Turbulence rib, turbulence rib construction method and turbine blade

Abstract

The present application provides a spoiler rib, a spoiler rib construction method and a turbine blade, the spoiler rib is a parabolic type of face symmetry, the rib wall of the spoiler rib includes a windward slope on one side of the parabolic opening and a leeward slope on the other side, the intersection line of the windward slope and the leeward slope is a rib ridge line, the rib ridge line is the maximum rib height at the symmetry plane and the rib height gradually decreases along the symmetry plane to both sides. It can solve the technical problems that the existing spoiler rib structure is difficult to balance low flow resistance and high heat transfer.

Description

Technical Field

[0001] This invention relates to the field of spoiler rib technology, and particularly to a spoiler rib, a spoiler rib construction method, and a turbine blade. Background Technology

[0002] Aero engines are crucial strategic equipment for ensuring national security, and increasing turbine inlet temperature is a core means of improving engine thermal efficiency and power output. Currently, advanced aero engines are developing towards wider airspace, higher speed ranges, and lower energy consumption, with turbine inlet temperatures far exceeding the tolerance limits of high-temperature alloy materials, and energy losses from turbine cooling bleed air are also gradually increasing. Therefore, efficient and low-resistance cooling structures are key requirements for reducing turbine temperature and cooling bleed air energy losses, ensuring long-term service of turbine blades, and supporting engine performance and safe and reliable operation.

[0003] Fluid-disrupting ribs are among the most widely used turbine cooling structures. They enhance wall heat transfer by increasing the heat transfer area, disturbing the boundary layer to induce fluid separation and reattachment, and inducing secondary flow to enhance the mixing of hot and cold fluids. Existing rib structures include straight ribs, oblique ribs, V-ribs, W-ribs, S-ribs, aircraft-shaped ribs, shark-scale ribs, discontinuous ribs, staggered ribs, and rib-recess combinations, which have achieved certain results in reducing channel resistance, enhancing wall heat transfer, and resisting particle deposition. However, existing rib structures always face the contradiction of significantly increasing resistance while enhancing heat transfer, and significantly weakening heat transfer while reducing resistance. They are difficult to simultaneously meet the design requirements of low flow resistance and high heat transfer, thus leading to a bottleneck in overall performance improvement. Summary of the Invention

[0004] In view of this, embodiments of the present invention provide a rib, a method for constructing a rib, and a turbine blade to solve the technical problem that existing rib structures cannot simultaneously achieve low flow resistance and high heat transfer.

[0005] This solution is implemented using the following technical methods, specifically including:

[0006] The first aspect of the present invention provides a spoiler rib, which is a parabolic shape with surface symmetry. The rib wall of the spoiler rib includes a windward slope on one side of the opening of the parabola and a leeward slope on the other side. The intersection line of the windward slope and the leeward slope is a rib height ridge line. The rib height ridge line has the maximum rib height at the plane of symmetry and the rib height gradually decreases from side to side along the plane of symmetry.

