Turbine blade leading edge reinforced swirl cooling structure and engine

Abstract

This invention provides a turbine blade leading-edge enhanced swirling cooling structure and an engine, comprising: a cold gas jet orifice, a jet stagnation region, a ridge, a first recess, a second recess, and a leading-edge cavity; a leading-edge cavity is provided at the leading edge of the turbine blade, and a cold gas jet orifice and multiple film cooling holes are provided on the leading-edge cavity. The cold gas jet enters the leading-edge cavity through the cold gas jet orifice. A wavy ridge is provided on the inner wall of the leading-edge cavity, and a jet stagnation region is provided on the adjacent wall surface of the ridge facing the cold gas jet; a first recess is provided on the ridge, and a second recess is provided at the jet stagnation region. The cold gas jet impacts the first and second recesses. This application achieves higher heat transfer enhancement performance and lower pressure loss by impacting the wall surface with recesses and ridges tangentially with the cold gas jet. At the same time, the cold gas jet spreads laterally when impacting the recessed wall surface, which is beneficial for improving heat transfer over a larger surface area.

Description

Technical Field

[0001] This invention relates to the field of turbine structures, and more specifically, to a turbine blade leading edge enhanced swirling cooling structure and an engine. Background Technology

[0002] Turbines are crucial heat-work conversion components in aero-engines and gas turbines. Increasing the turbine inlet gas temperature is an important means of improving the thermal efficiency of gas turbines and aero-engines. Currently, the turbine inlet gas temperature is far higher than the operating temperature limit of the metal materials used in turbine blades; therefore, turbine blades require cooling technologies to keep the blade wall temperature within the tolerance range of the metal materials.

[0003] Currently, conventional turbine blades employ internal impact cooling at the leading edge, with film cooling holes arranged on the leading edge wall. During turbine blade operation, high-temperature external combustion gases scour and sweep across the leading edge, subjecting the leading edge wall to the highest thermal load, making it susceptible to oxidation and hot corrosion, thus requiring highly efficient and reliable cooling. Improving the cooling performance of the turbine blade leading edge is crucial for enhancing the thermal efficiency and service life of gas turbines and aero-engines.

[0004] Currently, turbine blades rely on internal impingement cooling, convection cooling within the film cooling orifices, and film cooling formed on the outer wall of the leading edge by the outflow from the orifices for thermal protection. The current problem is that while internal impingement cooling is effective, the jet pressure loss is significant, resulting in uneven heat distribution on the wall. Furthermore, the flow recirculation vortex formed at the orifice inlet after the jet impacts the wall blocks the orifice inlet, reducing the flow rate and thus diminishing both internal and external film cooling. Additionally, the flow separation vortex within the orifices on the leading edge stagnation zone wall blocks the outflow of cool air, creating uneven flow velocity. This also degrades the external film cooling performance of the turbine blade leading edge, leading to high-temperature ablation at the blade leading edge and shortening the turbine blade's lifespan. Summary of the Invention

[0005] In view of the deficiencies in the prior art, the purpose of this invention is to provide a turbine blade leading edge enhanced swirling cooling structure and an engine.

[0006] A turbine blade leading edge enhanced swirling cooling structure according to the present invention includes: a cold gas jet hole, a jet stagnation region, a ridge, a first recess, a second recess, and a leading edge cavity;

[0007] A leading edge cavity is provided at the leading edge of the turbine blade. A cold gas jet hole and a plurality of film gas holes are provided on the leading edge cavity. The cold gas jet enters the leading edge cavity through the cold gas jet hole.

[0008] The inner wall of the leading edge cavity is provided with a ridge. The adjacent wall surface of the ridge facing the cold gas jet is provided with a jet stagnation area. The ridge is provided with an array of first recesses, and the jet stagnation area is provided with an array of second recesses. When the cold gas jet impacts the first and second recesses, it will spread laterally on the wall surfaces of the first and second recesses, which is beneficial to improve heat transfer on a larger surface. When the cold gas jet impacts the ridge with the first recess, a low-speed recirculation zone will be formed downstream of the ridge, that is, inside the blade leading edge stagnation area.

[0009] Preferably, the turbine blade is provided with a suction side wall and a pressure side wall that are connected in an enclosing manner, and the leading edge cavity is formed by a partition separating the leading edge portion of the cavity formed by the enclosing suction side wall and the pressure side wall.

