original blade dimensionless profile data set is obtained n .

[0036] S412. Perform atan2 function calculation on the discrete point set of the original blade revolution surface profile to obtain the dimensionless transverse coordinate G1 of the original blade dimensionless profile data set 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 Y1 in the discrete point set of the original blade revolution surface profile n and Z1 n, perform the atan2 function calculation to obtain G1 n , that is, G1 n =atan2(Y1 n , Z1 n ).

[0037] S413. According to the original stratified meridian discrete point set and the original stratified meridian dimensionless arc length, using the original axial coordinate as the interpolation point, obtain the original characteristic point dimensionless axial coordinate Q1. During implementation, using the original axial coordinate T1x as the interpolation point, for M1x in the original stratified meridian discrete point set i and the original stratified meridian dimensionless arc length M1s i to form an array (M1x i , M1s i ) for interpolation to obtain the original characteristic point dimensionless axial coordinate Q1.

[0038] Further, in step S42, according to the new stratified meridian discrete point set (M2x i , M2z i ) and the new stratified meridian dimensionless arc length M2s i , using the new axial coordinate T2x as the interpolation point, for the X - direction coordinate M2x in the new stratified meridian discrete point set (M2x i , M2z i ) and the new stratified meridian dimensionless arc length M2s i to form an array (M2x i , M2s i , M2s i ) for interpolation to obtain the new characteristic point dimensionless axial coordinate Q2. The interpolation operation in this step S42 is the same as the above steps S411 - S413, and will not be elaborated in this invention.

[0039] Further, in step S43, obtain the new airfoil rectangular coordinate data set of each blade section, specifically including: S431. According to the difference between the original characteristic point dimensionless axial coordinate and the new characteristic point dimensionless axial coordinate, translate the original blade dimensionless airfoil data set to obtain the new blade dimensionless airfoil data set. Specifically, according to the original characteristic point dimensionless axial coordinate Q1, the new characteristic point dimensionless axial coordinate Q2, and the original blade dimensionless airfoil data set (F1 n , G1 n ), through the formula F2 n =F1 n +Q2 - Q1, G2 n =G1 n calculate the new blade dimensionless airfoil data set (F2 n , G2 n ), where F2n is the dimensionless axial coordinate of the nth discrete point of the new blade, G2 n is the dimensionless transverse coordinate of the nth discrete point of the new blade.

[0040] S432. According to the new stratified meridian dimensionless arc length and the new stratified meridian discrete point set, interpolate the array (M2s i , M2x i ), using the axial coordinates of the new blade dimensionless airfoil data set as the interpolation points, to obtain the X - coordinate of the new airfoil rectangular coordinate data set of the blade section; S433. According to the new stratified meridian discrete point set, using the X - coordinate of the new airfoil rectangular coordinate data set of the blade section as the interpolation points, interpolate the array (M2x i , M2z i ) to obtain the perpendicular distance from the new airfoil discrete points of the blade section to the turbine rotation axis; S434. According to the perpendicular distance from the new airfoil discrete points of the blade section to the turbine rotation axis and the new blade dimensionless airfoil data set, perform function calculations to obtain the Y - coordinate and Z - coordinate of the new airfoil rectangular coordinate data set of the blade section.

[0041] The specific processes of the above steps S432 - S434 are as follows: According to the new blade dimensionless airfoil data set (F2 n , G2 n ) of each blade section, the new stratified meridian discrete point set (M2x i , M2z i ), and the new stratified meridian dimensionless arc length M2s i , calculate the rectangular coordinate data set (X2 n , Y2 n , Z2 n ) of the new airfoil, where X2 n , Y2 n , Z2 n are the coordinates of the nth discrete point of the new airfoil 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 points, interpolate the array (M2s i , M2x i ) to calculate X2 n . Y2 n and Z2 n can be calculated in the following way: Using X2 n as the interpolation points, interpolate the array (M2x i , M2z i ) to calculate R2 n, and then calculate to obtain Y2 n = cos(G1 n ) * R2 n , Z2 n = sin(G1 n ) * R2 n . Among them, R2 n is the vertical distance from the nth discrete point of the new blade profile to the axis of rotation of the turbine.