[0007] A second aspect of the present invention provides a method for constructing a spoiler rib, the method being used to generate a spoiler rib as described in the first aspect, the method comprising the following steps: A coordinate system is constructed with the intersection of the first bottom contour line corresponding to the symmetry plane and the bottom surface of the leeward slope as the origin. The plane containing the second bottom contour line corresponding to the bottom surface of the windward slope and the first bottom contour line is the xy plane, and the plane containing the symmetry plane is the xz plane. The fixed points and control points of the spoiler ribs are determined. The fixed points include the first coordinate point (0,0,0) and the third coordinate point corresponding to the endpoint of the second bottom contour line. l , w / 2,0), the fourth coordinate point corresponding to the intersection of the second bottom contour line and the symmetry plane ( l 2,0,0), the fifth coordinate point corresponding to the intersection of the symmetry plane and the rib ridge line ( l 3,0 e The control points include a first control point (0, y 1,0), second control point ( x 2, y 2,0), Third control point ( x 3, y 3,0), Fourth control point ( l 2, y 4,0), Fifth control point ( x 5,0, z 5) Sixth control point ( x 6,0, e ), the seventh control point ( x 7,0, e ) and the eighth control point ( x 8,0, z 8), among which, For the first x-coordinate of control point =2, 3, 5, 6, 7, 8, For the first The ordinate of the control point =1, 2, 3, 4, For the first Vertical coordinates of control points =5, 8, w The width of the spoiler rib. l is The length of the spoiler ribs l 2 represents the distance from the origin to the intersection of the second bottom contour line and the plane of symmetry. e For the maximum rib height, l 3 represents the maximum rib height. x Axial length; Based on the fixed points and the control points, a non-uniform rational B-spline is used to parametrically describe and obtain the first bottom contour line, the second bottom contour line, the leeward slope ridge line, and the windward slope ridge line. The first coordinate point, the first control point, the second control point, and the third coordinate point are used to control the generation of the first bottom contour line; the third coordinate point, the third control point, the fourth control point, and the fourth coordinate point are used to control the generation of the second bottom contour line; the first coordinate point, the fifth control point, the sixth control point, and the fifth coordinate point are used to control the generation of the leeward slope ridge line; and the fifth coordinate point, the seventh control point, the eighth control point, and the fourth coordinate point are used to control the generation of the windward slope ridge line. The leeward slope ridge line is the intersection of the plane of symmetry and the leeward slope, and the windward slope ridge line is the intersection of the plane of symmetry and the windward slope. The leeward slope is obtained by sweeping the ridge line of the leeward slope along the first bottom surface contour line, and the windward slope is obtained by sweeping the ridge line of the windward slope along the second bottom surface contour line, thereby obtaining the turbulence rib.

[0008] A third aspect of the present invention provides a turbine blade, comprising a blade tip, a blade body, a rim plate, an extension root, and a tenon arranged sequentially. The blade body is provided with an internal cooling channel, and a rib structure is provided along the internal cooling channel. The rib structure includes at least one rib constructed using a rib construction method described in the second aspect, and the opening of the rib faces the direction of the incoming cold air flow.

[0009] Compared with the prior art, the beneficial effects that at least one technical solution adopted in the embodiments of this specification can achieve include at least: The flow-deflecting ribs of this invention adopt an axisymmetric parabolic structure, whose topological configuration is modeled after real parabolic sand dunes in nature. The parabolic opening faces the incoming cold air flow, and the rib height gradually decreases along the axis of symmetry to both sides, thereby making the streamlines of the rib wall smoother, increasing the fluid velocity in the near-wall region, increasing the scouring intensity of the fluid on the wall, and at the same time reducing the intensity of secondary flow and the mixing intensity of hot and cold fluids after separation and reattachment behind the rib. Therefore, heat transfer can be improved while reducing flow resistance. Attached Figure Description

[0010] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0011] Figure 1 This is a perspective view of a baffle rib provided in an embodiment of the present invention; Figure 2 This is a top view of a spoiler rib provided in an embodiment of the present invention; Figure 3 yes Figure 2Sectional view of AA; Figure 4 This is a schematic diagram of the relevant fixing points and control points of the second bottom contour line and the first bottom contour line provided in the embodiment of the present invention; Figure 5 This is a schematic diagram of the relevant fixed points and control points of the windward slope ridge line and the leeward slope ridge line provided in the embodiments of the present invention; Figure 6 This is a schematic diagram of the structure of a turbine blade provided in an embodiment of the present invention; Figure 7 A schematic diagram of numerical simulation using a straight channel; Figure 8 This is a schematic diagram of the structure of the first bleeder rib provided in an embodiment of the present invention; Figure 9 This is a schematic diagram of the structure of the second friction rib provided in an embodiment of the present invention; Figure 10 This is a schematic diagram of the structure of the third bleeder rib provided in an embodiment of the present invention; Figure 11 This is a schematic diagram of an internal cooling channel provided by the present invention.

