Turbine vane mounting structure, turbine

Abstract

A turbine vane mounting structure includes an upper cover plate, a lower support plate, and a turbine vane positioned between the upper cover plate and the lower support plate, the turbine vane including an upper edge plate for cooperating with the upper cover plate and a lower edge plate for cooperating with the lower support plate, the structure further including a plurality of balls disposed between the upper edge plate and the upper cover plate and / or the lower edge plate and the lower support plate; the upper cover plate and / or the lower support plate further including a recess for receiving the balls to form a rolling fit between the upper cover plate, the lower edge plate and / or the lower edge plate, the lower support plate. The above structure can alleviate the thermal mismatch problem. A turbine is also provided.

Description

Technical Field

[0001] This invention relates to the field of aero-engines, and more specifically to the field of CMC turbine guide vanes. Background Technology

[0002] The turbine inlet temperature of civil aircraft engines is increasing, and the required service life is also growing. For example, modern commercial aircraft engines have a design life of no less than 10,000 flight cycles, or 20,000 hours, for their hot-end components. The turbine inlet gas temperature during high-temperature takeoff has reached 1978K. Under the limitations of current traditional cooling technologies and thermal barrier coating technologies, the operating temperature and service performance of traditional high-temperature alloy materials used in high-temperature turbine stators are nearing their limits, making it difficult to meet the design requirements of next-generation advanced aircraft engines. Replacing traditional high-temperature alloy materials with ceramic matrix composites is the best way to improve the temperature resistance and efficiency of hot-end components in aircraft engines.

[0003] Compared to traditional high-temperature alloys, ceramic matrix composites (CMCs) offer several advantages, including high temperature resistance, corrosion resistance, and low density. However, due to technological limitations, guide vanes or other components cannot be entirely made of CMC materials. Therefore, a significant amount of metallic materials, such as nickel-based metals, are still required for the support and assembly structures of turbine guide vanes.

[0004] Compared to nickel-based metals, ceramic matrix composites (CMCs) have a much lower coefficient of thermal expansion. Therefore, under engine operating conditions, the inconsistent thermal deformation of CMCs and metals leads to thermal mismatch between the CMC and metal structures, posing significant challenges to their assembly and installation. Existing solutions primarily address thermal mismatch through elastic elements, clearance fits, or preload. However, these solutions generally suffer from the following problems: First, under vibration, clearance fits can easily cause friction between the CMC structure and the metal, leading to cracks, reduced structural strength, and ultimately, structural failure. Furthermore, clearance fits struggle to provide deterministic constraint and force transmission for the guide vanes. Second, elastic structures or preload methods suffer from severe degradation of the metal's elastic properties at high temperatures due to a sharp decrease in the metal's modulus, reducing guide vane lifespan and increasing design complexity. Third, the relatively high surface roughness of CMCs results in significant sliding friction between the metal and CMC under high-temperature thermal mismatch conditions, potentially causing structural components to jam and damage the components. Summary of the Invention

[0005] One object of the present invention is to provide a turbine guide vane structure that can alleviate thermal mismatch problems and avoid jamming.

[0006] To achieve the above objectives, a turbine guide vane mounting structure includes an upper cover plate, a lower support plate, and a CMC turbine guide vane located between the upper cover plate and the lower support plate. The CMC turbine guide vane includes an upper edge plate for engaging with the upper cover plate and a lower edge plate for engaging with the lower support plate. The structure also includes a plurality of balls disposed between the upper edge plate and the upper cover plate and / or the lower edge plate and the lower support plate. The upper cover plate and / or the lower support plate also include grooves for receiving the balls. The upper cover plate, the lower edge plate and / or the lower edge plate and the lower support plate form a rolling fit with each other by means of the balls.

[0007] In one or more embodiments, the structure further includes an elastic element for supporting the ball.

[0008] In one or more embodiments, the elastic element is a spring disposed in the groove, with one end for abutting against the bottom surface of the groove and the other end for supporting the ball and allowing the ball to roll.

