Cooling assembly, blade and gas turbine

Abstract

The application discloses a cooling assembly, a vane and a gas turbine, and relates to the technical field of the gas turbine, and discloses a cooling assembly, a vane and a gas turbine, which comprises a first plate body, a plurality of first ribs and a plurality of second ribs, a plurality of first holes are arranged on the first plate body, the first plate body and a target plate body are oppositely arranged, the target plate body has a target surface facing the first plate body, a preset included angle is formed between the axial direction of the first hole and the normal direction of the target surface, the plurality of first ribs are arranged on the target surface, and the plurality of second ribs are arranged on the target surface; the first rib group and the second rib group are alternately arranged in a first direction, the first ribs and the second ribs in the adjacent first rib group and the second rib group are arranged in a staggered mode in the first direction, and the first direction and a second direction are orthogonal. The cooling assembly disclosed by the application can strengthen the heat exchange effect and improve the cooling effect of the impact cooling.

Description

Technical Field

[0001] This invention belongs to the field of gas turbine technology, specifically relating to a cooling assembly, blades, and a gas turbine. Background Technology

[0002] Turbine blades are important components of gas turbines. In turbine impact cooling structures of related technologies, the downstream impact cooling effect decreases as the crossflow of accumulated cold gas upstream increases, resulting in poor cooling performance and affecting the reliability of component operation. Summary of the Invention

[0003] The present invention aims to at least partially solve one of the technical problems in the related art.

[0004] Therefore, embodiments of the present invention provide a cooling assembly that can enhance heat exchange and improve the cooling effect of shock cooling.

[0005] An embodiment of the present invention also proposes a blade.

[0006] An embodiment of the present invention further proposes a gas turbine.

[0007] A cooling assembly according to an embodiment of the present invention includes:

[0008] A first plate has a plurality of first holes. The first plate and a target plate are arranged opposite to each other. The target plate has a target surface facing the first plate. The axial direction of the first hole and the normal direction of the target surface have a preset angle.

[0009] Multiple first ribs are disposed on the target surface. The multiple first ribs are divided into multiple groups of first ribs, which are spaced apart along a first direction. Each group of first ribs has multiple first ribs, and the multiple first ribs within the same group are spaced apart along a second direction.

[0010] Multiple second ribs are arranged on the target surface. The multiple second ribs are divided into multiple groups of second ribs. The multiple groups of second ribs are arranged at intervals along the first direction. Each group of second ribs has multiple second ribs. The multiple second ribs in the same group of second ribs are arranged at intervals along the second direction.

[0011] The first rib group and the second rib group are arranged alternately in the first direction, and the first rib and the second rib in adjacent first rib groups and second rib groups are arranged in a staggered manner in the first direction, and the first direction and the second direction are orthogonal.

[0012] The cooling assembly of this invention can enhance heat exchange, improve the cooling effect of impact cooling, and thus improve the stability of component operation.

[0013] In some embodiments, the plurality of first holes are divided into multiple groups of first holes, the multiple groups of first holes are arranged at intervals along a first direction, each group of first holes has a plurality of first holes, and the plurality of first holes in the same group of first holes are arranged at intervals along a second direction.

[0014] In some embodiments, the preset angle between the axial direction of the first hole and the normal direction of the target surface is 0 degrees to 30 degrees; and / or

[0015] The distance between the target surface and the first plate is d to 4d, where d is the diameter of the first hole; and / or

[0016] The spacing between two adjacent groups of the first holes in the first direction is 3d to 15d, where d is the diameter of the first hole; and / or

[0017] In the same group of first holes, the distance between two adjacent first holes in the second direction is 3d to 15d, where d is the diameter of the first hole.

[0018] In some embodiments, the first rib is a wedge-shaped rib in the form of a triangular pyramid, the first rib having a base and a vertex corresponding to the base, the base of the first rib being an isosceles triangle, and the projection of the vertex of the first rib onto the target surface coinciding with the intersection of the two legs of the isosceles triangle.

