Turbine moving blade internal cooling structure

Abstract

A series of impact holes are formed in the front edge of a blade, the diameter of the impact holes is determined according to the cooling requirement and the strength of the blade, the diameter of the impact holes ranges from 0.5 mm to 2 mm, the impact holes are arranged in an array mode, it is guaranteed that cooling airflow can impact the inner surface of the front edge of the blade at a high speed, strong convective heat exchange is formed, and the service life of the blade is prolonged. The included angle between the axis of the impact hole and the inner surface of the front edge of the blade is 30-60 degrees, so that cooling airflow can be effectively diffused along the surface of the blade after impact, the cooling effect is enhanced, and formation of local hot spots is reduced; and tail edge cooling grooves are formed in the blade tail edge at equal intervals. The device has the advantages that all parts of the blades can be efficiently cooled, impact holes, air film holes and a turbulent flow structure cooperate, heat exchange is enhanced, the cooling efficiency is further improved through the pin fins, smooth and anti-blocking effects are guaranteed through reasonable air inlet and filtering design, stable operation of the whole device is guaranteed through cooling of the blade platform and the top cover, and the service life is prolonged.

Description

Technical Field

[0001] The invention relates to the technical field of turbine blade cooling, and in particular to an internal cooling structure of a turbine blade. Background Art

[0002] As an important energy conversion device, turbines are widely used in many fields such as electricity, aviation, and petrochemicals. During its operation, turbine blades are in direct contact with high-temperature and high-pressure fluid media (such as gas and steam), and are subject to extremely high thermal loads and mechanical stresses. For example, in a gas turbine, the gas temperature can reach over 1000°C, while turbine blades are usually made of metal materials, which have limited high temperature resistance.

[0003] Traditional turbine blade cooling technology has many shortcomings. In the early simple cooling channel design, the cooling medium flowed relatively slowly in the channel, mainly relying on natural convection heat exchange, with low cooling efficiency, and it was difficult to meet the strict requirements of modern turbines for blade cooling. With the development of technology, although some improvement measures have emerged, such as a single air film cooling method, in actual applications, the stability of the air film is difficult to guarantee and is easily disturbed by external airflow and ruptured, resulting in local cooling failure. The blades are still at risk of overheating and damage.

[0004] In addition, some cooling structures only focus on cooling a certain local area of ​​the blade, ignoring the different heat load distribution characteristics and interrelationships of the leading edge, middle and trailing edge of the blade. For example, the leading edge of the blade is directly impacted by high-temperature and high-speed fluid, so the heat load is concentrated and strong, while the trailing edge of the blade also has special thermal stress conditions due to changes in the fluid flow state. Traditional cooling methods are difficult to carry out comprehensive and efficient cooling of these areas in a targeted manner, which not only affects the working performance and reliability of the turbine blades, but also increases the equipment operating costs and reduces production efficiency due to frequent maintenance or replacement of the blades. Therefore, it is urgent to develop a more advanced, comprehensive and efficient internal cooling structure for turbine blades to meet the needs of modern industry for improving the performance of turbine equipment.

[0005] To this end, we propose an internal cooling structure for turbine blades to solve the above problems. Summary of the invention

[0006] The purpose of the present invention is to solve the problems in the prior art and to propose an internal cooling structure for turbine moving blades.

[0007] In order to achieve the above object, the present invention adopts the following technical solutions:

[0008] A turbine blade internal cooling structure, comprising:

[0009] The leading edge of the blade is provided with a series of impact holes. The diameter of the impact holes is determined according to the cooling requirements and the strength of the blade. The diameter of the impact holes is between 0.5mm and 2mm. The impact holes are arranged in an array to ensure that the cooling airflow can impact the inner surface of the leading edge of the blade at a high speed to form a strong convection heat exchange. The angle between the axis of the impact hole and the inner surface of the leading edge of the blade is set between 30° and 60°, so that the cooling airflow can effectively diffuse along the blade surface after impact, thereby enhancing the cooling effect and reducing the formation of local hot spots;

[0010] The trailing edge of the blade has trailing edge cooling grooves equidistantly arranged on the trailing edge of the blade;

[0011] The middle part of the blade connects the leading edge of the blade and the trailing edge of the blade, and the thickness of the middle part of the blade is greater than the thickness of the leading edge of the blade and the thickness of the trailing edge of the blade;

[0012] A cooling channel, wherein a spoiler structure is arranged inside the cooling channel;

[0013] The air film holes are arranged on the leading edge, the middle part and the trailing edge of the blade. The diameter of the air film holes is set at 0.3mm-1.5mm. The air film holes are opened at a certain angle along the blade surface, and the setting angle is between 20°-45°.

