A method and system for transplanting a turbine blade

Abstract

The present invention belongs to the technical field of turbomachines, and provides a method and a system for transplanting turbomachine blades. The method includes: dividing the original turbomachine blades into multiple blade cross-sections; obtaining the discrete point set of the stratified meridian and the dimensionless arc length of the stratified meridian at the relative height where the blade cross-section is located; calculating the original axial coordinates of the discrete point set of the blade profile on the original revolution surface and the characteristic points in the original flow passage, as well as the new axial coordinates of the characteristic points in the new flow passage; obtaining the new blade profile rectangular coordinate data set of all blade cross-sections in the new flow passage; and using the new blade profile rectangular coordinate data set of all the blade cross-sections to perform stretching through the skinning method to obtain the blade shape under the new flow passage. The present invention can realize the transplantation of blades in different flow passages, and the characteristics of the blades can be basically kept unchanged before and after transplantation, which enables excellent blades to be repeatedly borrowed 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 Art

[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 flow passage shapes and sizes 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 achieve the transplantation of blades in different flow passages, and the characteristics of the blades can be basically kept 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:

[0005] 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;

[0006] 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, 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;

[0007] 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 and the original axial coordinate of the characteristic point in the original flow passage; according to the design requirements of the turbomachine 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;

[0008] 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, 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;

[0009] S5. Adopt the new airfoil rectangular coordinate data set of all the blade sections, and stretch it by the skin method to obtain the blade profile under the new flow channel.

[0010] Further, in the above step S2, for each of the blade sections, obtain the stratified meridian discrete point set at its relative height, including:

[0011] S21. Perform equal-arc-length encryption on the downstream channel line and the upstream channel line to obtain multiple encrypted point connection lines. Among them, one end of the encrypted point connection line is the downstream channel encrypted discrete point, and the other end is the upstream channel encrypted discrete point;

[0012] 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 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;

[0013] 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.

[0014] Further, in the above step S2, calculate the stratified meridian dimensionless arc length according to the stratified meridian discrete point set, including:

[0015] S24. Along the flow channel direction, define the stratified meridian dimensionless arc length of the first stratified meridian discrete point in the stratified meridian discrete point set as zero;

[0016] S25. Calculate the stratified meridian dimensionless arc length of the remaining stratified meridian discrete points except the first stratified meridian discrete point according to the stratified meridian 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.

[0017] Even further, in the above step S22, according to the formula:

[0018] Ms i =Ms i-1 +((Mx i -Mx i-1 ) 2 +(Mz i -Mz i-1 ) 2 ) 0.5 / Mz i Calculate the stratified meridian dimensionless arc length of the remaining stratified meridian discrete points except the first stratified meridian discrete point, where Ms i is the stratified meridian dimensionless arc length of the i-th stratified meridian discrete point, Ms i-1is the dimensionless arc length of the stratified meridian for the (i - 1)-th stratified meridian discrete point, (Mx i , Mz i ) is the coordinate of the i-th stratified meridian discrete point, and (Mx i-1 , Mz i-1 ) are the coordinates of the (i - 1)-th stratified meridian discrete point in the X direction and the Z direction respectively, where i is an integer greater than or equal to 2.

[0019] Furthermore, 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 rotary surface profile discrete point set and the original axial coordinates of the characteristic points in the original flow channel includes:

[0020] S31. Form the original stratified meridian 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 turbine rotation axis to form the original blade rotary surface;

[0021] S32. Use all of the original blade rotary surfaces to intercept the original turbine blades to obtain the original blade rotary surface profile discrete point set in rectangular coordinates;

[0022] S33. According to the original blade rotary surface profile discrete point set, obtain the original axial coordinates of the characteristic points in the original flow channel.

[0023] Furthermore, in the above step S4, through the stratified meridian discrete point set, the dimensionless arc length of the stratified meridian, the original blade rotary 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 channel includes:

[0024] S41. Through the original stratified meridian discrete point set, the dimensionless arc length of the original stratified meridian, the original blade rotary surface profile discrete point set, and the original axial coordinates, obtain the original dimensionless blade profile data sets and the original dimensionless axial coordinates of the characteristic points of each of the blade cross-sections by interpolation;

[0025] S42. According to the new stratified meridian discrete point set, the dimensionless arc length of the new stratified meridian, and the new axial coordinates, obtain the new dimensionless axial coordinates of the characteristic points of each of the blade cross-sections by interpolation;

[0026] S43. According to the original dimensionless axial coordinates of the characteristic points, the new dimensionless axial coordinates of the characteristic points, the original dimensionless blade profile data sets, 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 sets of each of the blade cross-sections.

