A turbine working blade bionic cooling structure

Abstract

The application discloses a turbine working blade bionic cooling structure in the technical field of blade cooling, which replaces the traditional meandering channel with a bionic cooling channel to cool the blade basin surface and the blade back surface, improves the coverage of the cooling airflow on the blade basin surface and the blade back surface, improves the heat exchange efficiency, improves the cooling effect of the cooling airflow on the blade, under the same cooling airflow flow, improves the cooling effect of the cooling airflow on the blade, under the same cooling effect, reduces the demand for the cooling airflow flow, helps to improve the performance of the engine, and effectively shortens the distance of the cooling airflow flowing in the blade, the heat exchange coefficient of the local area in the blade cavity can be adjusted by changing the width, length and mixed cavity diameter of the first channel and the second channel, so that the metal temperature of the local area of the blade is regulated, and the metal temperature gradient is further reduced by the designer.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of blade cooling, in particular to a turbine working blade bionic cooling structure. BACKGROUND

[0002] With the increasing of the temperature in front of the advanced aero-engine turbine, the heat protection requirement of the turbine blade is also higher and higher. The most commonly used heat protection way of the turbine blade is to cool the blade, usually the inside of the blade is hollowed out, different cooling structures are arranged, and cold air flows into the cavity to reduce the temperature of the blade metal and ensure that the blade can work normally in the harsh environment of high temperature and high pressure.

[0003] The existing turbine working blade cooling mainly includes impact, meandering channel, air film, spoiler column and other cooling forms, and according to the structure of the turbine working blade and the influence of the environment, multiple cooling structures are usually combined to design. For high cycle parameter turbine working blade, the combination cooling form of "meandering channel + impact + air film + rib + split joint" is usually used. At present, this technology is very mature and has been widely used in large, medium and small aero-engines. However, with the further increase of the temperature in front of the aero-engine turbine, the heat exchange of the cooling form through the optimization of the cavity cooling structure is limited to reduce the temperature of the blade metal, and only passive air film cooling can be used to reduce the temperature of the blade, which also increases the cold air bleed ratio, resulting in the decline of the engine performance. At the same time, with the increasing requirement of high-performance lightweight engine on the weight of the engine, the weight reduction method of the traditional cooling form is limited under the premise of ensuring the cooling effect, which is difficult to meet the strict requirements of the new engine on the weight

[0004] Based on this, the present application designs a turbine working blade bionic cooling structure to solve the above problems. SUMMARY

[0005] In order to achieve the above purpose, the present application provides the following technical scheme: a turbine working blade bionic cooling structure, characterized by comprising a blade and a cooling structure for cooling the blade; the cooling structure comprises a bionic cooling channel, an air inlet for feeding cooling air into the bionic cooling channel, and an air outlet for discharging cooling air in the bionic cooling channel, two bionic cooling channels are arranged in the blade, one of the two bionic cooling channels is close to the blade basin surface, and the other is close to the blade back surface, which are respectively used for cooling the blade basin surface and the blade back surface; the cooling structure comprises a plurality of first channels connecting the air inlet and the air outlet, a plurality of second channels vertically interlaced with the first channels, and a mixing chamber arranged at the interlaced position of the first channels and the second channels, the cooling air flows into the second channels through the first channels, and the cooling air in the first channels and the second channels flows in the mixing chamber to form a vortex.

[0006] As a further scheme of the present application, the first channels are arranged along a first direction, and the second channels are arranged along a second direction, the mixing cavities on two adjacent first channels are staggered in the second direction, and the mixing cavities on two adjacent second channels are staggered in the first direction.

[0007] As a further scheme of the present application, the first channels and the second channels are rectangular in projection in a third direction, and the third direction is perpendicular to the first direction and the second direction.

[0008] As a further scheme of the present application, the blade pressure surface is provided with blade pressure surface air film holes communicating with the bionic cooling channels close to the blade pressure surface, and the blade suction surface is provided with blade suction surface air film holes communicating with the bionic cooling channels close to the blade suction surface.

