Multi-cavity moving blade laminate cooling structure for air-cooled turbine

Abstract

The invention discloses a multi-cavity movable blade laminate cooling structure for an air-cooled turbine, relates to the technical field of turbine blade cooling, and solves the problems that the number of cooling cavities of a traditional double-wall cooling blade is small, the heat exchange area is small, the convective heat exchange effect is insufficient, and cold air distribution is uneven. The blade comprises a blade top, a blade inner wall and a blade outer wall, wherein the blade top is arranged at one end of the blade outer wall in the spanwise direction; a blade inner wall is arranged in the blade outer wall, a plurality of impact cavities are arranged between the blade outer wall and the blade inner wall, a plurality of cold air cavities are arranged in the blade inner wall, the impact cavities and the cold air cavities are in one-to-one correspondence and are communicated through impact holes, and the impact cavities are communicated with the outer side of the blade outer wall through a plurality of air film holes. By means of the method that the turbulent flow columns are densely distributed in the impact cavity, the internal heat exchange area and the turbulence degree are increased, the cross flow phenomenon of the impact holes is reduced, meanwhile, the cooling cavity is further reasonably divided, and cold air on the suction side and the pressure side of the blade cooling cavity is evenly distributed.

Description

Technical Field

[0001] The present invention relates to the technical field of turbine blade cooling, in particular to a multi-chamber moving blade layer plate cooling structure for an air-cooled turbine. Background Art

[0002] As the thrust-to-weight ratio and efficiency of aircraft engines continue to increase, the temperature of the gas at the turbine inlet is also rising. Currently, the front inlet temperature of advanced aircraft engines exceeds 2100K, far exceeding the temperature limit of the materials used for turbine blades. This places enormous thermal loads on the high-pressure turbine blades. Therefore, turbine blades generally require efficient cooling solutions to improve their temperature resistance and ensure safe and stable operation of the turbine.

[0003] Traditional internal cooling of turbine blades primarily involves adding spoilers within the cooling channels of the internal cavity to enhance heat transfer. External cooling, on the other hand, involves film cooling holes in the blade surface. Cooling air drawn from the compressor passes through the blade's internal cooling cavity. A portion of the cooling air exits through the film holes or trailing edge slots, cooling the blade surface. The remainder exits through the blade tip and ultimately joins the main cooling system. However, with the continuous pursuit of higher performance in aircraft engines, traditional cooling technologies are increasingly unable to bridge the gap between turbine inlet temperatures and the operating temperatures of their materials. Double-wall cooling, combining external film cooling, internal impingement cooling, and enhanced heat transfer with spoilers, is considered an effective means of improving cooling performance. Traditional double-wall cooled blades have a small number of cooling chambers, and the impingement chambers only incorporate a limited number of spoilers, resulting in a small heat transfer area. The convective heat transfer coefficient needs to be further improved to adequately cool the blade. Furthermore, the cooling air suffers from uneven distribution and excessive concentration in a single area. Summary of the Invention

[0004] To address the aforementioned issues of conventional double-walled cooling blades, such as a limited number of cooling chambers, small heat exchange area, insufficient convective heat transfer, and uneven cooling air distribution, this invention proposes a multi-chambered blade plate cooling structure for air-cooled turbines. By densely distributing spoiler columns within the impingement chamber, this invention increases the internal heat exchange area and turbulence, reduces crossflow through the impingement holes, and further rationally divides the cooling chambers, ensuring even cooling air distribution between the suction and pressure sides of the blade cooling chamber.

[0005] The present invention proposes a multi-chamber moving blade plate cooling structure for an air-cooled turbine, which specifically includes a blade top, a blade inner wall and a blade outer wall. The blade outer wall is provided with a blade top at one end in the span direction; the blade outer wall is provided with a blade inner wall, and a plurality of impact cavities are provided between the blade outer wall and the blade inner wall. A plurality of cold air cavities are provided inside the blade inner wall. The impact cavities and the cold air cavities correspond one to one and are connected through impact holes. The impact cavities are connected to the outside of the blade outer wall through a plurality of air film holes.

