Turbine blade

Abstract

The present disclosure provides a turbine blade, relating to the field of turbine blades, comprising a blade body, the blade body being hollow inside, a plurality of first film holes being arranged at intervals on the trailing edge of the blade body; an end wall being arranged at the end of the blade body, a cold gas cavity being arranged on the end wall and being in communication with the inside of the blade body, the side of the cold gas cavity away from the blade body being open, a second film hole being arranged on the end wall and being in communication with the outside; an impact plate being arranged at the opening of the cold gas cavity, a plurality of first impact holes being arranged on the impact plate and being in communication with the cold gas cavity; a plurality of column ribs being arranged at intervals in the cold gas cavity, the column ribs being arranged along the radial direction of the blade body, and one end of the column rib close to the blade body being fixedly connected with the inner bottom wall of the cold gas cavity. The present disclosure has the effect of improving the impact cooling capacity of the end wall of the turbine blade.

Description

Technical Field

[0001] This disclosure relates to the technical field of turbine blades, and more particularly to turbine blades. Background Technology

[0002] With the development of technology, the inlet temperature of turbine blades is constantly increasing, and the inlet temperature has far exceeded the melting point of the blade material. In order to ensure the safe and reliable operation of the turbine, it is necessary to cool the turbine blades so that the temperature and stress distribution of the turbine blades can be kept reasonable.

[0003] The common cooling methods used for the end wall of the stator blade are impact cooling and film cooling. After the cold air flows in from the cold air hole of the impact plate, it impacts the end wall and flows into the film cooling hole of the end wall or the blade body, forming a film cooling on the end wall surface. However, the impact cooling downstream of the end wall is affected by the impact of the upstream cold air, which greatly weakens the effect of the impact cooling downstream of the end wall, so it needs to be improved. Summary of the Invention

[0004] In view of the above problems, this disclosure provides turbine blades to improve the poor impact cooling effect of turbine blade endwalls.

[0005] This disclosure provides a turbine blade, comprising: a blade body, the blade body being hollow inside, and a plurality of spaced-apart first film gas holes on the rear edge of the blade body; an end wall, disposed at the end of the blade body, the end wall having a cold air cavity communicating with the interior of the blade body, the side of the cold air cavity away from the blade body being open, and the end wall having a second film gas hole communicating with the outside; an impact plate, disposed at the opening of the cold air cavity, the impact plate having a plurality of first impact holes, the plurality of first impact holes being spaced-apart and all communicating with the cold air cavity; and a plurality of column ribs, the plurality of column ribs being spaced-apart within the cold air cavity, the column ribs being arranged radially along the blade body, and the end of the column rib near the blade body being fixedly connected to the inner bottom wall of the cold air cavity.

[0006] Optionally, the end of the column rib away from the blade is attached to the side of the impact plate near the blade, or the height of the column rib is not greater than half the distance between the bottom wall of the cold air chamber and the side of the impact plate near the blade.

[0007] Optionally, multiple first impact holes are arranged in a longitudinal and transverse manner, multiple column ribs are arranged in a longitudinal and transverse manner, and multiple rows of first impact holes and multiple rows of column ribs are spaced apart along the leading edge to the trailing edge of the blade, with one row of column ribs located between two adjacent rows of first impact holes.

[0008] Optionally, the number of column ribs in each column is not less than half the number of first impact holes in each column, and / or the diameter ratio of column ribs to first impact holes is (2-2.5):1.

[0009] Optionally, the front, middle and rear parts of the end wall are provided with a densification zone, and the arrangement density of the first impact hole in the densification zone is greater than the arrangement density of the first impact hole in the non-densification zone.

[0010] Optionally, the density of column ribs in the encrypted zone is greater than the density of column ribs in the unencrypted zone.

[0011] Optionally, the ratio of the diameter of the column rib in the encrypted zone to the diameter of the column rib in the unencrypted zone is 1:2 to 2:3.

