Turbine guide vane structure, turbine and aero-engine

Abstract

The invention relates to a turbine guide vane structure, a turbine and an aero-engine, belongs to the technical field of aerospace, and solves the problems that in the prior art, a turbine guide vane structure with an impact pipe is prone to inclination of a guide pipe during installation, and the cooling effect is not ideal. The device comprises an impact pipe, wherein a plurality of positioning bosses are arranged on the outer wall surface of the impact pipe; an impact hole is formed in the positioning boss; a cooling through hole is formed in the wall face of the front edge of the impact pipe and used for forming impact cooling on the front edge of the blade. According to the invention, the positioning precision and the cooling effect can be improved.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and in particular, to a turbine guide vane structure, a turbine, and an aeroengine. Background Art

[0002] At present, the turbine inlet temperature of advanced aeroengines is as high as 2200K, far higher than the temperature resistance limit of the turbine guide vane material. Therefore, an efficient cooling technology must be adopted to ensure its normal operation. The turbine guide vane faces high-temperature and high-speed airflows directly, and bears extreme conditions such as high temperature, thermal stress, complex corrosion, and aerodynamic load. The working environment is harsh. It is necessary to use the least amount of cooling air consumption and obtain high efficiency in cooling the turbine while ensuring the safe and reliable operation and service life requirements of the blade.

[0003] In view of the cooling problem of the turbine guide vane, various cooling structures have been proposed in the prior art to improve the cooling effect. However, the structure of the turbine guide vane is relatively complex, and there may be problems in the processing of local areas, especially the structure with an impact tube. During installation, the conduit is also prone to tilt, resulting in an unsatisfactory cooling effect. Summary of the Invention

[0004] In view of the above analysis, the embodiments of the present invention aim to provide a turbine guide vane structure, a turbine, and an aeroengine to solve the problems of easy tilting of the conduit and unsatisfactory cooling effect during installation in the prior art of the turbine guide vane structure with an impact tube.

[0005] The object of the present invention is mainly achieved through the following technical solutions:

[0006] In a first aspect of the present invention, a turbine guide vane structure is provided, including a guide vane inner cavity, an impact tube is arranged in the guide vane inner cavity, and a plurality of positioning bosses are arranged on the outer wall surface of the impact tube; impact holes are arranged inside the positioning bosses;

[0007] Cooling through holes are arranged at the leading edge of the impact tube, and the cooling through holes are used for forming impingement cooling on the leading edge of the blade.

[0008] Further, the positioning boss is semi-spherical.

[0009] Further, pits are arranged on the inner wall surface of the guide vane inner cavity at positions corresponding to the positioning bosses; the width of the pits is greater than the diameter of the positioning bosses.

[0010] Further, the ratio of the height of the positioning boss to the wall thickness of the guide vane is 0.3 - 0.8, the ratio of the flow direction pitch of the positioning boss to the diameter of the positioning boss is 1.5 - 5, and the ratio of the spanwise pitch of the positioning boss to the diameter of the positioning boss is 1.5 - 5.

[0011] Further, the central axis of the impact hole is perpendicular to the wall surface impinging jet, or has an upward included angle with the height direction of the guide vane, and the included angle is A, where 0° < A ≤ 60°.

[0012] Further, the cooling through hole is a trapezoidal hole, and the width of the trapezoidal hole increases along the height of the guide vane.

[0013] Further, there are a plurality of the trapezoidal holes, and there are partition ribs between the plurality of trapezoidal holes, and the width of the partition ribs is greater than 1 mm.

[0014] Further, it further includes turbulator posts, and the turbulator posts are cross - arranged in the inner cavity of the guide vane.

[0015] In the second aspect of the present invention, a turbine is provided, including the turbine guide vane structure described above.

[0016] In the third aspect of the present invention, an aero - engine is provided, including the turbine described above.