[0012] Figure reference numerals: 1. Leaf tip; 2. Leaf blade; 3. Edge plate; 4. Tenon; 5. Extending root; 6. Partition; 7. Deflector rib; 701. Windward slope; 702. Second bottom surface outline; 703. Leeward slope; 704. First bottom surface outline; 705. Shaped edge; 706. Windward slope ridge line; 707. Leeward slope ridge line; 708. Rib height ridge line; 8. Velocity inlet; 9. Pressure outlet; 10. Isofluid wall; 11. Insulating wall; 12. First turbulence rib; 13. Second turbulence rib; 14. Third turbulence rib. Detailed Implementation

[0013] The embodiments of this application will now be described in detail with reference to the accompanying drawings.

[0014] The following specific examples illustrate the implementation of this application. Those skilled in the art can easily understand other advantages and effects of this application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. This application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of this application. It should be noted that, in the absence of conflict, the following embodiments and features in the embodiments can be combined with each other. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0015] Inspired by parabolic sand dunes in nature, the inventors reverse-engineered and simplified these dunes to develop a flow-disrupting rib that improves heat transfer while reducing flow resistance. In this regard, the first aspect of the invention provides a flow-disrupting rib, such as... Figure 1 , Figure 2 and Figure 3 As shown, the spoiler rib is a parabolic shape with surface symmetry. The rib wall of the spoiler rib includes a windward slope 701 located on one side of the parabolic opening and a leeward slope 703 located on the other side. The intersection line of the windward slope and the leeward slope is the rib height ridge line 708. The rib height ridge line has the maximum rib height at the plane of symmetry and the rib height gradually decreases from side to side along the plane of symmetry.

[0016] To reduce the structural strength constraints and processing risks caused by sharp corners, a shaping edge 705 is provided at both ends of the first bottom surface outline 704 corresponding to the bottom surface of the leeward slope, and the shaping edge 705 is parallel to the symmetry plane.

[0017] Based on the rib structure provided in the first aspect, the second aspect of the present invention provides a method for constructing ribs, specifically, the method includes steps S1 to S4.

[0018] Step S1: Construct a coordinate system with the intersection of the first bottom contour line corresponding to the symmetry plane and the bottom surface of the leeward slope as the origin. The plane containing the second bottom contour line corresponding to the bottom surface of the windward slope and the first bottom contour line is the xy plane, and the plane containing the symmetry plane is the xz plane.

[0019] Step S2: Determine the fixing points and control points of the spoiler ribs, such as... Figure 4 and Figure 5 As shown, the fixed points include the first coordinate point (0,0,0) and the third coordinate point corresponding to the endpoint of the second bottom contour line 702. l , w / 2,0), the fourth coordinate point corresponding to the intersection of the second bottom contour line and the symmetry plane ( l2,0,0), the fifth coordinate point corresponding to the intersection of the symmetry plane and the rib ridge line ( l 3,0 e The control points include a first control point (0, y 1,0), second control point ( x 2, y 2,0), Third control point ( x 3, y 3,0), Fourth control point ( l 2, y 4,0), Fifth control point ( x 5,0, z 5) Sixth control point ( x 6,0, e ), the seventh control point ( x 7,0, e ) and the eighth control point ( x 8,0, z 8), among which, For the first x-coordinate of control point =2, 3, 5, 6, 7, 8, For the first The ordinate of the control point =1, 2, 3, 4, For the first Vertical coordinates of control points =5, 8, w The width of the spoiler rib. l is The length of the spoiler ribs l 2 represents the distance from the origin to the intersection of the second bottom contour line and the plane of symmetry. e For the maximum rib height, l 3 represents the maximum rib height. x Axial length.

[0020] Taking the shaping edge 705 into account, the fixed point in this step also includes the second coordinate point corresponding to one endpoint of the shaping edge. l - l 1, w / 2,0), where, l 1 represents the side length of the modified edge. The other endpoint of the modified edge is the third coordinate point ( l , w / 2,0).

[0021] Among them, the first control point (0, y (1,0) is located on the y-axis so that the spline curve intersects with... y The axes are tangent, ensuring that the bottom profile of the leeward slope is continuous at the origin. Third coordinate point ( l , w / 2,0) and the second coordinate point ( l - l 1, w / 2,0) y Same coordinates, fourth control point ( l 2, y 4,0) and the fourth coordinate point ( l The x-coordinates of (2, 0, 0) are the same, ensuring that the outline of the second bottom surface is first-order continuous at the fourth coordinate point.

