Turbine guide blade and aero-engine with same

Abstract

The invention relates to the technical field of turbine blade cooling, and discloses a turbine guide blade and an aero-engine with the same. The turbine guide blade comprises a blade body, the front edge of the blade body is provided with a tree-shaped channel, and the two ends of the tree-shaped channel communicate with the external environment; the front cavity is formed in the blade body, the end, facing the upper edge plate, of the front cavity communicates with the external environment, and the front cavity is arranged close to the front edge of the blade body; the rear cavity is arranged in the blade body, the rear cavity and the front cavity are arranged in an isolated mode, the end, facing the upper edge plate, of the front cavity communicates with the external environment, and an exhaust channel is arranged on the side, away from the front cavity, of the rear cavity and communicates with the external environment. By adopting the tree-shaped bionic channel at the front edge, the cooling effect of cold air can be greatly improved, the metal temperature of a high-temperature area at the front edge of the blade is obviously reduced, the amount of cold air needed by cooling is small, and therefore the cooling requirement of a new-generation high-cycle-parameter engine turbine guider is met.

Description

Technical Field

[0001] The present invention relates to the technical field of turbine blade cooling, and in particular to a turbine guide blade and an aircraft engine having the same. Background Art

[0002] The requirements of advanced aircraft engines for high power, low fuel consumption and other indicators are constantly increasing. The temperature before the engine turbine has reached above 2000K, which poses a severe test to the stable operation of turbine blades in high temperature and long-term environment. It is urgent to develop a new type of turbine blade cooling structure to meet the requirements of advanced aircraft engines for high cooling effect of turbine blades.

[0003] Existing turbine guide blade cooling mainly includes cooling forms such as serpentine channels, bosses, spoiler columns, impacts, and air films. Based on the structure and environmental impact of the turbine guide blades, a composite cooling design with multiple cooling structures is adopted. For advanced high-cycle parameter gas turbine secondary guide blades, due to the small amount of cooling air, a combined cooling form of "serpentine channels + ribs + impacts + slits" is usually adopted. At present, this technology is very mature and has been widely used in large, medium and small aircraft engines.

[0004] However, the above cooling method has limited effect in reducing the metal temperature of the blade by optimizing the inner cooling structure to enhance heat exchange. Only by increasing the amount of cold air intake can the metal temperature of the blade be significantly reduced, but this will also lead to a decrease in engine performance. The temperature before the turbine of the new generation of aircraft engines has further increased, and the cooling effect of the traditional blade cooling solution has limited improvement. The maximum temperature of the blade metal may exceed the allowable temperature value of the blade material, resulting in blade ablation. Summary of the invention

[0005] In view of this, the present invention provides a turbine guide vane and an aircraft engine having the same, so as to solve the problem of blade ablation risk when turbine blades in the prior art are used in a new generation of aircraft engines.

[0006] In a first aspect, the present invention provides a turbine guide blade, comprising:

[0007] The blade body has a tree-shaped channel at its front edge, and both ends of the tree-shaped channel toward the upper edge plate and the lower edge plate are connected to the external environment;

[0008] A front chamber is disposed in the blade body, wherein one end of the front chamber facing the upper edge plate is in communication with the external environment, and the front chamber is disposed close to the front edge of the blade body;

[0009] A rear chamber is arranged in the blade body, the rear chamber is isolated from the front chamber, the rear chamber is arranged on the side of the front chamber away from the leading edge of the blade body, the end of the front chamber facing the upper edge plate is connected to the external environment, and an exhaust passage is arranged on the side of the rear chamber away from the front chamber, and the exhaust passage is connected to the external environment.