[0042] The method for transplanting turbine blades provided by the present invention enables the original turbine blades to be transplanted in different flow channels while maintaining their characteristics basically unchanged. This enables excellent blade design results to be reused and inherited repeatedly in different turbines without being limited by the shape and size of the flow channel, thereby greatly improving the reusability of blade design results and the blade design efficiency. As shown in Figure 5 , the isentropic Mach number distribution on the blade surface of the original turbine blade is basically the same before and after transplantation.

[0043] Based on the same inventive concept, an embodiment of the present invention also provides a turbine blade transplantation system as described in the following embodiments. Since the principle of solving problems by the turbine blade transplantation system is similar to that of the turbine blade transplantation method disclosed in the above embodiments, the implementation of the turbine blade transplantation system can refer to the implementation of the turbine blade transplantation method, and the repeated parts will not be described again. As used hereinafter, the term "unit" or "module" can 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.

[0044] Figure 6 is a structural block diagram of a turbine blade transplantation system disclosed in an embodiment of the present invention. As shown in Figure 6 , the system includes a blade division module 601, a first calculation module 602, a second calculation module 603, a third calculation module 604, and a transplantation module 605. The following describes this structure.

[0045] Among them, the blade division module 601 is used to select a feature point on the original turbine blade as a transplantation reference, and divide the original turbine blade into multiple blade sections according to the blade profile complexity and relative height; The first calculation module 602 is used to obtain, for each of the blade sections, the set of discrete points on the stratified meridian at its relative height, and calculate the dimensionless arc length of the stratified meridian based on the set of discrete points on the stratified meridian. Among them, the set of discrete points on the stratified meridian includes the original set of discrete points on the stratified meridian and the new set of discrete points on the stratified meridian, and the dimensionless arc length of the stratified meridian includes the original dimensionless arc length of the stratified meridian and the new dimensionless arc length of the stratified meridian; The second calculation module 603 is configured to obtain the discrete point set of the original blade surface profile and the original axial coordinates of the feature points in the original flow channel according to the original layered meridian discrete point set of each blade section; and obtain the new axial coordinates of the feature points in the new flow channel according to the design requirements of the turbomachine and the given positions of the feature points in the new flow channel. The third calculation module 604 is configured to obtain the new blade profile rectangular coordinate data set of all the blade sections in the new flow channel through the layered meridian discrete point set, the dimensionless arc length of the layered meridian, the discrete point set of the original blade surface profile, the original axial coordinates, and the new axial coordinates. The transplantation module 605 is configured to stretch by means of skinning using the new blade profile rectangular coordinate data set of all the blade sections to obtain the blade profile under the new flow channel.

[0046] 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 transplantation method of the turbomachine blade as described above is implemented.

[0047] Specifically, the computer device may be a computer terminal, a server, or a similar computing device.

[0048] In this embodiment, a computer-readable storage medium is provided, and the computer-readable storage medium stores a computer program for executing the transplantation method of the turbomachine blade as described above.

[0049] 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.

[0050] Obviously, those skilled in the art should understand that the various modules or steps of the above 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 code executable by the computing device. Thus, 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 sequence different from that 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 for implementation. In this way, the embodiments of the present invention are not limited to any specific combination of hardware and software.