[0027] Further, in the above step S41, based on the original stratified meridian discrete point set, the dimensionless arc length of the original stratified meridian, the original blade revolution surface profile discrete point set, and the original axial coordinate, the original blade dimensionless profile data set and the dimensionless axial coordinate of the original characteristic points of each blade section are obtained through interpolation, including:

[0028] S411. According to the original stratified meridian discrete point set and the dimensionless arc length of the original stratified meridian, taking 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 set;

[0029] S412. Perform atan2 function calculation on the original blade revolution surface profile discrete point set to obtain the dimensionless transverse coordinates of the original blade dimensionless profile data set.

[0030] S413. According to the original stratified meridian discrete point set and the dimensionless arc length of the original stratified meridian, taking the original axial coordinate as the interpolation points, obtain the dimensionless axial coordinates of the original characteristic points.

[0031] Further, the interpolation operation in step S42 is the same as the above steps S411 - S413, and thus will not be elaborated herein in the present invention.

[0032] Furthermore, in the above step S43, based on the dimensionless axial coordinates of the original characteristic points, the dimensionless axial coordinates of the new characteristic points, the original blade dimensionless profile data set, the new stratified meridian discrete point set, and the dimensionless arc length of the new stratified meridian, obtain the new profile rectangular coordinate data set of each blade section, including:

[0033] S431. Translate the original blade dimensionless profile data set 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 new blade dimensionless profile data set;

[0034] S432. According to the dimensionless arc length of the new stratified meridian and the new stratified meridian discrete point set, taking the axial coordinates of the new blade dimensionless profile data set as the interpolation points, obtain the X - direction coordinates of the new profile rectangular coordinate data set of the blade section;

[0035] S433. According to the new stratified meridian discrete point set, taking the X - direction coordinates of the new profile rectangular coordinate data set of the blade section as the interpolation points, obtain the vertical distance from the new profile discrete points of the blade section to the turbine rotation axis;

[0036] S434. According to the vertical distance from the new profile discrete points of the blade section to the turbine rotation axis and the new blade dimensionless profile data set, perform function calculation to obtain the Y - direction coordinates and Z - direction coordinates of the new profile rectangular coordinate data set of the blade section.

[0037] An embodiment of the present invention also provides a transplant system for a turbine blade, which includes a blade division module, a first calculation module, a second calculation module, a third calculation module, and a transplant module.

[0038] Among them, the blade division module is used to select a feature 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;

[0039] The first calculation module is used to obtain a discrete point set of the stratified meridian at its relative height for each blade section, 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;

[0040] The second calculation module is used to obtain the discrete point set of the original blade's rotating surface profile and the original axial coordinate of the feature point in the original flow path according to the original discrete point set of the stratified meridian of each blade section; and obtain the new axial coordinate of the feature point in the new flow path according to the design requirements of the turbine and the given position of the feature point in the new flow path;

[0041] The third calculation module is used to obtain a new blade profile rectangular coordinate data set of all the blade sections 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's rotating surface profile, the original axial coordinate, and the new axial coordinate;

[0042] The transplant module is used to adopt the new blade profile rectangular coordinate data set of all the blade sections and obtain the blade shape under the new flow path through skinning stretching.

[0043] 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 this specification at least include:

[0044] The transplant method for turbine blades provided by the present invention can enable the original turbine blades to be transplanted in different flow paths while keeping 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 path, greatly improving the reusability of blade design results and the blade design efficiency. Brief Description of the Drawings

[0045] To more clearly illustrate the technical solutions of the embodiments of the present application, the following will briefly introduce the accompanying drawings required in the embodiments. Obviously, the accompanying 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 accompanying drawings can also be obtained based on these drawings.

[0046] Figure 1 It is a flowchart of the transplantation method of the turbine blade disclosed in the embodiments of the present invention;

[0047] Figure 2 It is the flow path line of the original flow path and the position of the original turbine blade in the original flow path disclosed in the embodiments of the present invention;

[0048] Figure 3 It is the flow path line of the new flow path and the position of the original turbine blade transplanted into the new flow path disclosed in the embodiments of the present invention;

[0049] Figure 4 It is a schematic diagram of intercepting the blade cross-section according to the relative height disclosed in the embodiments of the present invention;

[0050] 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;

[0051] Figure 6 It is an architecture diagram of the transplantation system of the turbine blade disclosed in the embodiments of the present invention;

[0052] 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

[0053] The following will describe the embodiments of the present application in detail with reference to the accompanying drawings.