[0009] As a further scheme of the present application, the first channels and the second channels are rectangular in cross section.

[0010] As a further scheme of the present application, the first channels and the second channels are rectangular in cross section.

[0011] As a further scheme of the present application, the cooling structure further comprises a rear cavity and a trailing edge offset split slot, the rear cavity is arranged in the blade close to the trailing edge, the rear cavity is arranged along the second direction, the trailing edge offset split slot communicates the rear cavity with the outside, and all the second channels in the two bionic cooling channels communicate with the rear cavity.

[0012] As a further scheme of the present application, the cooling structure further comprises a front cavity arranged in the blade close to the leading edge, the front cavity is arranged along the second direction and communicates with the air inlet at the bottom end, and a plurality of leading edge air film holes are arranged on the inner wall of the front cavity and communicate with the outer surface of the leading edge of the blade, so as to guide the cooling air flow in the front cavity to the leading edge of the blade to cool the leading edge.

[0013] As a further scheme of the present application, the cooling structure further comprises a middle cavity arranged at the center of the blade, the middle cavity is arranged along the second direction and communicates with the air inlet at the bottom end, and the middle cavity is located between the two bionic cooling channels to guide the cooling air flow to cool one side of the bionic cooling channel close to the center of the blade.

[0014] As a further scheme of the present application, the side of the middle cavity adjacent to the front cavity is provided with an impact hole communicating the front cavity and the middle cavity, so that the cooling air flow in the middle cavity can enter the front cavity through the impact hole.

[0015] The present application has the following advantages:

[0016] The present application replaces the traditional meandering channel with a bionic cooling channel to cool the blade basin surface and the blade back surface, the bionic cooling channel comprises vertically staggered first channels and second channels, and a mixing cavity is also arranged at the staggered position of the first channels and the second channels, so that a neuron bionic network channel formed by connecting a plurality of neuron structures is formed, the coverage of the cooling air flow on the blade basin surface and the blade back surface is improved, the heat exchange efficiency is improved, the cooling effect of the cooling air flow on the blade is improved, under the same cooling air flow, the cooling effect of the cooling air flow on the blade is improved, under the same cooling effect, the demand for the cooling air flow can be reduced, which is helpful to improve the performance of the engine, and the distance of the cooling air flow in the blade can be effectively shortened, the heat exchange coefficient of the local area of the blade cavity can be adjusted by changing the width, length and diameter of the mixing cavity of the first channel and the second channel, so that the metal temperature of the local area of the blade is regulated, and the metal temperature gradient is further reduced by the designer.

[0017] In addition to the objects, features and advantages described above, the present application has other objects, features and advantages. The present application will be further described in detail below with reference to the drawings. BRIEF DESCRIPTION OF DRAWINGS

[0018] The accompanying drawings, which form a part of this application, are included to provide a further understanding of the application, illustrate the preferred embodiments of the application and assist in the explanation of the application. In the drawings:

[0019] Figure 1 It is a cross-sectional schematic view of the present application.

[0020] Figure 2 It is a schematic view of the cooling air flow direction of the present application.

[0021] Figure 3 It is a schematic view of the bionic cooling channel structure in the present application.

[0022] Figure 4 It is a schematic view of the outlet structure of the present application.

[0023] Figure 5 It is a schematic view of the shell structure of the present application.

[0024] LEGEND

[0025] 1, blade; 11, air outlet; 2, bionic cooling channel; 21, first channel; 22, second channel; 23, mixing cavity; 24, blade basin air film hole; 25, blade back air film hole; 3, rear cavity; 4, trailing edge eccentric slot; 5, front cavity; 51, leading edge air film hole; 6, middle cavity; 61, impact hole. DETAILED DESCRIPTION

[0026] The embodiments of the present application will be described in detail below with reference to the accompanying drawings, but the present application can be implemented in various different ways as defined and covered by the following description.