[0010] Preferably, the cold air jet holes are disposed on the partition plate;

[0011] The protruding ridge includes: a first protruding ridge and a second protruding ridge, wherein the first protruding ridge is disposed on the inner sidewall of the suction sidewall and the second protruding ridge is disposed on the inner sidewall of the pressure sidewall.

[0012] Both the suction sidewall and the pressure sidewall have jet stagnation areas on their inner sidewalls, which are adjacent to the first ridge and the second ridge, respectively.

[0013] Preferably, the cold air jet orifice includes: a first jet orifice and a second jet orifice;

[0014] The cold air jet impacts the first depression of the first ridge and the second depression of the jet stagnation area adjacent to the first ridge in a tangential direction through the first jet hole, and the cold air jet impacts the first depression of the second ridge and the second depression of the jet stagnation area adjacent to the second ridge in a tangential direction through the second jet hole, thereby achieving higher heat transfer enhancement performance and lower pressure loss.

[0015] Preferably, the first recess is located on the side of the ridge facing the cold air jet.

[0016] Preferably, the area on the side of the first and second ridges facing away from the cold air jet is set as the blade leading edge stagnation area. A first film cooling hole is provided at the blade leading edge stagnation area. The interaction between the cold air jet and the ridge forms a low-speed backflow inside the blade leading edge stagnation area. This avoids the high-speed cold air jet directly sweeping across the film cooling hole, which is beneficial to improving the outflow of the first film cooling hole in the blade leading edge stagnation area and improving the external film cooling performance.

[0017] A second air film hole is provided in the area between the jet stagnation point area and the partition plate.

[0018] Preferably, multiple first and second ridges are provided along the height direction of the turbine blade, with multiple first ridges arranged at intervals, multiple second ridges arranged at intervals, and multiple first ridges and multiple second ridges arranged alternately.

[0019] Preferably, multiple first jet holes and multiple second jet holes are provided along the height direction of the turbine blade. The multiple first jet holes are arranged at intervals and correspond one-to-one with a first protruding ridge. The multiple second jet holes are arranged at intervals and correspond one-to-one with a second protruding ridge. The multiple first jet holes and multiple second jet holes are arranged alternately.

[0020] Preferably, the first ridge and the second ridge are arranged in a wave shape along the height direction of the turbine blade, with the crest of the first ridge corresponding to the trough of the second ridge, and the trough of the first ridge corresponding to the crest of the second ridge.

[0021] The first jet orifice and the second jet orifice correspond to the crest positions of the first ridge and the second ridge, respectively.

[0022] Preferably, the profile of the ridge is a trapezoidal cross-section with rounded or chamfered edges, or an arc shape, and smoothly transitions to the adjacent wall surface;

[0023] The depressions on the wall can be spherical, conical, cylindrical, oval, or grooved. These depressions can be interconnected, thereby increasing the contact area between the cold air and the wall and enhancing the heat transfer performance.

[0024] Compared with the prior art, the present invention has the following beneficial effects:

[0025] 1. This application achieves higher heat transfer enhancement performance and lower pressure loss by impacting the ridge with a cold air jet in a tangential direction. At the same time, the cold air jet will spread laterally when it impacts the ridge wall, which is beneficial to improve heat transfer on a larger surface area and improve heat transfer uniformity.

[0026] 2. There are multiple air film cooling holes on the wall of the stagnation zone at the leading edge of the blade. The interaction between the cold air jet and the ridge creates a low-speed backflow inside the stagnation zone at the leading edge of the blade. This avoids the high-speed cold air jet directly sweeping across the air film orifice, which is beneficial to improving the outflow of the air film orifice in the stagnation zone at the leading edge and improving the external air film cooling performance.

[0027] 3. The ridges undulate along the height of the blade, and the peaks and troughs of the ridges on the pressure side wall are staggered from the peaks and troughs of the ridges on the opposite suction side wall. When the jet impacts the peak area of ​​the ridge, the depressions are arranged on the peak wall of the ridge and facing the direction of the jet flow, and the depressions are also arranged on the trough wall of the ridge.

[0028] 4. The impact of the cold air jet on the undulating ridges, blocked by the ridge crests, is more conducive to the diffusion of cold air in the lateral direction (i.e., the direction of blade height), thereby obtaining enhanced and uniform wall heat transfer. It is also conducive to the cold air flowing into the leading edge stagnation area along both sides of the ridges, and then cooling the outer wall of the blade through the air film pores on the leading edge wall.

