An adjustable turbine blade

Abstract

The present application provides an adjustable turbine blade, belonging to the technical field of aerospace. Specifically, it includes a leading-edge fixed blade body and an adjustable blade body. The leading-edge fixed blade body is fixed relative to the turbine disk, and the adjustable blade body is rotatably arranged relative to the leading-edge fixed blade body. A circular arc-shaped groove is provided at the rear end of the leading-edge fixed blade body, and a circular arc-shaped protrusion matching the circular arc-shaped groove is provided at the front end of the adjustable blade body. A cold air collecting cavity is arranged inside the leading-edge fixed blade body. Impact outflow holes are arranged at intervals along the blade height direction on the circular arc-shaped groove, and a cold air outflow slit extending along the blade height direction is provided on the circular arc-shaped groove. The impact outflow holes communicate with the cold air collecting cavity, and the cold air outflow slit communicates with the cold air collecting cavity. The cold air outflow slit is closer to the pressure surface of the blade than the impact outflow holes. The present application solves the problem that gas leakage easily occurs in the adjustable blade body with a two-section structure in the prior art and improves the aerodynamic performance of the blade.

Description

Technical Field

[0001] This application relates to the field of aerospace, and particularly to an adjustable turbine blade. Background Art

[0002] Hu Songyan. Variable Geometry Turbines and Their Design Features. Aeroengine, 1996(03): 21-26. The literature discloses that from the perspective of variable geometry turbine configurations, the rotating shaft type adjustable variable geometry turbine configuration is one of the commonly used engineering solutions; Li Feng. Application of Variable Geometry Turbines in Fighter Engines. Foreign Aviation, 1978, (8): 13-20. The literature discloses that the variable cycle engine XF120 developed by GE Corporation uses the variable geometry turbine technology with adjustable throat area of the turbine guide vane. The traditional all-metal rotating shaft type adjustable variable geometry blade solution requires a large amount of cooling air at the leading edge and rotating shaft parts of the blade to cool the blade to prevent the blade from being burned by high-temperature gas, which also brings great challenges to the control accuracy of the rotation angle, posing challenges to the engineering application and long-term service of variable geometry turbine blades.

[0003] The adjustable turbine blade is characterized in that the whole blade is divided into two typical components, a fixed blade and an adjustable blade, to achieve the rotation adjustment of the blade. However, due to the existence of a rotational gap between the two parts of the blade under the combined configuration, and when the turbine blade is working, the gas pressure on the pressure surface of the blade is higher than that on the suction surface, which causes the high-temperature gas to leak from the pressure surface of the blade to the suction surface through the rotational gap, resulting in the overheating of the metal blade body due to gas erosion and at the same time reducing the aerodynamic performance of the overall blade. Summary of the Invention

[0004] In view of this, this application provides an adjustable turbine blade, which solves the problem of easy gas leakage in the adjustable blade body with a two-section structure in the prior art and improves the aerodynamic performance of the blade.

[0005] An adjustable turbine blade provided by this application adopts the following technical solutions:

[0006] An adjustable turbine blade includes a leading-edge fixed blade body and an adjustable blade body. The leading-edge fixed blade body is fixed relative to the turbine disk, and the adjustable blade body is rotatably arranged relative to the leading-edge fixed blade body. A circular arc groove is provided at the rear end of the leading-edge fixed blade body, and a circular arc protrusion matching the circular arc groove is provided at the front end of the adjustable blade body. A cold air collecting cavity is arranged inside the leading-edge fixed blade body. Impact outflow holes are provided on the circular arc groove and are sequentially and spacedly distributed along the blade height direction. A cold air outflow slit extending along the blade height direction is provided on the circular arc groove. The impact outflow holes communicate with the cold air collecting cavity, and the cold air outflow slit communicates with the cold air collecting cavity. The cold air outflow slit is closer to the pressure surface of the blade than the impact outflow holes. The cold air flowing out from the cold air outflow slit flows through the pressure surface of the blade and then reaches the trailing edge of the blade.