[0010] When the turbine guide blades are working, the cold air flows from the upper edge of the turbine guide blades into the tree-shaped channel, the front chamber and the rear chamber. In the tree-shaped channel, the cold air flows along the radial direction of the blade body to the lower edge along the tree-shaped channel and flows out from the lower edge of the blade body to cool the leading edge of the blade body; the cold air entering the front chamber also flows along the radial direction of the blade body to the lower edge and flows out from the lower edge of the blade body to cool the side wall of the front chamber area on the blade body. The flow direction of the cold air entering the rear chamber rotates ninety degrees and is discharged from the exhaust channel at the trailing edge of the blade body. By using a tree-shaped bionic channel at the leading edge, the cooling effect of the cold air can be greatly improved, and the metal temperature in the high-temperature area of ​​the leading edge of the blade can be significantly reduced. The amount of cold air required for cooling is small, achieving the effect of high-efficiency cooling with a small amount of cold air, thereby meeting the cooling needs of the turbine guide of the new generation of high-cycle parameter engines.

[0011] In an optional embodiment, a front chamber vane basin side channel is provided in the inner wall of the front chamber on one side of the vane basin of the blade body, and both ends of the front chamber vane basin side channel facing the upper edge plate and the lower edge plate are connected to the external environment, and a honeycomb channel is provided in the front chamber vane basin side channel. By providing a front chamber vane basin side channel and setting the front chamber vane basin side channel as a honeycomb channel. By adopting a honeycomb bionic channel, the cooling effect of cold air in the area of ​​the front chamber facing the vane basin side of the blade body can be greatly improved, the metal temperature on the blade surface can be significantly reduced, and the cooling efficiency of the cold air can be improved.

[0012] In an optional embodiment, a front chamber blade back side channel is provided in the inner wall of the front chamber on the side of the blade back of the blade body, and both ends of the front chamber blade back side channel facing the upper edge plate and the lower edge plate are connected to the external environment, and a honeycomb channel is provided in the front chamber blade back side channel.

[0013] In an optional embodiment, a rear cavity blade basin side channel is provided in the inner wall of the rear cavity on one side of the blade basin of the blade body, the rear cavity blade basin side channel is connected to the rear cavity at one end close to the front cavity, the other end of the rear cavity blade basin side channel is connected to the exhaust channel, and a honeycomb channel is provided in the rear cavity blade basin side channel. By providing a rear cavity blade basin side channel, and setting the rear cavity blade basin side channel as a honeycomb channel. By adopting a honeycomb bionic channel, the cooling effect of cold air in the area of ​​the rear cavity facing the blade basin side of the blade body can be greatly improved, the metal temperature of the blade surface can be significantly reduced, and the cooling efficiency of cold air can be improved. At the same time, by setting the inlet of the rear cavity blade basin side channel on the side close to the front cavity, and the outlet is connected to the exhaust channel, the cold air flow flows in the rear cavity blade basin side channel along the extension direction of the blade body, thereby ensuring the cooling efficiency of the cold air on the blade body.

[0014] In an optional embodiment, the rear cavity blade basin side channels are arranged in multiple groups at intervals along the radial direction of the blade body, and each group of the rear cavity blade basin side channels is isolated from each other. The honeycomb channels in the area corresponding to the rear chamber on the blade body are separated by a partition, and the airflows in different areas along the radial direction will not cross each other, thereby avoiding the uneven flow distribution caused by the uneven static pressure distribution along the radial direction of the trailing edge cold air outlet.

[0015] In an optional embodiment, a rear chamber blade back side channel is provided in the inner wall of the rear chamber on the side of the blade back of the blade body, the rear chamber blade back side channel is connected to the rear chamber at one end close to the front chamber, and the other end of the rear chamber blade back side channel is connected to the exhaust channel, and a honeycomb channel is provided in the rear chamber blade back side channel.

[0016] In an optional embodiment, the back-cavity blade back-side channels are arranged in a plurality of groups at intervals along the radial direction of the blade body, and each group of the back-cavity blade back-side channels is isolated from each other.

[0017] In an optional embodiment, the tree-shaped channel includes radial channels and connecting channels. The radial channels are arranged to penetrate the blade body radially. Multiple groups of radial channels are arranged at intervals. The connecting channels are connected between adjacent radial channels. The angle between the connecting channels and the radial channels is 20° to 70°.

[0018] In an optional embodiment, the exhaust passage includes a blade basin side air film hole and a blade back side air film hole, the blade basin side air film hole is arranged in the inner wall of the blade basin side of the blade body, and the blade back side air film hole is arranged in the inner wall of the blade back side of the blade body, and the blade basin side air film hole and the blade back side air film hole both extend to the trailing edge area of ​​the blade body.