[0009] In one or more embodiments, the elastic element is a spring disposed within the groove, the top of the groove being tapered and the top aperture being smaller than the diameter of the ball, and the groove being able to maintain at least half the volume of the ball.

[0010] In one or more embodiments, the elastic element includes a support portion and a plurality of elastic plates. The support portion is fixedly disposed on the upper cover plate and / or the lower support plate. The plurality of elastic plates extend from the support portion toward the groove and form an elastic support layer above the groove. The elastic support layer is used to support the ball and allow the ball to roll.

[0011] In one or more embodiments, the elastic element includes an integral elastic plate, the integral elastic plate including a fixing part and a supporting part, the fixing part being used to fix to the upper cover plate and / or the lower support plate, the supporting part being located above the groove and used to rotatably engage with the ball, including a hollow part.

[0012] In one or more embodiments, the ball and the elastic element are made of high-temperature resistant materials.

[0013] In one or more embodiments, the groove depth that adapts to the ball is less than the diameter of the ball but greater than the radius of the ball.

[0014] In one or more embodiments, the groove depth that adapts to the ball is less than the sum of the ball diameter and the minimum length of the elastic element, but greater than the sum of the ball radius and the maximum length of the elastic element.

[0015] In one or more embodiments, the radius of the ball bearing located between the upper edge plate and the upper cover plate is greater than the gap height between the upper edge plate and the upper cover plate, and / or the radius of the ball bearing located between the lower edge plate and the lower support plate is greater than the gap height between the lower edge plate and the lower support plate.

[0016] Another object of the present invention is to provide a turbine in which the guide vanes are mounted using the above-described turbine guide vane mounting structure.

[0017] The aforementioned turbine guide vane mounting structure, through the cooperation of ball bearings and grooves, enables a free rolling contact between the metal cover plate and the upper and lower edge plates of the CMC (Chemical Mold Controlled Mechanism). This effectively reduces or eliminates high contact stress or jamming problems caused by axial and circumferential thermal mismatch between the upper and lower edge plates of the guide vane and the metal structure, preventing structural components from jamming together. The rolling contact eliminates the contact force in the normal direction of the curved surface between the edge plate and the metal interface, and also effectively reduces friction between the CMC structure and the metal. Furthermore, by incorporating elastic elements that cooperate with the ball bearings, the radial initial preload is reduced, effectively mitigating thermal mismatch and constraint or force transmission problems. Attached Figure Description

[0018] The above and other features, properties and advantages of the present invention will become more apparent from the following description taken in conjunction with the accompanying drawings and embodiments, wherein:

[0019] Figure 1 This is a schematic diagram of a typical engine structure.

[0020] Figure 2 This is a partial schematic diagram of the turbine structure.

[0021] Figure 3 This is a schematic diagram of one embodiment of a turbine guide vane structure.

[0022] Figure 4 This is a schematic diagram of one embodiment of a turbine guide vane structure.

[0023] Figure 5 This is a schematic diagram of the elastic support layer.

[0024] Figure 6 This is a top view of the overall elastic plate.

[0025] Figure 7 This is a schematic diagram of one embodiment of the groove.

[0026] Symbol marking explanation

[0027] 1. Nacelle

[0028] 2. Fan

[0029] 3. Boost stage

[0030] 5. Air compressor

[0031] 6. Combustion chamber

[0032] 7. Turbo

[0033] 8. Coccyx

[0034] 75. CMC turbine guide vanes

[0035] 701. Turbine outer casing

[0036] 703. Turbine blades

[0037] 704, turbine shaft

[0038] 751. Upper edge plate

[0039] 752. Lower edge plate

[0040] 901. Top cover plate

[0041] 902. Lower support plate

[0042] 903. Connecting screw

[0043] 904. Tighten the anti-loosening nut

[0044] 905, Cooling Sleeve

[0045] 911, Ball bearing

[0046] 912, Groove

[0047] 920. Elastic components

[0048] 921. Support section

[0049] 922, Flexible Plate

[0050] 923. Elastic support layer

[0051] 924. Integral elastic plate

[0052] 925. Fixing part

[0053] 926. Supporting Department

[0054] 927. Hollowed-out section

[0055] 928. Cover Detailed Implementation

[0056] The present invention will be further described below with reference to specific embodiments and accompanying drawings. More details are set forth in the following description in order to provide a full understanding of the present invention. However, the present invention can obviously be implemented in many other ways different from those described herein. Those skilled in the art can make similar extensions and derivations based on actual application situations without departing from the spirit of the present invention. Therefore, the scope of protection of the present invention should not be limited by the content of this specific embodiment.