[0029] 5. Creating recesses on the ridge and trough walls improves the heat transfer performance of jet flow from the opposite surface when it adheres to the wall, thereby enhancing the cooling performance of the wall. Furthermore, it allows the flow to spread laterally across the wall, reducing momentum flow in the flow direction and enabling better or more airflow to reach the leading edge stagnation region, thus improving the film cooling performance on the blade leading edge stagnation wall. Attached Figure Description

[0030] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0031] Figure 1 A schematic diagram of the overall structure of the turbine blade leading edge reinforced swirling cooling structure;

[0032] Figure 2 Schematic diagram of airflow direction after cold air jet impacts the ridge (I).

[0033] Figure 3 Schematic diagram of airflow direction after cold air jet impacts the ridge (II).

[0034] Figure 4 A diagram showing the distribution of spaced-out ridges and depressions in the jet stagnation area;

[0035] Figure 5 A diagram showing the positional relationship between the first and second depressions;

[0036] Figure 6 A schematic diagram of a wavy ridge;

[0037] Figure 7 This is a schematic diagram of the recessed location;

[0038] As shown in the figure:

[0039] Detailed Implementation

[0040] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0041] This embodiment provides a turbine blade leading edge enhanced swirling cooling structure suitable for aero-engines and gas turbines. The main design involves a ridge 5 on the inner wall of the turbine blade leading edge, with multiple recesses on the windward side and adjacent walls of the ridge 5. The cold gas jet impacts the recessed walls and ridge 5 tangentially, resulting in enhanced heat transfer performance and lower pressure loss. Simultaneously, the cold gas jet spreads laterally upon impact with the recessed walls, improving heat transfer over a larger surface area. The impact of the cold gas jet on the recessed ridge 5 creates a low-speed recirculation zone downstream of the ridge 5, within the blade leading edge stagnation region 8. Multiple rows of first film cooling holes 6 are located on the wall of the blade leading edge stagnation region 8. This prevents the high-speed cold gas jet from directly sweeping across the openings of the first film cooling holes 6, improving the outflow from the first film cooling holes 6 in the blade leading edge stagnation region 8 and enhancing external film cooling performance.

[0042] Specifically, such as Figure 1-3 As shown, this embodiment includes: a cold air jet hole 1, a baffle 2, a jet stagnation area 3, a suction side wall 4, a ridge 5, a first air film hole 6, a second air film hole 7, a blade leading edge stagnation area 8, a pressure side wall 9, a second recess 10, and a leading edge cavity 11.

[0043] The turbine blades are provided with a suction side wall 4 and a pressure side wall 9 that are connected in an enclosing manner. The leading edge cavity 11 is formed by a partition 2 that separates the leading edge portion of the cavity formed by the suction side wall 4 and the pressure side wall 9. The wall surface of the leading edge cavity 11 has multiple recessed structures. A ridge 5 is provided on the inner side wall of the leading edge cavity 11. A jet stagnation region 3 is provided on the adjacent wall surface of the ridge 5 facing the cold gas jet. The ridge 5 has an array of first recesses 503 arranged along its length direction. The first recesses 503 are located on the side of the ridge 5 facing the cold gas jet. An array of second recesses 10 is provided at the jet stagnation region 3. The cold gas jet impacts the first recesses 503 and the second recesses 10.

[0044] The ridge 5 includes a first ridge 501 and a second ridge 502. The first ridge 501 is disposed on the inner sidewall of the suction sidewall 4, and the second ridge 502 is disposed on the inner sidewall of the pressure sidewall 9. Both the suction sidewall 4 and the pressure sidewall 9 have jet stagnation areas 3 disposed on their inner sidewalls, which are adjacent to the first ridge 501 and the second ridge 502, respectively.

[0045] Combination Figure 7As shown, a cold air jet orifice 1 and multiple film cooling orifices are provided on the leading edge cavity 11. The cold air jet enters the leading edge cavity 11 through the cold air jet orifice 1. The cold air jet orifice 1 includes a first jet orifice 101 and a second jet orifice 102. The cold air jet impacts the first ridge 501 in a tangential direction towards the first recess 503 of the first ridge 501 and the second recess 10 of the jet stagnation region 3 adjacent to the first ridge 501 through the first jet orifice 101. The cold air jet impacts the second ridge 502 in a tangential direction towards the first recess 503 of the second ridge 502 and the second recess 10 of the jet stagnation region 3 adjacent to the second ridge 502. The area on the side of the first ridge 501 and the second ridge 502 facing away from the cold air jet is set as the blade leading edge stagnation region 8. A first film cooling orifice 6 is provided at the blade leading edge stagnation region 8, and a second film cooling orifice 7 is provided in the area between the jet stagnation region 3 and the septum 2.

