CN117189268A

CN117189268A - Turbine guide vane mounting structure and turbine

Info

Publication number: CN117189268A
Application number: CN202210618065.7A
Authority: CN
Inventors: 曹源; 胡寿丰
Original assignee: AECC Commercial Aircraft Engine Co Ltd
Current assignee: AECC Commercial Aircraft Engine Co Ltd
Priority date: 2022-06-01
Filing date: 2022-06-01
Publication date: 2023-12-08
Also published as: WO2023232028A1

Abstract

The turbine guide vane mounting structure comprises an upper cover plate, a lower supporting plate, a turbine guide vane positioned between the upper cover plate and the lower supporting plate, a plurality of balls and a plurality of guide vanes, wherein the upper cover plate is used for being matched with the upper cover plate, the lower supporting plate is used for being matched with the lower supporting plate, and the guide vanes are arranged between the upper cover plate and/or between the lower cover plate and the lower supporting plate; the upper cover plate and/or the lower support plate further comprises grooves for bearing balls, so that rolling fit is formed among the upper cover plate, the lower edge plate and/or the lower edge plate and the lower support plate. The structure can alleviate the problem of thermal mismatch. A turbine is also provided.

Description

Turbine guide vane mounting structure and turbine

Technical Field

The application relates to the field of aeroengines, in particular to the field of CMC turbine guide vanes.

Background

The temperature before the turbine of the civil aviation engine is higher and higher, and the service life requirement is longer and longer. For example, modern commercial aero-engines, the design life of the hot-end components is not less than 10000 flight cycles, i.e. 20000 hours. The temperature of the fuel gas before the high-temperature take-off turbine reaches 1978K. Under the limitations of the traditional cooling technology and the thermal barrier coating technology conditions at present, the service temperature and the service performance of the traditional high-temperature alloy material adopted by the high-temperature turbine stator are close to the limit, and the design requirement of the next generation advanced aeroengine is difficult to meet. The ceramic matrix composite material is adopted to replace the traditional high-temperature alloy material, so that the method is the best way for improving the temperature resistance and the efficiency of the hot end part of the aeroengine.

Compared with the traditional superalloy, the ceramic matrix composite (Ceramic Matrix Composites, CMC) has the advantages of high temperature resistance, corrosion resistance, low density and the like. However, due to technical limitations, the vanes or other components cannot be made entirely of CMC materials, and therefore a large number of metallic material structures, such as nickel-based metals, are also required for adaptation in the support and mounting structures of the turbine guide vane.

Compared with the nickel-based metal material, the CMC has a thermal expansion coefficient far smaller than that of the nickel-based metal material, so that under the operating condition of an engine, the thermal deformation of the ceramic-based composite material and the metal material is inconsistent, and the ceramic-based composite material structure and the metal structure generate thermal mismatch, thereby bringing great difficulty to the assembly and installation of the ceramic-based composite material structure and the metal structure. The existing scheme mainly solves the problem of thermal mismatch through elastic elements, clearance fit or pretightening force and the like. But generally has the following problems: under a vibration environment, clearance fit is easy to cause collision and abrasion between a CMC structure and metal, cracks are easy to generate, the structural strength is reduced, structural failure is further caused, and meanwhile, the clearance fit is difficult to realize deterministic constraint and force transmission of the guide vane; secondly, the modulus of the metal material is rapidly reduced in an elastic structure or a pretightening force mode at high temperature, so that the metal elastic performance is seriously degraded, the service life of the guide vane is reduced, and the design complexity is improved; thirdly, the surface roughness of the CMC structure is relatively high, and under the condition of high-temperature thermal mismatch, sliding friction force generated by relative movement of metal and CMC is large, so that structural components are easy to be blocked mutually, and the component structure is damaged.

Disclosure of Invention

An object of the present application is to provide a turbine vane structure that can alleviate the thermal mismatch problem and avoid the occurrence of sticking.

