A turbine working blade and a turbine fan device having the same

Abstract

The present application relates to the technical field of turbine blade, and discloses a turbine working blade and a turbine fan device with the same.The turbine working blade comprises a blade body, an inlet flow channel is arranged on the blade body, a first intermediate chamber and a second intermediate chamber are arranged in the blade body, and the first intermediate chamber and the second intermediate chamber are communicated with the inlet flow channel; a front chamber is arranged in the inside of a leading edge area of the blade body, and the front chamber is communicated with the first intermediate chamber; a trailing edge chamber is arranged in the inside of a trailing edge area of the blade body, one end of the trailing edge chamber is communicated with the second intermediate chamber, the other end of the trailing edge chamber is communicated with a trailing edge film hole, the trailing edge film hole is communicated with an external environment, and a honeycomb type airflow channel is arranged in the trailing edge chamber.By arranging the inside of the trailing edge chamber into the honeycomb type airflow channel, the honeycomb bionic channel is adopted, the cooling effect is greatly improved, and the metal temperature of the surface of the blade body can be obviously reduced.

Description

Technical Field

[0001] This invention relates to the field of turbine blade technology, and more specifically to a turbine working blade and a turbine fan device having the same. Background Technology

[0002] As aero engines demand increasingly higher performance in terms of power and fuel efficiency, turbine inlet temperatures have reached over 2000K, posing a severe challenge to the stable operation of turbine blades in high-temperature, long-term environments. There is an urgent need to develop new turbine blade cooling structures to meet the high cooling requirements of advanced aero engines.

[0003] Turbine blade cooling primarily includes various cooling methods such as impingement, meandering channels, film cooling, and turbulence columns. Depending on the turbine blade structure and environmental influences, a composite cooling design employs multiple cooling structures. For turbine blades with high cycle parameters, a combined cooling approach of "meandering channels + impingement + film cooling + ribs + slotting" is typically used. This technology is currently very mature and has been widely applied in large, medium, and small aero-engines.

[0004] However, as turbine inlet temperatures in aero-engines continue to rise, this cooling method, while optimizing the internal cooling structure to enhance heat transfer and reduce blade metal temperature, has limited effectiveness. It can only passively employ full-film cooling to lower blade temperature, which also increases the cold air bleed ratio, leading to a decrease in engine performance. Specifically, as the cold air flows through the meandering channel, it carries away heat from the high-temperature blade walls while its own temperature continuously increases, resulting in a weakening of heat dissipation capacity along the flow direction. This ultimately leads to uneven temperature distribution on the blade walls and thermal stress concentration. Moreover, most existing meandering channel structures, even after optimization, show little overall difference from the original prototype, offering limited improvement in heat transfer capacity. While adjusting the geometric parameters of the meandering channel and rib structure can improve cooling, it also increases flow resistance, making it difficult to achieve a balance. Summary of the Invention

[0005] In view of this, the present invention provides a turbine working blade and a turbine fan device having the same, to solve the problem that turbine blades in the prior art cannot meet the cooling requirements of turbine working blades in engines with high cycle parameters.

[0006] In a first aspect, the present invention provides a turbine blade, comprising:

[0007] The blade body has an inlet channel and a first intermediate chamber and a second intermediate chamber, both of which are connected to the inlet channel.

[0008] A front chamber is located inside the leading edge region of the blade body, and the front chamber communicates with the first intermediate chamber.

[0009] The trailing edge chamber is located inside the trailing edge region of the blade body. One end of the trailing edge chamber is connected to the second intermediate chamber, and the other end is connected to a trailing edge air film hole. The trailing edge air film hole is connected to the external environment, and a honeycomb-shaped airflow channel is provided inside the trailing edge chamber.

