Turbine guide vane assembly and force transmission structure and method of turbine guide vane

Abstract

The invention relates to a turbine guide vane assembly and a force transmission structure and method of a turbine guide vane. The force transmission structure comprises a supporting cylinder and a supporting rod, the supporting cylinder comprises a plurality of force transmission parts and a cylinder body, the cylinder body is located in an inner cavity of the turbine guide vane, the force transmission parts are connected to the cylinder body, each force transmission part comprises an attaching end and an adjusting end, the attaching ends extend out of the radial outer side of the outer wall face of the cylinder body, and the adjusting ends are located on the radial inner side of the outer wall face of the cylinder body; a driving force can be applied to the adjusting end to drive the attaching end to move in the radial direction of the cylinder body, so that the attaching end is attached to the wall face of an inner cavity of the turbine guide vane. And effective transmission of turbine guide vane stress is realized.

Description

Technical Field

[0001] The technical field of the present invention relates to a turbine guide vane assembly and a force transmission structure and a force transmission method of a turbine guide vane. Background Technology

[0002] In the future, the temperature before the turbine of civil aviation engines will be higher and higher, and the service life requirements will be longer and longer. For example, the design life of the hot end components of modern commercial aviation engines is not less than 10,000 flight cycles (20,000 hours), and the high-temperature takeoff gas temperature before the turbine has reached 1978K. At present, for high-temperature turbine stators, under the conditions of using traditional cooling technology and thermal barrier coating technology, the use temperature and service performance of traditional high-temperature alloy materials are close to the limit, and it is difficult to meet the design requirements of the next generation of advanced aviation engines. Using ceramic-based composite materials to replace traditional high-temperature alloy materials is the best way to improve the temperature resistance and efficiency of aviation engine hot end components.

[0003] Ceramic matrix composites (CMC) have high specific strength and specific stiffness at high temperatures, and are lightweight and corrosion-resistant. They can adapt to the working environment of the hot end components of aircraft engine turbines, significantly improve the upper temperature limit of the hot end components and the overall efficiency of the engine and reduce pollution emissions, making them very promising in the field of aircraft engines. At present, advanced aircraft engine manufacturers at home and abroad have successively applied CMC materials to the hot end components of aircraft engines, such as combustion chamber flame tubes, turbine outer rings, turbine blades, etc.

[0004] The traditional metal high-pressure turbine guide vanes transmit aerodynamic loads to the front and rear casings or other load-bearing structures through the upper and lower edge plates. The guide vanes will bend and twist under the action of aerodynamic forces, so large stress is generated in the rounded parts of the blade body and edge plates. However, due to current process conditions, the strength of the CMC parts near the rounding may decrease relative to the base body. Therefore, transferring stress through the blade manufacturing mating surface can effectively reduce the maximum stress of the CMC blade body.

[0005] If Figure 1 As shown in FIG. 1 , a common method for transferring load is to set a metal support sleeve 200 in the inner cavity of the CMC guide vane 100 , and set a plurality of force transfer bosses 300 on the metal support sleeve 200 to contact the inner wall surface 1001 of the CMC guide vane, thereby transferring the load.

[0006] At present, one of the methods for preparing CMC hollow blades is to lay layers around the core mold and then press the outer mold to ensure the outer surface size of the blade. This preparation method may result in poor molding accuracy of the inner cavity surface of the CMC blade, and it is impossible to ensure that the inner wall surface 1001 of the CMC guide vane fits the boss 300 of the metal support sleeve 200, and it is impossible to transfer the blade body force to the internal metal support sleeve 200 according to the designed transfer load path, which leads to increased stress on the CMC guide vane 100 and further damage. Summary of the invention​​

[0007] The object of the present invention is to provide a force transmission structure for a turbine guide vane.

[0008] Another object of the present invention is to provide a turbine guide vane assembly.

[0009] Yet another object of the present invention is to provide a method for transmitting force of a turbine guide vane.

[0010] A force transmission structure according to one aspect of the present invention is for a turbine guide vane. The turbine guide vane includes an inner cavity. The force transmission structure includes: a support cylinder, including a plurality of force transmission parts and a cylinder body. The cylinder body is located in the inner cavity of the turbine guide vane. The force transmission parts are connected to the cylinder body. The force transmission parts include a fitting end and an adjusting end. The fitting end extends radially outside the outer wall surface of the cylinder body. The adjusting end is located radially inside the outer wall surface of the cylinder body. Wherein, a driving force can be applied to the adjusting end to drive the fitting end to move in the radial direction of the cylinder body, so that the fitting end fits with the wall surface of the inner cavity of the turbine guide vane.