[0027] Please refer to Figures 1-5 , the present application provides a turbine working blade bionic cooling structure, by opening bionic cooling channel 2 on the blade 1, cooling airflow flows in the bionic cooling channel 2 to cool the blade 1, improve the utilization rate of cooling airflow, under the same cooling efficiency, can reduce the flow demand of cooling airflow, help to improve the overall performance of the engine.

[0028] Specifically, the tenon of the blade 1 is provided with an air inlet, the blade tip of the blade 1 is provided with an air outlet 11, two bionic cooling channels 2 are opened in the blade 1, the two bionic cooling channels 2 are respectively close to the blade face and the back face of the blade 1, and the two bionic cooling channels 2 are communicated with the air inlet and the air outlet 11. In the use process, the cooling airflow is transported into the two bionic cooling channels 2 through the air inlet, and the cooling airflow is discharged from the air outlet 11 after passing through the bionic cooling channel 2. The cooling airflow exchanges heat with the blade face and the back face of the blade 1 in the process of flowing in the bionic cooling channel 2, realizes the cooling of the blade face of the blade 1 and the back face of the blade 1, and prevents the blade face and the back face of the blade 1 from appearing high temperature ablation.

[0029] As Figure 3 shown, the bionic cooling channel 2 is composed of a plurality of first channels 21 and a plurality of second channels 22 which are vertically staggered, a cooling network is formed by the staggered first channels 21 and second channels 22, the blade face and the back face of the blade 1 are covered by the cooling airflow, and the high temperature area is avoided. The mixing chamber 23 is also opened at the position where the first channel 21 and the second channel 22 are staggered. The cooling airflow flowing in the first channel 21 and the second channel 22 will gather in the mixing chamber 23, and form vortex under the guidance of the mixing chamber 23, fully exchange heat with the blade face or the back face of the blade 1, cool the blade face or the back face of the blade 1, improve the cooling effect of the cooling airflow on the blade 1, and then the vortex in the mixing chamber 23 will enter the first channel 21 and the second channel 22 again through the other two openings of the mixing chamber 23, flow into the next circular chamber, so as to form a neuron bionic network channel connected by a plurality of neuron structures, improve the coverage of the cooling airflow on the blade face and the back face of the blade 1, improve the heat exchange efficiency, and improve the cooling effect of the cooling airflow on the blade 1. Under the same cooling airflow flow, the use of bionic cooling channel 2 can improve the heat exchange area of the cooling airflow and the blade 1, improve the cooling effect of the cooling airflow on the blade 1, and under the same cooling effect, the use of bionic cooling channel 2 can reduce the demand of cooling airflow flow, which is helpful to improve the performance of the engine.

[0030] The traditional serpentine passage is too long, and the cooling effect of the cooling airflow is poorer when the cooling airflow goes to the rear part of the serpentine passage, and a temperature gradient is formed on the surface of the blade 1. The bionic cooling passage 2 is composed of a plurality of first passages 21 and a plurality of second passages 22, which effectively shortens the distance of the cooling airflow flowing in the blade 1, and the heat exchange coefficient of the local area in the blade 1 can be adjusted by changing the width, length, and diameter of the mixing cavity 23, so as to control the metal temperature of the local area of the blade 1, and the metal temperature gradient is further reduced by the designer.

[0031] In some examples, the mixing cavity 23 is circular. When the shape of the mixing cavity 23 is closer to a circle, the resistance of the vortex flow in the mixing cavity 23 is smaller, and thus, the vortex flow is best formed when the mixing cavity 23 is circular.

[0032] Specifically, the size, length, number, and arrangement of the first passage 21, the second passage 22, and the mixing cavity 23 can be adjusted according to the size of the blade 1 and the flow and heat exchange calculation results.