The turbine guide vane mounting structure for achieving the purpose comprises an upper cover plate, a lower supporting plate and a CMC turbine guide vane arranged between the upper cover plate and the lower supporting plate, wherein the CMC turbine guide vane comprises an upper edge plate matched with the upper cover plate and a lower edge plate matched with the lower supporting plate, and a plurality of balls are arranged between the upper edge plate and the upper cover plate and/or between the lower edge plate and the lower supporting plate; the upper cover plate and/or the lower support plate further comprises a groove, the groove is used for bearing the balls, and rolling fit is formed among the upper cover plate, the lower edge plate and/or the lower edge plate and the lower support plate by means of the balls.

In one or more embodiments, the structure further comprises an elastic member for supporting the balls.

In one or more embodiments, the elastic member is a spring, and is disposed in the groove, one end of the elastic member is used to prop against the bottom surface of the groove, and the other end of the elastic member is used to support the ball and allow the ball to roll.

In one or more embodiments, the elastic member is a spring, disposed in the groove, the top of the groove is tapered, and the top aperture is smaller than the ball diameter, and the groove is capable of holding at least half of the volume that accommodates the ball.

In one or more embodiments, the elastic member 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 direction, and an elastic support layer is formed above the groove, and the elastic support layer is used for bearing the balls and allowing the balls to roll.

In one or more embodiments, the elastic member includes an integral elastic plate, the integral elastic plate includes a fixing portion and a bearing portion, the fixing portion is used for being fixed on the upper cover plate and/or the lower support plate, and the bearing portion is located above the groove and is used for being matched with the balls in a rolling manner, and the integral elastic plate includes a hollowed portion.

In one or more embodiments, the balls and the elastic member are high temperature resistant materials.

In one or more embodiments, the groove depth that mates with the ball is less than the ball diameter but greater than the ball radius.

In one or more embodiments, the depth of the groove that fits the ball is less than the sum of the ball diameter and the minimum length of the resilient member, but greater than the sum of the ball radius and the maximum length of the resilient member.

In one or more embodiments, a ball radius between the upper rim plate and the upper cover plate is greater than a gap height between the upper rim plate and the upper cover plate, and/or a ball radius between the lower rim plate and the lower tray is greater than a gap height between the lower rim plate and the lower tray.

It is still another object of the present application to provide a turbine, in which the above turbine vane mounting structure is used to mount the vanes.

According to the turbine guide vane mounting structure, through the matching of the balls and the grooves, a free rolling matching mode is formed between the metal cover plate and the CMC upper and lower edge plates, so that the problem of high contact stress or clamping stagnation caused by axial and circumferential thermal mismatch between the guide vane upper and lower edge plates and the metal structure is effectively reduced or eliminated, the phenomenon that structural components are mutually blocked is avoided, the rolling contact can eliminate the contact force of the edge plates and the metal interface in the normal direction of the curved surface, and the collision and abrasion between the CMC structure and the metal is also effectively slowed down. In addition, through setting up with ball complex elastic component, reduce radial initial pretightning force, effectively slow down thermal mismatch and restraint or biography power problem.

Drawings

The above and other features, properties and advantages of the present application will become more apparent from the following description in conjunction with the accompanying drawings and embodiments, in which:

FIG. 1 is a schematic diagram of an exemplary engine configuration.

FIG. 2 is a partial schematic view of a turbine structure.

FIG. 3 is a schematic view of an embodiment of a turbine vane structure.

FIG. 4 is a schematic diagram of an embodiment of a turbine vane structure.

Fig. 5 is a schematic structural view of the elastic support layer.

Fig. 6 is a top view of the integral elastic panel.

FIG. 7 is a schematic view of an embodiment of a groove.

Sign mark description

1. Nacelle (GY)

2. Fan with fan body

3. Supercharging stage

5. Air compressor

6. Combustion chamber

7. Turbine wheel

8. Caudal vertebra

75.CMC turbine guide vane

701. Turbine outer casing

703. Turbine bucket

704. Turbine shaft

751. Upper edge plate

752. Lower edge plate

901. Upper cover plate

902. Lower support plate

903. Connecting screw

904. Fastening locknut

905. Cooling sleeve

911. Ball bearing

912. Groove

920. Elastic piece

921. Support part

922. Elastic plate

923. Elastic supporting layer

924. Integral elastic plate

925. Fixing part

926. Bearing part

927. Hollowed-out part

928. Plugging cover

Detailed Description

The present application will be further described with reference to specific embodiments and drawings, in which more details are set forth in the following description in order to provide a thorough understanding of the present application, but it will be apparent that the present application can be embodied in many other forms than described herein, and that those skilled in the art may make similar generalizations and deductions depending on the actual application without departing from the spirit of the present application, and therefore should not be construed to limit the scope of the present application in terms of the content of this specific embodiment.