[0007] Optionally, a current-limiting rib extending along the blade height direction is provided on the circular arc groove, and the current-limiting rib is closer to the suction surface of the blade than the impact outflow holes.

[0008] Optionally, a first mating rib and a second mating rib extending along the blade height direction are provided on the circular arc protrusion, and the current-limiting rib is assembled between the first mating rib and the second mating rib.

[0009] Optionally, the first mating rib is located on the side of the current-limiting rib facing the pressure surface of the blade. At least one third mating rib extending along the blade height direction is further provided on the circular arc protrusion. The third mating ribs are distributed on the side of the first mating rib facing away from the second mating rib. When the first mating rib abuts against the current-limiting rib, the third mating rib closest to the pressure surface is closer to the pressure surface of the blade than the impact outflow holes. Part of the cold air flowing out from the impact outflow holes sequentially flows through the first mating rib, the second mating rib, and the pressure surface of the blade and then reaches the trailing edge of the blade.

[0010] Optionally, when the second mating rib abuts against the current-limiting rib, the cold air outflow slit is located on the side of the third mating rib closest to the pressure surface of the blade or the side of the first mating rib facing the pressure surface of the blade.

[0011] Optionally, rotating shafts are fixed at both the root end and the tip end of the adjustable blade body. The rotating shafts are rotatably arranged relative to the turbine disk. The adjustable blade body is hollow, and a trailing edge split slit communicating with the internal space of the adjustable blade body is provided at the trailing edge of the adjustable blade body. A channel extending along the axial direction of the rotating shaft is provided on the rotating shaft, and the channel communicates with the internal space of the adjustable blade body.

[0012] Optionally, the leading-edge fixed blade body includes a ceramic matrix composite material housing and a metal impact duct. A through hole along the blade height direction is provided inside the ceramic matrix composite material housing. The metal impact duct is located in the through hole, and the metal impact duct and the inner wall of the through hole are spaced apart. The two ends of the metal impact duct and the ceramic matrix composite material housing are hermetically arranged. The area between the metal impact duct and the inner wall of the through hole forms the cold air plenum chamber. A plurality of impact holes communicating with the cold air plenum chamber are provided on the side wall of the metal impact duct.

[0013] Optionally, leading-edge impact holes are sequentially distributed along the blade height direction on the side wall of the metal impact duct corresponding to the blade leading edge. Suction surface impact holes are sequentially distributed along the blade height direction on the side wall of the metal impact duct corresponding to the blade suction surface. Trailing-edge impact holes are sequentially distributed along the blade height direction on the side wall of the metal impact duct corresponding to the blade trailing edge.

[0014] Optionally, the current-limiting rib is made of ceramic matrix composite material, and the current-limiting rib and the ceramic matrix composite material housing are integrally provided.

[0015] Optionally, the adjustable blade body, the first mating rib, the second mating rib, and the third mating rib are made of metal, and the adjustable blade body, the first mating rib, the second mating rib, and the third mating rib are integrally provided.

[0016] In summary, the present application includes the following beneficial technical effects:

[0017] After the cold air enters the cold air plenum chamber, the cold air flows out from the cold air outflow slit and the impact outflow holes. After the cold air flowing out from the cold air outflow slit reaches the side of the arc-shaped protrusion close to the blade pressure surface, it flows through the pressure surface of the blade and finally reaches the trailing edge of the blade, cooling the leading-edge fixed blade body and the pressure surface of the blade. Moreover, the cold air flowing from the cold air outflow slit to the pressure surface reduces the hot gas flowing into the rotation gap between the leading-edge fixed blade body and the adjustable blade body, reducing the leakage of hot gas from the blade pressure surface to the suction surface and ensuring the aerodynamic performance of the turbine adjustable blade.