[0019] In a second aspect, the present invention further provides an aircraft engine having the turbine guide blades of the present invention. Since the aircraft engine includes the turbine guide blades, which have the same effect as the turbine guide blades, they will not be described in detail here. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0021] Figure 1 A schematic cross-sectional view of a turbine guide vane provided for an embodiment of the present invention, wherein the red arrow indicates the flow direction of cold air in the rear cavity area.

[0022] Figure 2 A schematic diagram of the internal airflow path of a turbine guide blade provided in an embodiment of the present invention, wherein the red arrow indicates the flow direction of cold air inside the turbine guide blade.

[0023] Figure 3 A schematic diagram of the structure of a tree-shaped channel provided for an embodiment of the present invention, wherein the red arrow indicates the flow direction of cold air in the tree-shaped channel.

[0024] Figure 4 A schematic diagram of the structure of a honeycomb channel provided for an embodiment of the present invention, wherein the red arrow indicates the flow direction of cold air in the honeycomb channel.

[0025] Explanation of the reference numerals in the accompanying drawings: 1. front chamber; 2. rear chamber; 3. tree-shaped channel; 4. channel on the blade basin side of the front chamber; 5. channel on the blade back side of the front chamber; 6. channel on the blade basin side of the rear chamber; 7. channel on the blade back side of the rear chamber; 8. air film hole on the blade basin side; 9. air film hole on the blade back side; 10. partition; 11. upper edge plate; 12. lower edge plate; 13. leading edge; 14. trailing edge; 15. radial channel; 16. connecting channel. DETAILED DESCRIPTION

[0026] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present invention.

[0027] Combine the following Figures 1 to 4 , describing an embodiment of the present invention.

[0028] According to an embodiment of the present invention, on one hand, a turbine guide vane is provided, comprising a blade body, wherein a front chamber 1 and a rear chamber 2 are arranged in the blade body.

[0029] A tree-shaped channel 3 is provided at the leading edge 13 of the blade body, and both ends of the tree-shaped channel 3 facing the upper edge plate 11 and the lower edge plate 12 are connected to the external environment. A front chamber 1 is provided in the blade body, and one end of the front chamber 1 facing the upper edge plate 11 is connected to the external environment, and the front chamber 1 is provided near the leading edge 13 of the blade body. A rear chamber 2 is provided in the blade body, and the rear chamber 2 is isolated from the front chamber 1. The rear chamber 2 is provided on the side of the front chamber 1 away from the leading edge 13 of the blade body, and one end of the front chamber 1 facing the upper edge plate 11 is connected to the external environment, and an exhaust channel is provided on the side of the rear chamber 2 away from the front chamber 1, and the exhaust channel is connected to the external environment.

[0030] When the turbine guide blade is working, the cold air flows from the upper edge of the turbine guide blade into the tree-shaped channel 3, the front chamber 1 and the rear chamber 2. In the tree-shaped channel 3, the cold air flows along the radial direction of the blade body to the lower edge along the tree-shaped channel 3 and flows out from the lower edge of the blade body to cool the leading edge 13 of the blade body; the cold air entering the front chamber 1 also flows along the radial direction of the blade body to the lower edge and flows out from the lower edge of the blade body to cool the side wall of the area of ​​the front chamber 1 on the blade body. The flow direction of the cold air entering the rear chamber 2 rotates ninety degrees and is discharged from the exhaust channel at the trailing edge 14 of the blade body. By using a tree-shaped bionic channel at the leading edge 13, the cooling effect of the cold air can be greatly improved, and the metal temperature of the high-temperature area of ​​the blade leading edge 13 can be significantly reduced. The amount of cold air required for cooling is small, and the effect of high-efficiency cooling with a small amount of cold air is achieved, thereby meeting the cooling requirements of the turbine guide device of the new generation of high-cycle parameter engines.