[0011] The technical solution of the present application enables the distance between the support cylinder and the wall surface of the inner cavity of the turbine guide vane to be adjustable by providing movable force transmission parts. Even if the forming accuracy of the wall surface of the inner cavity of the turbine guide vane is poor, it can still ensure that the wall surface of the inner cavity of the turbine guide vane contacts the force transmission parts of the support cylinder. Moreover, the number and arrangement positions of the force transmission parts are not limited, and the contact points can be made to meet the requirements of fitting, so as to transmit the aerodynamic force received by the blade body to the support cylinder, reduce the stress on the blade body, and extend the service life.

[0012] In one or more embodiments of the force transmission structure, the force transmission part is threadedly connected to the cylinder body, and the adjusting end includes a groove.

[0013] In one or more embodiments of the force transmission structure, the force transmission part includes a head and a rod body. The circumferential dimension of the head is larger than that of the rod body. One side of the head is connected to one end of the rod body. The other side of the head is the fitting end. The other end of the rod body is the adjusting end. The rod body is provided with a threaded structure, and the cylinder body is provided with a threaded hole to be connected to the rod body.

[0014] In one or more embodiments of the force transmission structure, the cylinder body includes a pressure surface and a suction surface. The force transmission part located on the pressure surface is the first force transmission part, and the force transmission part located on the suction surface is the second force transmission part. The fitting end of the first force transmission part fits with the wall surface of the inner cavity of the turbine guide vane, and the fitting end of the second force transmission part has a set gap with the wall surface of the inner cavity of the turbine guide vane.

[0015] In one or more embodiments of the force transmission structure described above, the force transmission structure includes an assembly cold state and a working hot state. In the assembly cold state, the gap between the fitting end of the second force transmission part and the wall surface of the inner cavity of the turbine guide vane is the set gap; in the working hot state, the gap between the fitting end of the second force transmission part and the wall surface of the inner cavity of the turbine guide vane is 0.

[0016] In one or more embodiments of the force transmission structure described above, at least one of the plurality of force transmission parts is located axially inside the barrel body.

[0017] According to another aspect of the present invention, a turbine guide vane assembly includes the force transmission structure and the turbine guide vane as described above. The turbine guide vane includes an inner cavity. The barrel body of the support barrel of the force transmission structure is located in the inner cavity. The barrel body of the support barrel is provided with force transmission parts, and the fitting ends of the force transmission parts are used to fit with the wall surface of the inner cavity.

[0018] In one or more embodiments of the turbine guide vane assembly described above, the turbine guide vane is made of a ceramic matrix composite material, and the support barrel is made of a metal material.

[0019] In one or more embodiments of the turbine guide vane assembly described above, the barrel body of the support barrel includes a pressure surface and a suction surface. The force transmission part located on the pressure surface is the first force transmission part, and the force transmission part located on the suction surface is the second force transmission part; the turbine guide vane assembly includes a first state and a second state: in the first state, the fitting end of the first force transmission part fits with the wall surface of the inner cavity of the turbine guide vane, and the fitting end of the second force transmission part has a set gap with the wall surface of the inner cavity of the turbine guide vane; in the second state, the fitting ends of both the first force transmission part and the second force transmission part fit with the wall surface of the inner cavity of the turbine guide vane.

[0020] According to another aspect of the present invention, a force transmission method for a turbine guide vane includes: placing a support barrel in the inner cavity of the turbine guide vane, and the barrel body of the support barrel is provided with a plurality of force transmission parts; applying a driving force to one end of the plurality of force transmission parts to drive the other ends of the plurality of force transmission parts to extend different distances radially outward of the barrel body, so that the other ends fit with the wall surface of the inner cavity of the turbine guide vane or have a set gap. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The above and other features, properties, and advantages of the present invention will become more apparent through the following description in conjunction with the drawings and embodiments. The same reference numerals in the drawings always represent the same features. It should be noted that these drawings are only examples and are not drawn under the condition of equal scale, and should not be used to limit the actual protection scope required by the present invention, where:

[0022] Figure 1 Schematic diagram of the force transmission structure of the CMC guide vane for a comparative scheme.