[0014] In the above-mentioned internal cooling structure of the turbine moving blade, the arrangement density of the film holes is adjusted according to the heat load distribution at different positions of the blade, and the film holes are arranged more densely in the area with high heat load.

[0015] In the above-mentioned turbine blade internal cooling structure, it also includes

[0016] The blade platform is arranged at the lower end of the turbine blade. An air intake passage is opened on the blade platform. The air intake passage adopts a gradually expanding design to reduce the pressure loss when the airflow enters.

[0017] In the above-mentioned turbine moving blade internal cooling structure, blade platform cooling holes are opened on the blade platform.

[0018] In the above-mentioned turbine blade internal cooling structure, it also includes

[0019] The top cover is arranged at the leading edge of the blade, the middle part of the blade and the upper end of the trailing edge of the blade, and a top cover cooling hole is opened at the upper end of the top cover.

[0020] In the above-mentioned turbine moving blade internal cooling structure, the spoiler structure is provided with a first spoiler rib, a U-shaped spoiler rib, a second spoiler rib and a third spoiler rib in sequence from the leading edge of the blade to the trailing edge of the blade;

[0021] The U-shaped spoiler ribs include long spoiler ribs and short spoiler ribs, the long spoiler ribs are close to the first spoiler ribs, the short spoiler ribs are close to the third spoiler ribs, and the second spoiler ribs are located between the long spoiler ribs and the short spoiler ribs.

[0022] In the above-mentioned internal cooling structure of the turbine moving blade, an air intake baffle is provided at the lower end of the U-shaped spoiler rib, and the air intake baffle divides the air intake channel into a left air intake channel and a right air intake channel. The left air intake channel and the right air intake channel are respectively provided with a first filter screen and a second filter screen.

[0023] In the above-mentioned internal cooling structure of the turbine moving blade, the first spoiler rib, the U-shaped spoiler rib, the second spoiler rib and the third spoiler rib divide the cooling channel into a first channel, a second channel, a U-shaped channel, a third channel and a fourth channel, and the lower end of the second channel is connected to the left air intake channel, the right air intake channel is connected to the lower ends of the third channel and the fourth channel, and the second channel and the third channel are both connected to the U-shaped channel.

[0024] In the above-mentioned internal cooling structure of the turbine moving blade, the second channel, the third channel and the U-shaped channel are all provided with inclined cooling layer plates on the side close to the second channel, and the U-shaped channel is provided with an inclined convection plate on the side close to the third channel, and adjacent convection plates are symmetrically arranged, and the planes on which the upper surfaces of the convection plates are located are perpendicular to each other.

[0025] In the above-mentioned turbine moving blade internal cooling structure, the inner wall of the fourth passage is provided with pin-shaped fins, and the pin-shaped fins are vertically arranged on the inner wall of the blade.

[0026] Compared with the prior art, the present invention has the following beneficial effects:

[0027] 1. By setting impact holes with a diameter of 0.5mm-2mm on the leading edge of the blade and arranging them in an array, the cooling airflow can impact the inner surface of the leading edge of the blade at a high speed. This impact cooling method forms a strong convection heat exchange, which can quickly take away the heat accumulated on the leading edge of the blade due to the scouring of high-temperature gas. At the same time, the angle between the axis of the impact hole and the inner surface of the leading edge of the blade is between 30°-60°, so that the cooling airflow can effectively diffuse along the blade surface after impact, enhance the cooling effect and reduce the formation of local hot spots, effectively prevent the leading edge of the blade from overheating and damage, and extend the service life of the leading edge of the blade.

[0028] 2. The thickness of the middle part of the blade is greater than that of the leading and trailing edges of the blade. The cooling channel runs through it and is provided with a spoiler structure. The spoiler fins can destroy the laminar boundary layer of the cooling medium, increase the turbulence of the airflow, improve the convective heat transfer coefficient, and strengthen the cooling of the middle part of the blade. Air film holes are also provided in the middle part of the blade. The diameter is 0.3mm-1.5mm and the inclination angle is between 20°-45°. An air film can be formed on the surface of the middle part of the blade, reducing the direct contact between the high-temperature combustion gas and the surface of the middle part of the blade, and further reducing the surface temperature of the middle part of the blade. The arrangement density of the air film holes is adjusted according to the heat load distribution to make the cooling more uniform and efficient.

