A perforated ribbed cooling structure and turbine blades thereof

Abstract

This invention discloses a perforated ribbed cooling structure and a turbine blade constructed therefrom. The novel perforated ribbed cooling structure includes ribs with a plurality of cooling holes formed on them. The length direction of the ribs forms a certain angle with the cooling flow direction. The turbine blade includes an outer surface, film cooling holes, impact holes, and a turbulence column array. The outer surface of the blade has the mid-section airfoil of an E3 blade. This invention enhances heat transfer on the blade surface and ensures a uniform temperature distribution, thereby guaranteeing normal operation of the turbine blade and extending its service life.

Description

Technical Field

[0001] This invention relates to the field of internal cooling structure technology for turbine blades, specifically to a perforated ribbed cooling structure and a turbine blade made therefrom. Background Technology

[0002] In recent years, many scholars have conducted research on finned cooling, including fin shape, angle, fin spacing, and height ratio. The principle of finned cooling to enhance heat transfer is the separation and reattachment of the cold fluid. When the cooling fluid flows through the upstream fin, it first impacts the area near the upper wall of the fin, thereby enhancing heat transfer. After flowing through the upstream fin, cooling flow separation occurs downstream of the fin, and then reattachment occurs upstream of the downstream fin, thus enhancing the heat transfer effect upstream of the downstream fin. Although the arrangement of the finned cooling structure can enhance the heat transfer effect near the leading edges of the upstream and downstream fins, backflow occurs at the trailing edge of the upstream fin, weakening heat transfer in that area and resulting in poor cooling performance in that region.

[0003] For real turbine blades, considering the difficulty of blade manufacturing and blade strength issues, a relatively simple internal cooling structure is usually used to reduce the surface temperature of the blade. For example, CN111271133A discloses a turbine guide vane with a straight-rib internal cooling structure, which divides the internal cooling chamber into three cooling channels to form a serpentine cooling channel. Several straight ribs are arranged in the cooling channel perpendicular to the cooling flow direction. The cold airflow flows in from the first cooling channel, flows along the ribbed serpentine channel, and finally flows out from the trailing edge slit. Although turbine guide vanes with straight-rib internal cooling channels can increase the heat exchange area, enhance the turbulence of the cooling flow, and improve the heat exchange efficiency, straight ribs are the most basic rib cooling structure. Currently, optimization has been carried out on parameters such as rib shape and angle, and structures such as oblique ribs, V-ribs, and W-ribs have emerged. Oblique ribs have been applied to the internal cooling structure of real turbine blades. In addition, this patent does not consider the cooling of the high-temperature region at the leading edge and the trailing edge. The leading edge region is most severely eroded by the high-temperature airflow and requires more effective cooling technology. The trailing edge region also needs a turbulence column cooling structure to reduce the temperature in this area. CN111271133A discloses an intermittent rib cooling structure for internal cooling channels of turbine blades. Each row of intermittent ribs consists of intermittent ribs and intermittent regions. Along the flow direction of the cooling flow, the number of intermittent ribs and intermittent regions in each row of intermittent ribs gradually increases. This intermittent rib cooling structure has a stronger disturbance effect on the airflow. However, when the number of intermittent ribs and intermittent regions in the front row is small, the low heat transfer area at the trailing edge of the ribs cannot be uniformly strengthened. When the number of intermittent ribs and intermittent regions is large, the low heat transfer area at the trailing edge of the ribs can be uniformly strengthened, but the strength of the rib structure will be weakened. Summary of the Invention

[0004] In order to overcome the above technical problems, the purpose of this invention is to provide a perforated ribbed cooling structure and a turbine blade made therefrom;

[0005] The first objective of this invention is to provide a novel perforated ribbed cooling structure. When the cooling flow passes through the perforated ribbed rib, a small portion of the fluid enters the cooling holes on the ribbed rib and then flows out from the cooling holes at the rear edge of the ribbed rib, impacting the wall surface of the internal channel. This greatly enhances the disturbance effect of the wall surface flow field, destroys the backflow area at the rear edge of the rib, thereby achieving the effect of enhanced heat transfer and making up for the deficiency of heat transfer weakened by backflow at the rear edge of existing ribs.