[0022] The total number of degrees of freedom for the first and second bottom surface contour lines is 10.

[0023] Sixth control point ( x 6,0, e ), the seventh control point ( x 7,0, e ) and the fifth coordinate point ( l 3,0 e The vertical coordinates of the ridge lines are the same, ensuring that the ridge lines on the windward and leeward slopes are continuous at the fifth coordinate point. The total number of degrees of freedom for the ridge lines is 8.

[0024] That is, the total number of degrees of freedom of the ribs in this scheme is 18.

[0025] By adjusting the aforementioned fixed points and control points, the width, length, trimmed edge, spanwise expansion angle, and shape of the disturbance can be controlled.

[0026] To achieve low flow resistance and high heat transfer under optimal conditions for the fringe, the following settings can be adopted for various parameters at the fixed point and control point: y 1 = 3.35 x 2 = 5.59 y 2 = 9.65 w =25.4, l =15.67, x 3 = 9.65 y 3 = 7.11 y 4 = 3.30 l 2 = 6.86 x 5 = 0.89 z 5 = 0.89 x 6 = 1.93 e =2.40, l 3 = 4.06 x 7 = 6.35 x 8 = 5.33 z 8 = 1.32.

[0027] Step S3: Based on the fixed points and the control points, a non-uniform rational B-spline is used to parametrically describe and obtain the first bottom contour line, the second bottom contour line, the leeward slope ridge line 707, and the windward slope ridge line 706. The first coordinate point, the first control point, the second control point, and the third coordinate point are used to control the generation of the first bottom contour line; the third coordinate point, the third control point, the fourth control point, and the fourth coordinate point are used to control the generation of the second bottom contour line; the first coordinate point, the fifth control point, the sixth control point, and the fifth coordinate point are used to control the generation of the leeward slope ridge line 707; and the fifth coordinate point, the seventh control point, the eighth control point, and the fourth coordinate point are used to control the generation of the windward slope ridge line 706. The leeward slope ridge line 707 is the intersection of the plane of symmetry and the leeward slope, and the windward slope ridge line 706 is the intersection of the plane of symmetry and the windward slope.

[0028] The profiles and ridges of both the windward and leeward slopes are third-order non-uniform rational B-splines, each controlled by four points.

[0029] In step 2, if a shaping edge 705 is designed, the first bottom contour line is generated based on the first coordinate point, the first control point, the second control point, and the second coordinate point.

[0030] Step S4: Sweep the leeward slope ridge line 707 along the first bottom surface contour line to obtain the leeward slope, and sweep the windward slope ridge line 706 along the second bottom surface contour line to obtain the windward slope, thereby obtaining a turbulence rib with a smooth and continuous curved surface.

[0031] A third aspect of the present invention provides a turbine blade, such as Figure 6 As shown, the blade includes a blade tip 1, a blade body 2, a fin plate 3, an extension root 5, and a tenon 4 arranged sequentially. The blade body 2 has an internal cooling channel, and a rib structure is provided along the internal cooling channel. The rib structure includes at least one rib constructed using any of the rib construction methods described in the second aspect. The opening of the rib 7 faces the direction of the incoming cold airflow. The internal cooling channel is formed by the area between two baffles 6 in the blade body 2.

[0032] Specifically, the friction ribs are arranged on the suction side or pressure side wall of the internal cooling channel.

[0033] The blade may have the cooling forms available to conventional blades, including but not limited to impact holes, film cooling holes, turbulence columns, tail slots, impact bushings, laminates, double walls, etc.

[0034] Multiple rows of friction ribs can be arranged, and adjacent rows of friction ribs are preferably staggered to enhance the disturbance of the wall boundary layer and thus enhance heat transfer.

[0035] The ratio of the maximum rib height e of the friction rib to the height of the internal cooling channel is greater than or equal to 0.02 and less than or equal to 0.08, and the ratio of the flow direction spacing between two adjacent sets of friction ribs to the maximum rib height e is greater than or equal to 8 and less than or equal to 15.

[0036] The ratio of the width to the height of the internal cooling aisle is greater than or equal to 1 and less than or equal to 4.