[0029] 3. The equidistant trail cooling grooves at the trailing edge of the blade can effectively take away the heat at the trailing edge, ensuring that the temperature of the trailing edge of the blade is within a reasonable range during operation, thereby avoiding degradation or damage to the blade performance due to overheating of the trailing edge.

[0030] 4. The cooling channel is divided into multiple channels by spoiler fins and the channels are interconnected. This design makes the flow path of the cooling medium in the channel more reasonable and can fully utilize the cooling capacity of the cooling medium. For example, the inclined cooling layer plates and convection plates set in the U-shaped channel optimize the flow and heat exchange of the cooling medium in this area and improve the heat exchange efficiency of the entire cooling channel.

[0031] 5. The air intake channel on the blade platform adopts a gradually expanding design, which reduces the pressure loss when the airflow enters and ensures that the cooling medium can smoothly enter the cooling system. The air intake channel is divided into a left air intake channel and a right air intake channel, and is respectively provided with a first filter and a second filter, which can effectively filter impurities in the cooling medium and prevent impurities from entering the cooling channel and causing blockage, thereby ensuring the long-term stable operation of the cooling system.

[0032] To sum up, the present invention can efficiently cool all parts of the blade. The impact holes, air film holes and spoiler structures work together to enhance heat exchange. The pin fins further improve the cooling efficiency. Reasonable air intake and filtration design ensure smooth flow and prevent blockage. The cooling of the blade platform and top cover ensures the stable operation of the entire device and extends its service life. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 A schematic diagram of the internal cooling structure of a turbine blade proposed by the present invention;

[0034] Figure 2 A schematic diagram of the structure of a turbine blade internal cooling structure proposed by the present invention without the top cover, cooling layer plate and convection plate;

[0035] Figure 3 The present invention provides an internal cross-sectional view of an internal cooling structure for a turbine moving blade.

[0036] In the figure: 1 blade leading edge, 2 blade middle, 3 blade trailing edge, 4 impact hole, 5 trailing edge cooling groove, 6 cooling channel, 7 air film hole, 8 blade platform, 9 air inlet channel, 11 blade platform cooling hole, 12 top cover, 13 top cover cooling hole, 14 first spoiler rib, 15 U-type spoiler rib, 16 second spoiler rib, 17 third spoiler rib, 18 long spoiler rib, 19 short spoiler rib, 20 first channel, 21 second channel, 22 U-type channel, 23 third channel, 24 fourth channel, 25 left air inlet channel, 26 right air inlet channel, 27 first filter, 28 second filter, 29 cooling layer plate, 30 convection plate, 31 pin fin. DETAILED DESCRIPTION

[0037] The following examples are for illustrative purposes only and are not intended to limit the scope of the present invention.

[0038] Example

[0039] Reference Figure 1-3 , a turbine blade internal cooling structure, comprising

[0040] A blade leading edge 1, on which a series of impact holes 4 are arranged, wherein the diameter of the impact holes 4 is determined according to the cooling requirements and the blade strength, and the diameter of the impact holes 4 is between 0.5 mm and 2 mm, and the impact holes 4 are arranged in an array to ensure that the cooling airflow can impact the inner surface of the blade leading edge 1 at a high speed, thereby forming a strong convection heat exchange, and the angle between the axis of the impact hole 4 and the inner surface of the blade leading edge 1 is set between 30° and 60°, so that the cooling airflow can effectively diffuse along the blade surface after impact, thereby enhancing the cooling effect and reducing the formation of local hot spots;

[0041] The blade trailing edge 3 has trailing edge cooling grooves 5 equidistantly formed on the blade trailing edge 3;

[0042] The blade middle part 2 connects the blade leading edge 1 and the blade trailing edge 3, and the thickness of the blade middle part 2 is greater than the thickness of the blade leading edge 1 and the thickness of the blade trailing edge 3;

