Cooling structure and cooling member for turbine blade

Abstract

This invention discloses a cooling structure suitable for turbine blades, comprising a body having a first chamber and a second chamber that are interconnected. The bottom of the first chamber has a first air intake area and a second air intake area arranged at intervals along a first direction. The top surface of the first chamber has a first impact area and a second impact area arranged at intervals along the first direction. The first air intake area and the first impact area are arranged correspondingly, and the second air intake area and the second impact area are arranged correspondingly. The second chamber has a cooling channel, an air outlet, and an air inlet. The cooling channel is located within the second chamber and communicates with the air outlet. The cooling channel has a turbulence zone. The air outlet is located on the top surface of the second chamber, and the air inlet is located on the bottom surface of the second chamber. The cooling structure for turbine blades of this invention has the advantages of high heat transfer intensity and good cooling performance.

Description

Technical Field

[0001] This invention relates to the field of turbine blade cooling technology, and more specifically, to a cooling structure and cooling retaining ring suitable for turbine blades. Background Technology

[0002] Gas turbines are widely used in aviation, marine, and power generation. Increasing the inlet temperature of turbine components or reducing the cooling air volume can effectively improve the efficiency of gas turbines, making them more economical and competitive in the market. However, increasing the inlet temperature of turbine components can easily cause the blades and endwall materials to be ablated by the high-temperature mainstream combustion gases. Therefore, effective measures are needed to reduce the operating environment temperature of high-temperature components; however, traditional methods such as column-fin cooling have limited cooling capacity. Summary of the Invention

[0003] This invention aims to at least partially solve one of the technical problems in related technologies. To this end, embodiments of this invention propose a cooling structure suitable for turbine blades, which has the advantages of high heat transfer intensity and good cooling performance.

[0004] The cooling structure for turbine blades according to embodiments of the present invention includes a body, the body having a first chamber and a second chamber that are interconnected, the bottom of the first chamber having a first air intake area and a second air intake area arranged at intervals along a first direction, and the top surface of the first chamber having a first impact area and a second impact area arranged at intervals along the first direction, the first air intake area and the first impact area being arranged correspondingly, and the second air intake area and the second impact area being arranged correspondingly.

[0005] The second chamber has a cooling channel, an air outlet, and an air inlet. The cooling channel is located inside the second chamber and communicates with the air outlet. The cooling channel has a turbulence zone. The air outlet is located on the top surface of the second chamber, and the air inlet is located on the bottom surface of the second chamber.

[0006] The cooling structure for turbine blades in this embodiment of the invention introduces cold air into a first chamber through a first intake zone and a second intake zone. The cold air entering the first chamber through the first intake zone impacts a first impact zone, and the cold air entering the first chamber through the second intake zone impacts a second impact zone. This effectively increases the flow disturbance of the cold air in the first chamber, prolonging its residence time and thus improving the heat transfer intensity. Subsequently, the cold air flows into the second chamber and moves within the turbulence zone. Simultaneously, cold air is introduced into the second chamber through the intake port to further increase the disturbance of the cold air, prolonging its residence time. This further improves the heat transfer intensity and cooling performance of the cooling structure for turbine blades in this embodiment of the invention, and also effectively reduces the amount of cooling air required.

[0007] In some embodiments, the first air intake area includes a plurality of first air inlets, and the first impact area includes a plurality of protrusions protruding toward the first air inlets, with the plurality of first air inlets and the plurality of protrusions arranged corresponding to each other.

[0008] In some embodiments, the second air intake region includes a plurality of second air inlets, the second impact region has a plurality of concave surfaces, the concave surfaces being recessed in a direction away from the second air inlets, and the plurality of second air inlets being arranged corresponding to the plurality of concave surfaces.

[0009] In some embodiments, the distribution density of the plurality of first air inlets is greater than the distribution density of the plurality of second air inlets, and the distribution density of the plurality of protrusions is greater than the distribution density of the plurality of concave surfaces.

[0010] In some embodiments, the turbulence zone has a plurality of column ribs, which are spaced apart within the cooling channel.