[0019] In some embodiments, the apex angle of the bottom surface of the first rib is 40 degrees to 100 degrees; and / or

[0020] The distance between the vertex angle and the base of the isosceles triangle on the bottom surface of the first rib is 0.5d to 3d, where d is the diameter of the first hole; and / or

[0021] The distance between the vertex of the first rib and the bottom surface of the first rib is 0.25d to 4d, where d is the diameter of the first hole; and / or

[0022] The spacing between two adjacent groups of the first ribs in the first direction is 3d to 15d, where d is the diameter of the first hole; and / or

[0023] In the same group of first ribs, the distance between two adjacent first ribs in the second direction is 3d to 15d, where d is the diameter of the first hole.

[0024] In some embodiments, the first hole and the first rib are respectively provided in a one-to-one correspondence, and the airflow direction of the first hole corresponds to the vertex of the first rib so that the airflow flows along the three sides of the first rib.

[0025] In some embodiments, the second rib is a hemispherical convex rib.

[0026] In some embodiments, the diameter of the second rib is d to 2.5d, where d is the diameter of the first hole; and / or

[0027] The spacing between two adjacent groups of the second ribs in the first direction is 3d to 15d, where d is the diameter of the first hole; and / or

[0028] In the same group of second ribs, the distance between two adjacent second ribs in the second direction is 3d to 15d, where d is the diameter of the first hole.

[0029] The blade according to an embodiment of the present invention comprises:

[0030] A blade body having an internal cavity;

[0031] The cooling assembly is the cooling assembly described in any of the above embodiments. The cooling assembly is disposed in the inner cavity of the blade body. The inner wall surface of the blade body is the target surface. The first plate is disposed corresponding to the inner wall surface of the blade body. The first rib and the second rib are disposed on the inner wall surface of the blade body. The first direction is the same as the airflow direction.

[0032] The gas turbine according to embodiments of the present invention includes the cooling assembly or the blades described in any of the foregoing embodiments. Attached Figure Description

[0033] Figure 1 This is a front view of the cooling assembly according to an embodiment of the present invention.

[0034] Figure 2 This is a perspective structural diagram of the cooling assembly according to an embodiment of the present invention.

[0035] Figure 3 This is a top view of the cooling assembly according to an embodiment of the present invention.

[0036] Figure 4 This is a schematic diagram of the arrangement of the first and second ribs on the target surface in an embodiment of the present invention.

[0037] Figure 5 This is a schematic diagram of the arrangement of the first and second ribs on the target surface in another embodiment of the present invention.

[0038] Figure 6 This is a front view schematic diagram of the first rib structure according to an embodiment of the present invention.

[0039] Figure 7 This is a top view of the first rib in an embodiment of the present invention.

[0040] Figure 8 These are the target surface average Nusselt number and Reynolds number curves of the cooling component in this embodiment of the invention and the cooling component in related technologies.

[0041] Figure 9 This is a schematic diagram of the blade structure according to an embodiment of the present invention.

[0042] Figure label:

[0043] 100. Cooling components;

[0044] 1. First plate; 11. First hole;

[0045] 2. Target surface;

[0046] 3. First rib;

[0047] 4. Second rib;

[0048] 200. Leaf blade. Detailed Implementation

[0049] Embodiments of the present invention are described in detail below, examples of which are illustrated in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain the present invention, and should not be construed as limiting the present invention.

[0050] like Figures 1-4 As shown, the cooling assembly 100 of this embodiment includes a first plate 1 with a plurality of first holes 11. The first plate 1 and a target plate are arranged opposite to each other. The target plate has a target surface 2 facing the first plate 1. The axial direction of the first hole 11 and the normal direction of the target surface 2 have a preset angle. Cold air flows to the target surface 2 through the first hole 11. Since the axial direction of the first hole 11 and the normal direction of the target surface 2 have a preset angle, the cold air can flow to the target surface 2 at a certain angle. When the cooling assembly 100 is arranged on the turbine blade 200, the target plate is the side wall of the turbine blade 200, and the target surface 2 is the inner wall surface of the turbine blade 200.

