Gas turbine end wall flow rib modeling method, gas turbine, and gas turbine

Abstract

The invention belongs to the technical field of gas turbines, and provides a gas turbine end wall flow direction rib modeling method, a gas turbine and a gas turbine.The method comprises the steps that the velocity vector of fluid at a cascade channel is obtained, and orthogonal skin coordinate data of a modeling area is determined according to the velocity vector, a flow function and a potential function; determining a rib height maximum value of the flow direction rib, and generating a three-dimensional curved surface based on the orthogonal skin coordinate data and the rib height maximum value; wherein the three-dimensional curved surface is used for representing the structural form of the non-axisymmetric end wall; and according to the three-dimensional curved surface, a pre-established extension direction and normal phase height distribution function and a pre-established extension frontal line direction height distribution function, correcting the rib height maximum value to obtain a flow direction rib structure. According to the scheme provided by the invention, the non-axisymmetric end wall structure is combined with the flow direction ribs, so that the vortex system strength of a secondary flow vortex system is inhibited, the thermal boundary layer development form of an end wall area is optimized, and collaborative optimization of aerodynamic performance and cooling performance is realized.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbines, and particularly to a method for shaping flow ribs on the end wall of a gas turbine, a gas turbine, and a gas turbine engine. Background Art

[0002] In the field of modern turbomachinery, the flow characteristics near the turbine end wall have a crucial impact on the overall performance of the turbine. The flow near the turbine end wall exhibits significant three-dimensional flow characteristics, and this complex flow pattern gives rise to many intractable problems.

[0003] On the one hand, the secondary flow loss in the end region is serious. This secondary flow results from the interaction between the mainstream and the end wall boundary layer, and the complex flow structures such as vortices generated by it greatly consume the mechanical energy of the fluid, directly reducing the aerodynamic efficiency of the turbine, and further affecting the power output and energy utilization efficiency of the entire turbine system. For example, in the turbine components of an aeroengine, the secondary flow loss in the end region may lead to adverse consequences such as a decrease in engine thrust and an increase in fuel consumption.

[0004] On the other hand, due to the complexity of the three-dimensional flow near the end wall, it is difficult for the film cooling air to effectively cover the end wall. As a key means to protect the turbine end wall from the erosion of high-temperature gas, the film cooling technology requires the cooling air to be evenly and fully spread on the end wall surface to form an effective heat insulation film. However, the actual three-dimensional flow interference causes the cooling air to dissipate rapidly during the flow process, and it is impossible to maintain a stable and effective heat insulation layer on the end wall surface, seriously threatening the thermal protection performance of the end wall and increasing the risk of failure of the end wall material due to overheating.

[0005] To address the above problems, the non-axisymmetric end wall technology has emerged. By carefully designing the geometric shape of the end wall, the pressure distribution near the end wall is changed, thereby suppressing the generation of secondary flow and reducing the secondary flow loss to a certain extent. However, this technology has obvious limitations in practical applications. While suppressing the secondary flow loss, it usually comes with a decline in the cooling effectiveness. This is because the geometric change of the non-axisymmetric end wall affects the mixing characteristics of the cooling air and the mainstream, making the coverage range and heat insulation effect of the cooling air on the end wall surface worse, which is not conducive to the improvement of the comprehensive performance of the turbine, that is, it is impossible to achieve both high aerodynamic performance and good thermal protection performance simultaneously.

[0006] Therefore, the traditional turbine end wall shaping scheme has the technical problem of being difficult to balance the aerodynamic performance and the cooling performance. Summary of the Invention

[0007] The present invention provides a method for shaping flow ribs on the end wall of a gas turbine, a gas turbine, and a gas turbine engine, so as to solve the defect that the traditional turbine end wall shaping scheme is difficult to balance the aerodynamic performance and the cooling performance.

[0008] On the one hand, the present invention provides a method for shaping the flow direction ribs of a gas turbine end wall, the method comprising:

[0009] Obtain the velocity vector of the fluid at the cascade passage, and determine the orthogonal body-fitted coordinate data of the shaping region based on the velocity vector, the stream function and the potential function;

[0010] Determine the maximum rib height of the flow direction ribs, and generate a three-dimensional surface based on the orthogonal body-fitted coordinate data and the maximum rib height; wherein, the three-dimensional surface is used to characterize the structural form of the non-axisymmetric end wall;

[0011] Modify the maximum rib height according to the three-dimensional surface and the pre-established height distribution function along the flow direction and the normal direction and the height distribution function along the frontal line direction to obtain the flow direction rib structure.