[0012] Optionally, the second air film pores are arranged obliquely downwards from the leading edge to the trailing edge of the blade.

[0013] Optionally, the tail end of the end wall is provided with a tail cooling assembly for further cooling the tail end of the end wall.

[0014] Optionally, the tail cooling assembly includes: a baffle located at the rear edge of the cooling chamber, the baffle dividing the cooling chamber into a front cooling area and a tail cooling area, the first impact hole, the column rib, and the second film air hole all located in the front cooling area, the baffle having multiple spaced second impact holes, and the tail of the end wall having multiple third film air holes; and a baffle located at the tail of the end wall, with multiple baffles located in the tail cooling area, the multiple baffles and the multiple third film air holes being staggered.

[0015] The at least one technical solution used in the embodiments of this disclosure has at least the following beneficial effects:

[0016] The column ribs serve two purposes: firstly, they interfere with the lateral flow of cold air within the cooling chamber, disturbing the free flow of cold air, increasing the heat exchange area of ​​the end wall, extending the residence time of cold air within the cooling chamber, improving the enhanced heat exchange effect of the cold air, and effectively reducing the temperature of the end wall; secondly, they transform the lateral flow into a rotating vortex system, allowing the upstream cold air to bypass the downstream impact hole after impacting the end wall. This ensures that the downstream cold air is not affected by the lateral flow formed upstream when impacting the end wall, reducing the direct impact of the upstream lateral flow on the downstream cold air and improving the cooling effect of the downstream cold air impact.

[0017] By setting up a densification zone, the intensity of convection and impingement heat transfer in the leading edge, trailing edge, and throat area between two adjacent blades is enhanced, thereby reducing the temperature in the high heat load area of ​​the endwall and improving the stability of turbine blade operation.

[0018] By controlling the relative arrangement of the column ribs and impact holes, it is not only easier to process the product, but also to maximize the cooling effect of the cold air.

[0019] A tail cooling assembly is installed in the tail region of the end wall, and the tail impingement airflow is disturbed to enhance the heat exchange intensity in the tail region, thereby further cooling the end wall. Attached Figure Description

[0020] To gain a more complete understanding of this disclosure and its advantages, reference will now be made to the following description taken in conjunction with the accompanying drawings, wherein:

[0021] Figure 1 This schematic diagram illustrates a cross-sectional view of a turbine blade provided in an embodiment of the present disclosure.

[0022] Figure 2 This schematically illustrates a cross-sectional view of a turbine blade provided in an embodiment of the present disclosure from another perspective;

[0023] Figure 3 This schematically illustrates a cross-sectional view of the turbine blade endwall provided in an embodiment of the present disclosure.

[0024] Figure 4 A schematic top view of a turbine blade impact plate provided in an embodiment of this disclosure is shown.

[0025] Figure 5 This schematically illustrates a cross-sectional view of the turbine blade endwall provided in an embodiment of the present disclosure from another perspective;

[0026] Figure 6 Schematic illustration Figure 1 A schematic diagram showing the flow of intercooled air from the leading edge to the trailing edge of the end wall;

[0027] Figure 7 A schematic diagram illustrating the flow of cold air within the air conditioning chamber;

[0028] Figure 8 The diagram illustrates the flow of cold air in the cold air chamber when the column ribs and tail cooling assembly are missing.

[0029] [Explanation of Labels in the Attached Image]

[0030] 1-Blade body; 11-First film cooling hole; 2-End wall; 21-Cooling air chamber; 211-Front cooling area; 212-Tail cooling area; 22-Second vent; 23-Second film cooling hole; 24-Third film cooling hole; 3-Impact plate; 31-First impact hole; 32-First vent; 4-Column rib; 5-Tail cooling assembly; 51-Baffle; 511-Second impact hole; 52-Breakout block; 6-Reinforcing column;

[0031] 101-Forward transverse flow; 102-Reverse transverse flow; 103-Tail transverse flow; 104-Upstream transverse flow; 105-Downstream impinging flow; 106-Vortex;

[0032] F1 - Blade radial direction. Detailed Implementation

[0033] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to specific embodiments and the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this invention. All other embodiments obtained by those skilled in the art based on the embodiments of this invention without creative effort are within the scope of protection of this invention.