[0054] The following illustrates the implementation manners of the present application through specific specific examples. 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 of protection of the present application.

[0055] An embodiment of the present invention discloses a method for transplanting a turbine blade, which 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:

[0056] S1. Select a feature 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;

[0057] 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;

[0058] 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;

[0059] 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 leaf profile rectangular coordinate data set of all the blade sections in the new flow channel;

[0060] S5. Use the new leaf 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 channel.

[0061] Further, in the above step S1, the feature point includes 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 blade profile complexity, and the number of blade sections is proportional to the blade profile complexity, usually not less than 10, including the blade sections at two relative heights of 0% and 100%. Among them, the schematic diagram of intercepting the blade section according to the relative height is as Figure 4 shown. The blade profile complexity includes any one or more of the blade curvature, twist angle, thickness, width, surface roughness, and geometric shape, and the relative height is the longitudinal position from the blade base to the blade top.

[0062] Further, in the above step S2, for each of the blade sections, obtaining the discrete point set of the stratified meridian at its relative height includes:

[0063] S21. Perform equal-arc-length encryption on the downstream channel line and the upstream channel line to obtain multiple encrypted point connection lines. Among them, 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. During specific implementation, equal-arc-length encryption can be performed on the upstream channel line and the downstream channel line of the original / new channel line, and the number of encrypted points on the upstream channel line and the downstream channel line is equal. The hierarchical meridian discrete points of the downstream channel line in the encrypted point connection line are represented as A i , and the hierarchical meridian discrete points of the upstream channel line are represented as B i , and the number of encrypted point connection lines is not less than 1000.

[0064] S22. For each blade section, select a point on each encrypted point connection line such that the ratio of the length between the point and 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. During specific implementation, the points selected on each encrypted point connection line 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.

[0065] S23. For each blade section, extract the coordinates of all the points selected on the encrypted point connection lines to obtain a set of hierarchical meridian discrete points. Connect the points selected on all the encrypted point connection lines for each blade section to form the hierarchical meridian of the blade section, and its set of hierarchical meridian discrete points can be represented as (Mx i , Mz i ). Among them, the original set of hierarchical meridian discrete points can be represented as (M1x i , M1z i ), (M1x i , M1z i ) respectively represent the coordinates in the X direction and the Z direction of the i-th hierarchical meridian discrete point in the original channel. The new set of hierarchical meridian discrete points can be represented as (M2x i , M2z i ), (M2x i , M2z i ) respectively represent the coordinates in the X direction and the Z direction of the i-th hierarchical meridian discrete point in the new channel, where i takes values of 1, 2, 3, ……, m, and m is an integer ≥ 1000, M1 represents the original channel, and M2 represents the new channel.

[0066] Furthermore, in step S2 above, calculating the dimensionless arc length of the hierarchical meridian based on the set of hierarchical meridian discrete points includes:

[0067] S24. Along the flow path direction, define the dimensionless arc length of the stratified meridian of the first stratified meridian discrete point in the stratified meridian discrete point set to be zero.

[0068] S25. Calculate the dimensionless arc length of the stratified meridian of the remaining stratified meridian discrete points except the first stratified meridian discrete point based on the dimensionless arc length of the stratified meridian 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.

[0069] Furthermore, in the above step S22, according to the formula:

[0070] 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 stratified meridian of the i-th stratified meridian discrete point, Ms i-1 is the dimensionless arc length of the stratified meridian 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, and i is an integer greater than or equal to 2.

[0071] Among them, the original dimensionless arc length of the stratified meridian M1s i 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 .

[0072] The new dimensionless arc length of the stratified meridian M2s i can be expressed as: when i = 1, M2s i = 0; when i ≥ 2, M2s i = M2si-1 +((M2x i -M2x i-1 ) 2 +(M2z i -M2z i-1 ) 2 ) 0.5 / M2z i 。

[0073] Furthermore, in the above step S3, according to the original stratified meridian discrete point sets of each of the blade cross-sections, an original blade revolution surface profile discrete point set and the original axial coordinates of the characteristic points in the original flow passage are obtained, including:

[0074] S31. Form an original stratified meridian 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 turbine rotation axis to form an original blade revolution surface.

