Adjustable turbine blade

Abstract

The invention provides an adjustable turbine blade, and belongs to the technical field of aerospace, the adjustable turbine blade specifically comprises a front edge fixed blade body and an adjustable blade body, the front edge fixed blade body is fixed relative to a turbine disc, the adjustable blade body is rotationally arranged relative to the front edge fixed blade body, and an arc-shaped groove is formed in the rear end of the front edge fixed blade body; the front end of the adjustable blade body is provided with an arc-shaped protrusion matched with the arc-shaped groove, a cold air collecting cavity is formed in the front edge fixed blade body, impact outflow holes sequentially distributed at intervals in the blade height direction are formed in the arc-shaped groove, a cold air outflow seam extending in the blade height direction is formed in the arc-shaped groove, the impact outflow holes are communicated with the cold air collecting cavity, and the impact outflow holes are communicated with the cold air collecting cavity. The cold air outflow seams communicate with the cold air collecting cavity, and the cold air outflow seams are closer to the pressure faces of the blades than the impact outflow holes. The problem that in the prior art, an adjustable blade body of a two-section structure is prone to gas leakage is solved, and the pneumatic performance of the blade is improved.

Description

Technical Field

[0001] The present application relates to the field of aerospace, and in particular to an adjustable turbine blade. Background Art

[0002] Hu Songyan. Variable geometry turbine and its design features. Aero Engines, 1996(03):21-26. The literature discloses that from the perspective of variable geometry turbine configuration, the shaft-type variable geometry turbine configuration is one of the commonly used solutions in engineering; Li Feng. Application of variable geometry turbine in fighter engines. Foreign Aviation, 1978,(8):13-20. The literature discloses that the variable cycle engine XF120 developed by GE uses variable geometry turbine technology with adjustable turbine guide vane throat area. The traditional all-metal shaft-type variable geometry blade solution consumes a lot of cold air to cool the blade at the leading edge and shaft of the blade to prevent the blade from being burned by high-temperature combustion gas. At the same time, it brings great challenges to the control accuracy of the rotation angle, which brings challenges to the engineering application and long-term service of variable geometry turbine blades.

[0003] The characteristic of adjustable turbine blades is that the entire blade is divided into two typical components, a fixed blade and an adjustable blade, to achieve the adjustable rotation of the blade. However, due to the rotation gap between the two parts of the blade in the combined configuration, the gas pressure on the pressure surface of the turbine blade is higher than the gas pressure on the suction surface when the turbine blade is working, which causes the high-temperature gas to leak from the pressure surface of the blade to the suction surface through the rotation gap, causing the metal blade to be overheated due to the scouring of the gas, while reducing the aerodynamic performance of the entire blade. Summary of the invention

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

[0005] The adjustable turbine blade provided in this application adopts the following technical solution: The adjustable turbine blade comprises a leading edge fixed blade body and an adjustable blade body, the leading edge fixed blade body being fixed relative to a turbine wheel disk, and the adjustable blade body being rotatably arranged relative to the leading edge fixed blade body, the rear end of the leading edge fixed blade body being provided with an arc-shaped groove, the front end of the adjustable blade body being provided with an arc-shaped protrusion matching the arc-shaped groove, a cold air collecting cavity being provided inside the leading edge fixed blade body, the arc-shaped groove being provided with impact outlet holes distributed in sequence at intervals along the blade height direction, the arc-shaped groove being provided with a cold air outlet flow slot extending along the blade height direction, the impact outlet hole being connected to the cold air collecting cavity, the cold air outlet flow slot being connected to the cold air collecting cavity, the cold air outlet flow slot being closer to the pressure surface of the blade than the impact outlet hole, and the cold air flowing out of the cold air outlet flow slot reaches the trailing edge of the blade after passing through the pressure surface of the blade.

[0006] Optionally, the arc-shaped groove is provided with a flow-limiting convex strip extending along the blade height direction, and the flow-limiting convex strip is closer to the suction surface of the blade than the impact outlet hole.

[0007] Optionally, the arc-shaped protrusion is provided with a first matching protrusion and a second matching protrusion extending along the blade height direction, and the flow-limiting protrusion is assembled between the first matching protrusion and the second matching protrusion.