[0010] During turbine blade operation, cool air enters the blade body through the inlet channel and splits into two streams, flowing into the first and second intermediate chambers respectively. The cool air in the first intermediate chamber flows towards the front chamber and then exits, cooling the leading edge region and the central portion near the leading edge of the blade body. The cool air in the second intermediate chamber flows towards the trailing edge chamber, flows through the trailing edge film cooling holes, and then exits, cooling the trailing edge region and the central portion near the trailing edge of the blade body. By designing the trailing edge chamber as a honeycomb-shaped airflow channel, a honeycomb biomimetic channel is employed, resulting in a significant improvement in cooling efficiency. This noticeably reduces the metal temperature on the blade surface while requiring a smaller volume of cool air. The honeycomb airflow channel allows for precise control of cooling in different regions by adjusting its structural parameters, thereby changing the heat transfer area and heat transfer coefficient. This enables precise control of cooling in the high-temperature and low-temperature regions of the blade, reducing the temperature gradient of the blade metal, improving the cooling effect of the vortex blade, and allowing the vortex blade to better meet the cooling requirements of turbine blades in high-cycle-parameter engines. This provides a new approach to improving the cooling effect of subsequent vortex working blades.

[0011] In one optional embodiment, the blade body further comprises a first basin-side chamber and a first back-side chamber. The first basin-side chamber is located on the side of the first intermediate chamber facing the leaf base of the blade body, and the first back-side chamber is located on the side of the first intermediate chamber facing the back of the blade body. A honeycomb-shaped airflow channel is provided within the first basin-side chamber and / or the first back-side chamber. By providing the first basin-side chamber and the first back-side chamber on both sides of the first intermediate chamber, and by providing honeycomb-shaped airflow channels therein, the cooling effect of the cold airflow on the blade body in the first intermediate chamber region can be enhanced.

[0012] In one optional embodiment, the blade body further comprises a second basin-side chamber and a second dorsal-side chamber. The second basin-side chamber is located on the side of the second intermediate chamber facing the leaf base of the blade body, and the second dorsal-side chamber is located on the side of the second intermediate chamber facing the back of the blade body. A honeycomb-shaped airflow channel is provided in the second basin-side chamber and / or the second dorsal-side chamber, and this honeycomb-shaped airflow channel is arranged perpendicularly to the honeycomb-shaped airflow channel in the trailing edge chamber. By providing a second basin-side chamber and a second dorsal-side chamber on both sides of the second intermediate chamber, and providing honeycomb-shaped airflow channels therein, the cooling effect of the cold airflow on the blade body in the second intermediate chamber region can be enhanced.

[0013] In one optional embodiment, the first intermediate chamber and the front chamber are connected by a front chamber impact hole, and the front chamber impact hole is provided at intervals.

[0014] In one optional embodiment, the end of the front cavity impact hole that communicates with the front chamber is disposed facing the inner wall of the blade back side of the front chamber, thereby constructing a leading edge swirling impact structure. This allows the airflow to form a vortex as it flows radially upward when it enters the front chamber from the front cavity impact hole, thereby enhancing the heat exchange capacity of the cold air inside the front chamber.

[0015] In one optional embodiment, at least two layers of honeycomb-shaped airflow channels are provided on the inner wall of the front chamber to enhance the cooling effect of the cold flow on the blade body in the front chamber area.

[0016] In one optional embodiment, multiple trailing edge chambers are spaced apart in the radial direction of the blade body. The multiple trailing edge chambers are separated to avoid the increase in metal temperature gradient caused by uneven flow distribution in the honeycomb channels of the trailing edge region in the radial direction. Multiple trailing edge chambers can be arranged in the radial height, and the honeycomb channels in different trailing edge chambers are separated by partitions. The airflow in different regions in the radial direction will not cross each other, thereby avoiding the phenomenon of uneven flow distribution caused by uneven static pressure distribution in the radial direction of the trailing edge cold air outlet.

[0017] In one optional embodiment, the front chamber is provided with a front chamber tip hole at the end facing the blade tip, and the front chamber tip hole communicates with the external environment.

[0018] In one optional embodiment, the blade body is provided with a tenon, and the flow inlet channel is located in the inner cavity of the tenon.

[0019] Secondly, the present invention also provides a turbofan device having the turbine blades described in the present invention. The turbofan device can be an aircraft engine or a gas turbine, as the turbofan device includes turbine blades and has the same effects as turbine blades, which will not be elaborated further here. Attached Figure Description

[0020] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0021] Figure 1 A cross-sectional view of a turbine blade provided for an embodiment of the present invention.