[0051] 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 changes and modifications 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 method for transplanting a turbine blade, characterized in that For transplanting the original turbine blade from the original flow path to a new flow path, the method includes: Select a characteristic point on the original turbine blade as the transplant reference, and divide the original turbine blade into multiple blade sections according to the blade profile complexity and relative height; For each of the blade sections, obtain the discrete point set of the stratified meridian at its relative height, and calculate the dimensionless arc length of the stratified meridian based on the discrete point set of the stratified meridian, where the discrete point set of the stratified meridian includes the original discrete point set of the stratified meridian and the new discrete point set of the stratified meridian, and the dimensionless arc length of the stratified meridian includes the original dimensionless arc length of the stratified meridian and the new dimensionless arc length of the stratified meridian; According to the original discrete point set of the stratified meridian of each blade section, obtain the discrete point set of the original blade revolution surface profile and the original axial coordinate of the characteristic point in the original flow path; according to the design requirements of the turbine and the given position of the characteristic point in the new flow path, obtain the new axial coordinate of the characteristic point in the new flow path; Through the discrete point set of the stratified meridian, the dimensionless arc length of the stratified meridian, the discrete point set of the original blade revolution surface profile, the original axial coordinate and the new axial coordinate, obtain the new leaf profile rectangular coordinate data set of all the blade sections in the new flow path; Adopt the new leaf profile rectangular coordinate data set of all the blade sections, and obtain the blade shape under the new flow path by stretching through the skinning method.

2. The transplantation method of the turbine blade according to claim 1, characterized in that, For each of the blade sections, obtaining the discrete point set of the stratified meridian at its relative height includes: Perform equal-arc-length encryption on the downstream flow path line and the upstream flow path line to obtain multiple encrypted point connection lines, where one end of the encrypted point connection line is the downstream flow path encrypted discrete point and the other end is the upstream flow path encrypted discrete point; For each of the blade sections, select a point on each of the encrypted point connection lines such that the ratio of the length from the point to the downstream flow path encrypted discrete point to the length of the encrypted point connection line is equal to the relative height where the blade section is located; For each of the blade sections, extract the coordinates of the points selected on all the encrypted point connection lines to obtain the discrete point set of the stratified meridian.

3. The transplantation method of the turbomachine blade according to claim 1 or 2, characterized in that, Calculating the dimensionless arc length of the stratified meridian based on the discrete point set of the stratified meridian includes: Along the flow path direction, define the dimensionless arc length of the first stratified meridian discrete point in the discrete point set of the stratified meridian to be zero; Based on the dimensionless arc length of the previous stratified meridian discrete point, the current stratified meridian discrete point coordinates and the previous stratified meridian discrete point coordinates, calculate the dimensionless arc length of the remaining stratified meridian discrete points except the first stratified meridian discrete point.

4. The method for transplanting a turbine blade 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 stratified meridian discrete points other than 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, (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.

5. The method for transplanting a turbine blade according to claim 1, characterized in that, According to the original discrete point set of the stratified meridian of each blade section, obtaining the discrete point set of the original blade revolution surface profile and the original axial coordinate of the characteristic point in the original flow path includes: Form the original stratified meridian according to the original discrete point set of the stratified meridian of each blade section, and rotate each of the original stratified meridians around the turbine rotation axis to form the original blade revolution surface; Adopt all the original blade revolution surfaces to intercept the original turbine blade, and obtain the discrete point set of the original blade revolution surface profile in rectangular coordinates; Obtain the original axial coordinates of the characteristic points in the original flow passage according to the set of discrete points of the original blade revolution surface profile.

6. The method for transplanting a turbine blade according to claim 1, characterized in that, Obtain the new blade profile Cartesian coordinate data sets of all the blade sections in the new flow passage through the set of discrete points of the stratified meridian, the dimensionless arc length of the stratified meridian, the set of discrete points of the original blade revolution surface profile, the original axial coordinates, and the new axial coordinates, including: Obtain the original blade dimensionless profile data set and the original characteristic point dimensionless axial coordinates of each blade section by interpolation through the original set of discrete points of the stratified meridian, the original dimensionless arc length of the stratified meridian, the set of discrete points of the original blade revolution surface profile, and the original axial coordinates; Obtain the new characteristic point dimensionless axial coordinates of each blade section by interpolation according to the set of discrete points of the new stratified meridian, the dimensionless arc length of the new stratified meridian, and the new axial coordinates; Obtain the new blade profile Cartesian coordinate data set of each blade section according to the original characteristic point dimensionless axial coordinates, the new characteristic point dimensionless axial coordinates, the original blade dimensionless profile data set, the set of discrete points of the new stratified meridian, and the dimensionless arc length of the new stratified meridian.