It is noted that these and other figures are merely examples, which are not drawn to scale and should not be construed as limiting the scope of the application as it is actually claimed. In fig. 1, the X direction indicates an axial direction, the Y direction indicates a radial direction, and the radial direction is also the up-down direction in fig. 2 to 5.

A typical construction of a gas turbine engine is shown in FIG. 1, and includes a nacelle 1, a fan 2, a compressor 5, a combustor 6, a turbine 7, and a tailcone 8. After entering from the fan 2, the gas is pressurized by the pressurizing stage 3 and enters the combustion chamber 6, and the gas is combusted by the combustion chamber 6 to apply work to the turbine 7 to drive the fan 2 to generate thrust.

Turbine vanes (turbine vanes) are components that rectify and output high temperature, high pressure gas from upstream to downstream in a gas turbine engine high temperature turbine component. As shown in fig. 2, the turbine guide vane is mounted on the turbine outer casing 701, and forms a stator together with the turbine outer casing 701, and the turbine guide vane 703 is opposite to the stator and rotates around the turbine shaft 704. The turbine guide vane needs to bear a high-temperature link for a long time, so that the ceramic matrix composite is commonly adopted to manufacture the CMC turbine guide vane at present. However, due to the limitations of the prior art, CMC turbine vanes still need to be adapted to metal components, such as on the support and mounting structures of the turbine guide vanes, and also require the use of a significant amount of metallic material, such as nickel-based.

Compared with nickel-based metal materials, the ceramic-based composite material has a small thermal expansion coefficient of 4-5.10 ^-6 K; and the nickel-based metal material is 10-20.10 ^-6 and/K. Therefore, under the operating condition of the engine, the thermal deformation of the CMC and the metal material is inconsistent, so that the CMC structure and the metal structure generate thermal mismatch, thereby bringing serious harm.

The turbine guide vane mounting structure is used for solving the problem of thermal mismatch, particularly avoiding the problems of friction, component blocking and the like which are easy to generate in a traditional connection mode, and relieving thermal stress in multiple directions.

Turbine vane mounting structure is understood with reference to FIG. 3, including an upper cover plate 901 of metallic material, a lower support plate 902, and CMC turbine vanes 75 of CMC material. CMC turbine vane 75 is located between upper cover plate 901 and lower tray 902, and includes upper edge plate 751 for mating with upper cover plate 901 and lower edge plate 752 for mating with lower tray 902, and blade body 756 located between upper edge plate 751 and lower edge plate 752. The upper lip 751, lower lip 752 and blade 756 may be integrally formed, with the fibers being continuous, or may be assembled together by a mortise and tenon structure, with the fibers being discontinuous.

Blade 756 includes a hollow cavity 757 through which connecting screw 903 and cooling sleeve 905 extend, and two ends of which are secured to upper cover plate 901 and lower plate 902, respectively. The coupling screw 903 and the cooling jacket 905 may be integrally coupled by means such as welding. In one embodiment, a fastening locknut 904 is used to couple the connecting screw 903 with the cooling sleeve 905 and the upper cover plate 901, lower plate 902 and to provide an initial bolt pretension to initially pretension the upper cover plate 901, CMC turbine vane 75, and lower plate 902. In another embodiment, one end of the connecting screw 903 may be fixed to the upper cover plate 901 or the lower support plate 902 by welding, bolts, or the like, and the other end is fastened by fastening locknuts 904.