[0017] Compared with the prior art, the present invention can achieve at least one of the following beneficial effects:

[0018] (1) In the prior art, usually a boss is machined on the blade suction surface or the inner side of the guide vane to position the installation of the impact tube. However, the guide vane is made of single - crystal superalloy material and is usually formed by investment casting. The forming accuracy of the boss is poor and the processing cost is high. The present invention uses a positioning boss on the outer surface of the impact tube. On the one hand, it reduces the processing cost and difficulty, and prevents the impact tube from tilting during installation, resulting in an unsatisfactory cooling effect. On the other hand, the positioning boss can also be used as a turbulator structure to enhance heat transfer. The impact hole is arranged in the positioning boss, reducing the influence of the impact cross - flow on the cold air flowing along the flow direction and the weakening of the impact effect by the flowing cold air, improving the cold air convective heat transfer coefficient and heat transfer area, strengthening the turbulator, and improving the cooling effect. The cold air through - hole is arranged at the leading edge of the impact tube, so that the cold air flows out from the cold air through - hole and impacts the leading edge to achieve impingement cooling.

[0019] (2) The present invention uses a concave pit in cooperation with the positioning boss for positioning. On the one hand, the concave pit is machined corresponding to the inner wall of the guide vane. Compared with the boss on the inner wall of the guide vane in the prior art, the concave pit is easier to machine, and the positioning accuracy of the cooperation between the concave pit and the positioning boss of the impact tube is higher. On the other hand, the setting of the concave pit is beneficial to the outflow of the impact air in the impact hole, and because the aerodynamic loss of the concave pit is small, it is beneficial for the cold air to have a strong heat transfer ability during the long - channel flow. To avoid large separation generated by the passing of the cooling air flow, the width of the concave pit is set to be greater than the diameter of the positioning boss.

[0020] (3) In the present invention, the positioning boss is set as a semi-circular spherical shape, which is convenient for processing. When used as a flow disturbance structure, there will be no large separation of the airflow along the flow direction, and it has a good flow disturbance effect. If the height of the positioning boss is too large, it is not easy for the impact holes to discharge fluid; if the height of the positioning boss is too small, the positioning effect is weak. In this embodiment, the ratio of the height of the positioning boss to the wall thickness of the guide vane is set to be 0.3 - 0.8; along the fluid flow direction, the distance between two adjacent positioning bosses is the flow direction spacing; perpendicular to the fluid flow direction, the distance between two adjacent positioning bosses is the spanwise spacing. If the flow direction spacing and the spanwise spacing are too small, the flow resistance is too large, and the pressure loss of the cold air flowing along the flow direction is too large, making it not easy to discharge fluid. If the flow direction spacing and the spanwise spacing are too large, the flow disturbance effect and the positioning effect are also poor. In order to balance the flow disturbance effect and the fluid discharge ability, the present invention sets the ratio of the flow direction spacing of the positioning boss to the diameter to be 1.5 - 5, and the ratio of the spanwise spacing of the positioning boss to the diameter to be 1.5 - 5.

[0021] (4) In the present invention, after the low-temperature cooling gas from the cold air source enters the impact tube, it is ejected onto the inner surface of the turbine guide vane in the form of a high-speed jet through the impact holes. The high-speed cold air jet undergoes strong convective heat transfer with the inner surface of the blade, taking away the heat from the inner surface of the blade and reducing the temperature of the blade. In the jet stagnation region, the heat transfer coefficient is extremely high, and it can quickly and effectively cool the blade. The central axis of the impact hole is perpendicular to the direction of the wall-impinging jet, or according to the cooling requirement, it has an upward angle of 0° < A ≤ 60° with the blade height direction, so that the impact hole can impact the cold air onto the inner wall surface of the blade, enhancing the local cooling effect.

[0022] (5) The leading edge wall surface of the impact tube is provided with cold air through holes for passing cold air to achieve impact cooling of the blade leading edge region. In order to reasonably utilize the space at the blade leading edge, the present invention sets the cold air through holes as trapezoidal holes with a width gradually increasing along the blade height, which is adapted to the structural feature that the blade leading edge gradually increases in width along the blade height, so that a large amount of cold air can flow out from the trapezoidal holes. The structure is simple and the cooling effect is good, reducing the problem of uneven temperature distribution caused by strong local cooling during impact cooling. There are partition ribs between multiple trapezoidal holes. In order to prevent the strength of the impact tube from being significantly weakened, the width of the partition ribs is greater than 1 mm.