[0008] Optionally, the first mating ridge is located on the side of the flow limiting ridge facing the pressure surface of the blade, and the arc-shaped protrusion is also provided with at least one third mating ridge extending along the blade height direction, and the third mating ridge is distributed on the side of the first mating ridge facing away from the second mating ridge, and when the first mating ridge abuts against the flow limiting ridge, the third mating ridge closest to the pressure surface is closer to the pressure surface of the blade than the impact outlet hole, and part of the cold air flowing out of the impact outlet hole flows through the first mating ridge, the second mating ridge and the blade pressure surface in turn and reaches the trailing edge of the blade.

[0009] Optionally, when the second mating ridge abuts against the flow-limiting ridge, the cold air outflow slot is located on the third mating ridge closest to the blade pressure surface or on the side of the first mating ridge facing the blade pressure surface.

[0010] Optionally, a rotating shaft is fixed to the root end and the tip end of the adjustable blade, and the rotating shaft is rotatably arranged relative to the turbine wheel. The adjustable blade is hollow, and the trailing edge of the adjustable blade is provided with a trailing edge slit connected to the internal space of the adjustable blade. The rotating shaft is provided with a channel along the axial direction of the rotating shaft, and the channel is connected to the internal space of the adjustable blade.

[0011] Optionally, the leading edge fixed blade body includes a ceramic-based composite material shell and a metal impact duct, the ceramic-based composite material shell is provided with a through hole along the blade height direction, the metal impact duct is located in the through hole, 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-based composite material shell are sealed, the area between the metal impact duct and the inner wall of the through hole forms the cold air collecting cavity, and the side wall of the metal impact duct is provided with a plurality of impact holes connected to the cold air collecting cavity.

[0012] Optionally, the side wall of the metal impact duct corresponding to the leading edge of the blade is provided with leading edge impact holes distributed sequentially along the blade height direction, the side wall of the metal impact duct corresponding to the suction surface of the blade is provided with suction surface impact holes distributed sequentially along the blade height direction, and the side wall of the metal impact duct corresponding to the trailing edge of the blade is provided with trailing edge impact holes distributed sequentially along the blade height direction.

[0013] Optionally, the current-limiting ridge is made of a ceramic-based composite material, and the current-limiting ridge and the ceramic-based composite material shell are integrally arranged.

[0014] Optionally, the adjustable blade body, the first matching ridge, the second matching ridge and the third matching ridge are made of metal, and the adjustable blade body, the first matching ridge, the second matching ridge and the third matching ridge are integrally arranged.

[0015] In summary, this application includes the following beneficial technical effects: After the cold air enters the cold air collecting cavity, the cold air flows out from the cold air outlet slit and the impact outlet hole. After the cold air flowing out from the cold air outlet slit reaches the side of the 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 and the pressure surface of the blade. In addition, the cold air flowing from the cold air outlet slit to the pressure surface reduces the gas flowing to the rotating gap between the leading edge fixed blade body and the adjustable blade body, reduces the leakage of gas from the pressure surface of the blade to the suction surface, and ensures the aerodynamic performance of the turbine adjustable blade.

[0016] At the same time, the cold air flowing out from the impact outlet hole reaches the gap between the arc-shaped protrusion and the arc-shaped groove, and then part of it flows toward the suction surface of the blade, and part of it flows toward the pressure surface of the blade, and finally reaches the trailing edge of the blade through the suction surface of the blade. The cold air cools the adjustable turbine blade from entering the air collecting cavity to flowing to the trailing edge of the blade; and the cold air flowing out from the impact outlet hole blocks the combustion gas on the pressure surface of the blade, reducing the leakage of combustion gas from the pressure surface of the blade to the suction surface, thereby ensuring the aerodynamic performance of the adjustable turbine blade. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0018] Figure 1 This is a schematic diagram of the overall structure of the adjustable turbine blades of this application; Figure 2 This is a schematic diagram of the overall structure of the leading edge fixed blade body of this application; Figure 3 This is a schematic diagram of the cross-sectional structure of the ceramic matrix composite material housing of the present application; Figure 4 A schematic diagram of the explosion structure for fixing the blade at the leading edge of this application; Figure 5 This is a schematic structural diagram of the adjustable turbine blade of the present application from another perspective; Figure 6A schematic diagram of the flow of gas and cold air on the adjustable turbine blades of this application; Figure 7 A schematic diagram of the structure for applying for an adjustable blade to rotate to different angles; Figure 8 This is a schematic diagram of the angles of the first matching convex strip, the second matching convex strip, and the third matching convex strip of the present application; Fig. 9 This is a schematic diagram of the dimension marking of the current limiting convex strip of this application.