[0051] Multiple first ribs 3 and multiple second ribs 4 are arranged on the target surface 2. Specifically, multiple first ribs 3 are arranged on the target surface 2, and the multiple first ribs 3 are divided into multiple groups of first ribs. The multiple groups of first ribs are arranged at intervals along a first direction. Each group of first ribs has multiple first ribs 3. The multiple first ribs 3 located in the same group of first ribs are arranged at intervals along a second direction. Multiple second ribs 4 are arranged on the target surface 2, and the multiple second ribs 4 are divided into multiple groups of second ribs. The multiple groups of second ribs are arranged at intervals along a first direction. Each group of second ribs has multiple second ribs 4. The multiple second ribs 4 located in the same group of second ribs are arranged at intervals along a second direction.

[0052] The first rib group and the second rib group are arranged alternately in the first direction. The first rib 3 and the second rib 4 in the adjacent first rib group and second rib group are staggered in the first direction. The first direction and the second direction are orthogonal. The cold air impacting the target surface 2 through the first hole 11 flows in the first direction. The cold air impacting the target surface 2 can not only reduce the thickness of the boundary layer gas film to enhance the heat transfer effect, but also destroy the boundary layer gas film to improve the internal heat transfer effect. In conjunction with the first rib 3 and the second rib 4, the flow effect of the cold air on the target surface 2 can be optimized to improve the cooling performance.

[0053] The cooling component 100 of this embodiment can enhance the heat exchange effect, improve the cooling effect of impact cooling, and thus improve the stability of component operation. The normal direction of the target surface 2 is the up-down direction. The first hole 11 is tilted to the right and forms a preset angle α with the normal direction of the target surface 2. The airflow direction between the first plate 1 and the target surface 2 flows from right to left.

[0054] The first direction is the left-right direction shown in the figure, and the second direction is the front-back direction shown in the figure.

[0055] like Figure 4 As shown, dashed box A represents a first rib group, and dashed box B represents a second rib group.

[0056] like Figures 1-4 As shown, in some embodiments, the plurality of first holes 11 are divided into multiple groups of first holes 11, the multiple groups of first holes 11 are arranged at intervals along a first direction, each group of first holes 11 has a plurality of first holes 11, and the plurality of first holes 11 located in the same group of first holes 11 are arranged at intervals along a second direction.

[0057] Furthermore, the projection of the axis of the first hole 11 onto the target surface 2 is the same as the first direction, which is the airflow direction of the cold air between the first plate 1 and the target surface 2. The first hole 11 is set at a certain angle relative to the target surface 2. The cold air flows towards the target surface 2, which can reduce the flow resistance and also impact and damage the boundary layer, reduce the boundary layer thickness, improve the heat exchange effect between the cold air and the target surface 2, and enable the cold air to contact the target surface 2 more effectively and fully.

[0058] like Figures 1-3As shown, in some embodiments, the preset angle α between the axial direction of the first hole 11 and the normal direction of the target surface 2 is 0 degrees to 30 degrees. For example, the preset angle α is 0 degrees, 10 degrees, 14 degrees, 22 degrees or 30 degrees. The distance Zn between the target surface 2 and the first plate 1 is d to 4d. For example, the value of Zn is d, 1.3d, 2.2d, 3.6d or 4d. The spacing Yn between two adjacent groups of first holes 11 in the first direction is 3d to 15d. For example, the value of Yn is 3d, 3.6d, 4.5d, 11d, 14.6d or 15d. In the same group of first holes 11, the spacing Xn between two adjacent first holes 11 in the second direction is 3d to 15d. For example, the value of Xn is 3d, 3.6d, 4.5d, 11d, 14.6d or 15d, where d is the diameter of the first hole 11.

[0059] By arranging the above parameters, the uniformity of the cold air on the target surface 2 can be ensured, the total amount of cold air can be reduced while meeting the cooling performance of the target surface 2, the heat exchange efficiency between the cold air and the target surface 2 can be improved, and the flow resistance can be reduced. In addition, the setting of the above parameters takes into account the factors of the production process, reduces the processing and production difficulty, and avoids the inability to process and produce some structures.