[0018] At the same time, after the cold air flowing out from the impact outflow holes reaches the gap between the arc-shaped protrusion and the arc-shaped groove, part of it flows towards the suction surface of the blade and part flows towards the pressure surface of the blade. Finally, it reaches the trailing edge of the blade after flowing through the suction surface of the blade. The cold air cools the adjustable turbine blade from entering the plenum chamber to flowing to the trailing edge of the blade. Moreover, the cold air flowing out from the impact outflow holes blocks the hot gas on the pressure surface of the blade, reducing the leakage of hot gas from the blade pressure surface to the suction surface and ensuring the aerodynamic performance of the turbine adjustable blade. Description of the Drawings

[0019] To more clearly illustrate the technical solutions of the embodiments of the present application, the accompanying drawings required for the embodiments will be briefly introduced below. Obviously, the accompanying drawings in the following description are only some embodiments of the present application. For those of ordinary skill in the art, without creative efforts, other accompanying drawings can be obtained based on these drawings.

[0020] Figure 1 It is a schematic diagram of the overall structure of the adjustable turbine blade of the present application;

[0021] Figure 2 It is a schematic diagram of the overall structure of the front-edge fixed blade body of the present application;

[0022] Figure 3 It is a schematic cross-sectional structure diagram of the ceramic matrix composite material shell of the present application;

[0023] Figure 4 It is a schematic explosion structure diagram of the front-edge fixed blade body of the present application;

[0024] Figure 5 It is a schematic structure diagram of the adjustable turbine blade of the present application from another perspective;

[0025] Figure 6 It is a schematic diagram of the gas and cold air flow directions on the adjustable turbine blade of the present application;

[0026] Figure 7 It is a schematic structure diagram of the adjustable blade body of the present application rotated to different angles;

[0027] Figure 8 It is a schematic diagram of the included angles of the first mating rib, the second mating rib, and the third mating rib of the present application;

[0028] Figure 9 It is a schematic diagram of the dimension marking of the flow-limiting rib of the present application.

[0029] Explanation of reference numerals: 1. Front-edge fixed blade body; 11. Ceramic matrix composite material flow-blocking plate; 12. Impinging outflow hole; 13. Cold air outflow slit; 14. Flow-limiting rib; 2. Metal impinging duct; 21. Front-edge impinging hole; 22. Suction surface impinging hole; 23. Trailing-edge impinging hole; 3. Adjustable blade body; 31. Rotating shaft; 32. Trailing-edge split; 33. First mating rib; 34. Second mating rib; 35. Third mating rib. Detailed implementation manners

[0030] The embodiments of the present application will be described in detail below with reference to the accompanying drawings.

[0031] The following describes the implementation manners of the present application through specific specific examples. Those skilled in the art can easily understand other advantages and effects of the present application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The present application can also be implemented or applied through other different specific implementation manners. Various details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, without conflict, the following embodiments and the features in the embodiments can be combined with each other. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without making creative efforts belong to the scope protected by the present application.

[0032] It should be noted that the following describes various aspects of the embodiments within the scope of the appended claims. It should be apparent that the aspects described herein can be embodied in a wide variety of forms, and any specific structure and / or function described herein is illustrative only. Based on the present application, those skilled in the art should understand that one aspect described herein can be implemented independently of any other aspect, and two or more of these aspects can be combined in various ways. For example, any number of the aspects described herein can be used to implement the device and / or practice the method. Additionally, this device and / or this method can be implemented using other structures and / or functions in addition to one or more of the aspects described herein.

[0033] It also needs to be noted that the diagrams provided in the following embodiments only schematically illustrate the basic concept of the present application. The diagrams only show the components related to the present application and are not drawn according to the number, shape, and size of the components in actual implementation. The type, quantity, and proportion of each component in its actual implementation can be arbitrarily changed, and the component layout type may also be more complex.

[0034] In addition, in the following description, specific details are provided to facilitate a thorough understanding of the examples. However, those skilled in the art will understand that the described aspects can be practiced without these specific details.

[0035] An embodiment of the present application provides an adjustable turbine blade.