[0011] In some embodiments, the second chamber further includes a partition extending along the first direction, the cooling channel being formed between the top surface of the partition and the top surface of the second chamber, one end of the column rib being connected to the top surface of the partition, and the other end of the column rib being connected to the top surface of the second chamber.

[0012] In some embodiments, the air inlet is located on the side of the bottom surface of the second chamber away from the first chamber, the air inlet extends in an upward direction and inclined toward the first chamber, and the central axis of the air inlet may extend to the bottom surface of the partition.

[0013] In some embodiments, the body further has a connecting channel located between the first chamber and the second chamber. One end of the connecting channel is connected to and communicates with the side of the first chamber adjacent to the second air intake area. The other end of the connecting channel extends along the first direction and is inclined in an upward direction. The other end of the connecting channel communicates with the second chamber.

[0014] The cooling component for turbine blades according to embodiments of the present invention includes:

[0015] The mounting member extends along a second direction and has a mounting chamber that extends along the second direction;

[0016] A connector is provided on one side of the mounting member, and the connector is used to install the mounting member on the equipment;

[0017] The main body is installed in the installation chamber, and the main body is the main body described above.

[0018] The cooling component for turbine blades in this embodiment of the invention is installed in an installation chamber, which can cool the installation component and thus cool the cooling component for turbine blades, thereby improving the cooling performance of the cooling component. This allows for further increases in the inlet temperature of the turbine component and improves the efficiency of the gas turbine. In addition, the cooling component has a simple structure and the installation method of the main body on the installation component is simple.

[0019] In some embodiments, there are multiple bodies, which are divided into multiple groups. The multiple groups of bodies are arranged sequentially along the second direction. Each group includes multiple bodies, and the multiple bodies in each group are arranged sequentially along a first direction, which is orthogonal to the second direction. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of a cooling structure applicable to turbine blades according to an embodiment of the present invention.

[0021] Figure 2 This is a cross-sectional view of a cooling structure applicable to turbine blades according to an embodiment of the present invention.

[0022] Figure 3 This is a schematic diagram of the flow of cold air in a cooling structure applicable to turbine blades according to an embodiment of the present invention.

[0023] Figure 4 This is a schematic diagram of the air intake area distribution of a cooling structure applicable to turbine blades according to an embodiment of the present invention.

[0024] Figure 5 This is a schematic diagram of the impact zone of a cooling structure applicable to turbine blades according to an embodiment of the present invention.

[0025] Figure 6 This is a schematic diagram of the rib distribution of a cooling structure applicable to turbine blades according to an embodiment of the present invention.

[0026] Figure 7 This is a schematic diagram of a cooling component for turbine blades according to an embodiment of the present invention.

[0027] Figure 8 This is a schematic diagram of the mounting component of a cooling part for turbine blades according to an embodiment of the present invention.

[0028] Figure 9 This is a cross-sectional schematic diagram of a cooling component applicable to turbine blades according to an embodiment of the present invention.

[0029] Figure 10This is a schematic diagram of the array distribution of the body of the cooling component for turbine blades on the mounting component according to an embodiment of the present invention.

[0030] Reference numerals: 100, body; 200, cooling component; 1, first chamber; 11, first air intake area; 111, first air inlet; 12, second air intake area; 121, second air inlet; 13, first impact area; 131, protrusion; 14, second impact area; 141, concave surface; 2, second chamber; 21, cooling channel; 22, air outlet; 23, air inlet; 24, turbulence area; 241, column rib; 25, partition; 3, connecting channel; 4, mounting component; 41, mounting chamber; 5, connector; 51, first part; 52, second part; 53, protrusion. Detailed Implementation

[0031] 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.

[0032] like Figure 1-10 As shown, the cooling structure for turbine blades according to an embodiment of the present invention includes a body 100, the body 100 having a first chamber 1 and a second chamber 2 that are interconnected, and the bottom of the first chamber 1 having a shape along a first direction (e.g., Figure 1 The first air intake zone 11 and the second air intake zone 12 are arranged at intervals in the left-right direction (as shown). The top surface of the first chamber 1 has a first impact zone 13 and a second impact zone 14 arranged at intervals in the first direction. The first air intake zone 11 and the first impact zone 13 are arranged correspondingly, and the second air intake zone 12 and the second impact zone 14 are arranged correspondingly.