[0012] According to the method for shaping the flow direction ribs of a gas turbine end wall provided by the present invention, determining the orthogonal body-fitted coordinate data of the shaping region based on the velocity vector, the stream function and the potential function includes:

[0013] Determine the inter-streamline flow rate value between two adjacent streamlines based on the velocity vector, the stream function and the potential function;

[0014] Starting from the streamline at the suction surface, successively advance each on-line node on the current streamline along the vertical direction of the velocity vector by the inter-streamline flow rate value to obtain a plurality of target nodes;

[0015] Connect the corresponding target nodes to obtain the orthogonal body-fitted coordinate data of the shaping region.

[0016] According to the method for shaping the flow direction ribs of a gas turbine end wall provided by the present invention, the expression of the inter-streamline flow rate value between two adjacent streamlines is as follows:

[0017]

[0018] Wherein, represents the inter-streamline flow rate value between two adjacent streamlines, n represents the number of segments of the equipotential lines from the suction surface to the pressure surface, Q represents the fluid flow rate flowing through the cascade passage, m represents a value determined according to n, v represents the first component of the velocity vector, u represents the second component of the velocity vector, (xm, ym) and both represent the node coordinates in the Cartesian coordinate system.

[0019] According to the method for shaping the flow direction ribs of a gas turbine end wall provided by the present invention, the relationship between the fluid flow rate flowing through the cascade passage and the stream function values of the streamlines at the suction surface and the pressure surface is as follows:

[0020]

[0021] Wherein, Q represents the fluid flow rate flowing through the cascade passage, v represents the first component of the velocity vector, u represents the second component of the velocity vector, Q0 represents the stream function value of the streamline at the suction surface, and Q1 represents the stream function value of the streamline at the pressure surface.

[0022] According to the gas turbine endwall streamwise rib shaping method provided by the present invention, the following relationship is satisfied between the fluid flow rate flowing through the cascade passage and the node coordinates on the streamline at the suction surface and the node coordinates on the streamline at the pressure surface:

[0023]

[0024] Wherein, Q represents the fluid flow rate flowing through the cascade passage, (x0, y0) represents the node coordinates on the streamline at the suction surface, (x1, y1) represents the node coordinates on the streamline at the pressure surface, v represents the first component of the velocity vector, and u represents the second component of the velocity vector.

[0025] According to the gas turbine endwall streamwise rib shaping method provided by the present invention, the streamwise rib structure includes: 7 rib structures arranged at equal intervals in the cascade passage along the flow direction, the starting position of the rib structure is the cascade frontal line, the ending position of the rib structure is at 30% of the axial chord length in front of the cascade trailing edge perpendicular to it, and the overall height of the streamwise rib structure conforms to the height layout of the non-axisymmetric endwall structure.

[0026] According to the gas turbine endwall streamwise rib shaping method provided by the present invention, the expression of the height distribution function along the flow direction and the normal direction is as follows:

[0027]

[0028] Wherein, A(Sx) represents the value of the height distribution function along the flow direction and the normal direction, B represents the maximum rib height, Sx represents the abscissa value of the node under the endwall coordinates, Sx0 represents the abscissa value at the position of the maximum rib height along the flow direction and the normal direction, and both w1 and w2 represent constant values.

[0029] According to the gas turbine endwall streamwise rib shaping method provided by the present invention, the expression of the height distribution function along the frontal line direction is as follows:

[0030]

[0031] Wherein, Z(Sx, Sy) represents the value of the height distribution function along the frontal line direction, A(Sx) represents the value of the height distribution function along the flow direction and the normal direction, Sx represents the abscissa value of the node under the endwall coordinates, Sx0 represents the abscissa value at the position of the maximum rib height along the flow direction and the normal direction, Sy represents the ordinate value of the node under the endwall coordinates, Sy0 represents the ordinate value at the position of the maximum rib height along the flow direction and the normal direction, and both w3 and w4 represent constant values.

[0032] On the other hand, the present invention also provides a gas turbine, and the end-wall streamwise rib structure of the gas turbine is established by any one of the above-mentioned gas turbine end-wall streamwise rib shaping methods.