[0037] To demonstrate the technical advantages of this scheme, numerical simulation was used to compare the flow and heat transfer performance of 45° oblique ribs, V-ribs, and the turbulence ribs of this scheme under the same rib spacing ratio, blockage ratio, and boundary conditions.

[0038] like Figure 7 As shown, a straight channel is used for simulation. The straight channel includes a velocity inlet (8), a pressure outlet (9), an isothermal wall (10), and an adiabatic wall (11). Two rows of baffles are arranged on the bottom surface of the straight channel, with adjacent rows staggered. The ends of the baffles are close to the sidewalls of the channel. Each row has 8 baffles, for a total of 16. The cross-sectional dimensions of the straight channel are... W × H =50.8 mm × 50.8 mm, W is The width of the straight channel, H is The height of the straight channel and its aspect ratio are both 1; the width of the spoiler ribs is also considered. w =25.4 mm, maximum rib height e =2.4 mm, rib spacing ratio P / e=10, rib blockage ratio e / H =0.047, P is The flow direction spacing between two adjacent spoiler ribs.

[0039] The working fluid in the numerical simulation of heat transfer in the internal cooling channel is incompressible air at room temperature. The boundary conditions include a velocity inlet (8), a pressure outlet (9), an isothermal wall (10), and an adiabatic wall (11). The inlet velocity is 9.12 m / s, the inlet temperature is 300 K, the outlet pressure is 1 atm, and the wall heat flux density is 1000 W / m². 2 The Reynolds number, defined by the hydraulic diameter of the channel, is 3 × 10⁻⁶. 4 .

[0040] With the maximum height and width of the ribs determined, different structures of ribs can be generated by adjusting the coordinates of various fixed points and control points, thereby achieving the adjustment of their flow resistance and heat transfer performance.

[0041] By adjusting the fixed points and control points, a first friction rib with low resistance, a second friction rib with high heat transfer, and a third friction rib with superior overall performance in terms of heat transfer and resistance were obtained. The first, second, and third friction ribs were constructed based on the fixed point and control point parameters shown in Table 1. The obtained first friction rib is as follows: Figure 8 As shown, the first spoiler rib has a long and gentle windward slope, a short rib span, a large rib expansion angle, and a small length-to-width ratio. The second spoiler rib is as follows. Figure 9 As shown, the second spoiler rib has a short and steep windward slope, a long rib span, a small rib expansion angle, and a large length-to-width ratio. The third spoiler rib is as follows: Figure 10 As shown.

[0042] Table 1. Parameters of fixing points and control points for the first, second, and third spoiler ribs.

[0043] Compared with arranging 45° oblique ribs and V ribs, arranging the third turbulence ribs reduced the pressure loss of the straight channel by 12.4% and 20.6% respectively, enhanced the heat transfer by 20.3% and 5.5% respectively, and improved the overall performance by 26.4% and 15.6% respectively.

[0044] Numerical simulation analysis shows that the high-order spline design of the parabolic dune turbulence rib and the gradually decreasing rib height along the span can make the rib wall streamline smoother, significantly increase the fluid velocity in the near-wall region, increase the scouring intensity of the fluid on the wall, and at the same time reduce secondary flow and fluid mixing, thereby improving heat transfer while reducing channel resistance.

[0045] To further improve the overall heat transfer uniformity of the channel, such as Figure 11 As shown, the internal cooling aisle is serpentine in shape, comprising a first channel segment, a first connecting segment, a second channel segment, a second connecting segment, and a third channel segment connected in sequence. The first, second, and third channel segments are arranged in parallel. The rib structure in the first channel segment is a single-row structure. The rib structure in the second and third channel segments includes two rows of deflector ribs 7, with adjacent rows of deflector ribs staggered. The rib structure in the first channel segment is the first deflector rib 12, the rib structure in the second channel segment is the second deflector rib 13, and the rib structure in the third channel segment is the third deflector rib 14.

[0046] The first channel section has a smaller channel width, so the baffles are arranged in a single row; the second and third channel sections have larger channel widths, so the baffles are arranged in a double row. Baffles with low flow resistance, high heat transfer performance, and excellent overall performance are sequentially arranged. As the cold air temperature gradually increases and the heat transfer capacity gradually decreases in the first, second, and third channel sections, different rib structures are used to improve the overall heat transfer uniformity of the channel.