[0031] In one embodiment, a front chamber blade basin side channel 4 is provided in the inner wall of the front chamber 1 on the side of the blade basin facing the blade body, and both ends of the front chamber blade basin side channel 4 facing the upper edge plate 11 and the lower edge plate 12 are connected to the external environment, and a honeycomb channel is provided in the front chamber blade basin side channel 4. Further, a front chamber blade back side channel 5 is provided in the inner wall of the front chamber 1 on the side of the blade back facing the blade body, and both ends of the front chamber blade back side channel 5 facing the upper edge plate 11 and the lower edge plate 12 are connected to the external environment, and a honeycomb channel is provided in the front chamber blade back side channel 5.

[0032] By providing the front chamber blade basin side channel 4 and the front chamber blade back side channel 5, and setting the front chamber blade basin side channel 4 and the front chamber blade back side channel 5 as honeycomb channels, the cooling effect of the cold air in the front chamber 1 toward the blade basin side area and the blade back side area can be greatly improved by adopting the honeycomb bionic channel, the metal temperature of the blade surface can be significantly reduced, and the cooling efficiency of the cold air can be improved.

[0033] In one embodiment, a rear cavity blade basin side channel 6 is provided in the inner wall of the rear cavity 2 on the side of the blade basin of the blade body, and the rear cavity blade basin side channel 6 is connected to the rear cavity 2 at one end close to the front cavity 1, and the other end of the rear cavity blade basin side channel 6 is connected to the exhaust channel, and a honeycomb channel is provided in the rear cavity blade basin side channel 6. The rear cavity blade basin side channel 6 is provided, and the rear cavity blade basin side channel 6 is provided as a honeycomb channel. A rear cavity blade back side channel 7 is provided in the inner wall of the rear cavity 2 on the side of the blade back of the blade body, and the rear cavity blade back side channel 7 is connected to the rear cavity 2 at one end close to the front cavity 1, and the other end of the rear cavity blade back side channel 7 is connected to the exhaust channel, and a honeycomb channel is provided in the rear cavity blade back side channel 7. By adopting the honeycomb bionic channel, the cooling effect of the cold air on the side wall of the rear cavity 2 facing the blade basin side of the blade body and the side wall of the rear cavity 2 facing the back side of the blade body can be greatly improved, the metal temperature of the blade surface can be significantly reduced, and the cooling efficiency of the cold air can be improved. At the same time, by arranging the inlet of the rear cavity blade basin side channel 6 and the inlet of the rear cavity blade back side channel 7 on the side close to the front chamber 1, the outlet is connected with the exhaust channel, so that the cold air flow flows in the rear cavity blade basin side channel 6 and the rear cavity blade back side channel 7 along the extension direction of the blade body, thereby ensuring the cooling efficiency of the cold air on the blade body.

[0034] Furthermore, in order to improve the stability of the blade during operation, multiple groups of rear cavity blade basin side channels 6 are arranged at intervals along the radial direction of the blade body, and each group of rear cavity blade basin side channels 6 is isolated from each other, and multiple groups of rear cavity blade back side channels 7 are arranged at intervals along the radial direction of the blade body, and each group of rear cavity blade back side channels 7 is isolated from each other. The honeycomb channels in the area corresponding to the rear chamber 2 on the blade body are separated by the partition 10, and the airflows in different areas along the radial direction will not cross each other, thereby avoiding the uneven flow distribution caused by the uneven static pressure distribution along the radial direction of the cold air outlet of the trailing edge 14.

[0035] In one embodiment, the tree-shaped channel 3 includes radial channels 15 and connecting channels 16. The radial channels 15 are arranged to penetrate the blade body in the radial direction. Multiple groups of radial channels 15 are arranged at intervals. The connecting channels 16 are connected between adjacent radial channels 15. The angle between the connecting channels 16 and the radial channels 15 is 20° to 70°.

[0036] In one embodiment, in order to ensure the cooling effect of the trailing edge 14 area, the exhaust passage includes a blade basin side air film hole 8 and a blade back side air film hole 9. The blade basin side air film hole 8 is arranged in the inner wall of the blade basin side of the blade body, and the blade back side air film hole 9 is arranged in the inner wall of the blade back side of the blade body. The blade basin side air film hole 8 and the blade back side air film hole 9 both extend to the trailing edge area of ​​the blade body.