[0006] Furthermore, the impact chamber includes a first impact chamber, a second impact chamber, a third impact chamber, a fourth impact chamber, a fifth impact chamber, a sixth impact chamber, a seventh impact chamber and an eighth impact chamber. The first impact chamber is arranged at the leading edge of the blade, the eighth impact chamber is arranged at the trailing edge of the blade, the second impact chamber, the third impact chamber and the fourth impact chamber are arranged on the suction side of the blade, and the fifth impact chamber, the sixth impact chamber and the seventh impact chamber are arranged on the pressure side of the blade; the second impact chamber, the third impact chamber, the fourth impact chamber, the fifth impact chamber, the sixth impact chamber, the seventh impact chamber and the eighth impact chamber are all provided with several interference flow columns.

[0007] Furthermore, the plurality of impact holes and the plurality of air film holes provided on the first impact cavity are alternately arranged in the span direction of the blade.

[0008] Furthermore, the eighth impact cavity is provided with four air film holes distributed in a matrix at a position close to the blade tip on the pressure side of the blade, and a plurality of air film holes are provided on the suction side of the blade.

[0009] Furthermore, the cold air cavity includes a first cold air cavity, a second cold air cavity, a third cold air cavity, a fourth cold air cavity, a fifth cold air cavity, a sixth cold air cavity, a seventh cold air cavity and an eighth cold air cavity. The first cold air cavity is arranged at the leading edge of the blade, the eighth cold air cavity is arranged at the trailing edge of the blade, the second cold air cavity, the third cold air cavity and the fourth cold air cavity are arranged on the suction side of the blade, and the fifth cold air cavity, the sixth cold air cavity and the seventh cold air cavity are arranged on the pressure side of the blade; the cold air cavities are respectively connected to the impact cavities with the same serial numbers.

[0010] Furthermore, a half-slit structure is provided at the trailing edge of the blade, and the half-slit structure is communicated with the eighth impact cavity.

[0011] Furthermore, the semi-split structure includes a trailing edge split, and a plurality of partition ribs are provided on the trailing edge split.

[0012] Furthermore, a plurality of trailing edge spoiler columns are provided upstream of the semi-slit structure.

[0013] Furthermore, the blade tip and the outer wall of the blade form a groove structure, and the blade tip is the groove bottom of the groove structure.

[0014] Furthermore, a plurality of dust removal holes are provided on the blade top, and the dust removal holes are communicated with the cold air cavity.

[0015] The beneficial effects of the multi-chamber blade plate cooling structure for air-cooled turbines described in the present invention are: (1) The multi-chamber blade plate cooling structure for an air-cooled turbine described in the present invention achieves efficient temperature control by dividing the interior of the turbine blade into multiple cooling chambers and rationally distributing the cooling airflow on the suction side and the pressure side, thereby avoiding thermal stress concentration and blade overheating damage, and improving the service life and structural reliability of the blade. At the same time, it reduces the consumption of cooling air and optimizes the overall thermal efficiency and performance stability of the engine.

[0016] (2) The multi-chamber moving blade plate cooling structure for air-cooled turbines described in the present invention effectively breaks up the cold air flow by arranging dense spoiler columns on the leading edge of the blade, so as to promote the cold air to be evenly distributed in the leading edge area along the blade height direction, avoid excessive concentration of the cooling airflow on the blade tip, and at the same time enhance the turbulence intensity of the cold air, improve the convective heat exchange effect between the airflow and the inner wall of the blade, thereby improving the cooling efficiency, especially improving the cooling performance of the leading edge high heat load area, uniformly distributing the blade temperature, reducing the risk of thermal gradient and thermal stress concentration, and significantly improving the service life and reliability of the blade. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The drawings constituting a part of this application are used to provide a further understanding of the present invention. The illustrative embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute improper limitations on the present invention.