[0023] (6) The turbulator posts are cross - arranged in the inner cavity of the guide vane, which can increase the convective heat transfer coefficient and the heat transfer area of the cold air, strengthen the flow disturbance, and improve the cooling effect.

[0024] In the present invention, the above - mentioned technical solutions can also be combined with each other to achieve more preferred combination schemes. Other features and advantages of the present invention will be described in the following content. Moreover, some advantages can be made obvious from the specification, or understood by implementing the present invention. The purpose and other advantages of the present invention can be realized and obtained through the content specifically pointed out in the text and the drawings. Description of the Drawings

[0025] The accompanying drawings are only for the purpose of showing specific embodiments, and are not considered to be a limitation of the present invention. Throughout the drawings, the same reference signs denote the same components.

[0026] Figure 1 It is a schematic diagram of the external structure of the turbine guide vane;

[0027] Figure 2 It is a schematic diagram of the transverse sectional structure of the turbine guide vane;

[0028] Figure 3 It is Figure 2 an enlarged view of the impact tube boss and the internal impact holes of

[0029] Figure 4 It is a schematic diagram of the structure of the impact tube;

[0030] Figure 5 It is a schematic diagram of the structure of the trapezoidal hole of the impact tube;

[0031] Figure 6 It is a schematic diagram of the angle between the injection direction of the impact hole and the height direction of the guide vane;

[0032] Figure 7 It is a schematic diagram of the distribution structure of the turbulator bars;

[0033] Figure 8 It is a schematic diagram of the longitudinal sectional structure of the turbine guide vane;

[0034] Figure 9 It is a schematic diagram of the structure of the water droplet-shaped flow guiding support member.

[0035] Reference numerals:

[0036] 1-guide vane, 11-leading edge of the guide vane, 112-pit, 113-film hole, 12-middle chord of the guide vane, 121-turbulator bar, 13-trailing edge of the guide vane, 131-flow guiding support member, 14-inner cavity of the guide vane, 141-impact tube, 1411-positioning boss, 1412-impact hole, 1413-cold air through hole, 2-upper edge plate of the guide vane, 3-lower edge plate of the guide vane. Specific embodiments

[0037] The preferred embodiments of the present invention will be specifically described below with reference to the accompanying drawings. The accompanying drawings form a part of the present invention and are used together with the embodiments of the present invention to explain the principles of the present invention, and are not used to limit the scope of the present invention.

[0038] Embodiment 1

[0039] A specific embodiment of the present invention, as Figure 1 and Figure 2As shown, a turbine vane structure is disclosed, including a vane inner cavity 14; an impact tube 141 is arranged in the vane inner cavity 14, and a plurality of positioning bosses 1411 are arranged on the outer wall surface of the impact tube 141; impact holes 1412 are arranged inside the positioning bosses 1411;

[0040] A cold air through-hole is arranged at the leading edge of the impact tube 141 for impingement cooling of the vane leading edge 11.

[0041] In the prior art, bosses are usually machined on the vane suction surface or the inner side of the vane to position the installation of the impact tube. However, the vane is made of single-crystal superalloy material, usually formed by investment casting, and the forming accuracy of the boss is poor, and the processing cost is high. In the present invention, the outer surface of the impact tube 141 is provided with positioning bosses 1411. On the one hand, the processing cost and difficulty are reduced, and the situation of the impact tube 141 tilting during installation and the unsatisfactory cooling effect are prevented; on the other hand, the positioning bosses 1411 can also be used as a flow disturbance structure to enhance heat transfer. The impact holes 1412 are arranged in the positioning bosses 1411 to reduce the influence of the impact cross flow on the cold air flowing along the flow direction and the weakening of the impact effect by the flowing cold air, improve the cold air convection heat transfer coefficient and the heat transfer area, strengthen the flow disturbance, and improve the cooling effect. The cold air through-hole 1413 is arranged at the leading edge of the impact tube 141, so that the cold air flows out from the cold air through-hole 1413 to impact the vane leading edge 11 to achieve impingement cooling.