[0037] This embodiment proposes a novel blade inner cavity cooling flow path design, which uses a bionic channel in a confined space as a cooling structural unit, combines the characteristics of the guide blade blade profile and the cooling flow path of the air system, and constructs a combined cooling form for the turbine guide cavity. Compared with the traditional "winding channel + rib + impact + slit" cooling design, it can greatly improve the heat exchange capacity of the blade cavity and improve the blade cooling effect, thereby meeting the cooling requirements of the turbine guide of a new generation of high cycle parameter engines.

[0038] The bionic cooling structure of the turbine guide blade provided in this embodiment is a combined cooling structure of the tree-shaped channel 3 at the leading edge 13 of the blade, the honeycomb-shaped channel and the air film cooling at the middle to the trailing edge 14. Among them, the tree-shaped channel 3 is in the leading edge 13 area of ​​the blade body, the honeycomb-shaped channel is distributed on the blade basin side and the blade back side of the middle area of ​​the blade, and the air film hole is in the trailing edge 14 area of ​​the blade body. The secondary flow cold air is extracted from the two air flows in the combustion chamber. The cold air enters the front chamber 1, the tree-shaped channel 3, the front chamber blade basin side channel 4, the front chamber blade back side channel 5 and the rear chamber 2 of the blade body in the radial direction through the two cold air inlets on the upper edge plate 11. A part of the cold air flows out radially to the cold air outlet on the lower edge plate 12 for sealing between blade stages, and the other part of the cold air flows horizontally through the blade wall surface and is discharged into the mainstream combustion gas from the blade basin side air film hole 8 and the blade back side air film hole 9 in the trailing edge 14 area.

[0039] The inner cavity of the blade body is divided into two areas by a partition 10: a front cavity area and a rear cavity area. The front cavity area includes a front cavity 1, a tree-shaped channel 3, a front cavity blade basin side channel 4 and a front cavity blade back side channel 5, and the rear cavity area includes a rear cavity 2, a rear cavity blade basin side channel 6, a rear cavity blade back side channel 7, a blade basin side air film hole 8 and a blade back side air film hole 9. The shape of the tree-shaped channel 3 is adaptively improved and designed based on the shape of branch bifurcations in nature. Different circular tubes are connected through the shape of branch bifurcations to form a stable tree-shaped channel 3 bionic cooling structure. The shape of the honeycomb channel is also adaptively improved and designed based on the honeycomb structure in nature. The gaps between multiple hexagons are used to form a stable honeycomb network channel to construct a honeycomb channel bionic cooling structure for turbine blade cooling design.