[0036] Such as Figures 1 to 3As shown, an adjustable turbine blade includes a leading-edge fixed blade body 1 and an adjustable blade body 3. The leading-edge fixed blade body 1 is fixed relative to the turbine disk, and the adjustable blade body 3 is rotatably arranged relative to the leading-edge fixed blade body 1. A circular arc-shaped groove is provided at the rear end of the leading-edge fixed blade body 1, and a circular arc-shaped protrusion matching the circular arc-shaped groove is provided at the front end of the adjustable blade body 3. The circular arc-shaped protrusion, the circular arc-shaped groove, and the axis of rotation of the adjustable blade are coaxially arranged, and the axis of the axis of rotation of the adjustable blade is perpendicular to the axial direction of the turbine disk. A cold air collecting cavity is provided inside the leading-edge fixed blade body 1, and the cold air collecting cavity communicates with a cold air supply source. Impact outflow holes 12 are provided on the circular arc-shaped groove and are distributed at intervals in the blade height direction. A cold air outflow slit 13 extending in the blade height direction is provided on the circular arc-shaped groove. The impact outflow holes 12 communicate with the cold air collecting cavity, and the cold air outflow slit 13 communicates with the cold air collecting cavity. The cold air outflow slit 13 is closer to the pressure surface of the blade than the impact outflow holes 12. In the embodiment of the present application, a plurality of cold air outflow slits 13 are provided, and the plurality of cold air outflow slits 13 are arranged at intervals in the blade height direction. Among them, the impact outflow holes 12 are quadrilateral holes, and the cold air outflow slits 13 are strip-shaped and rectangular.

[0037] As Figure 6 shown, wherein the dotted line is the combustion gas and the solid line is the cold air; in the embodiment of the present application, after the cold air enters the cold air collecting cavity, the cold air flows out from the cold air outflow slit 13 and the impact outflow holes 12. After the cold air flowing out from the cold air outflow slit 13 reaches the side of the circular arc-shaped protrusion close to the pressure surface of the blade, it flows through the pressure surface of the blade and finally reaches the trailing edge of the blade, cooling the leading-edge fixed blade body 1 and the pressure surface of the blade. Moreover, the cold air flowing from the cold air outflow slit 13 to the pressure surface can reduce the combustion gas flowing into the rotation gap between the leading-edge fixed blade body 1 and the adjustable blade body 3, reduce the leakage of the combustion gas from the pressure surface of the blade to the suction surface, and ensure the aerodynamic performance of the turbine adjustable blade. At the same time, the cold air flowing out from the impact outflow holes 12 reaches the gap between the circular arc-shaped protrusion and the circular arc-shaped groove, and part of it flows to the suction surface of the blade and part of it flows to the pressure surface of the blade. Finally, it passes through the suction surface of the blade and reaches the trailing edge of the blade. The cold air cools the adjustable turbine blade from entering the collecting cavity to flowing to the trailing edge of the blade; moreover, the cold air flowing out from the impact outflow holes 12 blocks the combustion gas on the pressure surface of the blade, reduces the leakage of the combustion gas from the pressure surface of the blade to the suction surface, and ensures the aerodynamic performance of the turbine adjustable blade. In the embodiment of the present application, the pressure of the cold air is greater than the pressure of the combustion gas, which can enable the cold air to have a better blocking effect on the combustion gas.

[0038] As Figures 2 to 4As shown in the figure, the leading-edge fixed blade body 1 includes a ceramic matrix composite material housing and a metal impact conduit 2. A through hole extending in the blade height direction is provided inside the ceramic matrix composite material housing. The metal impact conduit 2 is located in the through hole, and there is a gap between the metal impact conduit 2 and the inner wall of the through hole. The two ends of the metal impact conduit 2 are hermetically sealed with the ceramic matrix composite material housing. The area between the metal impact conduit 2 and the inner wall of the through hole forms the cold air collecting chamber, and a plurality of impact holes communicating with the cold air collecting chamber are provided on the side wall of the metal impact conduit 2.