[0018] In the attached figure: Figure 1 This is a schematic structural diagram of the pressure surface of a multi-chamber moving blade plate cooling structure for an air-cooled turbine according to the present invention; Figure 2 This is a schematic structural diagram of the suction surface of a multi-chamber moving blade plate cooling structure for an air-cooled turbine according to the present invention; Figure 3 This is a schematic diagram of the overall structure of a multi-chamber moving blade plate cooling structure for an air-cooled turbine according to the present invention; Figure 4 This is a schematic structural diagram of an internal cavity of a multi-cavity moving blade plate cooling structure for an air-cooled turbine according to the present invention; Figure 5 Schematic diagram of the internal structure of a multi-chamber blade plate cooling structure for an air-cooled turbine according to the present invention; Figure 6 The invention relates to a multi-chamber blade plate cooling structure for an air-cooled turbine. Figure 5 A partial enlarged view of point I in the middle; Figure 7 This is a schematic structural diagram of the pressure surface of the internal structure of a multi-chamber moving blade plate cooling structure for an air-cooled turbine according to the present invention; Figure 8This is a schematic structural diagram of the suction surface of the internal structure of a multi-chamber moving blade plate cooling structure for an air-cooled turbine according to the present invention; Among them: 1-blade leading edge, 2-blade suction side, 3-blade pressure side, 4-blade trailing edge, 5-air film hole, 6-dust removal hole, 7-blade top, 8-partition rib, 9-trailing edge slit, 10-first impact cavity, 11-fifth impact cavity, 12-first cold air cavity, 13-second impact cavity, 14-fifth cold air cavity, 15-second cold air cavity, 16-third cold air cavity, 17-sixth impact cavity, 18-sixth cold air cavity, 19-third impact cavity, 20-fourth cold air cavity, 21-seventh cold air cavity, 22-fourth impact cavity, 23-seventh impact cavity, 24-eighth impact cavity, 25-eighth cold air cavity, 26-trailing edge spoiler, 27-blade inner wall, 28-blade outer wall, 29-impact hole, 30-spoiler. DETAILED DESCRIPTION

[0019] The following will clearly and completely describe the technical solutions of the present invention in conjunction with the accompanying drawings. Obviously, the embodiments described are only some of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making any creative efforts shall fall within the scope of protection of the present invention.

[0020] In the description of the present invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," "outer," and the like, indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings and are intended solely to facilitate the description of the present invention and simplify the description. They do not indicate or imply that the devices or components referred to must have a specific orientation, be constructed, or operate in a specific orientation. Therefore, they should not be construed as limitations on the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0021] In the description of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "installed," "connected," and "connected" should be understood in a broad sense. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to mechanical connections or electrical connections; they can refer to direct connections or indirect connections through an intermediate medium; and they can refer to internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on the specific circumstances.

[0022] In the description of the present invention, it should be noted that the term "spanwise" should be understood as the direction extending generally between the blade root and the blade tip, and the term "chordwise" should be understood as the direction extending generally in an arc shape between the leading edge and the trailing edge of the blade body.

[0023] In addition, the technical features involved in different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0024] Specific implementation method 1: See Figures 1-8 This embodiment is described in detail. The multi-chambered blade plate cooling structure for an air-cooled turbine described in this embodiment specifically includes a blade tip 7, a blade inner wall 27, and a blade outer wall 28. The blade outer wall 28 is provided with the blade tip 7 at one end in the span direction, and the blade inner wall 27 is provided within the blade outer wall 28. The blade outer wall 28 surrounds the outer circumference of the blade inner wall 27, thereby forming a double-walled turbine blade body. The turbine blade includes four regions: a leading edge 1, a trailing edge 4, a suction side 2, and a pressure side 3. Eight impact cavities are provided between the blade outer wall 28 and the blade inner wall 27. Eight cooling air cavities are provided within the blade inner wall 27. The impact cavities correspond to the cooling air cavities and are individually connected through a plurality of impact holes 29 arranged along the span direction. The cooling air cavities are not connected to each other. The impact cavities are connected to the outer side of the blade outer wall 28 via a plurality of film holes 5. Cooling air within the impact cavities is ejected through the film holes 5 and forms film cooling on the outer surface of the blade, preventing direct ablation of the blade surface by the combustion gas and further improving the cooling effect. The air film hole 5 is elliptical or in other shapes. The diameter of the impact hole can be reasonably set according to specific needs.