[0043] A cooling channel 6 is provided with a spoiler structure inside the cooling channel 6. The spoiler structure is provided with a first spoiler rib 14, a U-shaped spoiler rib 15, a second spoiler rib 16 and a third spoiler rib 17 in sequence from the leading edge 1 of the blade to the trailing edge 3 of the blade; the U-shaped spoiler rib 15 includes a long spoiler rib 18 and a short spoiler rib 19, and the long spoiler rib 18 is close to the first spoiler rib 14, the short spoiler rib 19 is close to the third spoiler rib 17, and the second spoiler rib 16 is located between the long spoiler rib 18 and the short spoiler rib 19. An air intake baffle 10 is provided at the lower end of the U-shaped spoiler rib 15. The air intake baffle 10 divides the air intake channel 9 into a left air intake channel 25 and a right air intake channel 26. The left air intake channel 25 and the right air intake channel 26 are respectively provided with a first filter screen 27 and a second filter screen 28. The first spoiler rib 14, the U-shaped spoiler rib 15, the second spoiler rib 16 and the third spoiler rib 17 are provided in sequence. The spoiler ribs 16 and the third spoiler ribs 17 divide the cooling channel 6 into a first channel 20, a second channel 21, a U-shaped channel 22, a third channel 23 and a fourth channel 24, and the lower end of the second channel 21 is communicated with the left air intake channel 25, the right air intake channel 26 is communicated with the lower ends of the third channel 23 and the fourth channel 24, the second channel 21 and the third channel 23 are both communicated with the U-shaped channel 22, the second channel 21, the third channel 23 and the U-shaped channel 22 are all provided with an inclined cooling layer plate 29 on one side close to the second channel 21, the U-shaped channel 22 is provided with an inclined convection plate 30 on one side close to the third channel 23, and adjacent convection plates 30 are symmetrically arranged, and the planes on which the upper surfaces of the convection plates 30 are located are perpendicular to each other, and the inner wall of the fourth channel 24 is provided with a pin-shaped fin 31, and the pin-shaped fin 31 is vertically arranged on the inner wall of the blade;

[0044] The air film holes 7 are arranged on the leading edge 1, the middle part 2 and the trailing edge 3 of the blade. The diameter of the air film holes 7 is set at 0.3 mm-1.5 mm. The air film holes 7 are inclined at a certain angle along the surface of the blade. The setting angle is between 20° and 45°. The arrangement density of the air film holes 7 is adjusted according to the heat load distribution at different positions of the blade. The air film holes 7 are arranged more densely in the area with high heat load.

[0045] The blade platform 8 is arranged at the lower end of the turbine blade. The blade platform 8 is provided with a blade platform cooling hole 11. The blade platform 8 is provided with an air inlet passage 9. The air inlet passage 9 adopts a gradually expanding design to reduce the pressure loss when the airflow enters;

[0046] The top cover 12 is arranged at the upper ends of the leading edge 1 of the blade, the middle part 2 of the blade, and the trailing edge 3 of the blade. A top cover cooling hole 13 is opened at the upper end of the top cover 12 .

[0047] Introduction of cooling medium: The cooling medium (usually air, etc.) enters the device through the air inlet channel 9 opened on the blade platform 8. The air inlet channel 9 adopts a gradually expanding design, which can effectively reduce the pressure loss when the airflow enters, so that the cooling medium can flow in more smoothly. In addition, after the air inlet baffle 10 separates the air inlet channel 9 into a left air inlet channel 25 and a right air inlet channel 26, the left air inlet channel 25 and the right air inlet channel 26 are respectively provided with a first filter 27 and a second filter 28, which can filter the incoming cooling medium to prevent impurities from entering the cooling channel 6 and causing problems such as blockage.

[0048] Cooling of the blade leading edge 1: A series of impact holes 4 are provided on the blade leading edge 1, and the diameters thereof are between 0.5 mm and 2 mm and are arranged in an array. When the cooling medium enters the cooling channel 6, it will impact the inner surface of the blade leading edge 1 at a relatively high speed through the impact holes 4. The angle between the axis of the impact hole 4 and the inner surface of the blade leading edge 1 is set between 30° and 60°, which enables the cooling airflow to effectively diffuse along the blade surface after the impact. On the one hand, a strong convective heat exchange is formed to quickly take away the heat accumulated on the blade leading edge due to the scouring of high-temperature combustion gas and the like; on the other hand, it can enhance the cooling effect and reduce the formation of local hot spots.