[0040] In the front cavity area of ​​the blade, a part of the cold air enters the tree-shaped channel 3 radially through three vertically arranged circular tubes serving as radial channels 15. In the tree-shaped channel 3 network, the airflows between the circular tubes are mixed with each other through the connecting channels 16 during the process of flowing radially downward, and finally flow out from the cold air outlet on the lower edge plate 12. The outflowing cold air is used for sealing between the air system stages. When the turbine guide blade is working, the leading edge 13 area faces the combustion gas, forming a high-temperature area of ​​the blade. The heat exchange coefficient between the cold air and the inner wall in the tree-shaped channel 3 is greatly improved compared with the traditional serpentine channel, which can effectively cool the high-temperature area of ​​the leading edge 13 of the blade; by adjusting the diameter of the circular tube, the flow rate in the tree-shaped channel 3 can be effectively adjusted, thereby adjusting the heat exchange coefficient in the tree-shaped channel 3, and selecting a suitable circular tube diameter according to the cooling demand of the leading edge 13 of the blade, while the serpentine channel in the traditional solution has a large flow area and a wide coverage range. By adjusting the flow area of ​​the serpentine channel, the heat exchange coefficient of the inner cavity changes little, and it is difficult to effectively cool the high-temperature area of ​​the leading edge 13; the circular tubes are connected by a tree-shaped network. If a certain point in a certain pipeline is blocked, it will not affect the downward flow of cold air along other branches, and the stability of the cold air flow path is better; the tree-shaped channel 3 has a simple and changeable structure and shape, which can better adapt to the blade characteristics of the leading edge 13 compared with other bionic cooling structures. Figure 1 As shown, three circular tubes are set as radial channels 15 in the area near the leading edge 13 of the blade. Assuming that the middle circular tube is closer to the geometric stagnation point of the leading edge 13 of the blade, in order to ensure the cooling effect of the leading edge 13 of the blade and take into account the minimum wall thickness size limit of the blade, the distance between the middle circle and the geometric stagnation point of the leading edge 13 needs to be within the range of 0.4mm to 0.6mm, and the distance between the outer wall of the two circular tubes on both sides and the blade wall needs to be within the range of 0.4mm to 0.6mm. The diameter of the circular tube is generally between 0.3mm and 1.0mm, which needs to be determined based on the flow distribution and the cooling demand evaluation of the leading edge 13. Figure 3 As shown, the branch bifurcation angle θ in the tree-shaped channel 3 is in the range of 20° to 70°, the distances W1 and W2 between adjacent circular tubes are both in the range of 0.4 to 1.5 mm, the tree-shaped channel unit framed in the figure is assumed to be a layer of tree-shaped channel units, and the number of layers of tree-shaped channel units arranged radially in the blade leading edge 13 region is in the range of 2 to 10. The above parameters need to be determined by one-dimensional flow iterative calculation and three-dimensional temperature field iterative calculation.

[0041] In the front cavity area of ​​the blade, another part of the cold air directly enters the front cavity blade basin side channel 4 and the front cavity blade back side channel 5 along the radial direction. Figure 4As shown, after the cold air enters the honeycomb network channel, it continues to flow downward along the radial wall surface. At the corner of the honeycomb channel, the airflow will converge or diverge. The cold air in the honeycomb network channel will mix and flow with each other, increasing the heat exchange area, thereby greatly improving its cooling effect. Finally, the cold air will flow out from the outlet on the lower edge plate 12, and the outflowing cold air is used for air system interstage sealing. Honeycomb channels are set on the blade basin side and the blade back side of the front cavity area, and the wall cooling method is used to fit the blade shape. Honeycomb channels are arranged on the blade basin side and the blade back side, with a large heat exchange area and good cooling effect; by changing the structural parameters of the honeycomb channel unit at different positions on the blade, the cooling effect at different positions can be adjusted, so that the temperature in the high temperature area is reduced, the temperature in the low temperature area is increased, and the temperature gradient of the blade is reduced; compared with the traditional winding channel, the structural parameter channel seam width of the honeycomb channel unit is adjusted, and the inner cavity heat transfer coefficient is greatly improved, which can meet the cooling requirements of the new generation of wide-operating aircraft engines for blades; the structural parameters of the honeycomb channel unit can be adaptively changed in combination with the characteristics of the blade shape, and the structure is simple and changeable. Compared with the complex bionic cooling unit, it can be better applied to turbine cooling blades. In this embodiment, if Figure 4 As shown, the width of all honeycomb channels is 0.3mm-0.5mm, the inner angle γ is 60°-120°, D1 is 0.6mm-1.2mm, D2 is 0.3-0.6mm, and D3 is 1.0mm-3.0mm. The above γ, D1, D2 and D3 are all structural parameters of the honeycomb channel unit. Figure 4 The honeycomb channel unit in the middle frame is a single-layer honeycomb channel unit. On the front cavity blade basin side, 4 to 10 layers of honeycomb channel units are arranged radially, and 1 to 4 layers of honeycomb channel units are arranged laterally. On the back side of the front cavity blade, 4 to 10 layers of honeycomb channel units are arranged radially, and 1 to 5 layers of honeycomb channel units are arranged laterally. The above parameters need to be determined through one-dimensional flow iterative calculation and three-dimensional temperature field iterative calculation.