[0047] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, various modifications and variations can be made to the embodiments of the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A flow-deflecting rib, characterized in that, The spoiler rib is a parabolic shape with surface symmetry. The rib wall of the spoiler rib includes a windward slope (701) on one side of the parabolic opening and a leeward slope (703) on the other side. The intersection line of the windward slope and the leeward slope is the rib height ridge line (708). The rib height ridge line has the maximum rib height at the plane of symmetry and the rib height gradually decreases from side to side along the plane of symmetry.

2. The flow-deflecting rib as described in claim 1, characterized in that, A modified edge (705) is provided at both ends of the first bottom surface outline (704) corresponding to the bottom surface of the leeward slope, and the modified edge (705) is parallel to the symmetry plane.

3. A method for constructing a flow-deflecting rib, characterized in that, This construction method is used to generate a flow-disrupting rib as described in any one of claims 1 to 2, and the method includes the following steps: A coordinate system is constructed with the intersection of the first bottom contour line corresponding to the symmetry plane and the bottom surface of the leeward slope as the origin. The plane containing the second bottom contour line corresponding to the bottom surface of the windward slope and the first bottom contour line is the xy plane, and the plane containing the symmetry plane is the xz plane. The fixed points and control points of the spoiler ribs are determined. The fixed points include the first coordinate point (0,0,0) and the third coordinate point corresponding to the endpoint of the second bottom contour line (702). l , w / 2, 0), the fourth coordinate point corresponding to the intersection of the second bottom contour line and the symmetry plane ( l 2,0,0), the fifth coordinate point corresponding to the intersection of the symmetry plane and the rib ridge line ( l 3,0 e The control points include a first control point (0, y 1,0), second control point ( x 2, y 2,0), Third control point ( x 3, y 3,0), Fourth control point ( l 2, y 4,0), Fifth control point ( x 5,0, z 5) Sixth control point ( x 6,0, e ), the seventh control point ( x 7,0, e ) and the eighth control point ( x 8,0, z 8), among which, For the first x-coordinate of control point =2, 3, 5, 6, 7, 8, For the first The ordinate of the control point =1, 2, 3, 4, For the first Vertical coordinates of control points =5, 8, w The width of the spoiler rib. l is The length of the spoiler ribs l 2 represents the distance from the origin to the intersection of the second bottom contour line and the plane of symmetry. e For the maximum rib height, l 3 represents the maximum rib height. x Axial length; Based on the fixed points and the control points, a non-uniform rational B-spline is used to parametrically describe the first bottom contour line, the second bottom contour line, the leeward slope ridge line (707), and the windward slope ridge line (706). The first coordinate point, the first control point, the second control point, and the third coordinate point are used to control the generation of the first bottom contour line. The third coordinate point, the third control point, the fourth control point, and the fourth coordinate point are used to control the generation of the second bottom contour line. The first coordinate point, the fifth control point, the sixth control point, and the fifth coordinate point are used to control the generation of the leeward slope ridge line (707). The fifth coordinate point, the seventh control point, the eighth control point, and the fourth coordinate point are used to control the generation of the windward slope ridge line (706). The leeward slope ridge line (707) is the intersection of the symmetry plane and the leeward slope. The windward slope ridge line (706) is the intersection of the symmetry plane and the windward slope. The leeward slope ridge line (707) is swept along the first bottom surface contour line (704) to obtain the leeward slope (703), and the windward slope ridge line (706) is swept along the second bottom surface contour line (702) to obtain the windward slope (701), thereby obtaining the turbulence rib (7).

4. The method for constructing a flow-deflecting rib as described in claim 3, characterized in that, The fixed point also includes the second coordinate point corresponding to one endpoint of the trimmed edge. l - l 1, w / 2,0), where, l 1 represents the side length of the modified edge.