[0033] On the other hand, the present invention also provides a gas turbine engine, including the above-mentioned gas turbine.

[0034] The gas turbine end-wall streamwise rib shaping method, gas turbine and gas turbine engine provided by the present invention obtain the velocity vector of the fluid at the cascade passage, determine the orthogonal body-fitted coordinate data of the shaping area according to the velocity vector, the stream function and the potential function; determine the maximum rib height of the streamwise rib, and generate a three-dimensional surface for characterizing the structural form of the non-axisymmetric end wall based on the orthogonal body-fitted coordinate data and the maximum rib height; correct the maximum rib height according to the three-dimensional surface and the pre-established height distribution functions along the streamwise and normal directions and the height distribution function along the frontal line direction to obtain the streamwise rib structure. Since the non-axisymmetric end wall structure is combined with the streamwise rib, the vortex intensity of the secondary flow vortex system is effectively suppressed by the streamwise rib structure, the covered area of the total pressure loss core area is reduced, and at the same time, the development form of the thermal boundary layer in the end wall area is optimized, realizing the collaborative optimization of aerodynamic performance and cooling performance. Description of the Drawings

[0035] In order to more clearly illustrate the technical solutions in the present invention or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the following drawings are some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0036] Figure 1 is a schematic flow chart of the gas turbine end-wall streamwise rib shaping method provided by the embodiment of the present invention;

[0037] Figure 2 is a schematic diagram of the body-fitted grid structure corresponding to the orthogonal body-fitted coordinate data in the cascade passage;

[0038] Figure 3 is a schematic diagram of the overall height distribution form of the shaping area;

[0039] Figure 4 is a schematic diagram of the dimensionless height streamwise rib;

[0040] Figure 5 is a schematic diagram of the cooperative working state of the non-axisymmetric end wall structure and the streamwise rib structure from one perspective;

[0041] Figure 6 is a schematic diagram of the cooperative working state of the non-axisymmetric end wall structure and the streamwise rib structure from another perspective;

[0042] Figure 7 It is a schematic diagram of the collaborative working state of the non-axisymmetric end wall structure and the streamwise rib structure from another perspective. Specific embodiments

[0043] To make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the present invention will be clearly and completely described below with reference to the accompanying drawings in the present invention. Apparently, the described embodiments are some but not all of the embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in the present invention without making creative efforts shall fall within the protection scope of the present invention.

[0044] The following will be combined with Figures 1 to 7 Describe in detail the gas turbine end wall streamwise rib shaping method, gas turbine and gas turbine provided by the embodiments of the present invention.

[0045] Figure 1 It is a schematic flowchart of the gas turbine end wall streamwise rib shaping method provided by the embodiments of the present invention.

[0046] As Figure 1 shown, the gas turbine end wall streamwise rib shaping method provided by the embodiments of the present invention mainly includes the following steps:

[0047] Step 110: Obtain the velocity vector of the fluid at the cascade passage, and determine the orthogonal body-fitted coordinate data of the shaping region based on the velocity vector, stream function and potential function.

[0048] It can be understood that the stream function and potential function are two important functions used to describe fluid flow in fluid mechanics. The difference in the stream function within a certain region can represent the flow rate through this region. The gradient of the potential function gives the velocity vector. Therefore, the rate of change of the potential function reflects the magnitude and direction of the velocity.

[0049] Step 120: Determine the maximum rib height of the streamwise rib, and generate a three-dimensional surface based on the orthogonal body-fitted coordinate data and the maximum rib height; wherein, the three-dimensional surface is used to characterize the structural form of the non-axisymmetric end wall.

[0050] In practical applications, the maximum rib height of the streamwise rib can be reasonably set according to actual needs, and usually takes a value of about 1.4 mm - 1.5 mm.

[0051] Step 130: Modify the maximum rib height according to the three-dimensional surface and the pre-established height distribution functions along the streamwise and normal directions and the height distribution function along the frontal line direction to obtain the streamwise rib structure.

[0052] It should be noted that in this embodiment, a three-dimensional surface is obtained through an axisymmetric endwall shaping process, and the rib height is corrected by this three-dimensional surface to obtain a streamwise rib structure. Only one implementation process of an axisymmetric endwall shaping process is exemplarily shown in the above steps. In practical applications, other axisymmetric endwall shaping processes can also be used in this embodiment to realize the construction of a three-dimensional surface.