[0022] Figure 2 A top view of a turbine working blade provided for an embodiment of the present invention.

[0023] Figure 3 This is a schematic diagram of the flow path of the cool air in the inner cavity of the turbine working blade provided for an embodiment of the present invention, wherein the red arrow indicates the flow direction of the cool air.

[0024] Figure 4 This is a schematic diagram of a honeycomb airflow channel provided in an embodiment of the present invention, wherein the red arrow indicates the direction of cold air flow.

[0025] Explanation of reference numerals in the attached drawings: 1. Anterior chamber; 2. First intermediate chamber; 3. Second intermediate chamber; 4. Anterior chamber impact hole; 5. First basin side chamber; 6. First dorsal side chamber; 7. Second basin side chamber; 8. Second dorsal side chamber; 9. Tail edge chamber; 10. Tail edge air film hole; 11. Anterior chamber leaf tip hole; 12. First intermediate leaf basin leaf tip outlet; 13. First intermediate leaf dorsal leaf tip outlet; 14. Second intermediate leaf basin leaf tip outlet; 15. Second intermediate leaf dorsal leaf tip outlet; 16. Tenon inner cavity; 17. Root extension inner cavity. Detailed Implementation

[0026] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0027] The following is combined with Figures 1 to 4The following describes embodiments of the present invention.

[0028] According to an embodiment of the present invention, a turbine working blade is provided, including a blade body and a first intermediate chamber 2, a second intermediate chamber 3, a front chamber 1 and a trailing edge chamber 9 disposed inside the blade body.

[0029] The blade body is provided with an inlet channel. In this embodiment, the blade body is provided with a tenon, and the inlet channel is located in the inner cavity 16 of the tenon. A first intermediate chamber 2 and a second intermediate chamber 3 are provided in the middle region of the blade body. Both the first intermediate chamber 2 and the second intermediate chamber 3 are connected to the inlet channel. The front chamber 1 is located inside the leading edge region of the blade body and is connected to the first intermediate chamber 2. The trailing edge chamber 9 is located inside the trailing edge region of the blade body. One end of the trailing edge chamber 9 is connected to the second intermediate chamber 3, and the other end is connected to a trailing edge film air hole 10. The trailing edge film air hole 10 is connected to the external environment, and a honeycomb-shaped airflow channel is provided inside the trailing edge chamber 9.

[0030] When the turbine blades are operating, cool air enters the blade body cavity through the inlet channel and splits into two streams, entering the first intermediate chamber 2 and the second intermediate chamber 3 respectively. The cool air in the first intermediate chamber 2 flows towards the front chamber 1 and then exits from the front chamber 1, cooling the leading edge region and the middle part near the leading edge of the blade body. The cool air in the second intermediate chamber 3 flows towards the trailing edge chamber 9, flows into the trailing edge film cooling hole 10 in the trailing edge chamber 9, and then exits, cooling the trailing edge region and the middle part near the trailing edge of the blade body. By setting the interior of the trailing edge chamber 9 into a honeycomb-shaped airflow channel, a honeycomb biomimetic channel is adopted, which significantly improves the cooling effect, can significantly reduce the metal temperature of the blade surface, and requires less cool air. Honeycomb airflow channels can control the cooling effect in different regions by adjusting their structural parameters, thereby changing the heat transfer area and heat transfer coefficient. This allows for precise control of cooling in the high-temperature and low-temperature zones of the blades, reducing the temperature gradient of the blade metal, improving the cooling effect of vortex blades, and enabling them to better meet the cooling requirements of turbine blades in high-cycle-parameter engines. This provides a new approach for further improving the cooling effect of vortex blades.

[0031] In one embodiment, the blade body further includes a first basin-side chamber 5 and a first back-side chamber 6. The first basin-side chamber 5 is located on the side of the first intermediate chamber 2 facing the leaf base of the blade body, and the first back-side chamber 6 is located on the side of the first intermediate chamber 2 facing the back of the blade body. Honeycomb-shaped airflow channels are provided within the first basin-side chamber 5 and the first back-side chamber 6. By providing the first basin-side chamber 5 and the first back-side chamber 6 on both sides of the first intermediate chamber 2, and by providing honeycomb-shaped airflow channels within them, the cooling effect of the cold airflow on the blade body in the region of the first intermediate chamber 2 can be enhanced. In some other embodiments, if the blade body volume is small, only one of the first basin-side chamber 5 or the first back-side chamber 6 may be provided.