The turbine vane mounting structure further includes a plurality of balls 911, the balls 911 being disposed between the upper rim plate 751 and the upper cover plate 901 and/or the lower rim plate 752 and the lower tray 902. The upper cover plate 901 and/or the lower tray 902 further comprises grooves 912, the grooves 912 being adapted to bear balls 911 to form a rolling fit between the upper cover plate 901, the lower rim plate 752 and/or the lower rim plate 752, the lower tray 902.

Because the thermal deformation between the CMC material and the metal material is inconsistent, the ball 911 enables the original in-plane sliding friction contact on the contact interface of the CMC material and the metal material to be changed into free rolling contact, the rolling contact can effectively release stress in multiple directions, the contact force in the normal direction of the curved surface between the CMC material and the metal material interface can be eliminated simultaneously, and the problem of high contact stress or clamping stagnation caused by axial and circumferential thermal mismatch between the upper and lower edge plates and the metal cover plate and the supporting plate structure is reduced or eliminated through rolling contact, thereby avoiding the phenomena of friction and mutual clamping between parts and damaging the internal structure.

The specific number of the balls 911 can be designed in detail according to the stress, deformation and other conditions of the guide vane, and the diameter of each ball 911 can be determined by staff according to specific bearing strength, so that the guide vane is ensured to be stressed uniformly, deformed and coordinated, and large rigid displacement and rotation are avoided. The balls may be provided only between the lower plate 752 and the lower plate 902, or may be provided between the upper plate 751 and the upper plate 901. In addition, grooves 912 serve to both mate with balls 911 and prevent balls 911 from falling out. The depth of the groove 912 must ensure that the ball 911 does not come out of the groove due to thermal expansion of the structure during the full operating condition of the engine, as will be further described.

In one embodiment, the structure further includes a resilient member 920 for supporting the ball 911. As will be appreciated with continued reference to fig. 3 and 4, the balls 911 cooperate with the resilient members 920 to achieve a deterministic constraint and force transfer path of the vane in the radial direction of the engine. The resilient member 920 can provide an elastic pre-load force, reduce the initial installation pre-load force, and mitigate thermal mismatch issues with the CMC material and metal structure. The initial bolt preload provided by tightening locknut 904 pre-compresses spring member 920, compressing ball 911 directly against CMC upper and lower flanges 751 and 752. The overall compression force of the turbine vane mounting structure is controlled by the preload of the connecting screw 903 and the fastening locknut 904 and the amount of precompression of the spring member 920. By designing the bolt pretightening force and the precompression amount of the spring, the turbine guide vane mounting structure can keep the compression state of the CMC turbine guide vane 75 under all the design working conditions of the engine, and further the constraint of the CMC guide vane structure in the radial direction of the engine is realized.

The elastic member 920 may be configured to fit each ball 911 or may be configured to cooperate with a portion of the balls 911, such as in the embodiment shown in fig. 3, in which the elastic member 920 is disposed between the lower edge plate 752 and the lower support plate 902 in such a manner that the elastic structure is away from the high temperature region, thereby reducing performance degradation of the elastic member, and avoiding the problem of serious metal elastic performance degradation caused by rapid decrease of modulus of the metal material at high temperature, so as to increase service life of the guide vane. Meanwhile, sliding friction contact generated by inconsistent thermal deformation on the contact interface is changed into rolling contact due to the existence of the balls 911, and meanwhile, the contact force in the normal direction of the curved surface between the CMC flange plate and the metal supporting plate interface is eliminated.

In the first embodiment of the elastic member 920, the elastic member 920 is a spring, and is disposed in the groove 912, and has one end for abutting against the bottom surface of the groove 912 and the other end for supporting the ball 911 and allowing the ball 911 to roll. As shown in fig. 4, one end of the spring is positioned in a groove 912 in the bottom plate 902 and the other end holds a ball 911. The ball 911 makes rolling contact between the spring and the bottom plate 752. The springs provide an initial installation preload force that causes balls 911 in the grooves of lower plate 902 to bear against lower rim plate 752 and secure CMC turbine vane 75 with metal upper cover plate 901 and balls 911 between upper cover plate 901 and upper rim plate 751 to achieve a rolling fit between the contact interfaces.