[0033] Preferably, the mixing cavities 23 on the two adjacent first passages 21 are staggered in the second direction, and the mixing cavities 23 on the two adjacent second passages 22 are staggered in the first direction. In this way, the mixing cavities 23 are arranged in the first direction and the second direction while ensuring that each first passage 21 and each second passage 22 is provided with a mixing cavity 23, which maximizes the use of the limited space in the blade 1. The staggered arrangement of the mixing cavities 23 allows the cooling airflow to have enough length to guide the flow direction after leaving the mixing cavity 23, preventing the cooling airflow from entering the next mixing cavity 23 immediately after leaving the previous mixing cavity 23, which causes the cooling airflow to be unstable and unable to form a vortex. At the same time, the staggered arrangement of the mixing cavities 23 ensures that each first passage 21 and each second passage 22 is provided with a mixing cavity 23, which does not cause waste of the cooling airflow.

[0034] In the present example, a plurality of first channels 21 are arranged equidistantly along a first direction, and a plurality of second channels 22 are arranged equidistantly along a second direction. The first channels 21 are connected to the air inlet and the air outlet 11. During operation, cooling air is supplied to the first channels 21 through the air inlet. The cooling air flows along the first channels 21 after entering the first channels 21. When the cooling air flows through the intersection of the first channels 21 and the second channels 22, a portion of the cooling air flows into the second channels 22 along the second channels 22. The cooling air exchanges heat with the pressure surface or the suction surface of the blade 1 when flowing through the first channels 21 and the second channels 22, thereby cooling the pressure surface and the suction surface of the blade 1. When the cooling air in the first channels 21 and the second channels 22 flows into the mixing chamber 23, the cooling air forms a vortex in the mixing chamber 23. The vortex formed by the cooling air continues to exchange heat with the pressure surface or the suction surface of the blade 1, thereby improving the cooling effect on the pressure surface or the suction surface of the blade 1.

[0035] Specifically, the projection of the first channels 21 and the second channels 22 in the third direction is a rectangle. This means that the first channels 21 and the second channels 22 are straight when viewed from the pressure surface of the blade 1 or the suction surface of the blade 1. This can reduce the resistance of the cooling air flowing through the first channels 21 and the second channels 22 to some extent, thereby reducing the flow resistance loss of the cooling air due to the resistance during flow, and further improving the cooling effect.

[0036] It should be understood that the overall bionic cooling channel 2 needs to be twisted according to the blade profile to ensure that the bionic cooling channel 2 has an equal thickness with the pressure surface or the suction surface, and to ensure the heat exchange effect. Because the bionic cooling channel 2 needs to be twisted according to the blade profile, the first channels 21 and the second channels 22 cannot be completely straight. Instead, the projection of the first channels 21 and the second channels 22 in the third direction is straight, which can reduce the resistance of the cooling air flowing through the first channels 21 and the second channels 22 to the greatest extent possible.

[0037] Specifically, the first direction is the X direction, the second direction is the Y direction, and the third direction is the Z direction.

[0038] In some examples, the cross sections of the first channels 21 and the second channels 22 are rectangles. Designing the cross sections of the first channels 21 and the second channels 22 as rectangles is beneficial for matching the first channels 21 and the second channels 22 with the blade profile, controlling the wall thickness of the blade 1, and simplifying the structure of the bionic cooling channel 2. The rectangular first channels 21 and the second channels 22 are beneficial for flow control and calculation analysis of the internal cavity, and are convenient for the structural design of the internal cavity.

[0039] As Figure 3As shown, in some examples, the widths of the first channel 21 and the second channel 22 are both no greater than the radius of the mixing cavity 23. The width of the first channel 21 refers to its length in the X direction, and the width of the second channel 22 refers to its length in the Y direction. Both are no greater than the radius of the mixing cavity 23. This is beneficial for the cooling airflow to form vortices in the mixing cavity 23 and prevents the cooling airflow from quickly leaving the mixing cavity 23 through the other two openings after entering the mixing cavity 23 through one of the two openings.