[0023] Figure 2 Schematic perspective view of the three-dimensional structure of the turbine guide vane assembly for an embodiment.

[0024] Figure 3 Exploded view of the structure of the turbine guide vane assembly for an embodiment from the pressure surface perspective.

[0025] Figure 4 Exploded view of the structure of the turbine guide vane assembly for an embodiment from the suction surface perspective.

[0026] Figure 5 Schematic sectional view of the force transmission structure of the turbine guide vane assembly for an embodiment from one perspective.

[0027] Figure 6 Schematic sectional view of the first force transmission part for an embodiment.

[0028] Figure 7 Schematic sectional view of the second force transmission part for an embodiment.

[0029] Figure 8 Schematic perspective view of the force transmission part for an embodiment.

[0030] Figure 9 Schematic diagram of the step flow of the force transmission method of the turbine guide vane for an embodiment.

[0031] Reference numerals:

[0032] 100 - CMC guide vane;

[0033] 1001 - Inner wall surface of the CMC guide vane;

[0034] 200 - Metal support sleeve;

[0035] 300 - Boss;

[0036] 10 - Turbine guide vane assembly

[0037] 1 - Turbine guide vane;

[0038] 11 - Upper edge plate, 12 - Lower edge plate, 13 - Blade body, 131 - Inner cavity, 1311 - Wall surface of the inner cavity;

[0039] 2 - Support cylinder;

[0040] 21 - Upper bracket, 22 - Lower bracket, 23 - Cylinder body, 24 - Bolt;

[0041] 231 - Outer wall surface of the cylinder body, 232 - Threaded hole, 234 - Plane, 235 - Inner wall surface of the cylinder body;

[0042] 3 - Force transmission part;

[0043] 31 - Fitting end, 32 - Adjusting end, 321 - Groove;

[0044] 301 - Head, 302 - Shaft body, 303 - Thread structure;

[0045] 41 - Pressure surface, 42 - Suction surface;

[0046] 51 - First force transmission part, 52 - Second force transmission part;

[0047] 511 - Fitting end of the first force transmission part, 521 - Fitting end of the second force transmission part;

[0048] 6 - Feeler gauge;

[0049] 7 - Fixed position. Detailed implementation manners

[0050] Now, various embodiments of the present invention will be described in detail. Examples of these embodiments are shown in the drawings and described as follows. Although the present invention will be described in combination with exemplary embodiments, it should be realized that this specification is not intended to limit the present invention to those exemplary embodiments. On the contrary, the present invention is intended to cover not only these exemplary embodiments, but also various alternative forms, modified forms, equivalent forms and other embodiments that can be included within the spirit and scope of the present invention defined by the appended claims.

[0051] In the following description, the orientation or positional relationship indicated by terms such as "middle part", "inner", "outer" or other orientation terms is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or component referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as a limitation to the present invention.

[0052] The following directional terms such as "axial direction", "circumferential direction", and "radial direction" are based on the turbine guide vane / turbine guide vane assembly.

[0053] At the same time, specific words are used in this application to describe the embodiments of this application. Such as "an embodiment" and / or "one embodiment" mean a certain feature, structure or characteristic related to at least one embodiment of this application. Therefore, it should be emphasized and noted that the "one embodiment" or "an embodiment" mentioned twice or more at different positions in this specification does not necessarily refer to the same embodiment. In addition, certain features, structures or characteristics in one or more embodiments of this application can be appropriately combined.

[0054] Flowcharts are used in this application to illustrate the operations performed by the system according to the embodiments of the present application. It should be understood that the previous or following operations are not necessarily performed in exact order. Other operations may also be added to these processes, or one or more operations may be removed from these processes.

[0055] For the poor molding accuracy of the inner cavity surface of the CMC hollow blade, in order to ensure that the inner cavity surface 1001 of the CMC guide vane fits with the boss 300 of the metal support sleeve 200 to achieve force transmission, the current solution is to choose to set the boss 300 on the axial edge of the inner cavity surface of the CMC guide vane, because the edge is intuitively visible to technicians, which is convenient for judging and selecting the contact point that meets the requirements. However, this greatly limits the location and number of the boss, which in turn limits the force transmission effect, resulting in the CMC guide vane being unable to have a better stress bearing capacity.