5. The method for constructing a flow-deflecting rib as described in claim 3, characterized in that, The y 1 = 3.35 x 2 = 5.59 y 2 = 9.65 w =25.4, l =15.67, x 3 = 9.65 y 3 = 7.11 y 4 = 3.30 l 2 = 6.86 x 5 = 0.89 z 5 = 0.89 x 6 = 1.93 e =2.40, l 3 = 4.06 x 7 = 6.35 x 8 = 5.33 z 8 = 1.

32.

6. The method for constructing a flow-deflecting rib as described in claim 3, characterized in that, The y 1 = 3.56 x 2 = 5.84 y 2 = 10.16 w =25.40, l =13.51, x 3 = 10.16 y 3 = 6.35 y 4 = 2.54 l 2 = 10.16 x 5 = 0.97 z 5 = 1.02 x 6 = 2.21 e =2.40, l 3 = 3.43 x 7 = 5.08 x 8 = 6.10 z 8 = 1.

19.

7. The method for constructing a flow-deflecting rib as described in claim 3, characterized in that, The y 1 = 3.86 x 2 = 6.68 y 2 = 11.02, w =25.4, l =23.37, x 3 = 11.81 y 3 = 7.87 y 4 = 3.18 l 2 = 7.62, x 5 = 1.04 z 5 = 1.27 x 6 = 2.44 e =2.40, l 3 = 4.57 x 7 = 5.33 x 8 = 6.43 z 8 = 1.

35.

8. A turbine blade, comprising a blade tip (1), a blade body (2), a rim plate (3), an extension root (5), and a tenon (4) arranged sequentially, wherein the blade body (2) is provided with an internal cooling channel, characterized in that, A rib structure is provided along the internal cooling channel. The rib structure includes at least one rib constructed using a rib construction method according to any one of claims 3 to 7. The opening of the rib (7) faces the direction of the incoming cold air flow.

9. A turbine blade as described in claim 8, characterized in that, The ratio of the maximum rib height e to the height of the internal cooling channel is greater than or equal to 0.02 and less than or equal to 0.08, the ratio of the flow direction spacing between two adjacent bleed ribs to the maximum rib height e is greater than or equal to 8 and less than or equal to 15, and the ratio of the width of the internal cooling channel to the height of the internal cooling channel is greater than or equal to 1 and less than or equal to 4.

10. A turbine blade as described in claim 8, characterized in that, The internal cooling channel includes a first channel segment, a first connecting segment, a second channel segment, a second connecting segment, and a third channel segment connected in sequence. The first channel segment, the second channel segment, and the third channel segment are arranged in parallel. The rib structure in the first channel segment is a single-row structure. The rib structure in the second channel segment and the third channel segment includes two rows of baffle ribs (7), and the adjacent two rows of baffle ribs are staggered. The parameters for the fixed points and control points corresponding to the spoiler ribs in the first channel segment are as follows: y 1 = 3.56 x 2 = 5.84 y 2 = 10.16 w =25.40, l =13.51, x 3 = 10.16 y 3 = 6.35 y 4 = 2.54 l 2 = 10.16 x 5 = 0.97 z 5 = 1.02 x 6 = 2.21 e =2.40, l 3 = 3.43 x 7 = 5.08 x 8 = 6.10 z 8 = 1.19; The parameters for the fixed points and control points corresponding to the spoiler ribs in the second channel section are as follows: y 1 = 3.86 x 2 = 6.68 y 2 = 11.02, w =25.4, l =23.37, x 3 = 11.81 y 3 = 7.87 y 4 = 3.18 l 2 = 7.62, x 5 = 1.04 z 5 = 1.27 x 6 = 2.44 e =2.40, l 3 = 4.57 x 7 = 5.33 x 8 = 6.43 z 8 = 1.35; The parameters for the fixed points and control points corresponding to the spoiler ribs in the third channel segment are as follows: y 1 = 3.35 x 2 = 5.59 y 2 = 9.65 w =25.4, l =15.67, x 3 = 9.65 y 3 = 7.11 y 4 = 3.30 l 2 = 6.86 x 5 = 0.89 z 5 = 0.89 x 6 = 1.93 e =2.40, l 3 = 4.06 x 7 = 6.35 x 8 = 5.33 z 8 = 1.32.

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