[0033] Specifically, the first air intake zone 11 and the second air intake zone 12 are arranged at intervals in the left and right direction, and the first air intake zone 11 and the second air intake zone 12 are adapted to introduce cold air into the first chamber 1. The cold air entering the first chamber 1 through the first air intake zone 11 impacts the first impact zone 13, and the cold air entering the first chamber 1 through the second air intake zone 12 impacts the second impact zone 14. This can effectively increase the flow disturbance of the cold air in the first chamber 1, prolong the residence time of the cold air in the first chamber 1, and thus improve the heat exchange intensity of the cold air in the first chamber 1.

[0034] The second chamber 2 has a cooling channel 21, an air outlet 22 and an air inlet 23. The cooling channel 21 is located inside the second chamber 2 and is connected to the air outlet 22. The cooling channel 21 has a turbulence zone 24. The air outlet 22 is located on the top surface of the second chamber 2 and the air inlet 23 is located on the bottom surface of the second chamber 2.

[0035] Specifically, the cold air in the first chamber 1 enters the second chamber 2. Simultaneously, cold air is also introduced into the second chamber 2 through the air inlet 23. The two streams of cold air converge and flow into the cooling channel 21. The cold air introduced into the second chamber 2 through the air inlet 23 not only cools the cooling channel 21 but also ensures a stable supply of cold air flowing into the air outlet 22 through the cooling channel 21, preventing combustion gas intrusion. The cold air is agitated by the turbulence zone 24 within the cooling channel 21, extending the residence time of the cold air in the second chamber 2 and increasing the heat transfer intensity of the cold air in the second chamber 2. This improves the heat transfer intensity and cooling performance of the cooling structure applicable to turbine blades in this embodiment of the invention and effectively reduces the amount of cooling air required. The air outlet 22 is connected to the cooling channel 21 and extends in a rightward and upward inclined direction, making it easy for the cold air to form a stable air film after flowing out of the cooling channel 21 and cover the blades to complete the cooling of the turbine blades.

[0036] In some embodiments, the first air intake area 11 includes a plurality of first air intake ports 111, and the first impact area 13 includes a plurality of protrusions 131, the protrusions 131 protruding toward the first air intake ports 111, and the plurality of first air intake ports 111 are arranged correspondingly to the plurality of protrusions 131.

[0037] Specifically, the multiple first air inlets 111 are divided into multiple groups, and the multiple groups of first air inlets 111 are distributed in an array. For example, the multiple groups of first air inlets 111 are arranged at intervals along a first direction, and each group includes multiple first air inlets 111. The multiple air inlets 23 in each group are arranged at intervals along a second direction, which is orthogonal to the first direction. Cold air can be introduced into the first chamber 1 through the multiple first air inlets 111.

[0038] The multiple protrusions 131 are divided into multiple groups, and the multiple groups of protrusions 131 are also arranged in an array. For example, the multiple groups of protrusions 131 are arranged at intervals along the first direction, each group includes multiple protrusions 131, and the multiple protrusions 131 in each group are arranged at intervals along the second direction. The multiple protrusions 131 are arranged corresponding to multiple first air inlets 111, so that the cold air entering the first chamber 1 through the first air inlet 111 can impact the protrusions 131, thereby causing the protrusions 131 to disturb the cold air, thereby prolonging the residence time of the cold air in the first chamber 1, so as to improve the cooling performance and heat exchange intensity of the body 100.

[0039] In some embodiments, the second air intake region 12 includes a plurality of second air intake ports 121, and the second impact region 14 has a plurality of concave surfaces 141, which are recessed toward the direction away from the second air intake ports 121, and the plurality of second air intake ports 121 are arranged corresponding to the plurality of concave surfaces 141.

[0040] Specifically, the multiple second air inlets 121 are divided into multiple groups, and the multiple groups of second air inlets 121 are distributed in an array. For example, the multiple groups of second air inlets 121 are arranged at intervals along a first direction, and each group includes multiple second air inlets 121. The multiple air inlets 23 in each group are arranged at intervals along a second direction, which is orthogonal to the first direction. Cold air can be introduced into the first chamber 1 through the multiple second air inlets 121.