[0075] S32. Intercept the original turbine blades with all of the original blade revolution surfaces to obtain an 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.

[0076] S33. Obtain the original axial coordinate T1x of the characteristic points in the original flow passage according to the original blade revolution surface profile discrete point set.

[0077] Furthermore, in the above step S4, through the stratified meridian discrete point set, the dimensionless arc length of the stratified meridian, the original blade revolution surface profile discrete point set, the original axial coordinate, and the new axial coordinate, a new blade profile rectangular coordinate data set of all of the blade cross-sections in the new flow passage is obtained, including:

[0078] S41. Through the original stratified meridian discrete point set, the dimensionless arc length of the original stratified meridian, the original blade revolution surface profile discrete point set, and the original axial coordinate, an original dimensionless blade profile data set of each of the blade cross-sections and the original dimensionless axial coordinate Q1 of the original characteristic points are obtained by interpolation;

[0079] S42. According to the new stratified meridian discrete point set, the dimensionless arc length parameter of the new stratified meridian, and the new axial coordinate, the dimensionless axial coordinate Q2 of the new characteristic points of each blade section is obtained by discrete points through interpolation method;

[0080] S43. According to the dimensionless axial coordinate of the original characteristic points, the dimensionless axial coordinate 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, the new blade profile rectangular coordinate data set of each blade section is obtained.

[0081] Furthermore, in the above step S41, through the original stratified meridian discrete point set, the dimensionless arc length of the original stratified meridian, the discrete point set of the original blade revolution surface profile, and the original axial coordinate, the dimensionless blade profile data set of the original blade and the dimensionless axial coordinate Q1 of the original characteristic points of each blade section are obtained by interpolation method, including:

[0082] S411. According to the original stratified meridian discrete point set and the dimensionless arc length of the original stratified meridian, taking the discrete point set of the original blade revolution surface profile as the interpolation points, the dimensionless axial coordinate F1 of the dimensionless blade profile data set of the original blade 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 stratified meridian discrete point set i and the dimensionless arc length parameter M1s of the original stratified 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 dimensionless blade profile data set of the original blade is obtained n .

[0083] 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 dimensionless blade profile data set of the original blade 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 atan2 function calculation to obtain G1 n , that is, G1 n =atan2(Y1 n , Z1 n ).

[0084] S413. According to the original stratified meridian discrete point set and the dimensionless arc length of the original stratified meridian, taking the original axial coordinate as the interpolation points, the dimensionless axial coordinate Q1 of the original characteristic points is obtained. During implementation, taking the original axial coordinate T1x as the interpolation points, for M1x in the original stratified meridian discrete point seti and the dimensionless arc length of the original layer meridian M1s i The array composed of (M1x i , M1s i ) to interpolate and obtain the dimensionless axial coordinate Q1 of the original feature point.

[0085] Furthermore, in step S42, according to the new layered meridian discrete point set (M2x i ,M2z i ) and the dimensionless arc length M2s of the new layer meridian i , taking the new axial coordinate T2x as the interpolation point, the new layered meridian discrete point set (M2x i ,M2z i ) in the X-coordinate M2x i and the dimensionless arc length M2s of the new stratified meridian i An array composed of (M2x i , M2s i ) to interpolate and obtain the dimensionless axial coordinate Q2 of the new feature point. The interpolation operation in step S42 is the same as that in steps S411 to S413 above, and will not be described in detail in the present invention.

[0086] Furthermore, in step S43, obtaining a new blade profile rectangular coordinate data set for each blade cross section specifically includes:

[0087] S431, according to the difference between the dimensionless axial coordinate of the original feature point and the dimensionless axial coordinate of the new feature point, translate the original blade dimensionless profile dataset to obtain a new blade dimensionless profile dataset. Specifically, the dimensionless axial coordinate of the original feature point Q1, the dimensionless axial coordinate of the new feature point Q2 and the dimensionless axial coordinate of the original blade profile dataset (F1 n ,G1 n ), through formula F2 n =F1 n +Q2-Q1,G2 n =G1 n Calculate the dimensionless blade profile data set (F2 n ,G2 n ), where F2 n 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 leaf.