[0019] Explanation of the reference numerals: 1. fixed leading edge blade; 11. ceramic matrix composite material sealing plate; 12. impact outlet hole; 13. cold air outlet slot; 14. flow limiting rib; 2. metal impact duct; 21. leading edge impact hole; 22. suction surface impact hole; 23. trailing edge impact hole; 3. adjustable blade; 31. rotating shaft; 32. trailing edge splitting slot; 33. first matching rib; 34. second matching rib; 35. third matching rib. DETAILED DESCRIPTION

[0020] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0021] The following describes the implementation methods of the present application through specific examples, and those skilled in the art can easily understand other advantages and effects of the present application from the contents 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 methods, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, in the absence of 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 ordinary technicians in the field without making creative work belong to the scope of protection of the present application.

[0022] It should be noted that various aspects of the embodiments within the scope of the appended claims are described below. 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 merely illustrative. Based on the present application, it should be understood by those skilled in the art that an 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 aspects described herein can be used to implement the device and / or practice the method. In addition, other structures and / or functionalities other than one or more of the aspects described herein can be used to implement this device and / or practice this method.

[0023] It should also be noted that the illustrations provided in the following embodiments are only schematic illustrations of the basic concept of the present application. The illustrations only show the components related to the present application rather than being drawn according to the number, shape and size of the components in actual implementation. In actual implementation, the type, quantity and proportion of each component may be changed at will, and the component layout may also be more complicated.

[0024] Additionally, in the following description, specific details are provided to facilitate a thorough understanding of the examples. However, it will be understood by those skilled in the art that the aspects described may be practiced without these specific details.

[0025] An embodiment of the present application provides an adjustable turbine blade.

[0026] like Figures 1 to 3 As shown, an adjustable turbine blade comprises 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, a circular arc groove is arranged at the rear end of the leading edge fixed blade body 1, and a circular arc protrusion matching the circular arc groove is arranged at the front end of the adjustable blade body 3, the circular arc protrusion, the circular arc groove and the rotating shaft of the adjustable blade are coaxially arranged, and the rotating shaft axis 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 is connected to a cold air supply source. The arc-shaped groove is provided with impact outlet holes 12 that are spaced in sequence along the blade height direction. The arc-shaped groove is provided with a cold air outlet slit 13 that extends along the blade height direction. The impact outlet hole 12 is connected to the cold air collecting cavity, and the cold air outlet slit 13 is connected to the cold air collecting cavity. The cold air outlet slit 13 is closer to the pressure surface of the blade than the impact outlet hole 12. In the embodiment of the present application, a plurality of cold air outlet slits 13 are provided, and the plurality of cold air outlet slits 13 are spaced in sequence along the blade height direction, wherein the impact outlet hole 12 is a quadrilateral hole, and the cold air outlet slit 13 is long and rectangular.

[0027] like Figure 6As shown, the dotted line is the 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 outlet slit 13 and the impact outlet hole 12. After the cold air flowing out from the cold air outlet slit 13 reaches the side of the 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. In addition, the cold air flowing from the cold air outlet slit 13 to the pressure surface can reduce the gas flowing to the rotation gap between the leading edge fixed blade body 1 and the adjustable blade body 3, reduce the leakage of 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 of the impact outlet hole 12 reaches the gap between the arc-shaped protrusion and the arc-shaped groove, and then flows to the suction surface of the blade, and then flows to the pressure surface of the blade, and finally passes through the suction surface of the blade to reach the trailing edge of the blade. The cold air cools the adjustable turbine blade from entering the gas collecting cavity to flowing to the trailing edge of the blade; and the cold air flowing out of the impact outlet hole 12 has a blocking effect on the gas on the pressure surface of the blade, reducing the leakage of gas from the pressure surface of the blade to the suction surface, and ensuring 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 gas, so that the cold air can have a better blocking effect on the gas.