[0057] It should be noted that these and subsequent accompanying drawings are merely illustrative and are not drawn to scale, and should not be construed as limiting the scope of protection of the present invention. It should be noted that... Figure 1 In the diagram, the X direction represents the axial direction, the Y direction represents the radial direction, and the radial direction is also... Figures 2 to 5 The up and down directions in the middle.

[0058] A typical structure of a gas turbine engine is as follows: Figure 1 As shown, it includes a nacelle 1, a fan 2, a compressor 5, a combustion chamber 6, a turbine 7, and a tail cone 8. After entering through the fan 2, the gas is pressurized by the booster stage 3 and then enters the combustion chamber 6. After combustion in the combustion chamber 6, the gas does work on the turbine 7, driving the fan 2 to generate thrust.

[0059] Turbine vanes are components in the high-temperature turbine parts of a gas turbine engine that rectify and output high-temperature, high-pressure gas from upstream to downstream. Figure 2 As shown, the turbine guide vanes are mounted on the turbine outer casing 701, together forming the stator. Opposite to the stator is the turbine rotor 703, which rotates around the turbine shaft 704. Turbine guide vanes need to withstand high temperatures for extended periods; therefore, ceramic matrix composite (CMC) turbine guide vanes are commonly used. However, due to limitations in current technology, CMC turbine guide vanes still require compatibility with metal components. For example, the support and assembly structures of the turbine guide vanes still require the use of significant amounts of metal materials such as nickel-based materials.

[0060] Compared to nickel-based metal materials, ceramic matrix composites have a smaller coefficient of thermal expansion, typically 4–5.10. -6 / K; while nickel-based metal materials are in the range of 10 to 20.10 -6 Therefore, under engine operating conditions, the thermal deformation of the CMC and the metal material is inconsistent, causing thermal mismatch between the CMC structure and the metal structure, which leads to serious hazards.

[0061] The turbine guide vane mounting structure disclosed herein is used to solve the aforementioned thermal mismatch problem, and in particular, it can avoid problems such as rubbing and component jamming that are prone to occur in traditional connection methods, and alleviate thermal stress in multiple directions.

[0062] Turbine guide vane installation structure reference Figure 3 The components include a metal upper cover plate 901, a lower support plate 902, and a CMC turbine guide vane 75 made of CMC material. The CMC turbine guide vane 75 is located between the upper cover plate 901 and the lower support plate 902, and includes an upper edge plate 751 for mating with the upper cover plate 901, a lower edge plate 752 for mating with the lower support plate 902, and a blade body 756 located between the upper edge plate 751 and the lower edge plate 752. The upper edge plate 751, the lower edge plate 752, and the blade body 756 can be manufactured integrally with continuous fibers, or they can be assembled together using a mortise and tenon structure with discontinuous fibers.

[0063] The blade body 756 includes a hollow cavity 757, through which a connecting screw 903 and a cooling sleeve 905 pass, and are fixed at both ends to an upper cover plate 901 and a lower support plate 902, respectively. The connecting screw 903 and the cooling sleeve 905 can be connected as a single unit by means such as welding. In one embodiment, a locking nut 904 is used to connect the connecting screw 903 to the cooling sleeve 905, the upper cover plate 901, and the lower support plate 902, and to provide an initial bolt preload, thus pre-tightening the upper cover plate 901, the CMC turbine guide vane 75, and the lower support plate 902. In another embodiment, one end of the connecting screw 903 can be fixed to the upper cover plate 901 or the lower support plate 902 by welding, bolting, or other means, and the other end can be fastened with a locking nut 904.