[0060] like Figures 4-7 As shown, in some embodiments, the first rib 3 is a wedge-shaped rib in the form of a triangular pyramid. The first rib 3 has a base and a vertex corresponding to the base. The base of the first rib 3 is an isosceles triangle, and the projection of the vertex of the first rib 3 onto the target surface 2 coincides with the intersection of the two legs of the isosceles triangle. It should be understood that the shape of the first rib 3 is approximately a triangular pyramid, and the first rib 3 has a base and three lateral faces, all of which are approximately triangular.

[0061] Alternatively, it can be understood that the first rib 3 is a beveled triangular prism, and the shape of the first rib 3 is obtained by beveling the triangular prism through a bevel.

[0062] Furthermore, the first hole 11 is configured in a one-to-one correspondence with the first rib 3, and the airflow direction of the first hole 11 corresponds to the apex of the first rib 3 so that the airflow flows along the three sides of the first rib 3. When the airflow from the first hole 11 impacts the target surface 2, the cold air is dispersed and turbulent by the action of the first rib 3, which can disrupt the boundary layer gas film. Most of the cold air will disperse and flow along the sides corresponding to the two waists of the bottom surface of the first rib 3, and a portion will flow along the inclined surface corresponding to the bottom of the bottom surface. The dispersed cold air will be further turbulent by the other first ribs 3 and second ribs 4, thereby disrupting the boundary layer gas film and improving the heat transfer effect.

[0063] like Figures 4-7As shown, in some embodiments, the vertex angle β of the bottom surface of the first rib 3 is 40 degrees to 100 degrees, for example, the vertex angle β can be 40 degrees, 46 degrees, 68 degrees, 95 degrees or 100 degrees, and the distance H1 between the vertex angle and the base of the isosceles triangle on the bottom surface of the first rib 3 is 0.5d to 3d, for example, the distance H1 can be 0.5d, 1.2d, 2.2d, 2.8d or 3d.

[0064] The distance H2 between the vertex of the first rib 3 and the bottom surface of the first rib 3 is 0.25d to 4d. For example, the value of H2 is 0.25d, 0.75d, d, 1.6d, 3.3d or 4d.

[0065] The spacing Yc between two adjacent first rib groups in the first direction is 3d to 15d; for example, the value of Yc is 3d, 3.6d, 4.5d, 11d, 14.6d or 15d.

[0066] In the same first rib group, the distance Xc between two adjacent first ribs 3 in the second direction is 3d to 15d, for example, the value of Xc is 3d, 3.6d, 4.5d, 11d, 14.6d or 15d.

[0067] Where d is the diameter of the first hole 11.

[0068] The structural dimensions of the first rib 3 allow for a better determination of its impact on the airflow distribution of the cold air, enabling more uniform dispersion of the cold air on the target surface 2. The coordination with the diameter and tilt angle of the first hole 11 ensures that the disturbance and dispersion effect of the cold air impacting the target surface 2 is superior to the turbulence effect of ribs in related technologies. This guarantees the uniformity of the cold air distribution on the target surface 2, further reducing the thickness of the boundary layer gas film, disrupting the boundary layer gas film, and improving the heat transfer effect. When the structural dimensions of the first rib 3 exceed the above parameters, it can easily lead to increased flow resistance, low heat transfer efficiency, and difficulties in manufacturing and processing.

[0069] like Figures 1-4 As shown, in some embodiments, the second rib 4 is a hemispherical convex rib. It should be understood that the second rib 4 can be approximately hemispherical, and the second rib 4 has a spherical surface. When the cold airflow on the target surface 2 passes through the second rib 4, the spherical surface of the second rib 4 can be used to disturb and disperse the airflow, thereby destroying the gas film of the boundary layer, increasing the disturbance effect on the airflow, and improving the heat exchange efficiency.

[0070] like Figures 1-4 As shown, in some embodiments, the diameter D of the second rib 4 is from d to 2.5d, for example, the value of D is d, 1.2d, 1.8d, 2.3d or 2.5d.