[0025] The impact chamber includes a first impact chamber 10, a second impact chamber 13, a third impact chamber 19, a fourth impact chamber 22, a fifth impact chamber 11, a sixth impact chamber 17, a seventh impact chamber 23 and an eighth impact chamber 24. The first impact chamber 10 is arranged at the leading edge 1 of the blade, and the eighth impact chamber 24 has a Y-shaped structure and is arranged at the trailing edge 4 of the blade; the second impact chamber 13, the third impact chamber 19 and the fourth impact chamber 22 are arranged in sequence from left to right on the suction side 2 of the blade and are located between the first impact chamber 10 and the eighth impact chamber 24; the fifth impact chamber 11, the sixth impact chamber 17 and the seventh impact chamber 23 are arranged in sequence from left to right on the pressure side 3 of the blade and are located between the first impact chamber 10 and the eighth impact chamber 24; the overall outline of the first impact chamber 10, the second impact chamber 13, the third impact chamber 19, the fourth impact chamber 22, the fifth impact chamber 11, the sixth impact chamber 17, the seventh impact chamber 23 and the eighth impact chamber 24 is similar to the shape of the blade.

[0026] The first impact chamber 10 is not equipped with spoiler columns 30. However, the second impact chamber 13, the third impact chamber 19, the fourth impact chamber 22, the fifth impact chamber 11, the sixth impact chamber 17, the seventh impact chamber 23, and the eighth impact chamber 24 are all equipped with spoiler columns 30. These spoiler columns 30 are staggered and connect the inner and outer blade walls 27 and 28. The second impact chamber 13 is equipped with three rows of spoiler columns 30, and the fifth impact chamber 11 is equipped with two rows of spoiler columns 30. The dense distribution of spoiler columns 30 in the impact chambers near the leading edge ensures uniform cooling air distribution within the impact chamber, ensuring uniform cooling air flow to each film hole 5 near the leading edge, preventing excessive cooling air concentration at the leading edge tip, and preventing severe gas backflow in film holes 5 away from the blade tip 7, thereby avoiding poor leading edge film cooling. Because the suction side 2 of the blade generally bears a higher heat load, the third impact chamber 19 and the fourth impact chamber 22 are each equipped with two rows of spoiler columns 30. The sixth impact chamber 17 and the seventh impact chamber 23 are each provided with a row of spoiler columns 30. The eighth impact chamber 24 is provided with four rows of spoiler columns 30 on the suction side and three rows of spoiler columns 30 on the pressure side. The spoiler columns 30 not only improve the structural strength of the double-walled blade, but also increase the heat exchange area within the impact chamber, strengthen the convective heat transfer inside the blade, and improve the convective heat transfer coefficient. The cross-section of the spoiler columns 30 is circular, elliptical, or other shapes. Adding spoiler columns 30 can enhance the disturbance of the cold air, further expand the heat exchange area, and improve the utilization efficiency of the cold air.

[0027] The impact holes 29 on the second impact chamber 13 and the spoiler 30 disposed therein on the right end are arranged alternately; the impact holes 29 on the third impact chamber 19 and the spoiler 30 disposed therein on the right end are arranged alternately; the impact holes 29 on the fourth impact chamber 22 and the spoiler 30 disposed therein on the right end are arranged alternately; the impact holes 29 on the fifth impact chamber 11 and the spoiler 30 disposed therein on the right end are arranged alternately; the impact holes 29 on the sixth impact chamber 17 and the spoiler 30 disposed therein are arranged alternately; the impact holes 29 on the seventh impact chamber 23 and the spoiler 30 disposed therein are arranged alternately; and the impact holes 29 disposed near the suction side 2 of the eighth impact chamber 24 and the leftmost row of spoiler 30 of the corresponding four rows of spoiler 30 are arranged alternately, and the impact holes 29 disposed near the pressure side 3 of the eighth impact chamber 24 and the leftmost row of spoiler 30 of the corresponding three rows of spoiler 30 are arranged alternately. By arranging spoiler 30 between the impact holes 29, the influence of cross flow on the downstream impingement jet can be effectively reduced. This configuration helps suppress the expansion of the cross flow, thereby ensuring that the cooling effect of each set of impinging jets remains at a high level.

[0028] The plurality of impact holes 29 and the plurality of air film holes 5 provided on the first impact cavity 10 are alternately arranged in the span direction of the blade; the second impact cavity 13, the third impact cavity 19 and the fourth impact cavity 22 are provided with an exhaust film hole 5 on the corresponding blade suction side 2 along the span direction of the blade; the fifth impact cavity 11, the sixth impact cavity 17 and the seventh impact cavity 23 are provided with an exhaust film hole 5 on the corresponding blade pressure side 3 along the span direction of the blade.