7. The method for transplanting a turbine blade according to claim 6, characterized in that, Obtain the original blade dimensionless profile data set and the original characteristic point dimensionless axial coordinates of each blade section by interpolation through the original set of discrete points of the stratified meridian, the original dimensionless arc length of the stratified meridian, the set of discrete points of the original blade revolution surface profile, and the original axial coordinates, including: According to the original set of discrete points of the stratified meridian and the original dimensionless arc length of the stratified meridian, use the set of discrete points of the original blade revolution surface profile as the interpolation points to obtain the dimensionless axial coordinates of the original blade dimensionless profile data set; Perform atan2 function calculation on the set of discrete points of the original blade revolution surface profile to obtain the dimensionless transverse coordinates of the original blade dimensionless profile data set; According to the original set of discrete points of the stratified meridian and the original dimensionless arc length of the stratified meridian, use the original axial coordinates as the interpolation points to obtain the original characteristic point dimensionless axial coordinates.

8. The transplantation method of the turbine blade according to claim 6, characterized in that Obtain the new blade profile Cartesian coordinate data set of each blade section according to the original characteristic point dimensionless axial coordinates, the new characteristic point dimensionless axial coordinates, the original blade dimensionless profile data set, the set of discrete points of the new stratified meridian, and the dimensionless arc length of the new stratified meridian, including: Translate the original blade dimensionless profile data set according to the difference between the original characteristic point dimensionless axial coordinates and the new characteristic point dimensionless axial coordinates to obtain the new blade dimensionless profile data set; According to the dimensionless arc length of the new stratified meridian and the set of discrete points of the new stratified meridian, use the axial coordinates of the new blade dimensionless profile data set as the interpolation points to obtain the X - coordinate of the new blade profile Cartesian coordinate data set of the blade section; According to the set of discrete points of the new stratified meridian, use the X - coordinate of the new blade profile Cartesian coordinate data set of the blade section as the interpolation points to obtain the perpendicular distance from the new blade profile discrete points of the blade section to the axis of rotation of the turbomachine. Based on the vertical distance from the discrete points of the new blade profile of the blade cross-section to the rotation axis of the turbomachine and the dimensionless blade profile dataset of the new blade, function calculations are performed to obtain the Y-axis coordinates and Z-axis coordinates of the right-angle coordinate dataset of the new blade profile of the blade cross-section.

9. A transplanting system for a turbine blade, characterized in that, Including: A blade division module, which is used to select a characteristic point on the original turbomachine blade as the transplantation reference, and divide the original turbomachine blade into multiple blade cross-sections according to the blade profile complexity and relative height; A first calculation module, which is used to obtain the discrete point set of the stratified meridian at the relative height where each blade cross-section is located, and calculate the dimensionless arc length of the stratified meridian based on the discrete point set of the stratified meridian. Among them, the discrete point set of the stratified meridian includes the original discrete point set of the stratified meridian and the new discrete point set of the stratified meridian, and the dimensionless arc length of the stratified meridian includes the original dimensionless arc length of the stratified meridian and the new dimensionless arc length of the stratified meridian; A second calculation module, which is used to obtain the discrete point set of the original blade rotary surface profile and the original axial coordinate of the characteristic point in the original flow channel according to the original discrete point set of the stratified meridian of each blade cross-section; according to the design requirements of the turbomachine and the given position of the characteristic point in the new flow channel, obtain the new axial coordinate of the characteristic point in the new flow channel; A third calculation module, which is used to obtain the right-angle coordinate dataset of the new blade profile of all the blade cross-sections in the new flow channel through the discrete point set of the stratified meridian, the dimensionless arc length of the stratified meridian, the discrete point set of the original blade rotary surface profile, the original axial coordinate and the new axial coordinate; A transplantation module, which is used to adopt the right-angle coordinate dataset of the new blade profile of all the blade cross-sections and obtain the blade shape under the new flow channel by stretching through the skinning method.

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