[0071] The spacing Yb between two adjacent second rib groups in the first direction is 3d to 15d. For example, the value of Yb is 3d, 3.6d, 4d, 4.6d, 6.8d, 11d, 13.3d or 15d.

[0072] In the same group of second ribs, the distance Xb between two adjacent second ribs 4 in the second direction is 3d to 15d. For example, the value of Xb is 3d, 3.6d, 4d, 4.6d, 6.8d, 11d, 13.3d or 15d.

[0073] Where d is the diameter of the first hole 11.

[0074] Regarding the structural dimensions of the second rib 4, it further disperses and turbulents the cold air after it has been dispersed and turbulented by the first rib 3, disrupting the boundary layer gas film and improving heat transfer efficiency. The interaction between the first rib 3 and the second rib 4 fully utilizes their respective structural features, reducing the number of second holes, improving the impact cooling effect, and enhancing the turbulence effect of the cold air on the target surface 2. Specifically, the first rib 3 can use its three sides to disperse the impact airflow from the first hole 11 towards the target surface 2 in multiple directions, creating multi-directional impacts on the target surface 2 and improving the turbulence effect of the cold air on the target surface 2. The second rib 4, with its spherical surface, can disrupt the boundary layer gas film on the target surface 2, strengthening the turbulence effect and heat transfer effect of the cold air on the target surface 2. Furthermore, when the structural dimensions of the second rib 4 exceed the aforementioned parameter range, it can easily lead to increased flow resistance, low heat transfer efficiency, and difficulties in manufacturing and processing.

[0075] The flow structure and Nusselt number distribution of the impact cooling component in the related technology and the cooling component 100 in the embodiment of the present invention were compared under typical Reynolds number conditions. The linear disturbance of the cooling component 100 in the embodiment of the present invention is significantly stronger than that of the cooling component in the related technology.

[0076] like Figure 8 As shown, subsequent calculations compared the average Nusselt number of the target surface within the Reynolds number range of 1e5 to 1e6 for cooling air. The Nusselt number of the cooling component 100 in this embodiment of the invention is 16% to 20% higher than that of the impact cooling component in the related art, and the growth trend increases with the increase of the Reynolds number.

[0077] like Figure 9As shown, the blade 200 according to an embodiment of the present invention includes a blade body and a cooling assembly 100. The blade body has an inner cavity. The cooling assembly 100 is the cooling assembly 100 in any of the above embodiments. The cooling assembly 100 is disposed in the inner cavity of the blade body. The inner wall surface of the blade body is the target surface 2. The first plate 1 is disposed corresponding to the inner wall surface of the blade body. The first rib 3 and the second rib 4 are disposed on the inner wall surface of the blade body. The first direction is the same as the airflow direction. The airflow direction is the main direction of the flow of cold air between the first plate 1 and the inner wall surface of the blade body, and not the flow direction of cold air in the first hole 11, or the instantaneous flow direction of a small portion of cold air after being disturbed by the first rib 3 or the second rib 4. It should be understood that the blade body has a length direction. Under normal circumstances, the cold air enters the inner cavity from the air inlet end located at one end of the length direction of the blade body and flows out from the air outlet end (tail edge) at the other end of the length direction of the blade body. The airflow direction of the blade body is the length direction of the blade body, that is, the left and right direction shown in the figure.

[0078] The gas turbine according to embodiments of the present invention includes the cooling assembly 100 or the blades 200 in any of the above embodiments.

[0079] The beneficial effects achieved by the blades and gas turbine in the above embodiments are at least partially the same as those achieved by the cooling components in the above embodiments, and therefore will not be described again.

[0080] In the description of this invention, the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0081] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0082] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection, an electrical connection, or a connection that allows communication between them; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0083] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "over," and "on top" of the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0084] In this invention, the terms "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to a specific feature, structure, material, or characteristic described in connection with that embodiment or example, which is included in at least one embodiment or example of the invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0085] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention.