[0034] The terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the invention. The terms “comprising,” “including,” etc., as used herein indicate the presence of the stated features, steps, operations, and / or components, but do not exclude the presence or addition of one or more other features, steps, operations, or components.

[0035] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection, an electrical connection, or a connection that allows communication between them; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0036] Currently, the common cooling methods used for the endwall of stator blades are impact cooling and film cooling. After the cold air flows in through the cold air holes of the impact plate, it impacts the endwall and flows into the film cooling holes of the endwall or the blade body, forming a film cooling on the endwall surface. Usually, the impact plate and the endwall form a cold air chamber. After the cold air impacts the endwall through the impact holes on the impact plate upstream of the endwall, it flows in the cold air chamber to form a transverse flow (flowing from the leading edge to the trailing edge of the blade body). The transverse flow merges with the cold air flow impacting the endwall downstream and flows out of the endwall or into the blade body. However, the impact cooling effect of the cold air downstream of the endwall is greatly weakened due to the influence of the transverse flow impacted by the upstream cold air.

[0037] The purpose of this disclosure is to provide a turbine blade that improves the problem of poor impact cooling effect on the endwall of the turbine blade.

[0038] The present invention will be further described in detail below with reference to specific embodiments and the accompanying drawings.

[0039] Figure 1 This schematic diagram illustrates a cross-sectional view of a turbine blade provided in an embodiment of the present disclosure. Figure 2 This schematically illustrates a cross-sectional view of a turbine blade provided in an embodiment of the present disclosure from another perspective; Figure 3 The illustration schematically shows a cross-sectional view of the turbine blade endwall provided in an embodiment of the present disclosure.

[0040] Reference Figure 1 , Figure 2 and Figure 3 The turbine blade may include, for example, a blade body 1, an end wall 2, an impact plate 3, and a column rib 4.

[0041] The blade body 1 is hollow inside, and multiple first air film holes 11 are opened at intervals on the trailing edge of the blade body 1; the end wall 2 is located at the end of the blade body 1, and a cold air cavity 21 communicating with the interior of the blade body 1 is opened on the end wall 2. The side of the cold air cavity 21 away from the blade body 1 is open, and a second air film hole 23 communicating with the outside is opened on the end wall 2; the impact plate 3 is located at the opening of the cold air cavity 21, and multiple first impact holes 31 are opened on the impact plate 3. The multiple first impact holes 31 are arranged at intervals and are all connected to the cold air cavity 21; multiple column ribs 4 are provided, and the multiple column ribs 4 are arranged at intervals in the cold air cavity 21. The column ribs 4 are arranged radially along the blade body 1, and the end of the column rib 4 near the blade body 1 is fixedly connected to the inner bottom wall of the cold air cavity 21.