[0088] S432, according to the dimensionless arc length of the new layered meridian and the discrete point set of the new layered meridian, i , M2x i) interpolation is performed, using the axial coordinates of the new dimensionless blade profile data set as interpolation points to obtain the X-coordinates of the new blade profile rectangular coordinate data set of the blade cross section;

[0089] S433, according to the new layered 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, the array (M2x i ,M2z i ) to interpolate and obtain the vertical distance between the new blade profile discrete point of the blade cross section and the impeller rotation axis;

[0090] S434. Perform function calculation based on the vertical distance between the new blade profile discrete point of the blade cross section and the impeller rotation axis and the new blade dimensionless blade profile data set to obtain the Y-coordinate and Z-coordinate of the new blade profile rectangular coordinate data set of the blade cross section.

[0091] The specific process of the above steps S432-S434 is as follows: according to the new blade dimensionless blade profile data set (F2 n ,G2 n ) 、New layered meridian discrete point set (M2x i ,M2z i ), dimensionless arc length of the new layer meridian M2s i Calculate the rectangular coordinate data set of the new blade shape (X2 n ,Y2 n ,Z2 n ), where X2 n ,Y2 n ,Z2 n are the coordinates of the nth discrete point of the new blade in the X, Y, and Z directions respectively. n It can be calculated as follows: n For interpolation points, the array (M2s i , M2x i ) to interpolate and calculate X2 n Y2 n and Z2 n It can be calculated as follows: n For interpolation points, the array (M2x i , M2z i ) to interpolate and calculate R2 n , and then calculate Y2 n =cos(G1 n )* R2 n , Z2 n =sin(G1 n )* R2 n Among them, R2 nis the vertical distance from the n-th discrete point of the new blade profile to the axis of rotation of the turbomachine.

[0092] The method for transplanting the blades of a turbomachine provided by the present invention enables the original turbomachine blades to be transplanted in different flow channels while maintaining their characteristics basically unchanged. This allows excellent blade design results to be reused and inherited repeatedly in different turbomachines without being limited by the shape and size of the flow channels, thereby greatly improving the reusability of the blade design results and the blade design efficiency. Refer to Figure 5 As shown, the isentropic Mach number distribution on the blade surface of the original turbomachine blade is basically the same before and after transplantation.

[0093] Based on the same inventive concept, an embodiment of the present invention also provides a system for transplanting the blades of a turbomachine, as described in the following embodiments. Since the principle of solving problems by the system for transplanting the blades of a turbomachine is similar to the method for transplanting the blades of a turbomachine disclosed in the above embodiments, the implementation of the system for transplanting the blades of a turbomachine can refer to the implementation of the method for transplanting the blades of a turbomachine, and the repeated parts will not be described again. Hereinafter, the term "unit" or "module" may refer to 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.

[0094] Figure 6 is a structural block diagram of a system for transplanting the blades of a turbomachine disclosed in an embodiment of the present invention, as Figure 6 shown. 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.

[0095] Among them, the blade division module 601 is used to select a characteristic point on the original turbomachine blade as a transplantation reference, and divide the original turbomachine blade into multiple blade sections according to the blade profile complexity and relative height;

[0096] The first calculation module 602 is used to obtain, for each of the blade sections, a set of discrete points on the stratified meridian at its corresponding 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 an original set of discrete points on the stratified meridian and a new set of discrete points on the stratified meridian, and the dimensionless arc length of the stratified meridian includes an original dimensionless arc length of the stratified meridian and a new dimensionless arc length of the stratified meridian;

[0097] The second calculation module 603 is configured to obtain the discrete point set of the original blade rotating surface airfoil and the original axial coordinates of the characteristic points in the original flow channel according to the discrete point set of the original stratified meridian of each blade section; obtain the new axial coordinates of the characteristic points in the new flow channel according to the design requirements of the turbomachine and the given positions of the characteristic points in the new flow channel.

[0098] The third calculation module 604 is configured to obtain the new airfoil rectangular coordinate data set of all the blade sections in the new flow channel through the stratified meridian discrete point set, the dimensionless arc length of the stratified meridian, the discrete point set of the original blade rotating surface airfoil, the original axial coordinates, and the new axial coordinates.

[0099] The transplant module 605 is configured to stretch and obtain the blade shape under the new flow channel by using the new airfoil rectangular coordinate data set of all the blade sections through the skinning method.

[0100] 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 method for transplanting the turbomachine blade is implemented.

[0101] Specifically, the computer device may be a computer terminal, a server, or a similar computing device.