[0042] Specifically, the vane 1 includes a vane leading edge 11, a vane mid-chord 12, a vane trailing edge 13 and a vane inner cavity 14. The vane inner cavity 14 is arranged inside the vane 1. The impact tube 141 is arranged at the front part of the vane inner cavity 14 for impingement cooling of the vane leading edge 11. The impact tube 141 is a sheet-like annular structure, and its height is the same as the height of the vane 1, and is used to achieve impingement cooling in the entire height region of the vane 1. The material of the impact tube 141 is a high-temperature resistant and high-strength metal material to withstand the heat load of the high-temperature gas and the impact pressure of the cold air.

[0043] As Figure 3 and Figure 4 shown, a plurality of positioning bosses 1411 are arranged on the outer side wall surface of the impact tube 141 for positioning the impact tube 141 to prevent the situation of the conduit tilting during installation and the unsatisfactory cooling effect. Further, the positioning bosses 1411 are arranged circumferentially along the outer side wall surface of the impact tube 141, and the arrangement mode is an array or a staggered arrangement. On the one hand, the positioning accuracy and the efficiency of impingement cooling are improved, and on the other hand, when the cold air passes through, it serves as a flow disturbance structure to increase the flow disturbance of the cold air in the mid-chord region and improve the cold air heat transfer coefficient.

[0044] The positioning boss 1411 may be in various shapes such as hemispherical, elliptical, cylindrical, conical, cuboid, prism, etc. Preferably, the positioning boss 1411 in this embodiment is hemispherical, with a simple structure and convenient processing, and the flow along the flow direction will not produce a large separation, thereby enhancing the turbulence effect.

[0045] Furthermore, if Figure 3 and Figure 4 As shown, an impact hole 1412 is provided in the positioning boss 1411. The impact hole 1412 is a simple and easy-to-process circular hole. Specifically, one or more impact holes 1412 are provided in a single positioning boss 1411 to quickly cool the high-temperature area of the guide vane 1, so as to reduce the impact of the impact cross flow on the cold air flowing in the middle area along the flow direction, and enhance the impact effect of the cold air flowing in the flow direction.

[0046] To improve the cooling effect, Figure 2 As shown, the central axis of the impact hole 1412 is perpendicular to the direction of the wall impact jet, or according to the cooling requirements, such as Figure 6 As shown, there is an upward angle with the height direction of the guide vane 1, and the angle is A, then 0°<A≤60°, so that the impact hole 1412 impacts the cold air onto the inner wall surface of the guide vane 1 to enhance the local cooling effect.

[0047] After the low-temperature cooling gas from the cold air source enters the impact tube 141, it is ejected to the inner surface of the turbine guide vane 1 in the form of a high-speed jet through the impact hole 1412. The high-speed cold air jet undergoes intense convection heat exchange with the inner surface of the turbine guide vane 1, taking away the heat of the inner surface of the turbine guide vane 1 and reducing the temperature of the turbine guide vane 1. In the jet stagnation area, the heat transfer coefficient is extremely high, and the turbine guide vane 1 can be cooled quickly and effectively.

[0048] If the height of the positioning boss 1411 is too large, the impact hole 1412 is not easy to flow out; if the height of the positioning boss 1411 is too small, the positioning effect is weak. In this embodiment, the ratio of the height of the positioning boss 1411 to the wall thickness of the guide vane 1 is set to 0.3-0.8.