[0049] The middle part 2 of the blade is cooled: the middle part 2 of the blade connects the leading edge 1 of the blade and the trailing edge 3 of the blade, and its thickness is greater than the thickness of the leading edge 1 of the blade and the trailing edge 3 of the blade. The cooling channel 6 runs through the middle part 2 of the blade and is provided with a spoiler structure inside. The spoiler structure is provided with a first spoiler rib 14, a U-shaped spoiler rib 15, a second spoiler rib 16 and a third spoiler rib 17 in sequence from the leading edge 1 of the blade to the trailing edge 3 of the blade. These spoiler ribs will destroy the laminar flow state of the cooling medium in the cooling channel 6, increase the turbulence of the air flow, thereby improving the convective heat transfer coefficient and strengthening the cooling effect on the middle part 2 of the blade; at the same time, the air film hole 7 is provided on the middle part 2 of the blade, and its diameter is 0.3mm-1.5mm, and is opened at a certain angle along the surface of the blade (the angle is between 20°-45°). The cooling medium will spray out from the air film holes 7 to form an air film on the surface of the middle part 2 of the blade. This air film can reduce the direct contact between the high-temperature combustion gas and the surface of the middle part 2 of the blade, further reducing the surface temperature of the middle part 2 of the blade. The arrangement density of the air film holes 7 will be adjusted according to the heat load distribution at different positions of the middle part 2 of the blade. The air film holes 7 are arranged more densely in areas with high heat load.

[0050] The blade trailing edge 3 is cooled; trailing edge cooling grooves 5 are equidistantly provided on the blade trailing edge 3. When the cooling medium flows through this, the blade trailing edge 3 can be cooled through the trailing edge cooling grooves 5, taking away the heat at the blade trailing edge 3, thereby ensuring that the temperature of the blade trailing edge 3 is within a reasonable range during operation.

[0051] Flow and heat exchange of cooling medium in the channel: The first spoiler rib 14, the U-shaped spoiler rib 15, the second spoiler rib 16 and the third spoiler rib 17 divide the cooling channel 6 into a first channel 20, a second channel 21, a U-shaped channel 22, a third channel 23 and a fourth channel 24. Among them, the lower end of the second channel 21 is connected to the left air intake channel 25, the right air intake channel 26 is connected to the lower ends of the third channel 23 and the fourth channel 24, and the second channel 21 and the third channel 23 are both connected to the U-shaped channel 22. When the cooling medium flows in these channels, it continuously exchanges heat with the channel wall and various parts of the blade to achieve cooling of different areas of the blade.

[0052] An inclined cooling layer plate 29 is provided on one side of the U-shaped channel 22 close to the second channel 21, which can further enhance the heat exchange effect here; an inclined convection plate 30 is provided on one side of the U-shaped channel 22 close to the third channel 23, and adjacent convection plates 30 are symmetrically arranged, and the planes on which the upper surfaces of the convection plates 30 are located are perpendicular to each other, which also helps to optimize the flow and heat exchange of the cooling medium in the U-shaped channel 22.

[0053] Pin-fin cooling enhancement: Pin-shaped fins 31 are arranged on the inner wall of the fourth channel 24. The pin-shaped fins 31 are arranged vertically on the inner wall of the blade. When the cooling medium flows through the fourth channel 24, the pin-shaped fins 31 can greatly increase the heat exchange area. Heat can be conducted from the high-temperature channel wall through the pin-shaped fins 31 and then taken away by the cooling medium. At the same time, the presence of the pin-shaped fins 31 will also cause the cooling medium to generate strong disturbances in the fourth channel 24, destroying the boundary layer of the fluid, making the mixing between the fluid near the wall and the main fluid more complete, and further improving the cooling efficiency.

[0054] Cooling of the blade platform 8 and the top cover 12: The blade platform 8 is provided with a blade platform cooling hole 11, which can cool the blade platform 8 and take away the heat generated during operation; the top cover 12 is arranged at the upper end of the blade leading edge 1, the blade middle 2, and the blade trailing edge 3, and the upper end of the top cover 12 is provided with a top cover cooling hole 13, which can cool the top cover 12 to ensure that its temperature is appropriate and avoid adverse effects on the performance and operation of the entire device due to excessively high temperature.

[0055] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes according to the technical scheme and inventive concept of the present invention within the technical scope disclosed by the present invention, which should be covered by the protection scope of the present invention.