[0040] like Figure 1 As shown, the blade 1 has a blade basin air film hole 24 on its blade basin surface that connects to the biomimetic cooling channel 2 near the blade basin surface, and a blade back air film hole 25 on its blade back surface that connects to the biomimetic cooling channel 2 near the blade back surface. After the cooling airflow enters the biomimetic cooling channel 2, it will not only exchange heat with the blade basin surface or blade back surface of the blade 1 in the biomimetic cooling channel 2, but will also be drawn out from the blade basin air film hole 24 to the blade basin surface to form an air film or from the blade back air film hole 25 to the blade back surface to form an air film. The air film formed by the cooling airflow buffers the high temperature hot air impacting the blade back surface and blade basin surface of the blade 1, providing double protection for the blade basin surface and blade back surface of the blade 1.

[0041] Specifically, depending on the location of the air film vent 24 on the blade basin, the air film vent 24 on the blade basin is connected to the first channel 21, the second channel 22, or the mixing chamber 23. Depending on the location of the air film vent 25 on the blade back, the air film vent 25 on the blade back is connected to the first channel 21, the second channel 22, or the mixing chamber 23. The locations of the air film vent 24 on the blade basin and the air film vent 25 on the blade back are determined according to parameters such as blade shape and cooling requirements.

[0042] like Figure 1 As shown, a rear cavity 3 is provided inside the blade 1 near the trailing edge. The cooling structure also includes the rear cavity 3 and the trailing edge slit 4. The rear cavity 3 is opened along the second direction, and the trailing edge slit 4 connects the rear cavity 3 to the outside. All the second channels 22 in the two biomimetic cooling channels 2 are connected to the rear cavity 3. In the same biomimetic cooling channel 2, the first end of all the second channels 22 is connected to the rear cavity 3, and the second end passes through all the first channels 21 and ends at the first channel 21 farthest from the rear cavity 3. During operation, the cooling airflow flowing along the direction of the second channel 22 will eventually converge into the rear cavity 3, exchange heat with the trailing edge of the blade 1 in the rear cavity 3, cool the trailing edge of the blade 1, and finally leave the rear cavity 3 through the trailing edge slit 4 opened at the trailing edge, forming an air film at the trailing edge of the blade 1 to buffer the high-temperature hot air impacting the trailing edge of the blade 1, effectively protecting the trailing edge of the blade 1 and preventing high-temperature ablation of the trailing edge of the blade 1.

[0043] Specifically, the rear cavity 3 is opened along the second direction, which facilitates the connection of the rear cavity 3 to all the second channels 22, and the cross-sectional shape of the rear cavity 3 is designed according to the shape of the blade 1, so that the wall thickness of the rear cavity 3 at the position adjacent to the outer surface of the blade 1 is always equal, thereby preventing local overheating.

[0044] As shown in Figure 1 , the cooling structure further includes a front cavity 5 opened in the blade 1 near the leading edge, the front cavity 5 is opened along the second direction and the bottom end is communicated with the air inlet, the cooling airflow is input into the front cavity 5 through the air inlet to cool the leading edge of the blade 1, thereby preventing high-temperature ablation of the leading edge of the blade 1, a plurality of leading edge film holes 51 are opened in the inner wall of the front cavity 5 and communicated with the outer surface of the leading edge of the blade 1, so that the cooling airflow entering the front cavity 5 is guided out to the leading edge of the blade 1 to cool the leading edge position, and the cooling airflow entering the front cavity 5 is formed into a gas film on the surface of the leading edge of the blade 1 through the leading edge film holes 51, thereby buffering the high-temperature airflow impacting the leading edge of the blade 1 and providing double protection for the leading edge of the blade 1.