[0064] The turbine guide vane mounting structure also includes multiple balls 911 disposed between the upper edge plate 751 and the upper cover plate 901 and / or the lower edge plate 752 and the lower support plate 902. The upper cover plate 901 and / or the lower support plate 902 also include grooves 912 for receiving the balls 911, so that a rolling fit is formed between the upper cover plate 901, the lower edge plate 752 and / or the lower edge plate 752 and the lower support plate 902.

[0065] Due to the inconsistent thermal deformation between CMC material and metal material, the 911 ball bearing transforms the original in-plane sliding friction contact at the interface between CMC material and metal material into free rolling contact. Rolling contact can effectively release stress in multiple directions and simultaneously eliminate the contact force in the normal direction of the curved surface between the interface between CMC material and metal material. Furthermore, rolling contact reduces or eliminates the high contact stress or jamming problems caused by axial and circumferential thermal mismatch between the upper and lower edge plates and the metal cover plate and support plate structure, thereby avoiding the occurrence of rubbing between parts, jamming, and damage to the internal structure.

[0066] The specific number of balls 911 can be designed in detail according to the stress and deformation of the guide vane. The diameter of each ball 911 can also be determined by the staff based on the specific load-bearing capacity to ensure uniform stress and coordinated deformation of the guide vane, and to prevent large rigid body displacement and rotation. For example, the balls can be placed only between the lower edge plate 752 and the lower support plate 902, or between the upper edge plate 751 and the upper cover plate 901. Furthermore, the groove 912 serves both to fit the balls 911 and to prevent them from falling out. The depth of the groove 912 must ensure that, under full engine operating conditions, the balls 911 will not fall out of the groove due to structural thermal expansion; this will be explained further later.

[0067] In one embodiment, the structure further includes an elastic element 920 for supporting the ball 911. (Continuing with the previous sentence...) Figure 3 and Figure 4 Understanding is that the ball bearing 911, in conjunction with the elastic element 920, achieves deterministic constraint and force transmission path of the guide vane in the engine's radial direction. The elastic element 920 provides elastic preload, reducing the initial installation preload and mitigating thermal mismatch between the CMC material and the metal structure. The initial bolt preload provided by the locking nut 904 pre-compresses the spring element 920, directly pressing the ball bearing 911 against the upper and lower edge plates 751 and 752 of the CMC. The overall clamping force of the turbine guide vane mounting structure is controlled by the preload of the connecting screw 903 and the locking nut 904, and the preload of the spring element 920. By designing the bolt preload and the spring preload, the turbine guide vane mounting structure can maintain a clamping state on the CMC turbine guide vane 75 under all design operating conditions of the engine, thereby achieving constraint of the CMC guide vane structure in the engine's radial direction.

[0068] The elastic element 920 can be configured to fit each ball 911, or it can be configured to cooperate with some of the balls 911, such as... Figure 3 In the illustrated embodiment, the elastic element 920 is disposed between the lower edge plate 752 and the lower support plate 902. This arrangement keeps the elastic structure away from high-temperature regions, reducing the performance degradation of the elastic element and avoiding the problem of severe degradation of the metal's elastic properties due to a sharp decrease in the modulus of the metal material at high temperatures, thereby improving the service life of the guide vane. Simultaneously, the sliding friction contact caused by inconsistent thermal deformation at the contact interface becomes rolling contact due to the presence of the ball bearing 911, and the contact force in the normal direction of the curved surface between the CMC edge plate and the metal support plate interface is eliminated.

[0069] In the first embodiment of the elastic element 920, the elastic element 920 is a spring, disposed within the groove 912, with one end abutting against the bottom surface of the groove 912, and the other end supporting the ball 911 and allowing the ball 911 to roll. Figure 4As shown, one end of the spring is located in the groove 912 on the lower support plate 902, and the other end supports the ball 911. The ball 911 achieves rolling contact between the spring and the lower edge plate 752. The spring provides an initial installation preload, causing the ball 911 in the groove of the lower support plate 902 to press against the lower edge plate 752, and together with the metal upper cover plate 901 and the ball 911 located between the upper cover plate 901 and the upper edge plate 751, it fixes the CMC turbine guide vane 75, achieving a rolling fit between the contact interfaces.