In the second embodiment of the elastic member 920, the elastic member 920 is a spring and is disposed in the groove 912, the top 913 of the groove 912 is tapered, and the aperture of the top 913 is smaller than the diameter of the ball 911, so that the groove 912 can hold at least half of the volume of the ball 911. As shown in fig. 7, the spring member 920 and the balls 911 on the lower plate 902 are disposed in the groove 912 on the lower plate 902, but the top 913 of the groove 912 has a tapered shape such as a cone shape, and the aperture of the top 913 is smaller than the diameter of the balls 911, so that the groove 912 can continuously accommodate at least half of the volume of the balls 911, thereby effectively preventing the balls 911 from falling off. Only a portion of the ball 911 extends beyond the outer surface of the lower plate 902 and is in rolling contact with the lower lip 752. The spring may be secured to the bottom surface of the recess 912 by means such as welding. The bottom surface of the recess 912 may be part of the bottom plate 902 or may be a separate cover 928 used in the embodiment shown in fig. 7. The plug 928 may be welded or interference fit to the bottom of the bottom plate 902, which may be more convenient to use during assembly.

In the third embodiment of the elastic member 920, referring to fig. 5, the elastic member 920 includes a supporting portion 921 and a plurality of elastic plates 922, the supporting portion 921 is fixedly disposed on the upper cover plate 901 and/or the lower plate 902, the plurality of elastic plates 922 extend from the supporting portion 921 toward the groove 912, and form an elastic supporting layer 923 above the groove 912, and the elastic supporting layer 923 is used for supporting the balls 911 and allowing the balls 911 to roll, thereby releasing the force of the balls 911 in a plurality of directions and restraining the balls from falling off.

In the fourth embodiment of the elastic member 920, referring to fig. 6, the elastic member 920 includes 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 used to fix on the upper cover plate 901 and/or the lower supporting plate 902, and the supporting portion 926 is located above the groove 912 and is used to be engaged with the ball 911 in a rolling manner, and includes a hollowed portion 927. The plurality of hollowed-out portions 927 are arranged on the integral elastic plate 924, so that the elastic performance of the bearing portion 926 can be increased, lateral supporting force can be provided outside the radial supporting balls, and the falling-off of the balls 911 is restrained. The hollowed-out portion 927 may be a radioactive groove as shown in fig. 6, or may be other shapes.

Considering that turbine vanes are often in a high temperature environment, in one embodiment, both the balls 911 and the resilient member 920 are high temperature resistant materials to ensure the safety and durability of the components.

In the whole working state of the engine, the balls 911 and the elastic members 920 need to be ensured not to be separated from the turbine guide vane mounting structure, and the purposes can be achieved by designing the depth of the grooves 912, the diameters of the balls 911 and calculating the thermal deformation amount of the metal material and the CMC material.

As will be appreciated in connection with fig. 4, the groove 912 in the upper cover plate 901 has a depth H1, and cooperates with the balls 911 having a diameter D1, the upper cover plate 901 and the upper flange plate 751 have a spacing H1. The grooves 912 in the bottom plate 902 have a depth H2 and mate with balls 911 of diameter D2, and the bottom plate 902 is spaced from the bottom plate 752 by a distance H2. The CMC turbine vane 75 has a radial length Lc, where the radial direction refers to the up-down direction in fig. 4. The elastic member 920 has a radial length X under any operating condition.

During the full flight 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 needs to be larger than the radius of the balls 911 to avoid the balls 911 from sliding out of the grooves. When the ball 911 and the elastic member 920 cooperate with the groove 912, d2+x-h2=h2 < d2+x, that is, the depth of the groove matched with 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 is also necessary to satisfy X+D2/2 < H2, i.e. greater than the sum of the radius of the ball and the maximum length of the elastic member, to avoid the ball falling off. At the longest spring, such as the highest temperature, the center of the ball is also below the pit plane; at the shortest time of the spring, i.e. at room temperature, the ball top is also above the pit plane.