[0045] As shown in Figure 1 , the cooling structure further includes a middle cavity 6 opened in the center of the blade 1, the middle cavity 6 is opened along the second direction and the bottom end is communicated with the air inlet, and the middle cavity 6 is located between the two biomimetic cooling channels 2 to input the cooling airflow to cool one side of the biomimetic cooling channel 2 near the center of the blade 1, when the cooling airflow in the biomimetic cooling channel 2 exchanges heat with the surface of the blade 1 or the back surface of the blade 1, the temperature of the cooling airflow in the biomimetic cooling channel 2 will become higher and higher, and the high-temperature cooling airflow will transfer heat to the center of the blade 1, thereby causing heat accumulation in the center of the blade 1, so that the subsequent cooling airflow passing through the biomimetic cooling channel 2 needs to cool the outer surface of the blade 1 and the center of the blade 1 at the same time, thereby resulting in poor cooling effect, therefore, the middle cavity 6 is needed to be opened in the center of the blade 1, the middle cavity 6 is communicated with the air inlet, and the low-temperature cooling airflow is input into the middle cavity 6 through the air inlet, thereby not only cooling the center of the blade 1 to prevent heat accumulation, but also helping the biomimetic cooling channel 2 to dissipate heat, thereby reducing the heat dissipation pressure of the biomimetic cooling channel 2 and increasing the overall cooling effect.

[0046] Compared with the traditional meandering structure, the adoption of the biomimetic cooling channel 2 can also increase the opening size of the middle cavity 6, thereby reducing the weight of the overall blade 1,

[0047] As shown in Figure 1 , in some examples, the side of the middle cavity 6 adjacent to the front cavity 5 is provided with an impact hole 61 communicated between the front cavity 5 and the middle cavity 6, so that the cooling airflow in the middle cavity 6 can enter the front cavity 5 through the impact hole 61, the cooling airflow in the middle cavity 6 enters the front cavity 5 through the impact hole 61 to impact and cool the inner wall surface of the front cavity 5, and then mixes with the cooling airflow of the front cavity 5 and exits the front cavity 5 through the leading edge film holes 51 opened in the front cavity 5.

[0048] It should be understood that the size, number and opening position of the leading edge film hole 51, the impact hole 61, the blade basin film hole 24 and the blade back film hole 25 are calculated according to the shape, size and cooling requirements of the blade 1.

[0049] As shown in Figure 1 The working process of the cooling structure is as follows: first, the cooling air flow of the air inlet is divided into four parts. First, the first part of the cooling air flow directly enters the front cavity 5, and then is introduced from the front cavity 5 to the leading edge of the blade 1 through the leading edge film hole 51 for cooling the leading edge of the blade 1; the second part of the cooling air flow flows into the middle cavity 6, cools the inner wall surface of the middle cavity 6 of the blade 1, and then impacts the inner wall surface of the front cavity 5 through the impact hole 61, and then flows out of the blade 1 through the leading edge film hole 51 for strengthening the cooling of the leading edge of the blade 1 and preventing the problem of ablation in the high-temperature area of the leading edge of the blade 1; the third part of the cooling air flow flows into the biomimetic cooling channel 2 close to the blade basin surface, wherein part of the third part of the cooling air flow flows out from the blade basin film hole 24 to form a gas film covering on the blade basin surface to cool the metal outer wall surface of the blade basin, and part of the outlet 11 flows out of the blade 1, and the other part of the cooling air flow flows transversely to the trailing edge direction and flows into the rear cavity 3 to fully ensure the utilization rate of the cooling air flow; the fourth part of the cooling air flow flows into the biomimetic cooling channel 2 close to the blade back surface, and part of the fourth part of the cooling air flow flows out from the blade back film hole 25 to form a gas film covering on the blade back surface to cool the metal outer wall surface of the blade back, and part of the outlet 11 flows out of the blade 1, and the other part of the cooling air flow flows transversely to the trailing edge direction and flows into the rear cavity 3, and finally flows out of the blade 1 from the trailing edge split gap 4.

[0050] Since the heat exchange of the leading edge of the blade 1 is strong, the impact + film form of the front cavity 5 can effectively reduce the metal temperature of the leading edge of the blade 1; the middle chord and the trailing edge position of the blade 1 consume most of the cooling gas required by the blade 1, and the combination of the biomimetic cooling channel 2 + middle cavity 6 hollowing + film + tail split gap is adopted for the middle cavity 6 and the trailing edge, which can not only fully utilize the advantages of the biomimetic cooling channel 2 such as good cooling effect and small required cooling gas amount to improve the utilization rate of the cooling gas, but also reduce the weight of the blade 1 to meet the light weight requirement of the new type engine.