[0029] The eighth impact cavity 24 is provided with four air film holes 5 distributed in a matrix at a position near the blade top 7 on the blade pressure side 3; the eighth impact cavity 24 is provided with a row of air film holes 5 arranged along the span direction on the blade suction side 2, and a row of air film holes 5 arranged along the span direction is provided at the end of the blade trailing edge 4 area on the blade suction side 2 away from the blade top 7.

[0030] The cold air cavity includes a first cold air cavity 12, a second cold air cavity 15, a third cold air cavity 16, a fourth cold air cavity 20, a fifth cold air cavity 14, a sixth cold air cavity 18, a seventh cold air cavity 21 and an eighth cold air cavity 25. The first cold air cavity 12 is arranged at the leading edge 1 of the blade (such as Figure 4 The left end shown in FIG), provides cold air for leading edge cooling; the eighth cold air cavity 25 is provided at the position of the trailing edge 4 of the blade (as shown in FIG). Figure 4 right end as shown); the second cold air cavity 15, the third cold air cavity 16 and the fourth cold air cavity 20 are arranged on the suction side 2 of the blade and are located between the first cold air cavity 12 and the eighth cold air cavity 25; the fifth cold air cavity 14, the sixth cold air cavity 18 and the seventh cold air cavity 21 are arranged on the pressure side 3 of the blade, between the first cold air cavity 12 and the eighth cold air cavity 25, on the opposite side of the second cold air cavity 15, the third cold air cavity 16 and the fourth cold air cavity 20; the eighth cold air cavity 25 is in the middle of the Y-shaped fork of the eighth impact cavity 24; the contour shape formed by the several cold air cavities is similar to the shape of the blade.

[0031] The eight cooling cavities correspond to independent impact chambers, ensuring a reasonable distribution of cooling air between the suction and pressure sides, preventing excessive concentration of cooling air on the suction side. The cooling cavities are connected to the impact chambers via impact holes in the inner wall of the blade. The cooling air in the cooling cavities enters the impact chambers through the impact holes and is then sprayed onto the inner surface of the blade outer wall 28, creating impact cooling. Each cooling cavity is connected to the impact chamber with the same sequence number: the first cooling cavity 12 is connected to the first impact chamber 10, the second cooling cavity 15 is connected to the second impact chamber 13, the third cooling cavity 16 is connected to the third impact chamber 19, the fourth cooling cavity 20 is connected to the fourth impact chamber 22, the fifth cooling cavity 14 is connected to the fifth impact chamber 11, the sixth cooling cavity 18 is connected to the sixth impact chamber 17, the seventh cooling cavity 21 is connected to the seventh impact chamber 23, and the eighth cooling cavity 25 is connected to the eighth impact chamber 24.

[0032] A semi-slit structure is provided at the blade trailing edge 4, communicating with the trailing end of the Y-shaped structure of the eighth impingement cavity 24. This structure provides film cooling for the trailing edge, which bears a high heat load. Trailing edge spoilers 26 are positioned upstream of the slit to increase turbulence and heat exchange area, effectively boosting the heat exchange capacity of the internally cooled slit, significantly reducing blade wall temperature and enhancing thermal protection. The semi-slit structure includes a trailing edge slit 9, which is provided with a plurality of partition ribs 8. The partition ribs 8 can improve the stability of the trailing edge. In addition, a plurality of trailing edge spoiler columns 26 are provided upstream of the corresponding semi-slit structure within the eighth impact cavity 24, which helps to strengthen the flow and heat exchange in the trailing edge area. This not only promotes the formation and stability of the air film and prevents high-temperature ablation and fracture of the trailing edge under extremely high thermal loads, but also enhances the rigidity of the trailing edge, improves the structural strength of the blade, and enhances its stability under high-load conditions. The plurality of trailing edge spoiler columns 26 can not only improve the heat exchange capacity of the trailing edge and reduce the temperature of the blade wall, but also further enhance the stability of the trailing edge. The width and length of the trailing edge slit 9 and the position and number of the trailing edge spoiler columns 26 can be matched according to different working environments during design.