[0049] Along the cold air flow direction, the distance between two adjacent positioning bosses 1411 is the flow spacing; perpendicular to the fluid flow direction, the distance between two adjacent positioning bosses 1411 is the span spacing. If the flow spacing and span spacing are too small, the flow resistance will be too large, and the pressure loss of cold air along the flow direction will be too large to facilitate outflow. If the flow spacing and span spacing are too large, the flow disturbance effect and positioning effect will also be poor. In order to balance the flow disturbance effect and outflow capacity, the present embodiment sets the ratio of the flow spacing of the positioning bosses 1411 to the diameter to be 1.5 to 5, and the ratio of the span spacing of the positioning bosses 1411 to the diameter to be 1.5 to 5.

[0050] The leading edge of the impact tube 141 faces the high-temperature combustion gas directly, and local enhanced heat transfer is required. Therefore, cold air through holes 1413 are arranged on the wall surface of the leading edge of the impact tube 141 to pass cold air and achieve impingement cooling on the region of the leading edge 11 of the guide vane.

[0051] Preferably, in order to make reasonable use of the space of the leading edge 11 of the guide vane, as Figure 5 shown, in this embodiment, the cold air through holes 1413 are arranged as trapezoidal holes with a width gradually increasing along the blade height, which is adapted to the structural characteristics that the width of the leading edge 11 of the guide vane gradually increases as the height of the guide vane 1 increases, so that a large amount of cold air can flow out from the trapezoidal holes. The structure is simple and the cooling effect is good, reducing the problem of uneven temperature distribution caused by strong local cooling caused by impingement cooling.

[0052] There are partition ribs between multiple trapezoidal holes. In order not to greatly weaken the strength of the impact tube 141, the width of the partition ribs is greater than 1 mm.

[0053] Furthermore, as Figure 3 shown, multiple pits 111 are arranged on the inner wall surface of the guide vane 1 corresponding to the position of the positioning boss 1411, and the shape of the pits 111 corresponds to the shape of the positioning boss 1411. In the present invention, the pits 111 and the positioning boss 1411 are used for positioning. On the one hand, the pits 111 are machined on the inner wall of the guide vane 1. Compared with the convex bosses on the inner wall of the guide vane in the prior art, the pits 111 are easier to machine, and the positioning accuracy of the cooperation between the pits 111 and the positioning boss 1411 of the impact tube 141 is higher; on the other hand, the arrangement of the pits 111 is beneficial to the outflow of the impinging air in the impact holes 1412, and since the aerodynamic loss of the pits 111 is small, it is beneficial for the cold air to have a strong heat transfer ability when flowing in the long channel. To avoid large separation when the cooling air flow passes through, the width of the pits 111 is set to be greater than the diameter of the positioning boss 1411, and a transition arc is arranged at the edge of the pits 111. The depth of the pits 111 does not exceed the thickness of the guide vane 1, and it is ensured that the distance from the outer wall surface of the guide vane 1 to the inner wall surface of the pits 111 is greater than 0.5 mm to ensure the strength requirement.

[0054] As Figure 1 and Figure 2 shown, multiple film holes 113 are arranged on the wall surface of the guide vane 1. Film cooling can make the cold air cover the outer surface of the guide vane 1 and block the high-temperature combustion gas. Preferably, the diameter of the film holes 113 is 0.1 - 0.8 mm to reduce the mixing loss between the cold air flow and the mainstream.

[0055] Furthermore, as Figure 7 shown, it further includes turbulator columns 121, and the turbulator columns 121 are cross-arranged in the guide vane cavity 14. Preferably, the diameter of the turbulator columns 121 is 1.0 - 2.0 mm, so as to improve the convective heat transfer coefficient and heat transfer area of the cold air, strengthen the turbulence, and improve the cooling effect.

[0056] Reinforcing ribs are also provided between the positioning bosses 1411 or between the spoiler columns 121 to increase the heat exchange area, strengthen the flow disturbance, and at the same time increase the structural strength of the guide vane 1.