In one embodiment, the radius of the balls 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 balls between the lower edge plate 752 and the lower tray 902 is greater than the gap height h2 between the lower edge plate 752 and the lower tray 902 to avoid the falling-off of the balls. In addition, if the balls 911 between the upper rim plate 751 and the upper cover plate 901 are also fitted with the elastic member 920, the ball diameter and the spring length are also identical to those calculated as described above.

In the embodiment shown in FIG. 3, the resilient member 920 provides an initial installation preload force that causes the balls 911 to bear against the CMC vane lower edge plate 752 and secure the CMC turbine vane 75 with the upper cover plate 901 and the balls 911 between the upper cover plate 901 and the upper edge plate 751. The pre-tightening force of the elastic member 920 is calculated during room temperature installation to ensure that a certain design pre-tightening force can be maintained all the time when the engine is operated at any temperature.

Design pretightening force F of elastic member 920 _d ＝K _T ΔX＝K _T (X-X _T ) Wherein X is the length of the elastic member 920 in the natural state without being stressed, X _T Is the current spring length at a certain temperature, Δx is the spring length change from the natural state. With continued reference to FIG. 4, the distance between the upper cover plate 901 and the bottom of the recess in the lower plate 902 is L _M The relationship with the radial length Lc of CMC turbine vane 75 is L _M ＝L _c +d1+d2. Since the overall thickness of the metal upper cover plate 901 and lower plate 902 is thin relative to the radial length of CMC turbine vane 75, H1 and H2 may be considered to remain unchanged in height as the temperature changes. Assuming that D1, D2, H1 and H2 are unchanged, at a certain operating temperature, the relationship between the length changes of the metal and CMC caused by the inconsistent thermal expansion coefficients is as follows delta L _M ＝ΔL _c +(X _T -X ₀ ) Wherein X is ₀ Is the initial installation state of the elastic member 20 during installationState length. According to the design pretightening force F _d The calculation formula can calculate the length X of the spring at any current temperature _T Then from the delta L _M The relation is used for obtaining the initial installation state length X ₀ . According to the Huke equation F _a ＝K ₀ (X-X ₀ ) Wherein F _a Is the initial installation force, K ₀ Is the elastic rigidity in the initial installation state, and obtains the length X of the initial installation state ₀ The initial mounting force F of the elastic piece can be calculated according to the Huke formula _a 。

According to the turbine guide vane mounting structure, through the matching of the balls and the grooves, a rolling matching mode is formed between the metal cover plate and the CMC upper and lower edge plates, so that the problem of high contact stress or clamping stagnation caused by axial and circumferential thermal mismatch between the guide vane upper and lower edge plates and the metal structure is effectively reduced or eliminated, the phenomenon that structural components are mutually clamped is avoided, the rolling contact can eliminate the contact force in the normal direction of the curved surface between the edge plates and the metal interface, the collision and grinding between the CMC structure and the metal is also effectively slowed down, and radial deterministic constraint and force transfer of the guide vane are realized. In addition, through setting up with ball complex elastic component, reduce radial initial pretightning force, effectively slow down the thermal mismatch problem. Through careful design of bolt pretightening force and precompression amount of the spring, the turbine mounting structure keeps a compression state of the CMC turbine guide vane under all design working conditions of the engine, so that constraint of the CMC guide vane structure in the radial direction of the engine is realized.

By combining the description of the turbine guide vane mounting structure, the turbine can be further understood, the guide vane is mounted by adopting the turbine guide vane mounting structure, the problem of thermal mismatch between CMC materials and metal components is effectively alleviated, the whole turbine component is resistant to high temperature and corrosion, the combustion temperature and the thermal efficiency of the engine are further effectively improved, and pollutant emission can be further reduced.

In the description of the present application, it should be understood that the azimuth or positional relationships indicated by the azimuth terms such as "front, rear, upper, lower, left, right", "lateral, vertical, horizontal", and "top, bottom", etc., are generally based on the azimuth or positional relationships shown in the drawings, merely to facilitate description of the present application and simplify the description, and these azimuth terms do not indicate and imply that the apparatus or elements referred to must have a specific azimuth or be constructed and operated in a specific azimuth, and thus should not be construed as limiting the scope of protection of the present application; the orientation word "inner and outer" refers to inner and outer relative to the contour of the respective component itself.