[0046] like Figure 4-5 As shown, in one embodiment, multiple first ridges 501 and second ridges 502 are provided along the height direction of the turbine blade, where the height direction of the turbine blade refers to the direction perpendicular to the direction of the turbine blade. Figure 1 Extending in the direction shown in the cross-section, multiple first ridges 501 are arranged at intervals, multiple second ridges 502 are arranged at intervals, and the multiple first ridges 501 and multiple second ridges 502 are arranged alternately. Multiple first jet holes 101 and multiple second jet holes 102 are provided along the height direction of the turbine blade. The multiple first jet holes 101 are arranged at intervals and each corresponds to a first ridge 501, the multiple second jet holes 102 are arranged at intervals and each corresponds to a second ridge 502, and the multiple first jet holes 101 and multiple second jet holes 102 are arranged alternately.

[0047] like Figure 6 As shown, in one embodiment, the first ridge 501 and the second ridge 502 are arranged in a wave shape along the height direction of the turbine blade, with the crest of the first ridge 501 corresponding to the trough of the second ridge 502, and the trough of the first ridge 501 corresponding to the crest of the second ridge 502; the first jet hole 101 and the second jet hole 102 correspond to the crest positions of the first ridge 501 and the second ridge 502, respectively.

[0048] In one embodiment, the ridge 5 has an arc shape and smoothly transitions to the adjacent wall surface.

[0049] The working principle of this embodiment is as follows:

[0050] When the cold air jet impacts the second recess 10, the air in the second recess 10 acts as an air cushion, thus reducing the pressure loss from the jet impact.

[0051] The cold gas jet can generate a large-scale swirling flow in the leading edge chamber 11 of the blade through the staggered first jet hole 101 and second jet hole 102, which significantly improves heat transfer performance and heat transfer uniformity. However, the high-speed circumferential swirling flow will be deflected at a large angle when entering the film cooling hole, causing flow separation and blockage within the film cooling hole, resulting in problems such as uneven film cooling outflow and reduced film cooling efficiency.

[0052] Arranging intermittent ridges 5 under the biased jet can, on the one hand, induce the jet on the wall to flow laterally along the ridges 5, further improving the cooling uniformity and heat transfer intensity of the leading edge; on the other hand, it can cause the cold gas jet to interact with the wall of the ridges 5, and cause flow separation in advance before entering the first film gas hole 6, and then reattach it as a low-speed backflow at the stagnation zone 8 at the leading edge of the blade, providing uniform inflow conditions for the first film gas hole 6 and improving the uniformity of the film gas outflow.

[0053] This embodiment utilizes an array of recesses on local walls (suction-side wall 4 and pressure-side wall 9) and local ridges 5 to regulate the turbulent flow of the swirling stream, reducing the flow velocity of the swirling stream and the flow shear between the fluid and the wall, thereby reducing pressure loss. Simultaneously, the strategic arrangement of recesses in the high-speed flow region can significantly improve near-wall turbulent mixing, thus enhancing heat transfer.

[0054] Within the leading edge cavity 11, the offset jets impact the suction side wall 4 and the pressure side wall 9 in a staggered manner. Each jet corresponds to a ridge 5, which is discontinuously distributed on either the suction side wall 4 or the pressure side wall 9. For example, the discontinuous region corresponding to the middle of the discontinuous second ridge 502 arranged on the pressure side wall 9 is exactly where the jet impacts the same blade height on the suction side wall 4.

[0055] At the suction side wall 4 and the pressure side wall 9, multiple second recesses 10 are arranged in the jet stagnation region 3 corresponding to the upstream wall of the ridge 5, so as to make full use of the enhanced heat transfer effect of the high-speed near-wall flow. Here, multiple first recesses 503 are arranged along the corresponding length of the ridge 5, and the wall of the ridge 5 with the first recesses 503 faces the jet impact.