[0006] The second objective of this invention is to provide a turbine blade structure with a complex internal cooling structure and film cooling coupled heat transfer. This structure not only arranges a novel perforated rib cooling structure in the internal cooling channels of the suction and pressure surfaces in the middle of the blade, but also arranges an impact and film cooling coupled heat transfer structure in the high-temperature region of the blade leading edge, and a forked baffle cooling structure in the internal cooling channels of the blade trailing edge. The cooling methods from the leading edge to the trailing edge of this turbine blade structure are all designed in a relatively complete manner, and can be used in the design of real turbine blades. This invention can enhance heat transfer on the blade surface and make the blade surface temperature distribution uniform, thereby ensuring the normal operation of the turbine blade and extending its service life.

[0007] To achieve the above objectives, the technical solution adopted by the present invention is as follows:

[0008] A perforated oblique rib cooling structure includes oblique ribs 100, on which a plurality of cooling hole structures 101 are formed, and the length direction of the oblique ribs 100 is at a certain angle to the cooling flow direction.

[0009] The cross-section of the oblique rib 100 is square, the rib height H is the same as the rib width e, and the ratio of the rib spacing P to the rib width e ranges from 7 to 15.

[0010] The cooling hole structure 101 is a circular hole structure with the same spacing on the inclined rib 100. The inlet circular hole section 102 of the cooling hole structure 101 is tangent to the upper section 103 of the front edge of the inclined rib 100, and the outlet circular hole section 104 is tangent to the lower section 105 of the rear edge of the inclined rib 100. The diameter D of the inlet circular hole section 102 and the outlet circular hole section 104 is the same and the diameter is less than half of the height H of the inclined rib 100. The flow direction of the cooling hole structure 101 is the same as the flow direction of the cooling flow, and the center line of the hole forms a certain angle with the flow direction of the cooling flow. The angle value depends on the rib height H and the diameter D of the cooling hole.

[0011] A turbine blade includes an outer surface 106, film cooling holes 113, impact holes 114, and a baffle column 115, wherein the outer surface 106 is an E3 blade with a mid-section airfoil.

[0012] The blade contains six internal cooling channels, namely the first cooling channel 107, the second cooling channel 108, the third cooling channel 109, the fourth cooling channel 110, the fifth cooling channel 111 and the sixth cooling channel 112, which are arranged in sequence.

[0013] The first cooling channel 107 is located at the leading edge of the blade, the second cooling channel 108 is adjacent to the first cooling channel 107, the third cooling channel 109, the fourth cooling channel 110, and the fifth cooling channel 111 form a serpentine cooling channel, located in the middle of the blade, adjacent to the second cooling channel 108, and the sixth cooling channel 112 is located at the trailing edge of the blade, connecting to the trailing edge slotted structure 116 on the outer surface 106 of the blade.

[0014] The air film holes 113 are in two rows, equally spaced. The first row is located at the leading edge of the outer surface 106 of the blade, and the second row is located on the pressure surface of the blade corresponding to the fourth cooling channel 110.

[0015] The impact holes 114 are connected to the first cooling channel 107 and the second cooling channel 108, and are distributed at equal intervals.

[0016] The turbulence column array 115 is located in the sixth cooling channel 112, and is distributed in a crisscross pattern, connecting to the trailing edge split 116.

[0017] The perforated rib cooling structure is provided in any one or more internal cooling channels.

[0018] In a single internal cooling channel, the perforated rib cooling structure is arranged at a 45-degree angle to the cooling flow direction. It is located on the suction and pressure sides of the internal cooling channel and is evenly distributed on one side. The number of ribs is determined by the rib spacing and the length of the cooling channel. The perforated rib cooling structures on the suction and pressure sides are staggered. The cooling hole structure 101 is evenly distributed on the perforated ribs. Its flow direction is the same as the cooling flow direction, and the center line of the hole is at a certain angle to the cooling flow direction. The angle value depends on the rib height H and the diameter D of the cooling hole.

[0019] The cooling flow is divided into three streams, flowing into the turbine blade from the second cooling channel 108, the fifth cooling channel 111, and the sixth cooling channel 112. The first stream flows into the second cooling channel 108, and after being turbulent by the new perforated rib cooling structure, it flows into the first cooling channel 107 through the impact hole 114. Then, part of the cooling flow flows out from the leading edge film cooling hole 113 of the blade, covering the blade surface and forming a heat-insulating film. The remaining cooling flow flows out from the tip circular hole of the blade. The second stream flows into the serpentine channel through the fifth cooling channel 111. After being turbulent by the perforated rib cooling structure, part of the airflow flows through the fourth cooling channel 110 and flows out from the film cooling hole 113 on the pressure surface of the blade. The remaining airflow flows out from the tip circular hole of the third cooling channel 109. The third stream flows into the sixth cooling channel 112, and after being turbulent by the turbulence column 115, it flows out from the trailing edge slotted cooling structure 116.