[0028] like Figures 2 to 4 As shown, the leading edge fixed blade body 1 includes a ceramic-based composite shell and a metal impact duct 2, the ceramic-based composite shell is provided with a through hole along the blade height direction, the metal impact duct 2 is located in the through hole, the metal impact duct 2 and the inner wall of the through hole are spaced apart, the two ends of the metal impact duct 2 and the ceramic-based composite shell are sealed, the area between the metal impact duct 2 and the inner wall of the through hole forms the cold air collecting cavity, and the side wall of the metal impact duct 2 is provided with a plurality of impact holes connected to the cold air collecting cavity.

[0029] The arc-shaped groove is provided with a flow-limiting ridge 14 extending along the blade height direction, the flow-limiting ridge 14 is closer to the suction surface of the blade than the impact outlet hole 12, the flow-limiting ridge 14 is made of a ceramic-based composite material, and the flow-limiting ridge 14 and the ceramic-based composite material shell are integrally arranged. The flow-limiting ridge 14 can block the gas and further reduce the leakage of the gas from the pressure surface of the blade to the suction surface.

[0030] In the embodiment of the present application, the ceramic-based composite shell has good temperature resistance, which can reduce the consumption of cold air by the leading edge part and overcome the problem of overheating of the metal leading edge; the setting of the metal impact duct 2 can improve the bearing strength of the leading edge part, and the inner wall and outer wall of the leading edge fixed blade body 1 and the metal impact duct 2 are fin-shaped in the cross section perpendicular to the blade height direction. The metal impact duct 2 is connected to the cold air supply source, and the cold air enters the metal impact duct 2 and enters the air intake cavity after passing through the impact hole, cooling the metal impact duct 2 while providing cold air for the air collecting cavity. The sealing structure between the two ends of the metal impact duct 2 and the ceramic-based composite shell is specifically as follows: a ceramic-based composite sealing plate 11 is provided at both ends of the through hole of the ceramic-based composite shell, and the ceramic-based composite sealing plate 11 and the ceramic-based composite shell are integrally arranged, and the inner ring of the ceramic-based composite sealing plate 11 fits the outer wall of the metal impact duct 2, thereby sealing the two ends of the metal impact duct 2 and the end of the ceramic-based composite shell.

[0031] The impact holes on the metal impact duct 2 are specifically configured as follows: the side wall of the metal impact duct 2 corresponding to the leading edge of the blade is provided with leading edge impact holes 21 distributed sequentially along the blade height direction; the side wall of the metal impact duct 2 corresponding to the suction surface of the blade is provided with suction surface impact holes 22 distributed sequentially along the blade height direction; the side wall of the metal impact duct 2 corresponding to the trailing edge of the blade is provided with trailing edge impact holes 23 distributed sequentially along the blade height direction.

[0032] like Figure 1 and Figure 5 As shown, the blade root and blade tip 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 wheel, the adjustable blade body 3 is hollow, and the trailing edge of the adjustable blade body 3 is provided with a trailing edge slit 32 connected to the internal space of the adjustable blade body 3, and the rotating shaft 31 is provided with a channel along the axial direction of the rotating shaft 31, and the channel is connected to the internal space of the adjustable blade body 3. The channel of the rotating shaft 31 is connected to the cold air, and the cold air enters the adjustable blade body 3 through the rotating shaft 31 and then flows out from the trailing edge slit 32, covering the trailing edge surface of the blade, isolating the gas and cooling the adjustable blade body 3 at the same time.

[0033] The arc-shaped protrusion is provided with a first matching ridge 33 and a second matching ridge 34 extending in the blade height direction, and the flow-limiting ridge 14 is assembled between the first matching ridge 33 and the second matching ridge 34. When the adjustable blade 3 rotates forward and reverse, the first matching ridge 33 and the second matching ridge 34 alternately approach the flow-limiting ridge 14, and while limiting the rotation range of the adjustable blade 3, the first matching ridge 33 and the second matching ridge 34 cooperate with the flow-limiting ridge 14 to block the gas, further reducing the leakage of the gas from the pressure surface to the suction surface of the blade.