[0042] Specifically, the blade body 1 is hollow inside, and multiple first air film holes 11 are evenly spaced along the radial direction F1 of the blade body. There are two blade bodies 1, which are arranged in parallel and spaced apart. There are two end walls 2, which are symmetrically arranged at opposite ends of the blade body 1. The ends of the two blade bodies 1 are integrally formed with the end walls 2. Each end wall 2 has a cold air cavity 21. The side of the two end walls 2 that is far from each other is open. The inner bottom wall of the cold air cavity 21 has a second vent hole 22. The cold air cavity 21 is connected to the blade body 1 through the second vent hole 22. The end wall 2 has a second air film hole 23 that communicates with the outside. There are three groups of second air film holes 23, with two in each group. The three groups of second air film holes 23 are arranged alternately with the two blade bodies 1, and the second air film holes 23 are located near the trailing edge of the blade body 1. The two second air film holes 23 in each group are arranged along the radial direction F1 of the blade body 1. The blades 1 are spaced apart in a direction perpendicular to the gas flow direction; the impact plate 3 is fixedly installed at the opening of the cold air chamber 21. The impact plate 3 has multiple sets of first impact holes 31. Each set of first impact holes 31 has multiple holes. Each set of first impact holes 31 is evenly spaced from the front edge to the rear edge of the blade 1. The multiple first impact holes 31 in each set are evenly spaced along a direction perpendicular to the gas flow direction between the two blades 1. The impact plate 3 has two first vent holes 32. The two first vent holes 32 are located near the front edge of the blade 1 and are located directly above the two second vent holes 22. Multiple column ribs 4 are divided into multiple groups. Each group has multiple columns ribs. The multiple groups of column ribs 4 are spaced apart from the front edge to the rear edge of the blade 1. The multiple column ribs 4 in each group are evenly spaced along a direction perpendicular to the gas flow direction between the two blades 1.

[0043] It should be noted that the number of blades 1 in this embodiment is not specifically limited, and the number of blades 1 can be adjusted according to actual needs. Multiple blades 1 are arranged in parallel at intervals and integrally formed with the end wall 2. One end wall 2 has a second vent hole 22, while the other end wall 2 does not have a second vent hole 22. The first vent hole 32 on the impact plate 3 is also only opened in correspondence with the second vent hole 22. At the same time, the number of second air film holes 23 in this embodiment is not specifically limited, and the number of second air film holes 23 can be adjusted according to actual needs.

[0044] Based on the embodiments of this disclosure, continue to refer to Figure 1 and Figure 3 To facilitate processing, the end of the column rib 4 away from the blade 1 is attached to the side of the impact plate 3 near the blade 1. It should be noted that in other embodiments, the height of the column rib 4 can be adjusted, but the height of the column rib 4 is not greater than half the distance between the bottom wall of the cold air chamber 21 and the side of the impact plate 3 near the blade 1.

[0045] For example, the shape of the column rib 4 can be any one of a cylinder, a rhombus, or a hemisphere.

[0046] Based on the embodiments of this disclosure, continue to refer to Figure 1 and Figure 3 Multiple first impact holes 31 and multiple column ribs 4 are arranged longitudinally and transversely. Both rows of first impact holes 31 and rows of column ribs 4 are spaced apart along the leading edge to the trailing edge of the blade body 1, with one row of column ribs 4 located between two adjacent rows of first impact holes 31. The multiple rows of first impact holes 31 refer to the aforementioned multiple sets of first impact holes 31, and the multiple rows of column ribs 4 refer to the aforementioned multiple sets of column ribs 4. It should be noted that when setting the positions of the column ribs 4 and the first impact holes 31, the first impact holes 31 are set first, followed by the column ribs 4, ensuring that the cold air entering through each set of first impact holes 31 is turbulent by each set of column ribs 4 corresponding to each set of first impact holes 31 as it flows downstream.

[0047] Based on the embodiments of this disclosure, continue to refer to Figure 1 and Figure 3 In order to facilitate the machining of turbine blades and maximize the cooling effect of end wall 2, the number of column ribs 4 in each row is not less than half the number of first impact holes 31 in each row, and the diameter ratio of column ribs 4 to first impact holes 31 is (2-2.5):1.

[0048] Specifically, the ratio of the distance between two adjacent groups of first impact holes 31 to the diameter of the first impact hole 31 is 8:1, the ratio of the distance between two adjacent first impact holes 31 in each group to the diameter of the first impact hole 31 is 3.3:1, the ratio of the diameter of the column rib 4 to the diameter of the first impact hole 31 is 2.5:1, the distance between two adjacent groups of first impact holes 31 is equal to the distance between two adjacent groups of column ribs 4, and the ratio of the distance between two adjacent column ribs 4 in each group to the distance between two adjacent first impact holes 31 in each group is 2:1. It should be noted that the diameters of the column ribs 4 and the first impact holes 31 may not be limited.