[0020] The beneficial effects of this invention are:

[0021] 1. The perforated rib cooling structure of the present invention is a rib structure with equidistant cooling holes on the rib. When the cooling flow passes through the perforated rib, a small portion of the fluid will enter the cooling holes on the rib and then flow out from the cooling holes at the rear edge of the rib, impacting the wall surface of the internal channel. This greatly enhances the disturbance effect of the wall flow field and destroys the backflow area at the rear edge of the rib, thereby achieving the effect of enhanced heat transfer and making up for the deficiency of heat transfer weakened by backflow at the rear edge of the existing rib.

[0022] 2. The turbine blade of this invention has several perforated oblique rib cooling structures evenly spaced on the wall of the internal cooling channel, with the perforated oblique rib structures on the suction and pressure surfaces of the blade arranged alternately. The angle between the perforated oblique rib cooling structure and the cooling flow direction is 45 degrees, and the direction of the cooling holes is the same as the cooling flow direction. When the cooling flow flows into the internal cooling channel, each perforated oblique rib structure on the wall will cause disturbance to the fluid. Compared with the traditional fin cooling structure, the cooling hole structure on the fin will destroy the backflow area generated at the trailing edge of the fin, so the heat transfer of the internal channel wall near the trailing edge of each fin is enhanced, thereby greatly improving the uniformity of the wall cooling effect. In addition, the leading edge of the blade is most severely eroded by the mainstream gas. Therefore, film cooling holes are arranged at the leading edge of the blade and impact holes are arranged between the first and second channels. The coupling effect of film cooling and impact cooling will cause the cooling flow to flow out from the film cooling holes at the leading edge of the blade, covering the blade surface and forming a heat-insulating film, thereby protecting the leading edge surface of the blade from erosion by the mainstream high-temperature gas. In addition, the blade pressure surface is also affected by the high-temperature mainstream. Therefore, film cooling holes are arranged at the fourth cooling channel of the blade pressure surface. After the cooling flow is turbulent by the internal perforated ribs, it flows out from the film cooling holes on the pressure surface, covering the blade surface and forming a heat-insulating film, thereby protecting the blade pressure surface from erosion by the mainstream high-temperature gas. Finally, the third cooling flow flows into the sixth cooling channel, and after being turbulent by the turbulence columns, it flows out from the trailing edge slotted cooling structure, enhancing the heat transfer effect at the blade trailing edge. This invention provides a turbine blade structure with a complex internal cooling structure and film cooling coupled heat transfer. This structure not only arranges a novel perforated rib cooling structure in the internal cooling channels of the suction and pressure surfaces in the middle of the blade, but also arranges an impact and film cooling coupled heat transfer structure in the high-temperature region of the blade leading edge, and a forked turbulence column cooling structure in the internal cooling channel of the blade trailing edge. The cooling methods from the leading edge to the trailing edge of the turbine blade structure of this invention are all designed and are relatively complete. It can be used in the design of real turbine blades, which enhances the heat transfer on the blade surface and makes the blade surface temperature distribution uniform, thereby ensuring the normal operation of the turbine blade and extending its service life. Attached image description:

[0023] Figure 1 This is a three-dimensional structural schematic diagram of a perforated oblique rib cooling structure according to the present invention.

[0024] Figure 2 This is a partially enlarged top view of a perforated oblique rib cooling structure according to the present invention.

[0025] Figure 3 This is a side view of a perforated oblique rib cooling structure according to the present invention.

[0026] Figure 4 This is a top view of a turbine blade according to the present invention.

[0027] Figure 5This is a three-dimensional schematic diagram of the arrangement of the internal cooling structure of the turbine blades of the present invention.

[0028] Figure 6 This is a side view of a turbine blade according to the present invention.

[0029] Figure 7 This is an enlarged view of a partial area in the side view of the present invention. Attached image description:

[0031] Novel perforated rib cooling structure; 100-rib; 101-cooling hole; 102-cooling hole inlet section; 103-upper section of the leading edge of the rib; 104-cooling hole outlet section; 105-lower section of the trailing edge of the rib; 106-outer surface of the blade; 107-first internal cooling channel; 108-second internal cooling channel; 109-third internal cooling channel; 110-fourth internal cooling channel; 111-fifth internal cooling channel; 112-sixth internal cooling channel; 113-film cooling hole; 114-impact hole; 115-turbulence column array; 116-tail edge slit. Detailed Implementation

[0032] The present invention will be further described in detail below with reference to the embodiments.