[0041] Multiple concave surfaces 141 are divided into multiple groups, and the multiple groups of concave surfaces 141 are also arranged in an array. For example, multiple groups of concave surfaces 141 are arranged at intervals along a first direction, each group includes multiple concave surfaces 141, and the multiple concave surfaces 141 in each group are arranged at intervals along a second direction. The multiple concave surfaces 141 are arranged corresponding to multiple second air inlets 121, so that the cold air introduced into the first chamber 1 through the second air inlet 121 can impact the concave surfaces 141, thereby causing the concave surfaces 141 to disturb the cold air, thereby prolonging the residence time of the cold air in the second chamber 2, so as to further improve the cooling performance and heat exchange intensity of the body 100.

[0042] In some embodiments, the distribution density of the plurality of first air inlets 111 is greater than the distribution density of the plurality of second air inlets 121, and the distribution density of the plurality of protrusions 131 is greater than the distribution density of the plurality of concave surfaces 141.

[0043] Specifically, the first air inlet 111 is located to the left of the second air inlet 121, and the second chamber 2 is connected to the right side of the first chamber 1, so that the cold air entering the first chamber 1 through the first air inlet 111 and the second air inlet 121 will flow towards the second chamber 2 in a rightward direction.

[0044] The cold air entering the first chamber 1 through the first air inlet 111 and the second air inlet 121 has the same flow rate. Therefore, according to the crossflow ratio (i.e., the ratio of the distribution density of the first air inlet 111 multiplied by the flow rate of the cold air through the first air inlet 111 to the distribution density of the second air inlet 121 multiplied by the flow rate of the cold air through the second air inlet 121, the higher the ratio, the higher the heat exchange efficiency), the distribution density of the multiple first air inlets 111 is greater than the distribution density of the multiple second air inlets 121, which can effectively improve the heat exchange performance of the body 100.

[0045] Specifically, the protrusion 131 protrudes towards the first air inlet 111 in the vertical direction, and the concave surface 141 is recessed in the vertical direction away from the second air inlet 121. This makes the distance from the first air inlet 111 to the protrusion 131 in the vertical direction less than the distance from the second air inlet 121 to the concave surface 141. As a result, the path of cold air from the first air inlet 111 to the protrusion 131 is shorter than the path of cold air from the second air inlet 121 to the concave surface 141. Consequently, when cold air is simultaneously introduced into the first chamber 1 through the first air inlet 111 and the second air inlet 121, the cold air entering the first chamber 1 through the first air inlet 111 first impacts the protrusion 131, and then the cold air changes direction and flows downstream towards the first chamber 1 to disturb the cold air entering the first chamber 1 through the second air inlet 121. This prolongs the flow time of the cold air in the first chamber 1 and improves the cooling performance of the body 100. The vertical direction is orthogonal to the first and second directions.

[0046] In some embodiments, the turbulence zone 24 has a plurality of column ribs 241, which are spaced apart within the cooling channel 21.

[0047] Specifically, the arrangement of multiple column ribs 241 allows the column ribs 241 to disturb the flow of cold air in the cold zone channel, thereby prolonging the flow time of cold air in the cooling channel 21 and improving the cooling performance of the body 100, which can effectively reduce the amount of cooling air.

[0048] In some embodiments, the second chamber 2 further includes a partition 25 extending along a first direction, and a cooling channel 21 formed between the top surface of the partition 25 and the top surface of the second chamber 2. One end of the column rib 241 (e.g. Figure 1 The lower end of the column rib 241 shown is connected to the top surface of the spacer 25, and the other end of the column rib 241 (as shown) Figure 1 The upper end of the column rib 241 shown is connected to the top surface of the second chamber 2.

[0049] Specifically, the right end of the partition 25 is connected to the inner wall surface of the second chamber 2 away from the first chamber 1, the left end of the partition 25 extends to the left along the first direction, the cooling channel 21 is formed between the upper surface of the partition 25 and the top surface of the second chamber 2, and a plurality of column ribs 241 are arranged at intervals in the cooling channel 21.