[0049] Figure 4 A schematic top view of a turbine blade impact plate provided in an embodiment of this disclosure is shown. Figure 5 The diagram illustrates a cross-sectional view of the turbine blade endwall provided in an embodiment of this disclosure from another perspective.

[0050] According to embodiments of this disclosure, referring to Figure 3 , Figure 4 and Figure 5 The front, middle and rear parts of the end wall 2 are all provided with a densification zone, and the arrangement density of the first impact hole 31 in the densification zone is greater than that in the non-densification zone.

[0051] According to embodiments of this disclosure, the density of the column ribs 4 in the encrypted area is greater than the density of the column ribs 4 in the unencrypted area.

[0052] According to embodiments of this disclosure, the diameter ratio of the column rib 4 in the encrypted area to the diameter of the column rib 4 in the unencrypted area is 1:2 to 2:3.

[0053] Specifically, based on the characteristics of the turbine blade heat load distribution, the leading edges (regions 1a and 2a), trailing edges (regions 3a and 4a), and the throat area between the two blades (region 5a) have relatively large heat loads. Regions 1a, 2a, 3a, 4a, and 5a are all denser zones in this embodiment. The density of the first impact hole 31 in the denser zone is twice that in the non-dense zone. At the same time, the density of the column rib 4 corresponding to the denser zone is twice that of the column rib 4 corresponding to the non-dense zone. It should be noted that, due to circumferential leakage cooling at the throat area between the two blades (region 5b), the density of the first impact hole 31 in region 5b is the same as that in the non-dense zone, and the density of the column rib 4 in region 5b is the same as that in the non-dense zone.

[0054] According to embodiments of this disclosure, referring to Figure 1 and Figure 5 In order to allow the cold air in the cold air chamber 21 to flow out better from the second air film hole 23 and to allow the air film to better adhere to the outer periphery of the end wall 2 and isolate the combustion gas, the second air film hole 23 is arranged obliquely downward from the front edge to the rear edge of the blade 1.

[0055] According to embodiments of this disclosure, referring to Figure 1 , Figure 3 and Figure 5 In order to improve the cooling effect at the tail of the end wall 2, a tail cooling assembly 5 is provided at the tail of the end wall 2. The tail cooling assembly 5 is used to further cool the tail of the end wall 2.

[0056] According to embodiments of this disclosure, referring to Figure 1 , Figure 3 and Figure 5 The tail cooling assembly 5 includes a baffle 51 and a baffle block 52.

[0057] A baffle 51 is located at the rear edge of the cooling chamber 21, dividing the cooling chamber 21 into a front cooling area 211 and a rear cooling area 212. The first impact hole 31, the column rib 4, and the second air film hole 23 are all located in the front cooling area 211. Multiple second impact holes 511 are provided on the baffle 51 at intervals. Multiple third air film holes 24 are provided at the rear of the end wall 2. A turbulence block 52 is provided at the rear of the end wall 2. Multiple turbulence blocks 52 are provided and located in the rear cooling area 212. The multiple turbulence blocks 52 and the multiple third air film holes 24 are arranged alternately.

[0058] Specifically, the periphery of the baffle 51 is fixedly connected to the inner wall of the cooling air chamber 21, and the side of the baffle 51 away from the blade 1 is fixedly connected to the impact plate 3; the shape of the turbulence block 52 is hemispherical, and the diameter ratio of the turbulence block 52 to the first impact hole 31 is 1.5:1. It should be noted that the shape of the turbulence block 52 is not specifically limited in this embodiment, and the shape of the turbulence block can also be set as a cylinder.

[0059] Figure 6 Schematic illustration Figure 1 A schematic diagram showing the flow of intercooled air from the leading edge to the trailing edge of the end wall; Figure 7 A schematic diagram illustrating the flow of cold air within the air conditioning chamber; Figure 8 The diagram illustrates the flow of cold air in the cold air chamber when the column ribs and tail cooling assembly are missing.