[0039] A flow-limiting rib 14 extending in the blade height direction is provided on the arc-shaped groove. The flow-limiting rib 14 is closer to the suction surface of the blade than the impact outflow hole 12. The flow-limiting rib 14 is made of ceramic matrix composite material and is integrally provided with the ceramic matrix composite material housing. The flow-limiting rib 14 can play a role in blocking the gas, further reducing the leakage of gas from the pressure surface to the suction surface of the blade.

[0040] In the embodiment of the present application, the ceramic matrix composite material housing has good temperature resistance, which can reduce the consumption of cold air in the leading-edge part and overcome the problem of overheating of the metal leading edge. The setting of the metal impact conduit 2 can improve the bearing strength of the leading-edge part. The inner and outer walls of the leading-edge fixed blade body 1 and the metal impact conduit 2 are in a fin shape in the cross section perpendicular to the blade height direction. The metal impact conduit 2 is connected to the cold air supply source. After the cold air enters the metal impact conduit 2, it enters the intake chamber through the impact holes, cooling the metal impact conduit 2 and providing cold air for the collecting chamber at the same time. The specific sealing structure between the two ends of the metal impact conduit 2 and the ceramic matrix composite material housing is as follows: ceramic matrix composite material sealing plates 11 are provided at both ends of the through hole of the ceramic matrix composite material housing. The ceramic matrix composite material sealing plates 11 are integrally provided with the ceramic matrix composite material housing. The inner circle of the ceramic matrix composite material sealing plate 11 fits the outer wall of the metal impact conduit 2, thereby sealing the two ends of the metal impact conduit 2 and the ends of the ceramic matrix composite material housing.

[0041] The impact holes on the metal impact conduit 2 are specifically arranged as follows: leading-edge impact holes 21 are sequentially distributed in the blade height direction on the side wall of the metal impact conduit 2 corresponding to the leading edge of the blade, suction surface impact holes 22 are sequentially distributed in the blade height direction on the side wall of the metal impact conduit 2 corresponding to the suction surface of the blade, and trailing-edge impact holes 23 are sequentially distributed in the blade height direction on the side wall of the metal impact conduit 2 corresponding to the trailing edge of the blade.

[0042] As Figure 1 and Figure 5As shown, rotating shafts 31 are fixed to both the root end and the tip end of the adjustable blade body 3. The rotating shafts 31 are rotatably arranged relative to the turbine disk. The adjustable blade body 3 is hollow, and a trailing-edge split 32 communicating with the internal space of the adjustable blade body 3 is provided at the trailing edge of the adjustable blade body 3. A channel along the axial direction of the rotating shaft 31 is provided on the rotating shaft 31, and the channel communicates with the internal space of the adjustable blade body 3. Cold air is communicated through the channel of the rotating shaft 31. After the cold air enters the adjustable blade body 3 through the rotating shaft 31, it flows out from the trailing-edge split 32, covering the surface of the blade trailing edge, isolating the combustion gas and cooling the adjustable blade body 3 at the same time.

[0043] First mating ridges 33 and second mating ridges 34 extending in the blade height direction are provided on the arc-shaped protrusion. The flow-limiting ridge 14 is assembled between the first mating ridges 33 and the second mating ridges 34. When the adjustable blade body 3 rotates forward and backward, the first mating ridges 33 and the second mating ridges 34 alternately approach the flow-limiting ridge 14. While restricting the rotation range of the adjustable blade body 3, the first mating ridges 33 and the second mating ridges 34 cooperate with the flow-limiting ridge 14 to jointly block the combustion gas, further reducing the leakage of the combustion gas from the pressure side to the suction side of the blade.