[0056] Based on the above considerations, the inventor has conducted in-depth research and designed a force transmission structure for turbine guide vanes. By setting a movable force transmission part, the distance between the support tube and the inner wall of the turbine guide vane can be adjusted. Even if the forming accuracy of the inner wall of the turbine guide vane is poor, it can still ensure that the inner wall of the turbine guide vane is in contact with the force transmission part of the support tube. In addition, the number and arrangement of the force transmission parts are not limited, so that all contact points can meet the required fit, thereby transmitting the aerodynamic force on the blade to the support tube, reducing the stress on the blade and extending the service life.

[0057] Although the force transmission structure of the turbine guide vane disclosed in the embodiment of the present application is suitable for the CMC blades of the aircraft engine turbine to achieve the effect of reducing blade stress, it is not limited to this. As long as the blade force transmission can be applied, the force transmission structure of the turbine guide vane disclosed in the embodiment of the present application can be applied.

[0058] References Figure 2 、 Figure 3 and Figure 5As shown, in one embodiment, the specific structure of the turbine guide vane assembly 10 may be that it includes a turbine guide vane 1. The turbine guide vane 1 includes an upper flange 11, a lower flange 12 and a blade body 13. The blade body 13 includes an inner cavity 131. The upper flange 12 and the lower flange 13 are respectively connected to the upper and lower sides of the blade body 13 in the axial direction. It further includes a force transmission structure 1000. The force transmission structure 1000 includes a support cylinder 2. The support cylinder 2 includes an upper bracket 21, a lower bracket 22 and a cylinder body 23. The cylinder body 23 is located in the inner cavity 131. The upper bracket 21 and the lower bracket 22 are respectively connected to the upper and lower sides of the cylinder body 23 in the axial direction. The upper bracket 21 abuts against the upper flange 11, and the lower bracket 22 abuts against the lower flange 12 to fix the guide vane 1. The cylinder body 23 of the support cylinder 2 is provided with a plurality of force transmission parts 3. The force transmission parts 3 are used to fit with the wall surface 1311 of the inner cavity. During operation, the aerodynamic force received by the blade body 13 of the turbine guide vane 1 is directly transmitted to the upper bracket 21 and the lower bracket 22 through the force transmission parts 3, the upper flange 11 and the lower flange 12, and is transmitted to the upstream and downstream components through the upper bracket 21 and the lower bracket 22, thereby reducing the stress at the transition between the blade body 13, the upper flange 11 and the lower flange 12.

[0059] In one embodiment, the cylinder body 23 and the upper bracket 21 are integrally formed, and the cylinder body 23 and the lower bracket 22 are connected by bolts 24 to clamp and fix the guide vane 1.

[0060] In one embodiment, the turbine guide vane 1 is made of a ceramic matrix composite material, and the support cylinder 2 is made of a metal material. "Ceramics matrix composites (CMC)" is a composite material reinforced by continuous fibers with a ceramic as the matrix. Currently, its main materials include carbon / silicon carbide, silicon carbide / silicon carbide, zirconium boride / silicon carbide, and hafnium boride / silicon carbide, etc. It has the characteristics of high use temperature, good oxidation resistance and anti-microcrack performance, light weight, high strength and high stiffness.

[0061] Reference Figures 2 to 6 As shown, in one embodiment, the force transmission part 32 of the force transmission structure 1000 for the turbine guide vane may specifically be that the force transmission part 3 is connected to the cylinder body 23. The force transmission part 3 includes a fitting end 31 and an adjusting end 32. The fitting end 31 extends radially outside the outer wall surface 231 of the cylinder body, and the adjusting end 32 is located radially inside the outer wall surface 231 of the cylinder body. Among them, a driving force can be applied to the adjusting end 32 to drive the fitting end 31 to move radially on the cylinder body 23 so that the fitting end 31 fits with the wall surface 1311 of the inner cavity of the turbine guide vane 1.

[0062] The meaning of the "force transmission part 3" here refers to the structural component that connects the support cylinder 2 and the turbine guide vane 1 so that the aerodynamic force received by the turbine guide vane 1 can be transmitted to the support cylinder 2.

[0063] The meaning of the "fitting end 31" here refers to the end of the force transmission part 3 that fits with the wall surface 1311 of the inner cavity.

[0064] The meaning of the "adjusting end 32" here refers to the end of the force transmission part 3 that receives the driving force and enables the distance between the force transmission part 3 and the wall surface 1311 of the inner cavity to be adjustable.