[0034] like Figure 5 and Figure 6 As shown, the first matching ridge 33 is located on the side of the flow limiting ridge 14 facing the pressure surface of the blade, and the arc-shaped protrusion is further provided with at least one third matching ridge 35 extending along the blade height direction, and the third matching ridge 35 is distributed on the side of the first matching ridge 33 facing away from the second matching ridge 34, and when the first matching ridge 33 abuts against the flow limiting ridge 14, the third matching ridge 35 closest to the pressure surface is closer to the pressure surface of the blade than the impact outlet hole 12, as shown in FIG. Figure 8 As shown, part of the cold air flowing out of the impact outlet hole 12 flows through the first matching ridge 33, the second matching ridge 34 and the blade pressure surface in sequence and reaches the trailing edge of the blade, and another part of the cold air flows through the third matching ridge 35 and then passes through the blade pressure surface and reaches the trailing edge of the blade. In the embodiment of the present application, a third matching ridge 35 is provided, and the third matching ridge 35 is always located on the side of the impact outlet hole 12 facing the blade pressure surface. After the cold air flowing out of the impact outlet hole 12 impacts between the third matching ridge 35 and the first matching ridge 33, it flows to the side of the flow limiting ridge 14.

[0035] When the second matching convex strip 34 abuts against the flow limiting convex strip 14, the cold air outlet slit 13 is located on the side of the third matching convex strip 35 closest to the blade pressure surface facing the blade pressure surface, so that the cold air flowing out of the cold air outlet slit 13 can quickly reach the pressure surface side of the blade, thereby improving the blocking effect on the gas.

[0036] In the embodiment of the present application, the adjustable blade body 3, the rotating shaft 31, the first matching ridge 33, the second matching ridge 34 and the third matching ridge 35 are made of metal, and the adjustable blade body 3, the first matching ridge 33, the second matching ridge 34 and the third matching ridge 35 are integrally arranged.

[0037] The initial state of the adjustable blade 3 in the embodiment of the present application is as follows Figure 7 As shown in b, if the gas flow through the blade needs to be reduced during operation, the adjustable blade body 3 can be rotated counterclockwise, as shown in FIG. Figure 7 As shown in Figure c, if the gas flow through the blade needs to be increased, the adjustable blade body 3 can be rotated clockwise, as shown in Figure c. Figure 7 As shown in a.

[0038] like Figure 8 and Fig. 9As shown, in the embodiment of the present application, the cross-section of the flow-limiting convex strip 14, the first matching convex strip 33, the second matching convex strip 34 and the third matching convex strip 35 is a triangular prism with rounded apex angles, and the apex angle rounding radius r, side length Lx, and height Ly of the first matching convex strip 33, the second matching convex strip 34 and the third matching convex strip 35 of the flow-limiting convex strip 14 in the shape of a triangular prism with rounded apex angles are 0.2 mm, 1.8 mm, and 68 mm respectively; the apex angle β is 60°. Moreover, the flow-limiting convex strip 14, the first matching convex strip 33, the second matching convex strip 34 and the third matching convex strip 35 all protrude in the radial direction of the adjustable blade body rotating shaft 31, and the angle α of the first matching convex strip 33, the second matching convex strip 34 and the third matching convex strip 35 is 35°, and the first matching convex strip 33, the second matching convex strip 34 and the third matching convex strip 35 all retain a gap of 0.2 mm with the inner wall of the arc-shaped groove.

[0039] The above is only a specific implementation 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 a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. An adjustable turbine blade, comprising a fixed leading edge blade (1) and an adjustable blade (3), wherein the fixed leading edge blade (1) is fixed relative to a turbine wheel, and the adjustable blade (3) is rotatably arranged relative to the fixed leading edge blade (1), characterized in that: The rear end of the leading edge fixed blade (1) is provided with an arc-shaped groove, the front end of the adjustable blade (3) is provided with an arc-shaped protrusion matching the arc-shaped groove, a cold air collecting cavity is provided inside the leading edge fixed blade (1), the arc-shaped groove is provided with impact outlet holes (12) distributed in sequence along the blade height direction, the arc-shaped groove is provided with a cold air outlet slit (13) extending along the blade height direction, the impact outlet hole (12) is connected to the cold air collecting cavity, the cold air outlet slit (13) is connected to the cold air collecting cavity, the cold air outlet slit (13) is closer to the pressure surface of the blade than the impact outlet hole (12), and the cold air flowing out of the cold air outlet slit (13) reaches the trailing edge of the blade after passing through the pressure surface of the blade.