[0033] Example 1:

[0034] like Figure 1 The figure shows a three-dimensional structural schematic diagram of a novel perforated rib cooling structure for internal cooling channels of turbine blades provided by an embodiment of the present invention. As shown in the figure, the perforated rib cooling structure of this embodiment includes ribs 100 and cooling hole structures 101 opened on the ribs.

[0035] Specifically, finned cooling is currently the most commonly used internal cooling technology within the cooling channels of turbine blades. This technology enhances heat transfer by increasing the turbulence of the cooling flow within the internal channels and simultaneously increasing the heat transfer area. The 100° angled fin refers to the fin being at a certain angle to the cooling flow direction. The fin height H is the same as the fin width e, and the ratio of the fin spacing P to the fin width e is within the range of 10.

[0036] like Figure 2 , Figure 3 As shown, Figure 2 This is a partially enlarged top view of an embodiment of the present invention. Figure 3 This is a side view of an embodiment of the present invention. In this embodiment, the angle between the oblique ribs and the cooling flow direction is 45 degrees, the rib height is 0.335 mm, the ratio of rib spacing to rib height is 10, and the oblique ribs are evenly distributed. It is worth noting that the above values ​​are only for this embodiment. The angle of the oblique ribs, the rib height, and the ratio of rib spacing to rib height need to be set according to the size of the cooling channel of the turbine blades, and are not unique.

[0037] Furthermore, conventional finned cooling structures often create a backflow region at the trailing edge of the fins, thus weakening heat transfer in that area. To compensate for the shortcomings of conventional fins, this embodiment of the invention features cooling holes of equal spacing on the perforated fins. When the cooling flow passes through the perforated fins, a small portion of the fluid enters the cooling holes on the fins and then flows out from the cooling holes at the trailing edge of the fins, impacting the wall surface of the internal channel. This significantly enhances the disturbance of the wall flow field, disrupting the backflow region at the trailing edge of the fins, thereby achieving a stronger heat transfer effect. Figure 2 , Figure 3 As shown, Figure 2 This is a partially enlarged top view of an embodiment of the present invention. Figure 3 This is a side view of an embodiment of the present invention. In this embodiment, the inlet section 102 of the cooling hole structure 101 is tangent to the upper section 103 of the leading edge of the inclined rib, and the outlet section 104 is tangent to the lower section 105 of the trailing edge of the inclined rib. The diameter D of the cooling hole structure 101 is 0.15 mm, and five cooling holes are evenly distributed along the rib direction. The distance L between two cooling holes is 1 mm, and the direction of the cooling hole structure 101 is the same as the cooling flow direction. It is worth noting that the above values ​​are only for this embodiment. The radius, number, and spacing of the cooling holes need to be set according to the size of the inclined rib and are not unique.

[0038] Example 2:

[0039] This embodiment provides a turbine blade, such as Figures 4-7 , Figure 4 This is a top view of a turbine blade provided in an embodiment of the present invention. Figure 5 This is a three-dimensional schematic diagram of the internal cooling structure arrangement of the turbine blades provided in an embodiment of the present invention. Figure 6 This is a side view of a turbine blade; Figure 7 This is an enlarged view of a partial area in a side view of an embodiment of the present invention.

[0040] As shown in the figure, the turbine blade of this embodiment includes an outer blade surface 106, internal cooling channels 107-112, and several novel perforated rib cooling structures, film cooling holes 113, impact holes 114, a turbulence column array 115, and a trailing edge slit 116. The blade profile of the outer blade surface 106 is derived from the mid-section profile of the E3 blade. The turbine blade includes six internal cooling channels 107-112 and a trailing edge slit structure 116; the third, fourth, and fifth cooling channels 109-111 form a serpentine cooling channel.

[0041] like Figure 6As indicated by the flow arrows, the cooling flow is divided into three streams, flowing into the turbine blade from the second cooling channel 108, the fifth cooling channel 111, and the sixth cooling channel 112. The first stream flows into the second cooling channel 108, and after being turbulent by the novel perforated rib cooling structure, it flows into the first cooling channel 107 through the impact hole 114. Afterward, part of the cooling flow flows out from the leading edge film cooling hole 113, covering the blade surface and forming a heat-insulating film, while the remaining cooling flow flows out from the tip circular hole of the blade. The second stream flows into the serpentine channel through the fifth cooling channel 111, and after being turbulent by the novel perforated rib cooling structure, part of the airflow flows through the fourth cooling channel 110 and then flows out from the film cooling hole 113 on the blade pressure surface, while the remaining airflow flows out from the tip circular hole of the third cooling channel 109. The third stream flows into the sixth cooling channel 112, and after being turbulent by the turbulence column 115, it flows out from the trailing edge slotted cooling structure 116.