[0057] Further, as Figure 8 and Figure 9 shown, a plurality of flow guiding and supporting members 131 are longitudinally arranged on the flow guiding part of the trailing edge 13 of the guide vane to form flow guiding and support at the trailing edge 13 of the guide vane. On the one hand, the flow guiding and supporting members 131 can increase the flow disturbance at the trailing edge 13 of the guide vane, strengthen the trailing edge cooling, guide the uniform flow of the trailing edge cold air, and reduce the turbulence of the outlet air flow; on the other hand, it can strengthen the structural strength of the trailing edge 13 of the guide vane, reduce the deformation or vibration of the trailing edge 13 area due to the action of air flow scouring and thermal stress, and improve the structural reliability.

[0058] Further, the trailing edge 13 of the guide vane adopts a full split structure for cooling, and the flow guiding and supporting members 131 are arranged in the full split structure, and the full split structure forms film cooling. The full split structure mainly sets a series of dense split seams at the trailing edge 13 of the guide vane, so that the cooling gas flows through these split seams and discharges from the inside of the guide vane 1. In this process, the cooling gas exchanges heat with the inner wall of the trailing edge 13 of the guide vane, absorbs the heat of the guide vane 1, thereby reducing the temperature of the trailing edge 13 of the guide vane. At the same time, the discharged cooling gas can also form a film on the surface of the trailing edge 13 of the guide vane to form film cooling, which plays a covering and protecting role for the trailing edge 13 of the guide vane and reduces the direct scouring of the high-temperature gas on the trailing edge 13 of the guide vane.

[0059] Preferably, the flow guiding and supporting member 131 is set to have a structure with a semi-circular end at the leading edge, a pointed end at the trailing edge, and a streamlined side surface, which can guide the air flow to flow along the side surface and converge the air flow at the tail, so as to avoid the situation where the air flow cannot cover some areas at the trailing edge, make the film of the tail seam air flow cover more evenly, and the cooling effect more uniform.

[0060] Specifically, the semi-circular end at the leading edge can avoid strong separation of the air flow at the stagnation point, make the boundary layer smoothly adhere to the surface of the flow guiding plate; the pointed end at the trailing edge can accelerate the air flow peeling, reduce the range of the low-pressure area at the trailing edge 13 of the guide vane, and reduce the pressure difference resistance; the streamlined side surface can guide the air flow to flow along the side surface, optimize the aerodynamic profile of the trailing edge 13 of the guide vane, make the air flow smoothly transition, reduce the energy dissipation, and improve the turbine efficiency. The curved surface structure on the side surface can make the cooling jet mix more evenly with the mainstream, make the film of the tail seam air flow cover more evenly, and the cooling effect more uniform.

[0061] The working principle is as follows: When the guide vane is cooled, the cooling air flow enters the inner cavity 14 of the guide vane from the lower part of the guide vane. A part of the gas impacts the wall surface of the leading edge 11 of the guide vane through the trapezoidal holes 1413 at the leading edge of the impact tube 141 for impingement cooling. Another part of the cooling gas is directly ejected from the film holes 112 to form a gas film covering the leading edge 11 of the guide vane, blocking the heating of the wall surface of the guide vane 1 by the hot combustion gas; in the mid-chord region, it impacts the wall surface of the mid-chord 12 of the guide vane through the impact holes 1412 for impingement cooling. Another part of the cooling gas is directly ejected from the film holes 112 to form a gas film covering for cooling. At the same time, the positioning boss 1411 and the turbulator 121 form a turbulator structure for flow disturbance; the trailing edge 13 of the guide vane is cooled by means of gas film cooling formed by a full split structure and the flow guiding of the flow guiding support 131.