[0042] In the front cavity area of ​​the blade, a part of the cold air will directly enter the front cavity 1, but the hollowed-out front cavity 1 has no outlet on the lower edge plate 12, and the cold air will only swirl in the front cavity 1 without consuming the cold air. The front cavity 1 area of ​​the blade body relies on the tree-shaped channel 3, the front cavity blade basin side channel 4 and the front cavity blade back side channel 5 to fully meet the cooling needs of the front cavity area of ​​the blade, without the need for repeated cooling inside the blade, which can avoid consuming too much cold air; hollowing out the middle of the blade body is conducive to reducing the weight of the blade and reducing the production cost of the blade.

[0043] In the blade rear cavity area, the middle of the blade rear cavity 2 is hollowed out, and there is no cold air outlet on the lower edge plate 12 of the blade body. The cold air directly enters the rear cavity 2 along the radial direction. Part of the cold air swirls in the rear cavity cavity, and the other part of the cold air enters the rear cavity blade basin side channel 6 and the rear cavity blade back side channel 7 at different radial heights. Figure 4As shown, the cold air flows downward in the honeycomb channel of the front cavity area in the direction shown in the figure, and the honeycomb channel layout of the rear cavity area is rotated 90 degrees compared with the front cavity. In the cavity of the rear chamber 2, the cold air enters the rear cavity blade basin side channel 6 and the rear cavity blade back side channel 7 near the partition 10 respectively, and then the cold air continues to flow along the blade direction toward the trailing edge 14 area in a wall-cooled manner. The cold air on the blade basin side flows out from the blade basin side air film hole 8, and the cold air on the blade back side flows out from the blade back side air film hole 9. The cold air flowing out of the air film hole is discharged into the mainstream fuel gas, mixed with the mainstream fuel gas and flows toward the rotor blade row. In this embodiment, the parameter ranges of the honeycomb channel unit structure parameters γ, D1, D2, D3 and the channel seam width in the rear cavity area are consistent with those in the leading edge 13 area. 6 to 24 layers of honeycomb channel units are arranged radially on the side of the rear cavity blade basin, and 6 to 14 layers of honeycomb channel units are arranged transversely. 6 to 24 layers of honeycomb channel units are arranged radially on the back side of the rear cavity blade, and 6 to 16 layers of honeycomb channel units are arranged transversely. The above parameters need to be determined by one-dimensional flow iteration calculation and three-dimensional temperature field iteration calculation. Since the number of honeycomb channel layers involved in the rear cavity is large, and the static pressure distribution along the radial height of the air film hole outlet area of ​​the trailing edge 14 is uneven, in order to avoid the increase of the metal temperature gradient caused by the uneven flow distribution of the honeycomb channel in the radial direction of the rear cavity, the rear cavity area can be divided into 3 to 5 areas along the radial height. The honeycomb channels in the area are separated by the partition 10, and the airflows in different areas along the radial direction will not cross each other, thereby avoiding the uneven flow distribution caused by the uneven static pressure distribution along the radial direction of the cold air outlet of the trailing edge 14. In this embodiment, the diameter of the air film holes on the trailing edge 14 is 0.3 mm to 0.5 mm, and the number of the air film holes is 8 to 16.

[0044] In a second aspect, the present invention also provides an aircraft engine having the turbine guide blade of the present invention. By adopting a honeycomb bionic channel in the turbine guide blade, the cooling effect can be greatly improved, and the metal temperature on the blade surface can be significantly reduced. The leading edge 13 adopts a tree-shaped bionic channel, and the cooling effect is greatly improved, which can significantly reduce the metal temperature in the high-temperature area of ​​the leading edge 13 of the blade, and the required amount of cold air is small. Both the tree-shaped channel 3 and the honeycomb channel can control the cooling effect in different areas by adjusting their structural parameters and changing the heat exchange area and heat exchange coefficient in different areas, thereby realizing refined control of the cooling of the high-temperature and low-temperature areas of the blade, thereby reducing the temperature gradient of the blade metal.

[0045] Although the embodiments of the present invention have been described in conjunction with the accompanying drawings, those skilled in the art may make various modifications and variations without departing from the spirit and scope of the present invention, and such modifications and variations are all within the scope defined by the appended claims.