[0065] The beneficial effect is as follows. By setting a movable force transmission part, the distance between the support cylinder and the inner cavity wall surface of the turbine guide vane can be adjusted. Even if the forming accuracy of the inner cavity wall surface of the turbine guide vane is poor, it can still ensure that the inner cavity wall surface of the turbine guide vane contacts the force transmission part of the support cylinder. Moreover, the number and arrangement position of the force transmission parts are not restricted, and the contact points can be made to meet the requirements for fitting, so as to transmit the aerodynamic force received by the blade body to the support cylinder, reduce the stress on the blade body, and extend the service life.

[0066] Reference Figure 6 As shown, in one embodiment, the specific structure of the force transmission part 3 can be that the force transmission part 3 is threadedly connected to the barrel body 23. The adjusting end 32 includes a groove 321, and a tool matching the groove 321 can be used to apply torque to the force transmission part 3, so that the force transmission part 3 can move relative to the barrel body 23. Such a setting enables the distance between the force transmission part 3 and the wall surface 1311 of the inner cavity to be adjusted easily and quickly, so that the force transmission structure 1000 can meet the forming accuracy requirements of various inner cavities and achieve a good force transmission effect.

[0067] Reference Figures 6 to 8 As shown, in one embodiment, the specific structure of the force transmission part 3 can be that it includes a head 301 and a rod body 302. The circumferential dimension of the head 301 is larger than that of the rod body 302; one side of the head 301 is connected to one end of the rod body 302, the other side of the head 301 is the fitting end 31, and the other end of the rod body 302 is the adjusting end 32; a threaded structure 303 is provided on the rod body 302, and a threaded hole is opened in the barrel body 23 to connect with the rod body 302. Such a setting has a simple structure, makes little change to the traditional force transmission structure 1000, is easy to manufacture, has no restriction on the installation position, and very cleverly solves the problem that the CMC blade inner cavity has poor forming accuracy and cannot fit with the metal support structure for force transmission. In one embodiment, the force transmission part 3 is a reverse screw, that is, the head of the reverse screw does not have a force application groove (such as a "cross" or "one" shape), that is, the head is a smooth surface, and the force application groove is arranged at the bottom end of the rod body of the reverse screw.

[0068] Reference Figures 6 to 8As shown, in one embodiment, the specific structure of the force transmission structure 1000 may be that a plane 234 is milled on the outer wall surface 231 of the barrel body. The circumferential dimension of the plane 234 is greater than or equal to the circumferential dimension of the head 301. The plane 234 abuts against one side of the head 301. Since the outer wall surface 231 of the barrel body is a curved surface, such a setting can enable the force transmission part to better abut against the barrel body 23, and further better fit with the wall surface 1311 of the inner cavity of the turbine guide vane, so that the contact point meets the strength requirements.

[0069] Reference Figures 2 to 8 As shown, in one embodiment, the specific structure of the force transmission structure 1000 may be that the barrel body 23 includes a pressure surface 41 and a suction surface 42. The force transmission part 3 located on the pressure surface 41 is the first force transmission part 51, and the force transmission part 3 located on the suction surface 42 is the second force transmission part 52. The fitting end 511 of the first force transmission part 51 fits with the wall surface 1311 of the inner cavity of the turbine guide vane, and the fitting end 521 of the second force transmission part 52 has a set gap with the wall surface 1311 of the inner cavity of the turbine guide vane.

[0070] The meaning of "pressure surface 41" here refers to the part where the fluid velocity on the surface of the object is slower and the pressure is higher, such as Figure 5 As shown, the concave part of the barrel body 23 is the pressure surface.

[0071] The meaning of "suction surface 42" here refers to the part where the fluid velocity on the surface of the object is faster and the pressure is lower, such as Figure 5 As shown, the convex part of the barrel body 23 is the suction surface.

[0072] The "set gap" mentioned here and hereinafter refers to the size of the gap, which is a design dimension obtained by calculating the difference in the coefficient of thermal expansion of the materials.