Meanwhile, the present application uses specific words to describe embodiments of the present application. Reference to "one embodiment," "an embodiment," and/or "some embodiments" means that a particular feature, structure, or characteristic is associated with at least one embodiment of the application. Thus, it should be emphasized and should be appreciated that two or more references to "an embodiment" or "one embodiment" or "an alternative embodiment" in various positions in this specification are not necessarily referring to the same embodiment. Furthermore, certain features, structures, or characteristics of one or more embodiments of the application may be combined as suitable.

While the application has been described in terms of preferred embodiments, it is not intended to be limiting, but rather to the application, as will occur to those skilled in the art, without departing from the spirit and scope of the application. Therefore, any modification, equivalent variation and modification of the above embodiments according to the technical substance of the present application fall within the protection scope defined by the claims of the present application.

Claims

1. Turbine vane mounting structure comprising an upper cover plate (901), a lower support plate (902) and a CMC turbine vane (75) located between the upper cover plate (901) and the lower support plate (902), the CMC turbine vane (75) comprising an upper rim plate (751) for cooperation with the upper cover plate (901) and a lower rim plate (752) for cooperation with the lower support plate (902),

characterized in that the structure further comprises a plurality of balls (911) arranged 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) further comprise grooves (912), the grooves (912) are used for bearing the balls (911), and rolling fit is formed among the upper cover plate (901), the lower edge plate (752) and/or the lower edge plate (752) and the lower support plate (902) by means of the balls.

2. The turbine vane mounting structure of claim 1, further comprising an elastic member (920) for supporting the ball (911).

3. The turbine vane mounting structure of claim 2, characterized in that the elastic member (920) is a spring, disposed in the groove (912), with one end for abutting against the bottom surface of the groove (912) and the other end for supporting the ball (911) and allowing the ball (911) to roll.

4. The turbine vane mounting structure of claim 2, characterized in that the resilient member (920) is a spring disposed within the groove (912), a top (913) of the groove (912) is tapered, and a top (913) aperture is smaller than the ball (911) diameter, the groove (912) being capable of retaining at least half the volume that accommodates the ball (911).

5. The turbine vane mounting structure of claim 2, characterized in that the elastic member (920) includes a support portion (921) and a plurality of elastic plates (922), the support portion (921) being fixedly provided on the upper cover plate (901) and/or the lower blade (902), the plurality of elastic plates extending from the support portion (921) toward the groove (912) and forming an elastic support layer (923) above the groove (912), the elastic support layer (923) being for bearing the balls (911) and allowing the balls (911) to roll.

6. Turbine vane mounting structure according to claim 2, characterized in that the elastic member (920) comprises an integral elastic plate (924), the integral elastic plate (924) comprising a fixing portion (925) and a bearing portion (926), the fixing portion (925) being adapted to be fixed on the upper cover plate (901) and/or the lower plate (902), the bearing portion (926) being located above the recess (912) for being adapted to be rollably engaged with the ball (911), comprising a hollowed-out portion (927).

7. The turbine vane mounting structure of claim 2, characterized in that the balls (911) and the elastic member (920) are high temperature resistant materials.

8. The turbine vane mounting structure of claim 1, characterized in that the groove depth that mates with the ball (911) is smaller than the ball diameter but larger than the ball radius.

9. The turbine vane mounting structure of claim 2, characterized in that the groove depth fitted with the balls (911) is smaller than the sum of the ball diameter and the minimum length of the elastic member, but larger than the sum of the ball radius and the maximum length of the elastic member.

10. Turbine vane mounting structure according to claim 1, characterized in that the ball radius between the upper rim plate (751) and the upper cover plate (901) is larger than the gap height between the upper rim plate (751) and the upper cover plate (901) and/or the ball radius between the lower rim plate (752) and the lower carrier (902) is larger than the gap height between the lower rim plate (752) and the lower carrier (902).

11. Turbine, characterized in that the turbine vane is mounted using the turbine vane mounting structure as claimed in any one of claims 1 to 10.