2. The adjustable turbine blade according to claim 1, characterized in that: The arc-shaped groove is provided with a flow-limiting convex strip (14) extending in the blade height direction, and the flow-limiting convex strip (14) is closer to the suction surface of the blade than the impact outlet hole (12).

3. The adjustable turbine blade according to claim 2, characterized in that: The arc-shaped protrusion is provided with a first matching protrusion (33) and a second matching protrusion (34) extending in the blade height direction, and the flow-limiting protrusion (14) is assembled between the first matching protrusion (33) and the second matching protrusion (34).

4. The adjustable turbine blade according to claim 3, characterized in that: The first matching ridge (33) is located on the side of the flow limiting ridge (14) facing the pressure surface of the blade. The arc-shaped protrusion is also provided with at least one third matching ridge (35) extending along the blade height direction. The third matching ridge (35) is distributed on the side of the first matching ridge (33) facing away from the second matching ridge (34). When the first matching ridge (33) abuts against the flow limiting ridge (14), the third matching ridge (35) closest to the pressure surface is closer to the pressure surface of the blade than the impact outlet hole (12). Part of the cold air flowing out of the impact outlet hole (12) flows through the first matching ridge (33), the second matching ridge (34) and the pressure surface of the blade in sequence and then reaches the trailing edge of the blade.

5. The adjustable turbine blade according to claim 4, characterized in that: When the second matching convex strip (34) abuts against the flow limiting convex strip (14), the cold air outflow slot (13) is located on the side of the third matching convex strip (35) closest to the blade pressure surface or the first matching convex strip (33) facing the blade pressure surface.

6. The adjustable turbine blade according to claim 1, characterized in that: A rotating shaft (31) is fixed to the blade root and blade tip of the adjustable blade (3); the rotating shaft (31) is rotatably arranged relative to the turbine wheel; the adjustable blade (3) is hollow, and the trailing edge of the adjustable blade (3) is provided with a trailing edge slit (32) communicating with the internal space of the adjustable blade (3); the rotating shaft (31) is provided with a channel along the axial direction of the rotating shaft (31); the channel is communicated with the internal space of the adjustable blade (3).

7. The adjustable turbine blade according to claim 2, characterized in that: The leading edge fixed blade body (1) comprises a ceramic-based composite material shell and a metal impact duct (2); a through hole is provided in the ceramic-based composite material shell along the blade height direction; the metal impact duct (2) is located in the through hole; the metal impact duct (2) and the inner wall of the through hole are spaced apart; both ends of the metal impact duct (2) and the ceramic-based composite material shell are sealed; the area between the metal impact duct (2) and the inner wall of the through hole forms the cold air collecting cavity; and a plurality of impact holes connected to the cold air collecting cavity are provided on the side wall of the metal impact duct (2).

8. The adjustable turbine blade according to claim 7, characterized in that: The side wall of the metal impact conduit (2) corresponding to the leading edge of the blade is provided with leading edge impact holes (21) distributed in sequence along the blade height direction, the side wall of the metal impact conduit (2) corresponding to the suction surface of the blade is provided with suction surface impact holes (22) distributed in sequence along the blade height direction, and the side wall of the metal impact conduit (2) corresponding to the trailing edge of the blade is provided with trailing edge impact holes (23) distributed in sequence along the blade height direction.

9. The adjustable turbine blade according to claim 7, characterized in that: The current limiting convex strip (14) is made of a ceramic-based composite material, and the current limiting convex strip (14) and the ceramic-based composite material shell are integrally arranged.

10. The adjustable turbine blade according to claim 5, characterized in that: The adjustable blade body (3), the first matching convex strip (33), the second matching convex strip (34) and the third matching convex strip (35) are made of metal, and the adjustable blade body (3), the first matching convex strip (33), the second matching convex strip (34) and the third matching convex strip (35) are integrally arranged.

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