[0050] In some embodiments, the air inlet 23 is located on the side of the bottom surface of the second chamber 2 away from the first chamber 1, the air inlet 23 extends in an upward direction and is inclined toward the first chamber 1, and the central axis of the air inlet 23 can extend to the bottom surface of the partition 25.

[0051] Specifically, the cold air entering the second chamber 2 through the air inlet 23 serves to supplement the cold air supply. After entering the second chamber 2 through the air inlet 23, the cold air can contact the bottom surface of the partition 25 along its central axis to cool at least a portion of the partition 25. This further ensures the amount of cold air in the second chamber 2 and guarantees a stable supply of cold air into the cooling channel 21. This not only prevents combustion gases from intruding into the cooling channel 21 but also ensures that the cold air forms a stable cooling film after flowing out of the cooling channel 21.

[0052] In some embodiments, the body 100 further has a connecting channel 3, which is located between the first chamber 1 and the second chamber 2. One end of the connecting channel 3 is connected to the side of the first chamber 1 adjacent to the second air intake area 12 and communicates with the first chamber 1. The other end of the connecting channel 3 extends along a first direction and is inclined in an upward direction. The other end of the connecting channel 3 communicates with the second chamber 2.

[0053] Specifically, there are multiple connecting channels 3, which are arranged at intervals along the second direction. The left end of each connecting channel 3 is connected to and communicates with the wall of the first chamber 1 adjacent to the second chamber 2, and the right end of each connecting channel 3 is connected to and communicates with the wall of the second chamber 2 adjacent to the first chamber 1. The connecting channels 3 are inclined, and at least a portion of the right end of each connecting channel 3 corresponds to the cooling channel 21, so that after the cold air in the first chamber 1 flows into the second chamber 2 through the connecting channel 3, most of it can flow into the cooling channel 21, thereby ensuring the flow rate of the cold air in the cooling channel 21.

[0054] The cooling component for turbine blades according to an embodiment of the present invention includes a mounting member 4, a connecting member 5, and a body 100. The mounting member 4 extends along a second direction and has a mounting chamber 41 extending along the second direction. The body 100 is mounted inside the mounting chamber 41. The connecting member 5 is disposed on one side of the mounting member 4 and is used to mount the mounting member 4 onto a device.

[0055] The cooling component for turbine blades in this embodiment of the invention has a main body 100 installed in the mounting chamber 41, which can cool the mounting component 4 and thus cool the cooling component for turbine blades in this embodiment of the invention, improving the cooling performance of the cooling component 200. This allows for further increases in the inlet temperature of the turbine component and improves the efficiency of the gas turbine. In addition, the cooling component 200 has a simple structure, and the installation method of the main body 100 on the mounting component 4 is simple.

[0056] Specifically, there are two connectors 5, which are arranged at intervals along the first direction on the top surface of the mounting member 4. The connectors 5 extend along the second direction on the top surface of the mounting member 4. The connectors 5 are used to install the mounting member 4 on the equipment so as to cool the equipment through the mounting member 4.

[0057] Specifically, the connector 5 includes a first part 51 and a second part 52. The first part 51 extends along a second direction on the top surface of the mounting member 4 and is connected to the top surface of the mounting member 4. The second part 52 is connected to the side of the first part 51 away from the mounting member 4 and extends along the extending direction of the first part 51. The second parts 52 of the two connectors 5 extend in opposite directions.

[0058] The cooling component 200 also includes two protrusions 53, which are arranged along a second interval on the top surface of the mounting member 4 and located between the two connecting members 5. One side of the protrusion 53 is connected to the top surface of the mounting member 4, and both ends of the protrusion 53 are connected to the first part 51 of the two connecting members 5 respectively and extend upward.

[0059] In some embodiments, there are multiple bodies 100, which are divided into multiple groups. The multiple groups of bodies 100 are arranged sequentially along a second direction. Each group includes multiple bodies 100, and the multiple bodies 100 in each group are arranged sequentially along a first direction, which is orthogonal to the second direction.

[0060] Specifically, multiple bodies 100 are arranged in an array according to the actual situation to better improve the cooling effect of the cooling structure on the cooling component 200, thereby improving the cooling effect of the cooling component 200 on the equipment.