Claims

1. A cooling assembly, characterized in that, include: A first plate has a plurality of first holes. The first plate and a target plate are arranged opposite to each other. The target plate has a target surface facing the first plate. The axial direction of the first hole and the normal direction of the target surface have a preset angle. Multiple first ribs are arranged on the target surface. The multiple first ribs are divided into multiple groups of first ribs. The multiple groups of first ribs are arranged at intervals along a first direction. Each group of first ribs has multiple first ribs. Multiple first ribs in the same group of first ribs are arranged at intervals along a second direction. The first rib is a wedge-shaped rib in the shape of a triangular pyramid. The first rib has a base and a vertex corresponding to the base. The base of the first rib is an isosceles triangle. The projection of the vertex of the first rib on the target surface coincides with the intersection of the two legs of the isosceles triangle. as well as Multiple second ribs are arranged on the target surface. The multiple second ribs are divided into multiple groups of second ribs. The multiple groups of second ribs are arranged at intervals along the first direction. Each group of second ribs has multiple second ribs. The multiple second ribs in the same group of second ribs are arranged at intervals along the second direction. The second ribs are hemispherical convex ribs. The first rib group and the second rib group are arranged alternately in the first direction, and the first rib and the second rib in adjacent first rib groups and second rib groups are arranged in a staggered manner in the first direction, and the first direction and the second direction are orthogonal.

2. The cooling assembly according to claim 1, characterized in that, The plurality of first holes are divided into multiple groups of first holes, and the multiple groups of first holes are arranged at intervals along a first direction. Each group of first holes has a plurality of first holes, and the plurality of first holes in the same group of first holes are arranged at intervals along a second direction.

3. The cooling assembly according to claim 2, characterized in that, The preset angle between the axial direction of the first hole and the normal direction of the target surface is 0 degrees to 30 degrees; and / or The distance between the target surface and the first plate is d to 4d, where d is the diameter of the first hole; and / or The spacing between two adjacent groups of the first holes in the first direction is 3d to 15d, where d is the diameter of the first hole; and / or In the same group of first holes, the distance between two adjacent first holes in the second direction is 3d to 15d, where d is the diameter of the first hole.

4. The cooling assembly according to claim 1, characterized in that, The apex angle of the bottom surface of the first rib is 40 degrees to 100 degrees; and / or The distance between the vertex angle and the base of the isosceles triangle on the bottom surface of the first rib is 0.5d to 3d, where d is the diameter of the first hole; and / or The distance between the vertex of the first rib and the bottom surface of the first rib is 0.25d to 4d, where d is the diameter of the first hole; and / or The spacing between two adjacent groups of the first ribs in the first direction is 3d to 15d, where d is the diameter of the first hole; and / or In the same group of first ribs, the distance between two adjacent first ribs in the second direction is 3d to 15d, where d is the diameter of the first hole.

5. The cooling assembly according to claim 1 or 4, characterized in that, The first hole is provided in a one-to-one correspondence with the first rib, and the airflow direction of the first hole corresponds to the vertex of the first rib so that the airflow flows along the three sides of the first rib.

6. The cooling assembly according to claim 1, characterized in that, The diameter of the second rib is d to 2.5d, where d is the diameter of the first hole; and / or The spacing between two adjacent groups of the second ribs in the first direction is 3d to 15d, where d is the diameter of the first hole; and / or In the same group of second ribs, the distance between two adjacent second ribs in the second direction is 3d to 15d, where d is the diameter of the first hole.

7. A blade, characterized in that, include: A blade body having an internal cavity; A cooling assembly, wherein the cooling assembly is according to any one of claims 1-6, the cooling assembly is disposed in the inner cavity of the blade body, the inner wall surface of the blade body is the target surface, the first plate is disposed corresponding to the inner wall surface of the blade body, the first rib and the second rib are disposed on the inner wall surface of the blade body, and the first direction is the same as the airflow direction.

8. A gas turbine, characterized in that, Includes the cooling assembly according to any one of claims 1-6 or the blade according to claim 7.

Images