[0060] According to embodiments of this disclosure, referring to Figure 6 , Figure 7 and Figure 8 Without the support rib 4, the cold air flow in the cold air chamber 21 is as follows: Figure 8 As shown, cold air flows in from upstream of the impact plate 3. After impacting the end wall 2, the upstream cold air forms an upstream transverse flow 104, which interferes with the downstream impact flow 105 formed by the downstream cold air, thus weakening the intensity of the downstream impact flow 105. With the column ribs 4 in place, the cold air flow in the cold air chamber 21 is as follows... Figure 7As shown, cold air enters through the first impact hole 31 as the source and exits through the second film air hole 23 on the end wall 2 as the sink. The source is upstream, and the sink is downstream. The sink is located in the middle of the transverse direction of the end wall 2. Cold air flows in from the left and right ends of the transverse direction, forming a forward transverse flow 101 and a reverse transverse flow 102. The cold air flows in different directions with little interference. For each flow direction, after the upstream cold air impacts the end wall 2, the forward transverse flow 101 is deflected when it encounters the column rib 4 (e.g., Figure 7 As shown, a vortex 106 is formed after the column rib 4, which weakens the impact cooling effect of the forward transverse flow 101 on the downstream impacting cold air. Along the flow direction, each column rib 4 generates vortices, forming a vortex system, which improves the heat exchange effect between the cold air and the end wall 2 without increasing the amount of cold air. In the dense zone of the column rib 4, the flow vortex system is more complex, further improving the local heat exchange effect. For the tail region of the end wall 2, a second impact film cooling is performed. Part of the cold air in the cold air chamber 21 enters the second impact hole 511, impacting the inner side wall and bottom wall of the tail of the end wall 2. After the impact, the tail transverse flow 103 flows through the turbulence block 52 and forms a vortex system. After sufficient heat exchange with the tail of the end wall 2, it flows out of the third film hole 24. The turbulence block 52 disturbs the impact airflow in the tail region, which enhances the heat exchange of the entire tail region of the end wall 2.

[0061] The following is a further explanation of the embodiments disclosed herein, based on the implementation principle of the turbine blade: A portion of the cold air enters the cold air chamber 21 from the first vent 32 on the impact plate 3 at one end of the blade body 1, and then enters the interior of the blade body 1 through the second vent 22 to cool the blade body 1. Finally, it is discharged from the first film cooling hole 11. For the other end of the blade body 1, the cold air enters the cold air chamber 21 at the other end from the first impact hole 31 on the impact plate 3 at the other end of the blade body 1, and only impacts and cools the other end of the blade body 1. The cold air no longer enters the blade body 1. Meanwhile, a portion of the cold air flows into the front cooling area 211 from the first impact hole 31 upstream of the impact plate 3. The impact airflow accelerates and collides with the end wall 2, performing impact cooling on the end wall 2. The cold air after impact bypasses the column rib 4 and flows into the second gas film hole 23. A gas film is formed on the outer surface of the end wall 2, performing gas film cooling on the end wall 2. For the tail area, the cold air in the cold air chamber 21 enters the tail cooling area 212 through the second impact hole 511, impacts the tail of the end wall 2, and cools the tail of the end wall 2. Finally, it flows out through the third gas film hole 24.

[0062] In the description of this invention, it should be understood that the terms "longitudinal", "length", "circumferential", "front", "rear", "left", "right", "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 invention and simplifying the description, and do not indicate or imply that the subsystem 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 invention.

[0063] Throughout the accompanying drawings, identical elements are represented by the same or similar reference numerals. Conventional structures or configurations may be omitted where they might cause confusion in understanding the invention. Furthermore, the shapes, sizes, and positional relationships of the components in the drawings do not reflect actual size, scale, or actual positional relationships. Additionally, any reference numerals placed between parentheses in the claims should not be construed as limiting the claims.