[0033] The blade tip 7 and the outer wall 28 of the blade form a groove structure, with the blade tip 7 serving as the bottom of the groove structure. The blade tip 7 is provided with a plurality of dust removal holes 6, which communicate with the cooling air cavity. The grooved blade tip 7 significantly reduces aerodynamic losses and improves aerodynamic efficiency by reducing the leakage of high-temperature combustion gas through the gaps in the blade tip 7. At the same time, cooling air from the cooling cavity within the blade passes through the dust removal holes 6 in the blade tip 7, creating an air film covering the surface of the blade tip 7, reducing the heat load on the blade tip 7 surface, optimizing the cooling effect, and extending the service life of the blade.

[0034] The specific working process of the multi-chamber blade plate cooling structure for air-cooled turbines described in the present invention is as follows: The cooling air introduced by the compressor enters the cooling air cavity through the blade root. The first part, such as Figure 3 、 Figure 7 and Figure 8 As shown, the cold air directly passes through the cold air cavity and enters the groove of the blade top from the dust removal hole 6 on the blade top to form air film cooling; the second part, as shown Figure 6 As shown, the cold air enters the impact cavity from the cold air cavity through the impact hole 29 on the inner wall of the blade, and is ejected to impact the inner surface of the outer wall of the blade, forming impact cooling, and then passes through the spoiler column 30 to enhance heat exchange, and finally flows through the air film hole 5 on the outer wall of the blade to the blade surface and merges into the mainstream, forming air film covering cooling. The arrow in the figure is the schematic direction of the cold air flow; the third part, such as Figure 5 As shown, after the impact cooling is completed, the cold air in the eighth impact cavity 24 enters the trailing edge along the cooling channel of the impact cavity, passes through the trailing edge spoiler column 26 to enhance heat exchange, and flows out directly from the trailing edge slit 9, forming an air film at the trailing edge to cool and protect the blade.

[0035] The cooling structure proposed in this embodiment utilizes multiple cooling cavities on the suction and pressure sides to distribute cooling air based on design requirements. This cooling structure utilizes a super-cooling structure that combines internal impingement cooling, turbulent cooling, external film cooling, and trailing edge semi-slit cooling. This improves overall heat exchange efficiency and significantly reduces temperatures, while maintaining structural strength and extending blade life.

[0036] Those skilled in the art should understand that the dust removal hole 6 is named because it can remove dust under the action of the centrifugal force of the working blade. In view of this, in general, at least one dust removal hole needs to be arranged on the top of the turbine blade. It should be noted that this application uses the turbine engine blade for discussion, so there are blade tops and dust removal holes. However, the scope of application of this application is not limited to turbine blades, but is also applicable to turbine guide vanes. The concept of blade top dust removal holes will not be involved in the guide vanes, but this does not affect the scope of rights to be protected in this application.

[0037] Summarizing the above implementation cases, the multi-chambered blade plate cooling structure for air-cooled turbines described in the present invention achieves efficient temperature control by dividing the interior of the turbine blade into multiple cooling chambers and rationally distributing the cooling airflow on the suction and pressure sides. This avoids thermal stress concentration and blade overheating damage, thereby improving the service life and structural reliability of the blades, while reducing cooling air consumption and optimizing the overall thermal efficiency and performance stability of the engine. The multi-chambered blade plate cooling structure for air-cooled turbines described in the present invention effectively breaks up the cold air flow by arranging dense spoiler columns 30 on the leading edge 1 of the blade, promoting uniform distribution of the cold air along the blade height in the leading edge region, avoiding excessive concentration of the cooling airflow at the blade tip, and enhancing the turbulence intensity of the cold air, thereby improving the convective heat exchange effect between the airflow and the inner wall of the blade, thereby improving cooling efficiency, especially improving the cooling performance of the leading edge high heat load area, uniformizing the blade temperature distribution, reducing the risk of thermal gradient and thermal stress concentration, and significantly improving the service life and reliability of the blades.

[0038] The specific embodiments described above further illustrate the objectives, technical solutions, and beneficial effects of the present invention. It should be understood that the above description is merely a specific embodiment of the present invention and is not intended to limit the invention. Reasonable combinations of the features described in the above embodiments are also possible. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention shall be included in the scope of protection of the present invention.