[0061] In the description of this invention, it should be understood that 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.

[0062] 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.

[0063] 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.

[0064] 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.

[0065] 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.

[0066] Although the above embodiments have been shown and described, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Any changes, modifications, substitutions and variations made to the above embodiments by those skilled in the art are within the protection scope of the present invention.

Claims

1. A cooling structure suitable for turbine blades, characterized in that, The device includes a body (100) having a first chamber (1) and a second chamber (2) that are interconnected. The bottom of the first chamber (1) has a first air intake area (11) and a second air intake area (12) arranged at intervals along a first direction. The top surface of the first chamber (1) has a first impact area (13) and a second impact area (14) arranged at intervals along the first direction. The first air intake area (11) and the first impact area (13) are arranged correspondingly, and the second air intake area (12) and the second impact area (14) are arranged correspondingly. The second chamber (2) has a cooling channel (21), an air outlet (22) and an air inlet (23). The cooling channel (21) is located inside the second chamber (2) and communicates with the air outlet (22). The cooling channel (21) has a turbulence zone (24). The air outlet (22) is located on the top surface of the second chamber (2), and the air inlet (23) is located on the bottom surface of the second chamber (2). The turbulence zone (24) has a plurality of column ribs (241), which are spaced apart within the cooling channel (21); The second chamber (2) also has a partition (25) extending along the first direction, the cooling channel (21) being formed between the top surface of the partition (25) and the top surface of the second chamber (2), one end of the column rib (241) being connected to the top surface of the partition (25), and the other end of the column rib (241) being connected to the top surface of the second chamber (2).

2. The cooling structure for turbine blades according to claim 1, characterized in that, The first air intake area (11) includes a plurality of first air intake ports (111), and the first impact area (13) includes a plurality of protrusions (131). The protrusions (131) protrude toward the first air intake ports (111), and the plurality of first air intake ports (111) are arranged correspondingly to the plurality of protrusions (131).

3. The cooling structure for turbine blades according to claim 2, characterized in that, The second air intake area (12) includes a plurality of second air intakes (121), and the second impact area (14) has a plurality of concave surfaces (141). The concave surfaces (141) are recessed in a direction away from the second air intakes (121), and the plurality of second air intakes (121) are arranged corresponding to the plurality of concave surfaces (141).

4. The cooling structure for turbine blades according to claim 3, characterized in that, The distribution density of the plurality of first air inlets (111) is greater than that of the plurality of second air inlets (121), and the distribution density of the plurality of protrusions (131) is greater than that of the plurality of concave surfaces (141).

5. The cooling structure for turbine blades according to claim 1, characterized in that, The air inlet (23) is located on the side of the bottom surface of the second chamber (2) away from the first chamber (1). The air inlet (23) extends in an upward direction and is inclined toward the first chamber (1). The central axis of the air inlet (23) can extend to the bottom surface of the partition (25).

6. The cooling structure for turbine blades according to claim 1, characterized in that, The main body (100) also has a connecting channel (3) located between the first chamber (1) and the second chamber (2). One end of the connecting channel (3) is connected to the side of the first chamber (1) adjacent to the second air intake area (12) and communicates with the first chamber (1). The other end of the connecting channel (3) extends along the first direction and is inclined in an upward direction. The other end of the connecting channel (3) communicates with the second chamber (2).

7. A cooling component suitable for turbine blades, characterized in that, include: Mounting member (4), the mounting member (4) extending along a second direction, the mounting member (4) having a mounting chamber (41) extending along the second direction; A connector (5) is provided on one side of the mounting member (4) and is used to install the mounting member (4) on the equipment; The body (100) is installed in the mounting chamber (41), and the body (100) is the body (100) as described in any one of claims 1 to 6.

8. The cooling component for turbine blades according to claim 7, characterized in that, There are multiple bodies (100), and the multiple bodies (100) are divided into multiple groups. The multiple groups of bodies (100) are arranged sequentially along the second direction. Each group includes multiple bodies (100). The multiple bodies (100) in each group are arranged sequentially along the first direction, which is orthogonal to the second direction.

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