[0064] Similarly, to simplify the invention and aid in understanding one or more of the various disclosed aspects, in the above description of exemplary embodiments of the invention, various features of the invention are sometimes grouped together into a single embodiment, figure, or description thereof. The use of terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicates that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the invention. In this specification, illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0065] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0066] The specific embodiments described above provide a more detailed explanation of the technical solution of the present invention. It should be understood that the above descriptions are merely specific embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A turbine blade, characterized in that, include: Leaf body (1), the leaf body (1) is hollow inside, and a plurality of first air film holes (11) are opened at intervals on the rear edge of the leaf body (1); End wall (2) is provided at the end of the blade (1). A cold air chamber (21) communicating with the inside of the blade (1) is provided on the end wall (2). The side of the cold air chamber (21) away from the blade (1) is open. A second air film hole (23) communicating with the outside is provided on the end wall (2). An impact plate (3) is provided at the opening of the cold air chamber (21). The impact plate (3) has a plurality of first impact holes (31) arranged at intervals and all of them are connected to the cold air chamber (21). Multiple column ribs (4) are provided, and the multiple column ribs (4) are spaced apart in the cold air cavity (21). The column ribs (4) are arranged radially along the blade (1), and one end of the column rib (4) near the blade (1) is fixedly connected to the inner bottom wall of the cold air cavity (21). The end wall (2) is provided with a tail cooling assembly (5) at its tail end. The tail cooling assembly (5) is used to further cool the tail end of the end wall (2). The tail cooling assembly (5) includes: a baffle (51) located at the rear edge of the cold air chamber (21). The baffle (51) divides the cold air chamber (21) into a front cooling area (211) and a tail cooling area (212). The first impact hole (31), the column rib (4), and the second air film hole (2) are also included. 3) All are located in the front cooling area (211). The baffle (51) is provided with a plurality of spaced second impact holes (511). The tail of the end wall (2) is provided with a plurality of third air film holes (24). The turbulence block (52) is provided at the tail of the end wall (2). There are a plurality of turbulence blocks (52). The plurality of turbulence blocks (52) are located in the tail cooling area (212). The plurality of turbulence blocks (52) and the plurality of third air film holes (24) are staggered.

2. The turbine blade according to claim 1, characterized in that, The end of the column rib (4) away from the blade (1) is attached to the side of the impact plate (3) near the blade (1), or The height of the column rib (4) is no greater than half the distance between the bottom wall of the cold air chamber (21) and the side of the impact plate (3) near the blade (1).

3. The turbine blade according to claim 1, characterized in that, Multiple first impact holes (31) are arranged in a longitudinal and transverse manner, and multiple column ribs (4) are arranged in a longitudinal and transverse manner. Multiple rows of first impact holes (31) and multiple rows of column ribs (4) are spaced apart along the leading edge to the trailing edge of the blade (1), and one row of column ribs (4) is located between two adjacent rows of first impact holes (31).

4. The turbine blade according to claim 3, characterized in that, The number of column ribs (4) in each column is not less than half the number of the first impact holes (31) in each column, and / or The diameter ratio of the column rib (4) to the first impact hole (31) is (2-2.5):

1.

5. The turbine blade according to claim 1, characterized in that, The end wall (2) is provided with a densification zone at the front, middle and rear. The density of the first impact hole (31) in the densification zone is greater than the density of the first impact hole (31) in the non-densification zone.

6. The turbine blade according to claim 5, characterized in that, The density of the column ribs (4) in the encrypted zone is greater than the density of the column ribs (4) in the non-encrypted zone.

7. The turbine blade according to claim 6, characterized in that, The diameter ratio of the column rib (4) in the encrypted zone to the diameter of the column rib (4) in the unencrypted zone is 1:2 to 2:

3.

8. The turbine blade according to claim 1, characterized in that, The second air film pore (23) is arranged obliquely downward from the leading edge to the trailing edge of the blade (1).

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