Claims

1. A multi-chamber blade plate cooling structure for an air-cooled turbine, characterized by: The blade comprises a blade top (7), a blade inner wall (27) and a blade outer wall (28), wherein the blade top (7) is provided at one end of the blade outer wall (28) in the span direction; the blade inner wall (27) is provided inside the blade outer wall (28); a plurality of impact cavities are provided between the blade outer wall (28) and the blade inner wall (27); a plurality of cold air cavities are provided inside the blade inner wall (27); the impact cavities and the cold air cavities correspond to each other one by one and are connected through the impact hole (29); and the impact cavity is connected to the outer side of the blade outer wall (28) through a plurality of air film holes (5).

2. The multi-chamber blade plate cooling structure for an air-cooled turbine according to claim 1, characterized in that: The impact chamber comprises a first impact chamber (10), a second impact chamber (13), a third impact chamber (19), a fourth impact chamber (22), a fifth impact chamber (11), a sixth impact chamber (17), a seventh impact chamber (23) and an eighth impact chamber (24); the first impact chamber (10) is arranged at the leading edge (1) of the blade, the eighth impact chamber (24) is arranged at the trailing edge (4) of the blade, the second impact chamber (13), the third impact chamber (19) and the fourth impact chamber (22) are arranged on the suction side (2) of the blade, and the fifth impact chamber (11), the sixth impact chamber (17) and the seventh impact chamber (23) are arranged on the pressure side (3) of the blade; and a plurality of interfering flow columns (30) are arranged in the second impact chamber (13), the third impact chamber (19), the fourth impact chamber (22), the fifth impact chamber (11), the sixth impact chamber (17), the seventh impact chamber (23) and the eighth impact chamber (24).

3. The multi-chamber blade plate cooling structure for an air-cooled turbine according to claim 2, characterized in that: The plurality of impact holes (29) and the plurality of air film holes (5) provided on the first impact cavity (10) are alternately arranged in the span direction of the blade.

4. The multi-chamber blade plate cooling structure for an air-cooled turbine according to claim 2, characterized in that: The eighth impact cavity (24) is provided with four air film holes (5) distributed in a matrix at a position close to the blade tip (7) on the blade pressure side (3), and a plurality of air film holes (5) are provided on the blade suction side (2).

5. The multi-chamber blade plate cooling structure for an air-cooled turbine according to claim 2, characterized in that: The cold air cavity comprises a first cold air cavity (12), a second cold air cavity (15), a third cold air cavity (16), a fourth cold air cavity (20), a fifth cold air cavity (14), a sixth cold air cavity (18), a seventh cold air cavity (21) and an eighth cold air cavity (25). The first cold air cavity (12) is arranged at the leading edge (1) of the blade, the eighth cold air cavity (25) is arranged at the trailing edge (4) of the blade, the second cold air cavity (15), the third cold air cavity (16) and the fourth cold air cavity (20) are arranged at the suction side (2) of the blade, and the fifth cold air cavity (14), the sixth cold air cavity (18) and the seventh cold air cavity (21) are arranged at the pressure side (3) of the blade; the cold air cavities are respectively connected to the impact cavities of the same serial number.

6. The multi-chamber blade plate cooling structure for an air-cooled turbine according to claim 2, characterized in that: A semi-slit structure is provided at the trailing edge (4) of the blade, and the semi-slit structure is connected to the eighth impact cavity (24).

7. The multi-chamber blade plate cooling structure for an air-cooled turbine according to claim 6, characterized in that: The semi-split structure comprises a trailing edge split (9), and a plurality of partition ribs (8) are provided on the trailing edge split (9).

8. The multi-chamber blade plate cooling structure for an air-cooled turbine according to claim 6 or 7, characterized in that: A plurality of trailing edge spoiler columns (26) are provided upstream of the half-slit structure.

9. The multi-chamber blade plate cooling structure for an air-cooled turbine according to claim 1, characterized in that: The blade tip (7) and the blade outer wall (28) form a groove structure, and the blade tip (7) is the groove bottom of the groove structure.

10. The multi-chamber blade plate cooling structure for an air-cooled turbine according to claim 9, characterized in that: A plurality of dust removal holes (6) are provided on the blade top (7), and the dust removal holes (6) are communicated with the cold air cavity.

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