[0056] When the cold air jet impacts the wall of the ridge 5, it interacts with multiple first depressions 503 to generate depression vortices, further enhancing turbulent mixing and improving heat transfer. Furthermore, the wall where the first depressions 503 are located can extend the cold air flow in the lateral direction, thereby obtaining high heat transfer performance over a larger area and improving the uniformity of cold air in the leading edge cavity 11 of the blade.

[0057] Example 2

[0058] like Figure 1-3As shown in Figure 6, within the leading edge cavity 11 of the blade, offset cold gas jets are staggered and arranged near the pressure side wall 9 and suction side wall 4 of the blade. Each cold gas jet corresponds to the peak of a ridge 5, which undulates in a wave shape on the pressure side wall 9 (or suction side wall 4). For example, the jet arranged on the pressure side wall 9 impacts the peak of the ridge 5, which corresponds exactly to the valley area of ​​the ridge 5 on the suction side wall 4 at the same blade height. The ridge profile is a rounded or chamfered trapezoidal section, or an arc, smoothly transitioning to the wall surface. The adjacent ridge 5 corresponding to each jet hole is at a higher height (or has a ridge 5), while the corresponding ridge 5 on the other side wall of the leading edge is at a lower height (or has a gap in the ridge 5, or does not have a ridge 5). The height of the ridges 5 on the pressure side wall 9 and the suction side wall 4 is 0-10d, and the height of the ridges 5 varies from 0-5d, where d is the equivalent diameter of the jet orifice.

[0059] On the wavy ridge 5 wall surface corresponding to the jet orifice, further recesses can be arranged to obtain better heat transfer performance. Multiple recesses are present on the windward side of the ridge 5 and on adjacent walls. The cold air jet impacts the recessed wall surface and ridge tangentially, achieving higher heat transfer enhancement performance and lower pressure loss. When the cold air jet impacts the recessed wall surface, the air contained within the recesses acts as an air cushion, thus reducing the pressure loss from the jet impact.

[0060] like Figure 7 As shown, multiple first recesses 503 are arranged on the windward wall of the ridge 5, and multiple second recesses 10 are arranged in the stagnation region 8 at the leading edge of the blade, so as to make full use of the enhanced heat transfer effect of the high-speed near-wall flow. Here, multiple first recesses 503 are arranged along the length of the ridge 5, and the wall of the ridge 5 with the first recesses 503 faces the jet impact; the first recesses 503 are also arranged on the opposite side wall of the ridge 5.

[0061] When the cold air jet impacts the wall of the ridge 5, it interacts with multiple first depressions 503 to generate depression vortices, which further enhance turbulent mixing, improve heat transfer, and the depression wall can expand the cold air flow in the lateral direction, thereby obtaining high heat transfer performance over a larger area and improving the uniformity of cold air inside the leading edge of the blade.

[0062] The staggered and offset cooling gas jets can generate large-scale swirling flow within the leading edge cavity 11 of the blade, significantly improving heat transfer performance and uniformity. However, the high-speed circumferential swirling flow will be deflected at a large angle when entering the film cooling hole, initiating flow separation and blockage within the film cooling hole, resulting in problems such as uneven film cooling outflow and reduced film cooling efficiency.

[0063] Arranging wavy ridges 5 under the biased jet can, on the one hand, induce the wall jet to flow laterally along the ridges 5, further improving the cooling uniformity and heat transfer intensity of the leading edge; on the other hand, it can cause the cold gas jet to interact with the wall of the ridges 5, and cause flow separation in advance before entering the first film gas hole 6, and then reattach it as a low-speed backflow in the stagnation zone 8 at the leading edge of the blade, providing uniform inflow conditions for the first film gas hole 6 and improving the uniformity of the film gas outflow.

[0064] This embodiment utilizes an array of recesses on localized wall surfaces and ridges to regulate the turbulent flow of the swirling stream, reducing the flow velocity and the flow shear between the fluid and the wall, thereby decreasing pressure loss. Simultaneously, the strategic arrangement of recesses in the high-speed flow region significantly enhances near-wall turbulent mixing, thus strengthening heat transfer.