[0053] In this embodiment, the axisymmetric endwall can weaken the vortex intensity in the cascade passage, reduce the secondary flow loss, and the streamwise rib structure can guide the cold air to flow along the wall according to the flow field characteristics, reducing the mainstream mixing. The micro-rib parameters of the streamwise rib structure are matched with the axisymmetric endwall geometry in real time, which can ensure the performance stability under a complex flow field, thus realizing the collaborative optimization of aerodynamic performance and thermal performance.

[0054] In one embodiment, according to the velocity vector, stream function, and potential function, the orthogonal body-fitted coordinate data of the shaping region is determined, including:

[0055] First, according to the velocity vector, stream function, and potential function, the flow rate value between two adjacent streamlines is determined.

[0056] This embodiment is mainly based on the basic properties of the stream function and potential function, uses the velocity vector of the fluid at the cascade passage in the two-dimensional plane to calculate the stream function and potential function, and draws streamlines and equipotential lines.

[0057] Since the difference in the stream function between two equal streamlines is the flow rate between the two streamlines, let the stream function value of the streamline at the suction surface be Q0, and the stream function value of the streamline at the pressure surface be Q1, then the fluid flow rate through the cascade passage can be expressed as follows:

[0058]

[0059] where Q represents the fluid flow rate through the cascade passage, v represents the first component of the velocity vector, and u represents the second component of the velocity vector.

[0060] At the same time, the following relationship is satisfied between the node coordinates on the streamline at the suction surface, the node coordinates on the streamline at the pressure surface, and the fluid flow rate through the cascade passage:

[0061]

[0062] where Q represents the fluid flow rate through the cascade passage, (x0, y0) represents the node coordinates on the streamline at the suction surface, (x1, y1) represents the node coordinates on the streamline at the pressure surface, v represents the first component of the velocity vector, and u represents the second component of the velocity vector.

[0063] Assume that from the suction surface to the pressure surface, the equipotential line is divided into n segments, then the expression of the flow rate value between two adjacent streamlines is as follows:

[0064]

[0065] Among them, represents the line-to-line flow rate value between two adjacent streamlines, n represents the number of segments of the equipotential lines from the suction surface to the pressure surface, Q represents the fluid flow rate through the cascade passage, and m represents a value determined according to n. v represents the first component of the velocity vector, u represents the second component of the velocity vector, and (xm, ym) and both represent the node coordinates in the Cartesian coordinate system.

[0066] Then, starting from the streamline at the suction surface, each on-line node on the current streamline is successively advanced by the line-to-line flow rate value along the vertical direction of the velocity vector to obtain multiple target nodes.

[0067] It can be understood that according to the above-mentioned advancement method, the obtained streamwise rib structures are arranged circumferentially at equal intervals between the cascade passages.

[0068] Finally, the corresponding target nodes are connected to obtain the orthogonal body-fitted coordinate data of the modeling area. Figure 2 The orthogonal body-fitted coordinate data in the cascade passage is shown in the form of a body-fitted grid.

[0069] It should be noted that the modeling area in this embodiment includes but is not limited to the position from the cascade frontal line to the trailing edge of the cascade pressure surface.

[0070] In practical applications, first, the rib height of the streamwise rib is uniformly set to the maximum rib height, and then, based on the three-dimensional surface in the non-axisymmetric endwall modeling scheme, as well as the height distribution functions along the flow direction and the normal direction and the height distribution function along the frontal line direction, the rib height of the streamwise rib is corrected.

[0071] In this embodiment, the expression of the height distribution function along the flow direction and the normal direction is specifically as follows:

[0072]

[0073] Among them, A(Sx) represents the value of the height distribution function along the flow direction and the normal direction, B represents the maximum rib height, Sx represents the abscissa value of the node under the coordinates of the endwall, Sx0 represents the abscissa value of the position of the maximum rib height along the flow direction and the normal direction, and w1 and w2 are both constant values. In one value-taking scheme, w1 is the flow direction value of sx0 in the orthogonal body-fitted coordinates, and w2 is the subtraction of the maximum value of the modeling area from w1.