[0044] As Figure 5 and Figure 6 As shown, the first mating ridges 33 are located on the side of the flow-limiting ridge 14 facing the pressure side of the blade. At least one third mating ridge 35 extending in the blade height direction is further provided on the arc-shaped protrusion. The third mating ridges 35 are distributed on the side of the first mating ridges 33 facing away from the second mating ridges 34. When the first mating ridges 33 abut against the flow-limiting ridge 14, the third mating ridge 35 closest to the pressure side is closer to the pressure side of the blade than the impinging outflow holes 12, as Figure 8 As shown, part of the cold air flowing out from the impinging outflow holes 12 flows through the first mating ridges 33, the second mating ridges 34, and the pressure side of the blade in sequence and then reaches the trailing edge of the blade. Another part of the cold air flows through the third mating ridges 35 and then reaches the trailing edge of the blade after passing through the pressure side of the blade. In the embodiment of the present application, one third mating ridge 35 is provided. The third mating ridge 35 is always located on the side of the impinging outflow holes 12 facing the pressure side of the blade. The cold air flowing out from the impinging outflow holes 12 impinges between the third mating ridge 35 and the first mating ridge 33 and then flows toward the flow-limiting ridge 14.

[0045] When the second mating ridges 34 abut against the flow-limiting ridge 14, the cold air outflow slit 13 is located on the side of the third mating ridge 35 closest to the pressure side of the blade facing the pressure side of the blade. This enables the cold air flowing out from the cold air outflow slit 13 to quickly reach the pressure side of the blade, improving the blocking effect on the combustion gas.

[0046] In the embodiments of the present application, the adjustable blade body 3, the rotating shaft 31, the first mating rib 33, the second mating rib 34, and the third mating rib 35 are made of metal, and the adjustable blade body 3, the first mating rib 33, the second mating rib 34, and the third mating rib 35 are integrally provided.

[0047] The initial state of the adjustable blade body 3 in the embodiments of the present application is as Figure 7 shown in b in the figure. During operation, if it is necessary to reduce the gas flow rate passing through the blade, the adjustable blade body 3 can be rotated counterclockwise, as Figure 7 shown in c in the figure. If it is necessary to increase the gas flow rate passing through the blade, the adjustable blade body 3 can be rotated clockwise, as Figure 7 shown in a in the figure.

[0048] As Figure 8 and Figure 9 shown, in the embodiments of the present application, the cross-sections of the current-limiting rib 14, the first mating rib 33, the second mating rib 34, and the third mating rib 35 are triangular prisms with rounded top angles. The rounded top angle radius r, side length Lx, and height Ly of the triangular prism with rounded top angles of the current-limiting rib 14, the first mating rib 33, the second mating rib 34, and the third mating rib 35 are 0.2 mm, 1.8 mm, and 68 mm respectively; the top angle β is 60°. Moreover, the current-limiting rib 14, the first mating rib 33, the second mating rib 34, and the third mating rib 35 all protrude along the radial direction of the rotating shaft 31 of the adjustable blade body. The included angle α between the first mating rib 33, the second mating rib 34, and the third mating rib 35 is 35°, and there is a gap of 0.2 mm between the first mating rib 33, the second mating rib 34, and the third mating rib 35 and the inner wall of the arc-shaped groove.

[0049] The above is only the specific implementation manner of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the technical field of the present application within the technical scope disclosed by the present application should be covered within the protection scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. An adjustable turbine blade, comprising a leading-edge fixed blade body (1) and an adjustable blade body (3), wherein the leading-edge fixed blade body (1) is fixed relative to the turbine disk, and the adjustable blade body (3) is rotatably arranged relative to the leading-edge fixed blade body (1), and is characterized in that, The rear end of the fixed leading-edge blade body (1) is provided with an arc-shaped groove, and the front end of the adjustable blade body (3) is provided with an arc-shaped protrusion matching the arc-shaped groove. The fixed leading-edge blade body (1) is internally provided with a cold air collecting cavity. The arc-shaped groove is provided with impact outflow holes (12) spaced at intervals along the blade height direction, and the arc-shaped groove is provided with a cold air outflow slit (13) extending along the blade height direction. The impact outflow holes (12) communicate with the cold air collecting cavity, and the cold air outflow slit (13) communicates with the cold air collecting cavity. The cold air outflow slit (13) is closer to the pressure surface of the blade than the impact outflow holes (12). The cold air flowing out from the cold air outflow slit (13) reaches the trailing edge of the blade after flowing through the pressure surface of the blade. The arc-shaped groove is provided with a flow-limiting rib (14) extending along the blade height direction. The flow-limiting rib (14) is closer to the suction surface of the blade than the impact outflow holes (12).