Claims

1. A turbine blade internal cooling structure, characterized in that: include The leading edge (1) of the blade is provided with a series of impact holes (4), the diameter of the impact holes (4) is determined according to the cooling demand and the strength of the blade, the diameter of the impact holes (4) is between 0.5 mm and 2 mm, the impact holes (4) are arranged in an array, so as to ensure that the cooling airflow can impact the inner surface of the leading edge (1) of the blade at a high speed, thereby forming a strong convection heat exchange, and the angle between the axis of the impact hole (4) and the inner surface of the leading edge (1) of the blade is set between 30° and 60°, so that the cooling airflow can effectively diffuse along the blade surface after impact, thereby enhancing the cooling effect and reducing the formation of local hot spots; The blade trailing edge (3) is provided with trailing edge cooling grooves (5) at equal intervals; The middle part (2) of the blade connects the leading edge (1) of the blade and the trailing edge (3) of the blade, and the thickness of the middle part (2) of the blade is greater than the thickness of the leading edge (1) of the blade and the thickness of the trailing edge (3) of the blade; A cooling channel (6), wherein a turbulent flow structure is arranged inside the cooling channel (6); The air film holes (7) are arranged on the leading edge (1), the middle part (2) and the trailing edge (3) of the blade. The diameter of the air film holes (7) is set at 0.3 mm-1.5 mm. The air film holes (7) are opened at a certain angle along the blade surface, and the setting angle is between 20° and 45°.

2. The internal cooling structure of a turbine moving blade according to claim 1, characterized in that: The arrangement density of the air film holes (7) is adjusted according to the heat load distribution at different positions of the blade, and the air film holes (7) are arranged more densely in areas with high heat load.

3. The internal cooling structure of a turbine blade according to claim 1, characterized in that: Also includes The blade platform (8) is arranged at the lower end of the turbine blade. An air intake passage (9) is provided on the blade platform (8). The air intake passage (9) adopts a gradually expanding design to reduce the pressure loss when the airflow enters.

4. The internal cooling structure of a turbine moving blade according to claim 3, characterized in that: The blade platform (8) is provided with a blade platform cooling hole (11).

5. The internal cooling structure of a turbine blade according to claim 1, characterized in that: Also includes A top cover (12) is arranged at the upper ends of the leading edge (1), the middle part (2) and the trailing edge (3) of the blade, and a top cover cooling hole (13) is provided at the upper end of the top cover (12).

6. The internal cooling structure of a turbine moving blade according to claim 3, characterized in that: The spoiler structure is provided with a first spoiler rib (14), a U-shaped spoiler rib (15), a second spoiler rib (16) and a third spoiler rib (17) in sequence from the leading edge (1) of the blade to the trailing edge (3) of the blade; The U-shaped spoiler rib (15) comprises a long spoiler rib (18) and a short spoiler rib (19), wherein the long spoiler rib (18) is close to the first spoiler rib (14), the short spoiler rib (19) is close to the third spoiler rib (17), and the second spoiler rib (16) is located between the long spoiler rib (18) and the short spoiler rib (19).

7. The internal cooling structure of a turbine blade according to claim 6, characterized in that: An air intake baffle (10) is provided at the lower end of the U-shaped spoiler rib (15), and the air intake baffle (10) divides the air intake channel (9) into a left air intake channel (25) and a right air intake channel (26), and the left air intake channel (25) and the right air intake channel (26) are respectively provided with a first filter screen (27) and a second filter screen (28).

8. The internal cooling structure of a turbine blade according to claim 7, characterized in that: The first spoiler rib (14), the U-shaped spoiler rib (15), the second spoiler rib (16) and the third spoiler rib (17) divide the cooling channel (6) into a first channel (20), a second channel (21), a U-shaped channel (22), a third channel (23) and a fourth channel (24), and the lower end of the second channel (21) is connected to the left air intake channel (25), the right air intake channel (26) is connected to the lower ends of the third channel (23) and the fourth channel (24), and the second channel (21) and the third channel (23) are both connected to the U-shaped channel (22).

9. The internal cooling structure of a turbine moving blade according to claim 8, characterized in that: The second channel (21), the third channel (23) and the U-shaped channel (22) are all provided with an inclined cooling layer plate (29) on one side close to the second channel (21); the U-shaped channel (22) is provided with an inclined convection plate (30) on one side close to the third channel (23); adjacent convection plates (30) are symmetrically arranged, and the planes on which the upper surfaces of the convection plates (30) are located are perpendicular to each other.

10. The internal cooling structure of a turbine blade according to claim 8, characterized in that: The inner wall of the fourth channel (24) is provided with a needle-shaped fin (31), and the needle-shaped fin (31) is vertically arranged on the inner wall of the blade.

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