[0074] In this embodiment, the expression of the height distribution function along the frontal line direction is specifically as follows:

[0075]

[0076] Among them, Z(Sx, Sy) represents the value of the height distribution function in the direction of the frontal line, A(Sx) represents the value of the height distribution function in the flow direction and the normal direction, Sx represents the abscissa value of the node under the coordinate where the end wall is located, Sx0 represents the abscissa value of the position with the maximum rib height in the flow direction and the normal direction, Sy represents the ordinate value of the node under the coordinate where the end wall is located, Sy0 represents the ordinate value of the position with the maximum rib height in the flow direction and the normal direction, and both w3 and w4 represent constant values. In one value-taking scheme, w3 is the normal value of Sy0 in the orthogonal body-fitted coordinate, and w4 is the subtraction of the maximum value in the modeling area from w3.

[0077] In practical applications, according to the above maximum rib height and based on the body-fitted grid, a three-dimensional surface can be generated. Then, based on the three-dimensional surface and the pre-established height distribution functions in the flow direction and the normal direction and the height distribution function in the frontal line direction, the maximum rib height can be corrected to obtain the flow-direction rib structure. In this embodiment, the overall height distribution of the modeling area can be referred to Figure 3 as shown.

[0078] Figure 4 shows the structure of the dimensionless height flow-direction rib. Figure 5 、 Figure 6 and Figure 7 exemplarily show the cooperative working states of the non-axisymmetric end wall structure and the flow-direction rib structure from different perspectives respectively, Figure 5 、 Figure 6 and Figure 7 in which 210 represents the blade, Figure 6 in which 220 represents the rib structure.

[0079] As Figure 6 shown, the flow-direction rib structure includes: 7 rib structures 220 arranged at equal intervals in the flow direction between the cascade channels. The starting position of the rib structure 220 is the frontal line of the cascade, and the ending position of the rib structure 220 is at 30% of the axial chord length in front of the trailing edge of the cascade perpendicular to it. The overall height of the flow-direction rib structure conforms to the height layout of the non-axisymmetric end wall structure.

[0080] To sum up, the setting of the flow-direction rib structure can generate a vortex system structure with a rotation direction opposite to that of the secondary flow, thereby reducing the cross-flow effect of the cascade, effectively weakening the interaction intensity between the horseshoe vortex and the passage vortex, reducing the high-intensity vorticity, effectively suppressing the vorticity intensity of the secondary flow vortex system. At the same time, the flow-direction rib structure promotes the reduction of the coverage area of the total pressure loss core area. More significantly, the flow-direction rib structure can optimize the development form of the thermal boundary layer in the end wall area. The flow-direction rib structure can guide the cold air to flow along the wall according to the flow field characteristics, provide an attachment effect for the cold air, enhance the coherence of the cold air film coverage, reduce the mainstream mixing, and the micro-rib parameters are matched with the non-axisymmetric end wall geometry in real time to ensure the performance stability under complex flow fields, thereby realizing the collaborative optimization of aerodynamic performance and thermal performance through a dual action mechanism.

[0081] Based on the same general inventive concept, the present invention also protects a gas turbine and a gas turbine engine. The gas turbine and the gas turbine engine provided by the present invention will be described below, and the gas turbine and the gas turbine engine described below can be correspondingly referred to the gas turbine end wall streamwise rib shaping method described above.

[0082] It should be noted that the gas turbine provided by the embodiments of the present invention can establish the end wall streamwise rib structure by the gas turbine end wall streamwise rib shaping method in the above embodiments.

[0083] Furthermore, the gas turbine engine provided by the embodiments of the present invention specifically includes the above-mentioned gas turbine.

[0084] It can be understood that since the gas turbine end wall streamwise rib shaping method provided by this embodiment uses an asymmetric end wall to suppress secondary flow, thereby reducing aerodynamic losses, and the adiabatic cold effectiveness of the end wall is significantly improved through the streamwise rib structure, realizing the coupled design of the asymmetric end wall and the streamwise rib structure, providing a new solution for high-load gas turbines, and thus improving the working performance of the gas turbine and the gas turbine engine.

[0085] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that they can still modify the technical solutions recorded in the foregoing embodiments, or perform equivalent replacements on some of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A method for shaping the flow ribs on the end wall of a gas turbine, characterized in that, Including: Obtain the velocity vector of the fluid at the cascade passage, and determine the orthogonal body-fitted coordinate data of the modeling region based on the velocity vector, stream function, and potential function; Determine the maximum rib height of the streamwise rib, and generate a three-dimensional surface based on the orthogonal body-fitted coordinate data and the maximum rib height; wherein, the three-dimensional surface is used to represent the structural form of the non-axisymmetric end wall; Modify the maximum rib height according to the three-dimensional surface and the pre-established height distribution function along the flow direction and normal direction and the height distribution function along the frontal line direction to obtain the streamwise rib structure.