[0032] Furthermore, the blade body also includes a second basin-side chamber 7 and a second dorsal-side chamber 8. The second basin-side chamber 7 is located on the side of the second intermediate chamber 3 facing the leaf base of the blade body, and the second dorsal-side chamber 8 is located on the side of the second intermediate chamber 3 facing the back of the blade body. Honeycomb-shaped airflow channels are provided within the second basin-side chamber 7 and / or the second dorsal-side chamber 8, and these honeycomb-shaped airflow channels are arranged perpendicularly to the honeycomb-shaped airflow channels within the trailing edge chamber 9. By providing the second basin-side chamber 7 and the second dorsal-side chamber 8 on both sides of the second intermediate chamber 3, and providing honeycomb-shaped airflow channels within them, the cooling effect of the cold airflow on the blade body in the region of the second intermediate chamber 3 can be enhanced. In some other embodiments, if the blade body volume is small, only one of the second basin-side chamber 7 or the second dorsal-side chamber 8 may be provided.

[0033] In one embodiment, in order to improve the cooling effect of the cold flow on the front chamber 1, the first intermediate chamber 2 is connected to the front chamber 1 through a front chamber impact hole 4, and a plurality of front chamber impact holes 4 are provided at intervals.

[0034] Specifically, the end of the front chamber impact hole 4 that communicates with the front chamber 1 is positioned facing the inner wall of the blade back side of the front chamber 1, thereby constructing a leading-edge swirling impact structure. This allows the airflow to form vortices as it flows radially upward into the front chamber 1, enhancing the heat exchange capacity of the cold air inside the front chamber 1. At least two layers of honeycomb-shaped airflow channels are provided on the inner wall of the front chamber 1 to enhance the cooling effect of the cold air on the blade body in the front chamber 1 area. A front chamber tip hole 11 is provided at the end of the front chamber 1 facing the blade tip. The front chamber tip hole 11 communicates with the external environment to discharge the cold air in the front chamber 1 to the blade body through the front chamber tip hole 11.

[0035] In one embodiment, multiple trailing edge chambers 9 are arranged at intervals in the radial direction of the blade body. The multiple trailing edge chambers 9 are separated to avoid the increase in metal temperature gradient caused by uneven flow distribution in the honeycomb channels in the trailing edge region along the radial direction. Multiple trailing edge chambers 9 in the trailing edge region can be arranged along the radial height. The honeycomb channels in different trailing edge chambers 9 are separated by partitions, and the airflow in different regions along the radial direction will not cross each other, thereby avoiding the phenomenon of uneven flow distribution caused by uneven static pressure distribution in the radial direction of the trailing edge cold air outlet.

[0036] This embodiment proposes a novel cooling flow path design for the inner cavity of turbine working blades. Using a honeycomb biomimetic channel in a confined space as the cooling structural unit, and combining the characteristics of the working blade airfoil, a combined cooling form for the inner cavity of the turbine working blade is constructed. Compared with the traditional "winding channel + impact + air film + rib + slotted" cooling design, it can significantly improve the heat exchange capacity of the blade inner cavity under the condition of small cooling air volume, improve the blade cooling effect, and meet the cooling requirements of turbine working blades of the new generation of high cycle parameter engines.

[0037] The turbine blade provided in this embodiment is a combined cooling structure of leading-edge swirling impact, middle honeycomb channel, trailing-edge honeycomb channel, and trailing-edge film cooling hole 10. The swirling impact of the leading-edge impact hole 4 involved in this invention is located between the blade's leading-edge chamber 1 and the first intermediate chamber 2; the first basin-side chamber 5 is located between the first intermediate chamber 2 and the blade's blade basin wall; the first back-side chamber 6 is located between the first intermediate chamber 2 and the blade's back wall; the second basin-side chamber 7 is located between the second intermediate chamber 3 and the blade's blade basin wall; the second back-side chamber 8 is located between the second intermediate chamber 3 and the blade's back wall; the trailing-edge chamber 9 is connected to the second intermediate chamber 3; and the trailing-edge film cooling hole 10 is connected to the trailing-edge chamber 9.