[0051] Figure 5 A mold of a blade with a biomimetic cooling channel inside is shown.

[0052] The above only describes the preferred embodiments of the present application and is not used to limit the present application. For those skilled in the art, the present application can have various modifications and changes. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A biomimetic cooling structure for turbine blades, characterized in that: It includes blades (1) and a cooling structure for cooling the blades (1); The cooling structure includes a biomimetic cooling channel (2), an air inlet for supplying cooling airflow into the biomimetic cooling channel (2), and an air outlet (11) for discharging cooling air from the biomimetic cooling channel (2). Two biomimetic cooling channels (2) are provided in the blade (1). One of the two biomimetic cooling channels (2) is close to the leaf basin surface of the blade (1), and the other is close to the back surface of the blade (1), which are used to cool the leaf basin surface and the back surface of the blade (1) respectively. The biomimetic cooling channel includes several first channels (21) connecting the air inlet and the air outlet (11), several second channels (22) perpendicularly intersecting the first channels (21), and a mixing chamber (23) opened at the intersection of the first channels (21) and the second channels (22). The cooling airflow enters the second channel (22) through the first channel (21), and the cooling airflow in the first channel (21) and the second channel (22) converges in the mixing chamber (23) to form a vortex. Several first channels (21) are arranged at intervals along a first direction, and several second channels (22) are arranged at intervals along a second direction. The mixing cavities (23) opened on two adjacent first channels (21) are staggered in the second direction, and the mixing cavities (23) opened on two adjacent second channels (22) are staggered in the first direction. The widths of the first channel (21) and the second channel (22) are both no greater than the radius of the mixing cavity (23).

2. The biomimetic cooling structure for turbine blades according to claim 1, characterized in that: The projections of the first channel (21) and the second channel (22) in the third direction are both rectangles; The third direction is perpendicular to both the first and second directions.

3. The biomimetic cooling structure for turbine blades according to claim 1, characterized in that: The blade (1) has a leaf basin air film hole (24) that connects to the biomimetic cooling channel (2) near the leaf basin surface, and the blade (1) has a leaf back air film hole (25) that connects to the biomimetic cooling channel (2) near the leaf back surface.

4. The biomimetic cooling structure for turbine blades according to claim 1, characterized in that: The cross-sections of the first channel (21) and the second channel (22) are both rectangular.

5. The biomimetic cooling structure for turbine blades according to claim 1, characterized in that: The cooling structure also includes a rear cavity (3) and a trailing edge slit (4) opened in the blade (1) near the trailing edge. The rear cavity (3) is opened along the second direction. The trailing edge slit (4) connects the rear cavity (3) with the outside. All the second channels (22) in the two biomimetic cooling channels (2) are connected to the rear cavity (3).

6. The biomimetic cooling structure for turbine blades according to claim 1, characterized in that: The cooling structure also includes a front cavity (5) opened in the blade (1) near the leading edge. The front cavity (5) is opened along the second direction and its bottom end is connected to the air inlet. The inner wall of the front cavity (5) is provided with a plurality of leading edge air film holes (51) that connect to the outer surface of the leading edge of the blade (1) so as to draw the cooling airflow entering the front cavity (5) out to the leading edge of the blade (1) to cool the leading edge position.

7. The biomimetic cooling structure for turbine blades according to claim 6, characterized in that: The cooling structure also includes a central cavity (6) opened at the center of the blade (1). The central cavity (6) is opened along the second direction and its bottom end is connected to the air inlet. The central cavity (6) is located between the two bionic cooling channels (2) so as to introduce cooling airflow to cool the side of the bionic cooling channel (2) near the center of the blade (1).

8. The biomimetic cooling structure for turbine blades according to claim 7, characterized in that: An impact hole (61) is provided on the side of the middle cavity (6) adjacent to the front cavity (5) to connect the front cavity (5) and the middle cavity (6), so that the cooling airflow in the middle cavity (6) enters the front cavity (5) through the impact hole (61).

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