[0062] In this embodiment, an impact tube 141 is arranged in the inner cavity 14 of the guide vane. In addition to the gas film cooling formed by the film holes 113 at the leading edge 11 of the guide vane, the trapezoidal holes 1413 at the leading edge of the impact tube 141 are also used to impact-cool the leading edge 11 of the guide vane, improving the cooling effect; in the mid-chord 12 of the guide vane, in addition to the gas film cooling of the film holes 113 and the flow disturbance of the turbulator 121 in the prior art, the impact holes 1412 in the positioning boss 1411 of the impact tube 141 are also used to impact-cool the wall surface of the mid-chord 12 of the guide vane, and the positioning boss 1411 is used to disturb the cooling air flow, increasing the flow disturbance of the cold air in the mid-chord region and improving the heat transfer coefficient of the cold air; at the trailing edge 13 of the guide vane, in addition to the gas film cooling formed by the full split structure, a flow guiding support 131 is also arranged for flow guiding, making the gas film coverage of the air flow at the trailing edge 13 of the guide vane more uniform and the cooling effect more uniform; thus, in this embodiment, by combining multiple cooling methods at the leading edge 11, mid-chord 12, and trailing edge 13 of the guide vane, a significant improvement in the comprehensive cooling effect of the turbine guide vane is achieved.

[0063] Embodiment 2

[0064] The present invention also provides a turbine, including the structure of the turbine guide vane 1 in the above embodiment.

[0065] Furthermore, it further includes a guide vane upper edge plate 2 and a guide vane lower edge plate 3. The guide vane upper edge plate 2 is installed on the upper part of the turbine guide vane 1 structure, and the guide vane lower edge plate 3 is installed on the lower part of the turbine guide vane 1 structure.

[0066] Compared with the prior art, the advantages of the turbine in the embodiment of the present invention are the same as those of the above turbine guide vane 1, which will not be elaborated here.

[0067] Embodiment 3

[0068] The present invention also provides an aeroengine, including the turbine in the above embodiment.

[0069] Compared with the prior art, the aeroengine according to the embodiment of the present invention has the same advantages as those of the above-mentioned turbine guide vane 1 and turbine, which will not be elaborated herein.

[0070] The above are only the preferred specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed by the present invention should be covered within the protection scope of the present invention.

Claims

1. A turbine guide vane structure, characterized in that It includes a guide vane inner cavity (14), an impact tube (141) is arranged in the guide vane inner cavity (14), and a plurality of positioning bosses (1411) are arranged on the outer wall surface of the impact tube (141); an impact hole (1412) is arranged inside the positioning boss (1411); A cooling through hole (1413) is arranged at the leading edge of the impact tube (141), and the cooling through hole (1413) is used to form impingement cooling on the guide vane (1).

2. The turbine guide vane structure according to claim 1, characterized in that The positioning boss (1411) is semi-spherical.

3. The turbine guide vane structure according to claim 1, characterized in that, A pit (112) is arranged on the inner wall surface of the guide vane inner cavity (14) corresponding to the position of the positioning boss (1411); the width of the pit (112) is greater than the diameter of the positioning boss (1411).

4. The turbine guide vane structure according to claim 2, characterized in that, The ratio of the height of the positioning boss (1411) to the wall thickness of the guide vane is 0.3 - 0.8, the ratio of the flow direction pitch of the positioning boss (1411) to the diameter of the positioning boss (1411) is 1.5 - 5, and the ratio of the spanwise pitch of the positioning boss (1411) to the diameter of the positioning boss (1411) is 1.5 - 5.

5. The turbine guide vane structure according to claim 1, characterized in that, The central axis of the impact hole (1412) is perpendicular to the wall surface impinging jet, or has an upward included angle with the height direction of the guide vane (1), and the included angle is A, then 0° < A ≤ 60°.

6. The turbine guide vane structure according to claim 1, characterized in that, The cooling through hole (1413) is a trapezoidal hole, and the width of the trapezoidal hole increases along the height of the guide vane.

7. The turbine guide vane structure according to claim 6, characterized in that There are a plurality of the trapezoidal holes, and there are partition ribs between the plurality of trapezoidal holes, and the width of the partition ribs is greater than 1 mm.

8. The turbine guide vane structure according to claim 1, characterized in that It further includes spoiler columns (121), and the spoiler columns (121) are cross-arranged in the guide vane inner cavity (14).

9. A turbine, characterized in that, It includes the turbine guide vane structure according to any one of claims 1 - 8.

10. An aeroengine, characterized in that, It includes the turbine according to claim 9.

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