[0038] Secondary flow cold air is extracted from the two airflows in the combustion chamber. The cold air enters the tenon cavity 16 of the tenon through the cold air inlet on the blade tenon, and continues to flow upward through the root cavity 17. At this time, part of the cold air enters the first intermediate chamber 2, and the other part enters the second intermediate chamber 3. The cold air entering the first intermediate chamber 2 is divided into three airflows. One airflow enters the first intermediate chamber 2 directly along the radial direction, and then impacts the front chamber 1 through the front impact hole 4. At the same time, the front impact hole 4 is angled towards the front edge blade back, forming a leading edge swirling impact structure, which enables the airflow to form vortices during the radial upward flow of the front chamber, enhancing the heat exchange capacity of the cold air inside the front chamber. The cold air entering the front chamber 1 will eventually be discharged from the front blade tip hole 11. The other two streams of cold air entering the first intermediate chamber 2 directly enter the first basin-side chamber 5 and the first back-side chamber 6, respectively. A honeycomb channel network is arranged against the wall surface on the blade basin and back sides. This wall-mounted cooling combined with honeycomb channels effectively reduces the temperature of the blade's metal wall under low-volume cold air conditions. The cold air entering the honeycomb channels exits from the first intermediate blade basin tip outlet 12 and the first intermediate blade back tip outlet 13, respectively, after flowing through multiple honeycomb channel units. Similarly, the cold air entering the second intermediate chamber 3 is divided into three streams. One stream enters the second intermediate chamber 3 radially, then flows towards the trailing edge through the transverse honeycomb channels, and finally exits from the trailing edge film pore 10. The other two streams directly enter the second basin-side chamber 7 and the second back-side chamber 8, and exit from the second intermediate blade basin tip outlet 14 and the second intermediate blade back tip outlet 15, respectively, after passing through multiple honeycomb channel units.

[0039] The shape of the honeycomb channel is an adaptive improvement on the honeycomb structure found in nature. It uses gaps between multiple hexagons to form a stable honeycomb network channel, constructing a biomimetic cooling structure for turbine blade cooling. On the turbine blade, referencing the design concept of double-wall cooling, honeycomb channel units are arranged on both the blade head and back sides using wall cooling, achieving efficient cooling of the turbine blade body with a relatively small amount of cold air.

[0040] In the first intermediate chamber 2 of the blade body, a portion of the cold air directly enters the first intermediate chamber 2. The first intermediate chamber 2 is hollowed out in the middle, and there is no cold air outlet at the blade tip. The cold air in the first intermediate chamber 2 enters the front chamber 1 through the front chamber impact hole 4, generating a swirling impact effect. The cold air moves spirally upward in the front chamber and is discharged from the front chamber tip hole 11. In this embodiment, the outlet of the front chamber impact hole 4 is close to the leading edge of the blade back side. The diameter of the front chamber impact hole 4 is 0.3mm to 1.0mm, and the number of front chamber impact holes 4 is 8 to 20. The specific values ​​of the above parameters are determined based on one-dimensional flow calculations and three-dimensional temperature field calculations.