2. The flow rib shaping method for the gas turbine end wall according to claim 1, wherein Determine the orthogonal body-fitted coordinate data of the modeling region based on the velocity vector, stream function, and potential function, including: Determine the inter-streamline flow rate value between two adjacent streamlines based on the velocity vector, stream function, and potential function; Starting from the streamline at the suction surface, successively advance each on-stream node on the current streamline along the perpendicular direction of the velocity vector by the inter-streamline flow rate value to obtain a plurality of target nodes; Connect the corresponding target nodes to obtain the orthogonal body-fitted coordinate data of the modeling region.

3. The gas turbine end wall flow direction rib modeling method according to claim 2, characterized in that The expression of the inter-streamline flow rate value between two adjacent streamlines is as follows: Among them, represents the line-to-line flow value between two adjacent streamlines, n represents the number of segments of the equipotential lines from the suction surface to the pressure surface, Q represents the fluid flow through the cascade passage, and m represents a value determined according to n. v represents the first component of the velocity vector, u represents the second component of the velocity vector, and (xm, ym) and both represent the node coordinates in the Cartesian coordinate system.

4. The method for shaping the flow direction ribs of the gas turbine end wall according to claim 3, wherein The relationship between the fluid flow rate through the cascade passage and the stream function values of the streamlines at the suction surface and the pressure surface is as follows: Wherein, Q represents the fluid flow rate through the cascade passage, v represents the first component of the velocity vector, u represents the second component of the velocity vector, Q0 represents the stream function value of the streamline at the suction surface, and Q1 represents the stream function value of the streamline at the pressure surface.

5. The method for shaping the flow direction ribs of the gas turbine end wall according to claim 3, wherein, The relationship between the fluid flow rate through the cascade passage and the on-stream node coordinates at the suction surface and the on-stream node coordinates at the pressure surface is as follows: Wherein, Q represents the fluid flow rate through the cascade passage, (x0, y0) represents the on-stream node coordinates at the suction surface, (x1, y1) represents the on-stream node coordinates at the pressure surface, v represents the first component of the velocity vector, and u represents the second component of the velocity vector.

6. The method for shaping the flow direction ribs of the gas turbine end wall according to claim 1, characterized in that The streamwise rib structure includes: 7 rib structures arranged at equal intervals between the cascade passages along the flow direction, the starting position of the rib structure is the cascade frontal line, the ending position of the rib structure is 30% of the axial chord length in front of the cascade trailing edge perpendicular to it, and the overall height of the streamwise rib structure conforms to the height layout of the non-axisymmetric end wall structure.

7. The method for shaping the flow direction ribs of the gas turbine end wall according to claim 1, characterized in that The expression of the height distribution function along the flow direction and normal direction is as follows: Wherein, A(Sx) represents the value of the height distribution function along the flow direction and normal direction, B represents the maximum rib height, Sx represents the abscissa value of the node under the end wall coordinates, Sx0 represents the abscissa value of the position of the maximum rib height along the flow direction and normal direction, and w1 and w2 are both constant values.

8. The method for shaping the flow direction ribs of the gas turbine end wall according to claim 7, characterized in that The expression of the height distribution function along the frontal line direction is as follows: Wherein, Z(Sx, Sy) represents the value of the height distribution function along the frontal line direction, A(Sx) represents the value of the height distribution function along the flow direction and normal direction, Sx represents the abscissa value of the node under the end wall coordinates, Sx0 represents the abscissa value of the position of the maximum rib height along the flow direction and normal direction, Sy represents the ordinate value of the node under the end wall coordinates, Sy0 represents the ordinate value of the position of the maximum rib height along the flow direction and normal direction, and w3 and w4 are both constant values.

9. A gas turbine, characterized in that, The gas turbine establishes an end-wall flow rib structure by means of the end-wall flow rib shaping method according to any one of claims 1 to 8.

10. A gas turbine, characterized in that, It includes a gas turbine according to claim 9.

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