[0102] 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 method for transplanting the turbomachine blade.

[0103] 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.

[0104] 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 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 for implementation. In this way, the embodiments of the present invention are not limited to any specific combination of hardware and software.

[0105] The above are only the preferred embodiments of the present invention and are not used to limit the present invention. For those skilled in the art, the embodiments of the present invention can have various changes and modifications. 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 the 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 of the blade sections, obtain the discrete point set of the original blade's revolution surface profile and the original axial coordinate of the characteristic point in the original flow path; according to the turbine design requirements 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's 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 path, including: according to the original discrete point set of the stratified meridian and the original dimensionless arc length of the stratified meridian, using the discrete point set of the original blade's revolution surface profile as the interpolation points, obtain the dimensionless axial coordinate of the original blade's dimensionless profile data set; perform the atan2 function calculation on the discrete point set of the original blade's revolution surface profile to obtain the dimensionless lateral coordinate of the original blade's dimensionless profile data set; according to the original discrete point set of the stratified meridian and the original dimensionless arc length of the stratified meridian, using the original axial coordinate as the interpolation points, obtain the dimensionless axial coordinate of the original characteristic point; According to the new discrete point set of the stratified meridian, the new dimensionless arc length of the stratified meridian, and the new axial coordinate, obtain the dimensionless axial coordinate of the new characteristic point of each of the blade sections by interpolation method; According to the difference between the dimensionless axial coordinate of the original characteristic point and the dimensionless axial coordinate of the new characteristic point, translate the original blade's dimensionless profile data set to obtain the new blade's dimensionless profile data set; according to the new dimensionless arc length of the stratified meridian and the new discrete point set of the stratified meridian, using the axial coordinate of the new blade's dimensionless profile data set as the interpolation points, obtain the X-direction coordinate of the new blade profile rectangular coordinate data set of the blade section; according to the new discrete point set of the stratified meridian, using the X-direction coordinate of the new blade profile rectangular coordinate data set of the blade section as the interpolation points, obtain the vertical distance from the new blade profile discrete points of the blade section to the turbine rotation axis; according to the vertical distance from the new blade profile discrete points of the blade section to the turbine rotation axis and the new blade's dimensionless profile data set, perform function calculation to obtain the Y-direction coordinate and Z-direction coordinate of the new blade profile rectangular coordinate data set of the blade section; 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 shape under the new flow path.

2. The method for transplanting a turbine blade according to claim 1, characterized in that For each of the blade sections, obtain the discrete point set of the stratified meridian at its relative height, including: Perform equal arc length encryption on the downstream channel line and the upstream channel line to obtain multiple encrypted point connection lines. Among them, 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; 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 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; 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 turbine blade according to claim 1 or 2, characterized in that Calculate the dimensionless arc length of the stratified meridian based on the discrete point set of the stratified meridian, including: Along the flow channel direction, define 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; Based on 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, 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 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, (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 of the blade sections, 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 channel, including: Form the original stratified meridian according to the original discrete point set of the stratified meridian of each of the blade sections, and rotate each of the original stratified meridians around the rotation axis of the turbomachine to form the original blade revolution surface; Use all the original blade revolution surfaces to intercept the original turbomachine blades to obtain the discrete point set of the original blade revolution surface profile in rectangular coordinates; According to the discrete point set of the original blade revolution surface profile, obtain the original axial coordinate of the characteristic point in the original flow channel.

6. A transplanting system for a turbine blade, characterized in that, For transplanting the original turbomachine blades from the original flow channel to the new flow channel by using the turbomachine blade transplanting method according to any one of claims 1 to 5, the transplanting system includes: A blade division module, which is used to select a characteristic point on the original turbomachine blade as the transplant reference, and divide the original turbomachine blade into multiple blade sections according to the profile complexity and relative height; A first calculation module, which is used to, 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; A second calculation module, which is used to, according to the original discrete point set of the stratified meridian of each of the blade sections, 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 channel; according to the turbomachine design requirements 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 a new leaf profile rectangular coordinate data set of all blade sections in the new flow channel through the hierarchical meridian discrete point set, the hierarchical meridian dimensionless arc length, the original blade rotating surface profile discrete point set, the original axial coordinate, and the new axial coordinate; A transplantation module, which is used to stretch the blade profile under the new flow channel by the skinning method using the new leaf profile rectangular coordinate data set of all blade sections.

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