[0070] In a second embodiment of the elastic element 920, the elastic element 920 is a spring, disposed within a groove 912. The top 913 of the groove 912 is tapered, and the diameter of the top 913 is smaller than the diameter of the ball 911. The groove 912 can maintain at least half the volume of the ball 911. Figure 7 As shown, the spring 920 and the ball 911 on the lower support plate 902 are both disposed in the groove 912 on the lower support plate 902. However, the top 913 of the groove 912 is tapered, such as in the shape of a cone, and the diameter of the top 913 is smaller than the diameter of the ball 911. The groove 912 can continuously accommodate at least half the volume of the ball 911, thereby effectively preventing the ball 911 from falling out. Only a portion of the ball 911's spherical crown protrudes from the outer surface of the lower support plate 902 and rolls in contact with the lower edge plate 752. The spring can be fixed to the bottom surface of the groove 912 by means such as welding. The bottom surface of the groove 912 can be part of the lower support plate 902 or... Figure 7 In the illustrated embodiment, the ground cover 928 is used alone. The ground cover 928 can be welded or interference-fitted to the bottom of the lower support plate 902, and the use of the ground cover makes assembly more convenient.

[0071] In the third embodiment of the elastic element 920, referring to Figure 5 As shown, the elastic member 920 includes a support portion 921 and a plurality of elastic plates 922. The support portion 921 is fixedly disposed on the upper cover plate 901 and / or the lower support plate 902. The plurality of elastic plates 922 extend from the support portion 921 toward the groove 912 and form an elastic support layer 923 above the groove 912. The elastic support layer 923 is used to support the ball 911 and allow the ball 911 to roll, thereby releasing the force on the ball 911 in multiple directions and preventing the ball from falling off.

[0072] In the fourth embodiment of the elastic element 920, referring to Figure 6As shown, the elastic member 920 comprises an integral elastic plate 924, the integral elastic plate 924 includes a fixing portion 925 and a supporting portion 926, the fixing portion 925 is configured to be fixed to the upper cover plate 901 and / or the lower supporting plate 902, the supporting portion 926 is located above the groove 912, and is configured to be in rolling engagement with the ball 911, and includes a hollow portion 927. Providing a plurality of hollow portions 927 on the integral elastic plate 924 can improve the elastic performance of the supporting portion 926, and in addition to radially supporting the ball, can also provide a lateral supporting force, thereby restricting the ball 911 from falling off. The hollow portion 927 may be Figure 6 a radial groove as shown, and may also be in other shapes.

[0073] Considering that the turbine guide vane is often in a high-temperature environment, in one embodiment, both the ball 911 and the elastic member 920 are made of high-temperature resistant materials, so as to ensure the safety and durability of the components.

[0074] Under all operating conditions of the engine, it is necessary to ensure that the ball 911 and the elastic member 920 will not detach from the turbine guide vane mounting structure, and the above objective can also be achieved by designing the depth of the groove 912, the diameter of the ball 911, and calculating the thermal deformation amounts of the metal material and the CMC material.

[0075] In conjunction with Figure 4 the understanding, the depth of the groove 912 located on the upper cover plate 901 is H1, which is engaged with the ball 911 with a diameter of D1, and the distance between the upper cover plate 901 and the upper edge plate 751 is h1. The depth of the groove 912 located on the lower supporting plate 902 is H2, which is engaged with the ball 911 with a diameter of D2, and the distance between the lower supporting plate 902 and the lower edge plate 752 is h2. The radial length of the CMC turbine guide vane 75 is Lc, where the radial direction refers to Figure 4 the up-down direction in the drawing. The radial length of the elastic member 920 under any working condition is X.