[0042] Specifically, such as Figures 4-7 The perforated rib cooling structure is located in the internal cooling channels 107-112 of the turbine blade. Several perforated rib cooling structures are distributed at equal intervals, and the perforated rib cooling structures on the suction surface and the pressure surface are arranged alternately. The angle between the perforated rib cooling structure and the cooling flow direction is 45 degrees, and the direction of the cooling hole structure 101 is the same as the cooling flow direction.

[0043] The rib height of the diagonal rib is 0.335 mm, and the ratio of rib spacing to rib height is 10. Specifically, in the second cooling channel 108, 17 perforated diagonal rib cooling structures are arranged on the pressure surface, and 18 perforated diagonal rib cooling structures are arranged on the suction surface, with 3 cooling hole structures 101 evenly spaced on each perforated diagonal rib cooling structure; in the third and fourth cooling channels 109, 17 perforated diagonal rib cooling structures are arranged on both the suction and pressure surfaces, with 5 cooling hole structures 101 evenly spaced on each perforated diagonal rib cooling structure; in the fifth cooling channel 111, 16 perforated diagonal rib cooling structures are arranged on the pressure surface, with 9 cooling hole structures 101 evenly spaced on each perforated diagonal rib, and 14 perforated diagonal rib cooling structures are arranged on the suction surface, with 13 cooling hole structures 101 evenly spaced on each perforated diagonal rib.

[0044] The film cooling holes 113 have two rows. The first row is located at the leading edge of the blade, with 10 film cooling holes per row, evenly spaced, with a hole spacing of 3.1 mm and a hole diameter of 0.36 mm. The second row is located on the pressure surface of the fourth cooling channel of the blade, with 18 film cooling holes per row, evenly spaced, with a hole spacing of 3.35 mm and a hole diameter of 0.36 mm.

[0045] The impact holes 114 connect the first cooling channel 107 and the second cooling channel 108. There are 9 impact holes 114 in each row, which are evenly distributed with a hole spacing of 6.7 mm and a hole diameter of 0.84 mm.

[0046] The turbulence column array 115 is located in the sixth cooling channel of the blade, with a total of 5 rows, each row containing 25 / 26 columns in a staggered arrangement. The diameter of the turbulence column cross-section is 0.4 mm, the flow direction spacing is 1 mm, and the spanwise spacing is 1.2 mm. The turbulence column array connects to the trailing edge slits 116, and 41 slit structures are arranged on the trailing edge.

[0047] The above values ​​are only for this implementation case. The spacing, number, arrangement, and position of the perforated rib cooling structure, film cooling holes 113, impact holes 114, and turbulence column array 115 in the internal cooling channel need to be set according to the size of the turbine blade cooling channel, and are not unique.

[0048] In this embodiment, during turbine blade operation, when the cooling flow flows into the internal cooling channel, each perforated oblique rib structure on the wall surface turbules the fluid. Compared to traditional rib cooling structures, the cooling hole structure on the rib disrupts the backflow area generated at the trailing edge of the rib, thus enhancing the heat transfer of the internal channel wall near the trailing edge of each rib and greatly improving the uniformity of the cooling effect on the wall surface. Furthermore, the leading edge of the blade is most severely eroded by the mainstream gas. Therefore, film cooling holes are arranged at the leading edge of the blade, and impingement holes are arranged between the first and second channels. The coupling effect of film cooling and impingement cooling causes the cooling flow to exit from the film cooling holes at the leading edge of the blade, covering the blade surface and forming a heat-insulating film, thereby protecting the leading edge surface from erosion by the high-temperature mainstream gas. Additionally, the blade pressure surface is also affected by the high-temperature mainstream gas. Therefore, film cooling holes are arranged at the fourth cooling channel on the blade pressure surface. After being turbulent by the internal perforated oblique ribs, the cooling flow exits from the film cooling holes on the pressure surface, covering the blade surface and forming a heat-insulating film, thereby protecting the blade pressure surface from erosion by the high-temperature mainstream gas. Finally, the third cooling stream flows into the sixth cooling channel, and after being turbulent by the turbulence column, it flows out from the trailing edge slit cooling structure, enhancing the heat exchange effect at the trailing edge of the blade, ensuring the normal operation of the turbine blade, and extending its service life.