[0041] In the first intermediate chamber 2 of the blade, a portion of the cool air directly enters the first basin-side chamber 5 and the first back-side chamber 6. The cool air flows upward along the radial wall surface, and the airflow mixes at the corners of the honeycomb channels, resulting in a high heat transfer coefficient. Multiple honeycomb channel units are interconnected, increasing the heat transfer area and thus significantly improving the cooling effect. Finally, the cool air flows out from the blade tip outlet. The advantages of setting honeycomb channels on the blade basin and back sides are: using wall cooling to conform to the blade profile, arranging honeycomb channels on both the blade basin and back sides, resulting in a large heat transfer area and good cooling effect; by changing the structural parameters of the honeycomb channel units at different positions on the blade, the cooling effect at different positions can be adjusted, lowering the temperature in the high-temperature zone and raising the temperature in the low-temperature zone, reducing the blade temperature gradient; compared with traditional meandering channels, adjusting the structural parameters of the honeycomb channel units and the channel slot width results in a significant increase in the internal cavity heat transfer coefficient, which can meet the cooling requirements of the blades of the new generation of wide-condition aero-engines; the structural parameters of the honeycomb channel units can be adaptively changed according to the characteristics of the blade profile, with a simple and versatile structure, which can be better applied to turbine cooling blades compared to complex biomimetic cooling units. In this embodiment, the width F of all cellular channel slots is between 0.4 mm and 0.7 mm, the included angle γ is between 60° and 120°, D1 is between 0.8 mm and 1.4 mm, D2 is between 0.4 mm and 0.7 mm, and D3 is between 0.8 mm and 2.5 mm, where γ, D1, D2, and D3 are all structural parameters of the cellular channel unit. Figure 4 The honeycomb channel unit enclosed in the dashed box is a single layer of honeycomb channel unit. 5 to 12 layers of honeycomb channel units are arranged radially on the blade basin side of the front chamber 1, and 2 to 4 layers of honeycomb channel units are arranged transversely. 5 to 12 layers of honeycomb channel units are arranged radially on the blade back side of the front chamber 1, and 2 to 4 layers of honeycomb channel units are arranged transversely. The above parameters need to be determined by one-dimensional flow iterative calculation and three-dimensional temperature field iterative calculation, taking into account the rotation effect.

[0042] In the second intermediate chamber 3 of the blade, a portion of the cold air directly enters the second intermediate chamber 3. The second intermediate chamber 3 is hollowed out in the middle and has no cold air outlet at the blade tip; instead, it directly connects to the trailing edge chamber 9. The layout of the trailing edge chamber 9 is rotated 90 degrees compared to the honeycomb channels of the first intermediate chamber 2. The cold air entering the honeycomb channels in the trailing edge region continues to flow along the trailing edge direction of the blade and exits from the trailing edge film pores 10. In this invention, the parameter ranges of the honeycomb channel unit structure parameters γ, D1, D2, D3 and the channel slot width F of the second intermediate chamber 3 are consistent with those of the leading edge region. In the trailing edge region, 6 to 18 layers of honeycomb channel units are arranged radially, and 2 to 10 layers of honeycomb channel units are arranged transversely. The specific values ​​of these parameters need to be determined through one-dimensional flow iterative calculations and three-dimensional temperature field iterative calculations, taking into account the rotational effect. Because the static pressure distribution along the radial height of the outlet region of the trailing edge film gas hole 10 is uneven, to avoid the increase in metal temperature gradient caused by the uneven flow distribution of the honeycomb channels in the radial direction of the trailing edge region, the trailing edge region can be divided into 3 to 5 regions along the radial height. The honeycomb channels in each region are separated by baffles, and the airflow in different regions along the radial direction will not cross each other, thereby avoiding the phenomenon of uneven flow distribution caused by the uneven static pressure distribution along the radial direction of the trailing edge cold air outlet. In this invention, the diameter of the trailing edge film gas hole 10 is 0.3 mm to 0.5 mm, and the number of film gas holes is 6 to 20.

[0043] High-cycle-parameter engines subject turbine blades to high-temperature and harsh environments. The demand for high performance necessitates minimizing bleed air volume. The turbine blades provided in this embodiment balance low bleed air volume with high-efficiency cooling. Furthermore, adjustments to the localized cooling structure allow for control of metal temperatures in different blade regions, demonstrating significant engineering application value. The use of honeycomb biomimetic channels significantly improves cooling efficiency, noticeably reducing the metal temperature on the blade surface while requiring less cooling air. By adjusting the structural parameters of the honeycomb channels, the heat transfer area and coefficient in different regions can be altered to control the cooling effect in different areas, achieving precise control of cooling in both high-temperature and low-temperature zones of the blade, thereby reducing the temperature gradient of the blade metal.