[0076] During the entire flight process of the engine, when the ball 911 is directly engaged with the groove 912 without using the elastic member 920, the groove depth needs to satisfy the following condition: D1-h1=H1<D1<2H1, that is, the groove depth needs to be smaller than the diameter of the ball 911 to ensure rolling contact; but it needs to be larger than the radius of the ball 911 to prevent the ball 911 from sliding out of the groove. When the ball 911 and the elastic member 920 are jointly engaged with the groove 912, D2+X-h2=H2<D2+X, that is, the depth of the groove adapted to the ball 911 is smaller than the sum of the diameter D2 of the ball and the minimum length X of the elastic member, so as to ensure rolling contact; but it also needs to satisfy X+D2 / 2<H2, that is, greater than the sum of the radius of the ball and the maximum length of the elastic member, so as to prevent the ball from falling off. When the spring is at its longest, such as at the highest temperature, the center of the ball is also lower than the plane of the pit; when the spring is at its shortest, that is, at room temperature, the top of the ball is also higher than the plane of the pit.

[0077] In one embodiment, the radius of the ball bearing located between the upper edge plate 751 and the upper cover plate 901 is greater than the gap height h1 between the upper edge plate 751 and the upper cover plate 901, and / or the radius of the ball bearing located between the lower edge plate 752 and the lower support plate 902 is greater than the gap height h2 between the lower edge plate 752 and the lower support plate 902, to prevent the ball bearing from falling off. Furthermore, if the ball bearing 911 between the upper edge plate 751 and the upper cover plate 901 is also fitted with an elastic element 920, the ball bearing diameter and spring length are calculated in the same manner as described above.

[0078] exist Figure 3 In the illustrated embodiment, the elastic element 920 provides an initial installation preload, causing the balls 911 to press against the lower edge plate 752 of the CMC guide vane, and together with the upper cover plate 901 and the balls 911 located between the upper cover plate 901 and the upper edge plate 751, secure the CMC turbine guide vane 75. The preload of the elastic element 920 during room temperature installation needs to be calculated to ensure that a certain design preload is maintained at all times when the engine operates at any temperature.

[0079] The design preload F of the elastic element 920 d =K T ΔX=K T (XX T ), where X is the length of elastic element 920 in its natural state when it is not under force, X T This represents the spring length at a given temperature, and ΔX is the change in spring length relative to its natural state. (Continue referring to...) Figure 4 As shown, the distance between the bottom of the groove on the upper cover plate 901 and the lower support plate 902 is L. M The relationship between L and the radial length Lc of the CMC turbine guide vane 75 is L M =L c +D1+D2. Since the overall thickness of the metal upper cover plate 901 and lower support plate 902 is thinner relative to the radial length of the CMC turbine guide vane 75, H1 and H2 can be considered to have a constant height when the temperature changes. Assuming that D1, D2, H1, and H2 are constant, the relationship between the length changes of the metal and CMC due to the inconsistency of their thermal expansion coefficients at a certain operating temperature is as follows: ΔL M =ΔL c +(X T -X0), where X0 is the initial installation length of the elastic element 20 during installation. Based on the aforementioned design preload F... d The calculation formula can be used to calculate the spring length X at any current temperature. T Then, from the aforementioned ΔL M The initial installation length X0 is obtained from the relation. According to Hooke's formula F... a =K0(X-X0), where F aThe initial installation force is K0, and the elastic stiffness is K0 in the initial installation state. After obtaining the initial installation length X0, the initial installation force F of the elastic element can be calculated using Hooke's formula. a .

[0080] The aforementioned turbine guide vane mounting structure, through the cooperation of balls and grooves, creates a rolling fit between the metal cover plate and the upper and lower edge plates of the CMC (Chemical Movering System). This effectively reduces or eliminates high contact stress or jamming problems caused by axial and circumferential thermal mismatch between the upper and lower edge plates of the guide vane and the metal structure, preventing structural components from jamming together. The rolling contact eliminates the contact force in the normal direction of the curved surface between the edge plate and the metal interface, and also effectively reduces friction between the CMC structure and the metal, achieving radial deterministic constraint and force transmission for the guide vane. Furthermore, by incorporating elastic elements that cooperate with the balls, the initial radial preload is reduced, effectively mitigating thermal mismatch. Through careful design of the bolt preload and spring precompression, this turbine mounting structure maintains a compressed state on the CMC turbine guide vane under all engine design operating conditions, thereby achieving constraint of the CMC guide vane structure in the radial direction of the engine.