[0065] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0066] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A turbine blade leading edge enhanced swirl cooling structure, characterized in that, include: Cold air jet hole (1), jet stagnation area (3), ridge (5), first depression (503), second depression (10) and leading edge cavity (11); A leading edge cavity (11) is provided at the leading edge of the turbine blade. A cold air jet hole (1) and a plurality of air film holes are provided on the leading edge cavity (11). The cold air jet enters the leading edge cavity (11) through the cold air jet hole (1). The inner wall of the leading edge cavity (11) is provided with a ridge (5), and the adjacent wall of the ridge (5) facing the cold gas jet is provided with a jet stagnation area (3). The ridge (5) is provided with an array of first recesses (503), and the jet stagnation area (3) is provided with an array of second recesses (10). The cold gas jet impacts the first recess (503) and the second recess (10).

2. The turbine blade leading edge enhanced swirling cooling structure according to claim 1, characterized in that: The turbine blade is provided with a suction side wall (4) and a pressure side wall (9) that are connected in an enclosing manner. The leading edge cavity (11) is formed by a partition (2) that separates the leading edge portion of the cavity formed by the suction side wall (4) and the pressure side wall (9). The wall surface of the leading edge cavity (11) has multiple recessed structures.

3. The turbine blade leading edge enhanced swirling cooling structure according to claim 2, characterized in that: The cold air jet hole (1) is provided on the partition plate (2); The protruding ridge (5) includes: a first protruding ridge (501) and a second protruding ridge (502), wherein the first protruding ridge (501) is disposed on the inner sidewall of the suction sidewall (4), and the second protruding ridge (502) is disposed on the inner sidewall of the pressure sidewall (9); The suction sidewall (4) and the pressure sidewall (9) are each provided with a jet stagnation area (3) which is adjacent to the first ridge (501) and the second ridge (502) respectively.

4. The turbine blade leading edge enhanced swirling cooling structure according to claim 3, characterized in that, The cold air jet hole (1) includes: a first jet hole (101) and a second jet hole (102); The cold air jet impacts the first recess (503) of the first ridge (501) and the second recess (10) of the jet stagnation area (3) adjacent to the first ridge (501) in a tangential direction through the first jet hole (101); The cold air jet impacts the second jet hole (102) in the tangential direction toward the first depression (503) of the second ridge (502) and the second depression (10) of the jet stagnation area (3) adjacent to the second ridge (502).

5. The turbine blade leading edge enhanced swirling cooling structure according to claim 1, characterized in that: The first recess (503) is located on the side of the ridge (5) facing the cold air jet; The profile of the protruding ridge (5) is a trapezoidal cross section with rounded or chamfered corners, or an arc shape, and smoothly transitions to the adjacent wall surface.

6. The turbine blade leading edge enhanced swirl cooling structure according to claim 3, characterized in that: The area of ​​the first ridge (501) and the second ridge (502) facing away from the cold air jet is set as the blade leading edge stagnation area (8). A first air film hole (6) is provided at the blade leading edge stagnation area (8). A second air film hole (7) is provided in the area between the jet stagnation area (3) and the partition (2).

7. The turbine blade leading edge enhanced swirl cooling structure according to claim 3, characterized in that: The first protruding ridge (501) and the second protruding ridge (502) are provided in multiple ways along the height direction of the turbine blade. The multiple first protruding ridges (501) are arranged at intervals, the multiple second protruding ridges (502) are arranged at intervals, and the multiple first protruding ridges (501) and the multiple second protruding ridges (502) are arranged alternately.

8. The turbine blade leading edge enhanced swirling cooling structure according to claim 4, characterized in that: The first ridge (501) and the second ridge (502) are arranged in a wave shape along the height direction of the turbine blade. The peak of the first ridge (501) corresponds to the trough of the second ridge (502), and the trough of the first ridge (501) corresponds to the peak of the second ridge (502). The first jet hole (101) and the second jet hole (102) correspond to the crest positions of the first ridge (501) and the second ridge (502), respectively.

9. The turbine blade leading edge enhanced swirling cooling structure according to claim 4, characterized in that: Multiple first jet holes (101) and multiple second jet holes (102) are provided along the height direction of the turbine blade. Multiple first jet holes (101) are arranged at intervals and correspond to a first protrusion ridge (501) one by one. Multiple second jet holes (102) are arranged at intervals and correspond to a second protrusion ridge (502) one by one. Multiple first jet holes (101) and multiple second jet holes (102) are arranged alternately.

10. An engine, characterized in that: The turbine blade leading edge enhanced swirling cooling structure according to any one of claims 1-9 is adopted.

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