[0044] According to an embodiment of the present invention, in another aspect, a turbofan device is also provided, having the turbine blades described in the present invention. The turbofan device can be an aero-engine or a gas turbine, because the turbofan device includes turbine blades and has the same effect as the turbine blades. The turbine blades, by employing honeycomb biomimetic channels, achieve a significant improvement in cooling effect, substantially reducing the metal temperature on the blade surface, and requiring less cooling air. The honeycomb channels can control the cooling effect in different regions by adjusting their structural parameters to change the heat transfer area and heat transfer coefficient of different regions, achieving precise control of cooling in the high-temperature and low-temperature regions of the blade, thereby reducing the temperature gradient of the blade metal.

[0045] Although embodiments of the invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the invention, and such modifications and variations all fall within the scope defined by the appended claims.

Claims

1. A turbine blade, characterized in that, include: The blade body has an inlet channel and a first intermediate chamber (2) and a second intermediate chamber (3) are provided inside the blade body. Both the first intermediate chamber (2) and the second intermediate chamber (3) are connected to the inlet channel. The first intermediate chamber (2) is hollowed out in the middle, and the second intermediate chamber (3) is hollowed out in the middle; The front chamber (1) is located inside the leading edge region of the blade body, and the front chamber (1) is connected to the first intermediate chamber (2); The trailing edge chamber (9) is located inside the trailing edge region of the blade body. One end of the trailing edge chamber (9) is connected to the second intermediate chamber (3), and the other end is connected to the trailing edge air film hole (10). The trailing edge air film hole (10) is connected to the external environment. A honeycomb-shaped airflow channel is provided inside the trailing edge chamber (9). The blade body is further provided with a second basin-side chamber (7) and a second dorsal-side chamber (8). The second basin-side chamber (7) is located on the side of the second intermediate chamber (3) facing the leaf basin of the blade body. The second dorsal-side chamber (8) is located on the side of the second intermediate chamber (3) facing the back of the blade body. The second basin-side chamber (7) and / or the second dorsal-side chamber (8) are provided with honeycomb-shaped airflow channels. The honeycomb-shaped airflow channels provided in the second basin-side chamber (7) and / or the second dorsal-side chamber (8) are arranged perpendicularly to the honeycomb-shaped airflow channels provided in the trailing edge chamber (9). The honeycomb-shaped airflow channel is suitable for introducing cold air; Five to twelve honeycomb airflow channel units are arranged radially on the leaf basin side of the front chamber (1), and two to four honeycomb airflow channel units are arranged transversely. Five to twelve honeycomb airflow channel units are arranged radially on the leaf back side of the front chamber (1), and two to four honeycomb airflow channel units are arranged transversely. The trailing edge chambers (9) are arranged in multiple spaces in the radial direction of the blade body, and the multiple trailing edge chambers (9) are separated from each other. The trailing edge region is divided into 3 to 5 zones along the radial height, and the honeycomb-shaped airflow channels within the zone are separated by baffles.

2. The turbine blade according to claim 1, characterized in that, The blade body is further provided with a first basin-side chamber (5) and a first back-side chamber (6). The first basin-side chamber (5) is located on the side of the first intermediate chamber (2) facing the leaf basin of the blade body, and the first back-side chamber (6) is located on the side of the first intermediate chamber (2) facing the back of the blade body. The first basin-side chamber (5) and / or the first back-side chamber (6) are provided with honeycomb-shaped airflow channels.

3. The turbine blade according to claim 1 or 2, characterized in that, The first intermediate chamber (2) is connected to the front chamber (1) through a front chamber impact hole (4), and the front chamber impact hole (4) is provided at intervals.

4. The turbine blade according to claim 3, characterized in that, The front cavity impact hole (4) is located on the inner wall of the blade back side of the front cavity (1) at one end that is connected to the front cavity (1).

5. The turbine blade according to claim 1 or 2, characterized in that, The front chamber (1) is provided with a front chamber tip hole (11) at one end facing the blade tip, and the front chamber tip hole (11) is in communication with the external environment.

6. The turbine blade according to claim 1 or 2, characterized in that, The blade body is provided with a tenon, and the flow inlet channel is located in the inner cavity of the tenon.

7. A turbine fan device, characterized in that, It has turbine blades as described in any one of claims 1 to 6.

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