[0081] Based on the above description of the turbine guide vane mounting structure, it can be understood that a turbine using the aforementioned turbine guide vane mounting structure can effectively mitigate the thermal mismatch problem between CMC materials and metal components, making the turbine components as a whole resistant to high temperatures and corrosion, thereby enabling the engine to effectively improve combustion temperature and thermal efficiency, and thus reduce pollutant emissions.

[0082] In the description of this application, it should be understood that the orientation or positional relationship indicated by directional terms such as "front, back, up, down, left, right", "horizontal, vertical, horizontal" and "top, bottom" is usually based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing this application and simplifying the description. Unless otherwise stated, these directional terms do not indicate or imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on the scope of protection of this application; the directional terms "inner" and "outer" refer to the inner and outer contours relative to the outline of each component itself.

[0083] Furthermore, this application uses specific terms to describe embodiments of the application. For example, "an embodiment," "one embodiment," and / or "some embodiments" refer to a particular feature, structure, or characteristic related to at least one embodiment of the application. Therefore, it should be emphasized and noted that "an embodiment," "one embodiment," or "an alternative embodiment" mentioned twice or more in different locations in this specification do not necessarily refer to the same embodiment. In addition, certain features, structures, or characteristics in one or more embodiments of the application can be appropriately combined.

[0084] While the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the invention. Any variations and modifications can be made by those skilled in the art without departing from the spirit and scope of the invention. Therefore, any modifications, equivalent changes, and alterations made to the above embodiments based on the technical essence of the present invention, without departing from the scope of the invention, fall within the protection scope defined by the claims of the present invention.

Claims

1. A turbine guide vane mounting structure, including an upper cover plate (901), a lower support plate (902), and a CMC turbine guide vane (75) located between the upper cover plate (901) and the lower support plate (902), wherein the CMC turbine guide vane (75) includes an upper edge plate (751) for cooperating with the upper cover plate (901) and a lower edge plate (752) for cooperating with the lower support plate (902). Its features are, The structure also includes a plurality of balls (911) disposed between the upper edge plate (751) and the upper cover plate (901) and / or the lower edge plate (752) and the lower support plate (902); the upper cover plate (901) and / or the lower support plate (902) also include a groove (912) for carrying the balls (911), and the upper cover plate (901), the lower edge plate (752) and / or the lower edge plate (752) and the lower support plate (902) form a rolling fit with each other by means of the balls; The structure also includes an elastic element (920) for supporting the ball (911). The elastic element (920) includes a support portion (921) and a plurality of elastic plates (922). The support portion (921) is fixedly disposed on the upper cover plate (901) and / or the lower support plate (902). The plurality of elastic plates extend from the support portion (921) toward the groove (912) and form an elastic support layer (923) above the groove (912). The elastic support layer (923) is used to support the ball (911) and allow the ball (911) to roll. The opening width of the groove (912) is greater than the diameter of the ball (911) to release the force on the ball in multiple directions.

2. The turbine guide vane mounting structure as described in claim 1, characterized in that, The ball bearing (911) and the elastic element (920) are made of high-temperature resistant materials.

3. The turbine guide vane mounting structure as described in claim 1, characterized in that, The groove depth that is adapted to the ball (911) is less than the diameter of the ball but greater than the radius of the ball.

4. The turbine guide vane mounting structure as described in claim 1, characterized in that, The groove depth that is adapted to the ball (911) is less than the sum of the ball diameter and the minimum length of the elastic element, but greater than the sum of the ball radius and the maximum length of the elastic element.

5. The turbine guide vane mounting structure as described in claim 1, characterized in that, The radius of the ball bearing located between the upper edge plate (751) and the upper cover plate (901) is greater than the gap height between the upper edge plate (751) and the upper cover plate (901), and / or the radius of the ball bearing located between the lower edge plate (752) and the lower support plate (902) is greater than the gap height between the lower edge plate (752) and the lower support plate (902).

6. A turbine, characterized in that, The guide vane is installed using the turbine guide vane mounting structure as described in any one of claims 1-5.

Images