2. The adjustable turbine blade according to claim 1, wherein The arc-shaped protrusion is provided with a first mating rib (33) and a second mating rib (34) extending along the blade height direction. The flow-limiting rib (14) is assembled between the first mating rib (33) and the second mating rib (34).

3. The adjustable turbine blade according to claim 2, wherein, The first mating rib (33) is located on the side of the flow-limiting rib (14) facing the pressure surface of the blade. The arc-shaped protrusion is further provided with at least one third mating rib (35) extending along the blade height direction. The third mating rib (35) is distributed on the side of the first mating rib (33) facing away from the second mating rib (34). When the first mating rib (33) abuts against the flow-limiting rib (14), the third mating rib (35) closest to the pressure surface is closer to the pressure surface of the blade than the impact outflow holes (12). Part of the cold air flowing out from the impact outflow holes (12) reaches the trailing edge of the blade after flowing through the first mating rib (33), the second mating rib (34), and the pressure surface of the blade in sequence.

4. The adjustable turbine blade according to claim 3, characterized in that, When the second mating rib (34) abuts against the flow-limiting rib (14), the cold air outflow slit (13) is located on the side of the third mating rib (35) closest to the pressure surface of the blade or the first mating rib (33) facing the pressure surface of the blade.

5. The adjustable turbine blade according to claim 1, characterized in that, The root end and the tip end of the adjustable blade body (3) are both fixed with a rotating shaft (31). The rotating shaft (31) is rotatably arranged relative to the turbine disk. The adjustable blade body (3) is hollow, and the trailing edge of the adjustable blade body (3) is provided with a trailing edge split (32) communicating with the internal space of the adjustable blade body (3). The rotating shaft (31) is provided with a channel along the axial direction of the rotating shaft (31). The channel communicates with the internal space of the adjustable blade body (3).

6. The adjustable turbine blade according to claim 4, characterized in that, The leading-edge fixed blade body (1) includes a ceramic matrix composite material shell and a metal impact conduit (2). A through hole along the blade height direction is provided inside the ceramic matrix composite material shell. The metal impact conduit (2) is located in the through hole, and the metal impact conduit (2) and the inner wall of the through hole are spaced apart. The two ends of the metal impact conduit (2) and the ceramic matrix composite material shell are hermetically arranged. The area between the metal impact conduit (2) and the inner wall of the through hole forms the cold air collecting cavity, and a plurality of impact holes communicating with the cold air collecting cavity are provided on the side wall of the metal impact conduit (2).

7. The adjustable turbine blade according to claim 6, wherein, Leading-edge impact holes (21) are sequentially distributed along the blade height direction on the side wall of the metal impact conduit (2) corresponding to the blade leading edge. Suction surface impact holes (22) are sequentially distributed along the blade height direction on the side wall of the metal impact conduit (2) corresponding to the blade suction surface. Trailing-edge impact holes (23) are sequentially distributed along the blade height direction on the side wall of the metal impact conduit (2) corresponding to the blade trailing edge.

8. The adjustable turbine blade according to claim 6, wherein The current-limiting rib (14) is made of ceramic matrix composite material, and the current-limiting rib (14) is integrally provided with the ceramic matrix composite material shell.

9. The adjustable turbine blade according to claim 4, wherein The adjustable blade body (3), the first mating rib (33), the second mating rib (34), and the third mating rib (35) are made of metal, and the adjustable blade body (3), the first mating rib (33), the second mating rib (34), and the third mating rib (35) are integrally provided.

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