[0073] The reason for such a setting is that, as described in the above embodiments, the turbine guide vane 1 is mainly clamped and fixed by the force of the bolts between the upper bracket 21 and the lower bracket 22. The turbine guide vane assembly 10 includes a first state, namely the assembled cold state, in which the first force transmission part 51 is in contact with the wall surface 1311 of the inner cavity of the turbine guide vane, and is used to keep the turbine guide vane 1 fixed in the axial position when installed on the turbine. There is a set gap between the contact end 522 of the second force transmission part 52 and the wall surface 1311 of the inner cavity of the turbine guide vane. The turbine guide vane assembly 10 includes a second state, namely the working hot state. When the temperature rises, since the coefficient of thermal expansion of the metal is greater than that of the CMC, the amount of thermal expansion of the metal in the axial direction of the turbine guide vane 1 is large. Therefore, the clamping force originally holding the upper edge plate 11 and the lower edge plate 12 of the turbine guide vane disappears, and the support cylinder 2 is disengaged from contact with at least one side of the upper and lower edge plates of the turbine guide vane 1, and a gap appears in the axial direction. However, at the same time, the set gap between the second force transmission part 52 of the original suction surface and the inner cavity wall surface 1311 disappears due to the large amount of metal expansion, and the force transmission parts 3 are all in contact with the wall surface 1311 of the inner cavity of the turbine guide vane, forming an effective transfer of the limit and load of the CMC turbine guide vane, and will not cause excessive local stress. If in the assembled cold state, both the first force transmission part 51 and the second force transmission part 52 are in contact with the wall surface 1311 of the inner cavity, when it reaches the working hot state, the coefficient of thermal expansion of the metal is larger than that of the CMC, which will cause excessive local stress at the contact points.

[0074] In one embodiment, multiple force transmission parts 3 include at least one force transmission part 3 located on the axial inner side of the cylinder body 23. The number of the force transmission parts 3 can be designed as multiple according to needs and the arrangement positions are free. In the working state, they can all be in contact with the wall surface 1311 of the inner cavity of the turbine guide vane, which is beneficial to restricting the degrees of freedom of the turbine guide vane in all directions, and the force transmission effect is excellent.

[0075] In the embodiment as Figure 3 、 Figure 4 shown, the force transmission part 3 is located at the axial outer edge of the cylinder body 23. Such a setting is convenient for trimming and assembly, but compared with the embodiment in which it is arranged on the axial inner side of the cylinder body 23, the effect of restricting the degrees of freedom of the turbine guide vane in all directions is weaker, and the force transmission effect is poor.

[0076] As Figures 5 to 7 shown, in the assembled state, the first force transmission part 52 is in contact with the wall surface 1311 of the inner cavity, and there is a set gap between the second force transmission part 52 and the wall surface 1311 of the inner cavity, which is used to solve the thermal mismatch problem between the CMC turbine guide vane and the metal support cylinder. During assembly, when the support cylinder 2 is placed into the inner cavity 131, the second force transmission part 52 can be pre-tightened first, as Figure 7As shown, after inserting a feeler gauge 6 between the second force transmission part 52 and the wall surface 1311 of the inner cavity of the turbine guide vane, tighten the second force transmission part 52 to ensure that the set gap between the second force transmission part 52 and the wall surface 1311 of the inner cavity is the design dimension. Then adjust the first force transmission part 51 and tighten it to make the first force transmission part 51 fit against the wall surface 1311 of the inner cavity. Finally, take out the feeler gauge. After the position of the force transmission part 3 is fixed, weld or bond the force transmission part 3 to the barrel body 23 of the support cylinder, such as Figure 6 , Figure 7 shown, the fixed position 7 is at the contact point between the rod body 302 and the inner wall surface 235 of the barrel body to ensure the fixed position of the force transmission part 3 and at the same time ensure the sealing performance.

[0077] Refer to Figure 9 As shown, in one embodiment, the specific steps of the force transmission method of the turbine guide vane may include: placing a support cylinder in the inner cavity of the turbine guide vane, and a plurality of force transmission parts are arranged on the barrel body of the support cylinder; applying a driving force to one end of the plurality of force transmission parts to drive the other ends of the plurality of force transmission parts to extend different distances radially outward of the barrel body, so that the other ends fit against the wall surface of the inner cavity of the turbine guide vane or have a set gap. By adjusting the extension amount of the force transmission part, the distance from the support cylinder to the wall surface of the inner cavity of the turbine guide vane can be adjusted, which can ensure that even when there is a large deviation between the machining dimension and the theoretical dimension of the wall surface of the inner cavity of the CMC turbine guide vane, the metal force transmission structure can still fit against the inner cavity surface of the CMC turbine guide vane, so as to transfer the aerodynamic load received by the blade body to the upper and lower brackets and then to other upstream and downstream components, reduce the stress on the turbine guide vane, and extend the service life.