Claims

1. A turbine blade with a perforated oblique rib cooling structure, characterized in that, It includes the outer surface of the blade (106), film vents (113), impact vents (114) and a turbulence column array (115), wherein the outer surface of the blade (106) is the mid-section air profile of the E3 blade; The blade contains six internal cooling channels, namely the first cooling channel (107), the second cooling channel (108), the third cooling channel (109), the fourth cooling channel (110), the fifth cooling channel (111), and the sixth cooling channel (112), which are arranged in sequence. The first cooling channel (107) is located at the leading edge of the blade, the second cooling channel (108) is adjacent to the first cooling channel (107), the third cooling channel (109), the fourth cooling channel (110), and the fifth cooling channel (111) form a serpentine cooling channel, located in the middle of the blade, adjacent to the second cooling channel (108), and the sixth cooling channel (112) is located at the trailing edge of the blade, connecting the trailing edge slit structure (116) of the outer surface (106) of the blade. The air film holes (113) are arranged in two rows at equal intervals. The first row is located at the leading edge of the outer surface (106) of the blade, and the second row is located on the pressure surface of the blade corresponding to the fourth cooling channel (110). The impact holes (114) are connected to the first cooling channel (107) and the second cooling channel (108) and are distributed at equal intervals; The turbulence column array (115) is located in the sixth cooling channel (112), and is distributed in a cross pattern, connecting the trailing edge split (116). The perforated rib cooling structure is provided in any one or more internal cooling channels; In a single internal cooling channel, the perforated rib cooling structure is arranged at an angle of 45 degrees to the cooling flow direction. It is arranged on the suction and pressure sides of the internal cooling channel and is equally spaced on one side. The number is determined by the rib spacing and the length of the cooling channel. At the same time, the perforated rib cooling structures on the suction and pressure sides are staggered. The cooling hole structure (101) is equally spaced on the perforated rib. Its flow direction is the same as the cooling flow direction, and the center line of the hole is at a certain angle to the cooling flow direction. The angle value depends on the rib height H and the diameter D of the cooling hole. A perforated rib cooling structure includes a rib (100) with a plurality of cooling holes (101) formed on the rib (100), and the length direction of the rib (100) is at a certain angle to the cooling flow direction. The cross section of the oblique rib (100) is square, the rib height H is the same as the rib width e, and the ratio of the rib spacing P to the rib width e is in the range of 7-15. The cooling hole structure (101) consists of circular holes with the same spacing on the inclined rib (100). The inlet section (102) of the cooling hole structure (101) is tangent to the upper section (103) of the leading edge of the inclined rib (100). The diameter D of the inlet circular hole section (102) and the outlet circular hole section (104) are the same and the diameter is less than half of the height H of the inclined rib (100). The flow direction of the cooling hole structure (101) is the same as the flow direction of the cooling flow, and the center line of the hole forms a certain angle with the flow direction of the cooling flow. The angle value depends on the rib height H and the diameter D of the cooling hole. When the cooling flow passes through the perforated ribs, a small portion of the fluid enters the cooling holes on the ribs and then flows out from the cooling holes at the rear edge of the ribs, impacting the wall of the internal channel, enhancing the disturbance of the wall flow field, and disrupting the backflow area at the rear edge of the ribs.

2. The turbine blade according to claim 1, characterized in that, The cooling flow is divided into three streams, flowing into the turbine blade from the second cooling channel (108), the fifth cooling channel (111), and the sixth cooling channel (112). The first stream flows into the second cooling channel (108), and after being turbulent by the new perforated rib cooling structure, it flows into the first cooling channel (107) through the impact hole (114). Then, part of the cooling flow flows out from the air film hole (113) at the leading edge of the blade, covering the blade surface and forming a heat-insulating air film. The remaining cooling flow flows out from the tip hole of the blade. The second stream flows into the serpentine channel through the fifth cooling channel (111), and after being turbulent by the perforated rib cooling structure, part of the airflow flows through the fourth cooling channel (110) and flows out from the air film hole (113) on the pressure surface of the blade. The remaining airflow flows out from the tip hole of the third cooling channel (109). The third stream flows into the sixth cooling channel (112), and after being turbulent by the turbulence column (115), it flows out from the trailing edge slotted cooling structure (116).

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