Claims

1. A turbine guide blade, characterized in that: include: The blade body has a tree-shaped channel (3) disposed at its front edge (13), and both ends of the tree-shaped channel (3) facing the upper edge plate (11) and the lower edge plate (12) are in communication with the external environment; A front chamber (1) is arranged in the blade body, one end of the front chamber (1) facing the upper edge plate (11) is in communication with the external environment, and the front chamber (1) is arranged close to the front edge (13) of the blade body; A rear chamber (2) is arranged in the blade body, the rear chamber (2) is isolated from the front chamber (1), the rear chamber (2) is arranged on the side of the front chamber (1) away from the leading edge (13) of the blade body, the end of the front chamber (1) facing the upper edge plate (11) is connected to the external environment, and an exhaust passage is arranged on the side of the rear chamber (2) away from the front chamber (1), and the exhaust passage is connected to the external environment.

2. The turbine guide blade according to claim 1, characterized in that: A front chamber blade basin side channel (4) is provided in the inner wall of the front chamber (1) on one side of the blade basin of the blade body, and both ends of the front chamber blade basin side channel (4) facing the upper edge plate (11) and the lower edge plate (12) are connected to the external environment, and a honeycomb channel is provided in the front chamber blade basin side channel (4).

3. The turbine guide blade according to claim 1, characterized in that: A front chamber blade back side channel (5) is provided in the inner wall of the front chamber (1) on the side facing the blade back of the blade body, and both ends of the front chamber blade back side channel (5) facing the upper edge plate (11) and the lower edge plate (12) are connected to the external environment, and a honeycomb channel is provided in the front chamber blade back side channel (5).

4. The turbine guide blade according to claim 1, characterized in that: A rear chamber blade basin side channel (6) is provided in the inner wall of the rear chamber (2) on one side of the blade basin facing the blade body, and one end of the rear chamber blade basin side channel (6) close to the front chamber (1) is connected to the rear chamber (2), and the other end of the rear chamber blade basin side channel (6) is connected to the exhaust channel, and a honeycomb channel is provided in the rear chamber blade basin side channel (6).

5. The turbine guide blade according to claim 4, characterized in that: The rear cavity blade basin side channels (6) are arranged in a plurality of groups at intervals in the radial direction of the blade body, and each group of the rear cavity blade basin side channels (6) is isolated from each other.

6. The turbine guide blade according to claim 1, characterized in that: A rear-cavity blade back side channel (7) is provided in the inner wall of the rear-cavity blade back side channel (2) on the side facing the blade back of the blade body; one end of the rear-cavity blade back side channel (7) close to the front chamber (1) is connected to the rear-cavity blade back side channel (2); the other end of the rear-cavity blade back side channel (7) is connected to the exhaust channel; a honeycomb-shaped channel is provided in the rear-cavity blade back side channel (7).

7. The turbine guide vane according to claim 6, characterized in that: The back-cavity blade back-side channels (7) are arranged in a plurality of groups at intervals in the radial direction of the blade body, and each group of the back-cavity blade back-side channels (7) is isolated from each other.

8. The turbine guide vane according to any one of claims 1 to 7, characterized in that: The tree-shaped channel (3) comprises a radial channel (15) and a connecting channel (16); the radial channel (15) is arranged to penetrate the blade body in a radial direction; a plurality of radial channels (15) are arranged at intervals; the connecting channel (16) is connected between adjacent radial channels (15); and an angle between the connecting channel (16) and the radial channel (15) is 20° to 70°.

9. The turbine guide blade according to any one of claims 1 to 7, characterized in that: The exhaust passage comprises a blade basin side air film hole (8) and a blade back side air film hole (9), wherein the blade basin side air film hole (8) is arranged in the inner wall of the blade basin side of the blade body, and the blade back side air film hole (9) is arranged in the inner wall of the blade back side of the blade body, and the blade basin side air film hole (8) and the blade back side air film hole (9) both extend to the trailing edge area of ​​the blade body.

10. An aircraft engine, characterized in that: A turbine guide blade according to any one of claims 1 to 9.

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