[0078] Although the present invention is disclosed above with preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications without departing from the spirit and scope of the present invention. Therefore, any modification, equivalent change and decoration made to the above embodiments based on the technical essence of the present invention without departing from the technical solution of the present invention shall fall within the protection scope defined by the claims of the present invention.

Claims

1. A force transmission structure for a turbine guide vane, the turbine guide vane comprising an inner cavity, characterized in that: The force transmission structure comprises: A support cylinder, comprising a plurality of force transmission parts and a cylinder body, wherein the cylinder body is located in the inner cavity of the turbine guide vane, the force transmission part is connected to the cylinder body, the force transmission part comprises a fitting end and an adjustment end, the fitting end extends outwardly from the radial direction of the outer wall surface of the cylinder body, and the adjustment end is located inwardly from the radial direction of the outer wall surface of the cylinder body; Wherein, a driving force may be applied to the adjusting end to drive the fitting end to move in the radial direction of the barrel body so that the fitting end fits with the wall surface of the inner cavity of the turbine guide vane.

2. The force transmission structure according to claim 1, characterized in that: The force transmission part is threadedly connected to the barrel, and the adjustment end includes a groove.

3. The force transmission structure according to claim 2, characterized in that: The force transmission part includes a head and a shaft, the circumferential size of the head is larger than the circumferential size of the shaft; one side of the head is connected to one end of the shaft, the other side of the head is the fitting end, and the other end of the shaft is the adjustment end; the shaft is provided with a threaded structure, and the barrel is provided with a threaded hole to be connected with the shaft.

4. The force transmission structure according to claim 1, characterized in that: The cylinder body includes a pressure surface and a suction surface. The force transmission part located on the pressure surface is a first force transmission part, and the force transmission part located on the suction surface is a second force transmission part. The fitting end of the first force transmission part fits with the wall surface of the inner cavity of the turbine guide vane, and the fitting end of the second force transmission part has a set gap with the wall surface of the inner cavity of the turbine guide vane.

5. The force transmission structure according to claim 4, characterized in that: The force transmission structure includes an assembled cold state and an operating hot state. In the assembled cold state, the gap between the fitting end of the second force transmission part and the wall surface of the inner cavity of the turbine guide vane is the set gap; In the working hot state, the gap between the fitting end of the second force transmission portion and the wall surface of the inner cavity of the turbine guide vane is zero.

6. The force transmission structure according to claim 1, characterized in that: The multiple force transmission parts include at least one force transmission part located on the axial inner side of the barrel.

7. A turbine guide vane assembly, characterized in that: It comprises a force transmission structure and a turbine guide vane as described in any one of claims 1 to 6, wherein the turbine guide vane comprises an inner cavity, a body of a support tube of the force transmission structure is located in the inner cavity, a force transmission part is provided on the body of the support tube, and a fitting end of the force transmission part is used to fit with a wall surface of the inner cavity.

8. The turbine guide vane assembly according to claim 7, characterized in that: The turbine guide vane is made of ceramic-based composite material, and the support tube is made of metal material.

9. The turbine guide vane assembly according to claim 7, characterized in that: The body of the support cylinder includes a pressure surface and a suction surface, the force transmission part located on the pressure surface is a first force transmission part, and the force transmission part located on the suction surface is a second force transmission part; the turbine guide vane includes a first state and a second state: In the first state, the fitting end of the first force transmission part fits with the wall surface of the inner cavity of the turbine guide vane, and the fitting end of the second force transmission part has a set gap with the wall surface of the inner cavity of the turbine guide vane; In the second state, the fitting end of the first force transmission portion and the fitting end of the second force transmission portion both fit with the wall surface of the inner cavity of the turbine guide vane.

10. A method for transmitting force of a turbine guide vane, characterized in that: include: A support cylinder is placed in the inner cavity of the turbine guide vane, wherein the body of the support cylinder is provided with a plurality of force transmission parts; A driving force is applied to one end of the plurality of force transmission parts to drive the other end of the plurality of force transmission parts to extend radially outward of the barrel at different distances, so that the other end fits with the wall surface of the inner cavity of the turbine guide vane or has a set gap.

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