A turbine guide vane

Abstract

The application belongs to the technical field of turbine guide vane design of an aero-engine, and particularly relates to a turbine guide vane, which comprises a blade body made of a ceramic matrix composite material and having a cavity structure with a plurality of film holes arranged on a side wall thereof; and a flow guide pipe made of a metal material, having a plurality of impact holes on a side wall thereof, arranged in the cavity, and forming an impact cavity with the side wall of the blade body, and having a plurality of Omega-shaped corrugated protruding parts on the side wall thereof; and the Omega-shaped corrugated protruding parts of the flow guide pipe are axially extended and abut against the side wall of the blade body.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of turbine guide vane design of an aero-engine, and particularly relates to a turbine guide vane. BACKGROUND

[0002] Increasing the turbine inlet temperature of an aero-engine and reducing the structural weight are main approaches to improving the thrust-to-weight ratio thereof.

[0003] The turbine guide vane of an aero-engine is located at the turbine inlet position, and under the requirement of improving the thrust-to-weight ratio, the turbine guide vane bears a relatively high temperature.

[0004] Ceramic matrix composite material has low density and excellent high-temperature resistance, and thus is used to manufacture the turbine guide vane, which can not only enhance the ability to bear high temperature but also reduce the mass, so as to effectively improve the thrust-to-weight ratio of the aero-engine.

[0005] Although the turbine guide vane manufactured from ceramic matrix composite material can bear a relatively high temperature and can be well applied to most working conditions of the aero-engine, the temperature received by the turbine guide vane under certain extreme working conditions will exceed its bearing capacity, which will affect the overall performance of the aero-engine and even cause danger. At present, the following two measures are mainly taken:

[0006] 1) The turbine guide vane manufactured from ceramic matrix composite material is designed as a hollow structure, and a plurality of film holes are formed in the side wall of the blade body. When the aero-engine is working, cooling gas is introduced into the hollow cavity, and the cooling gas is discharged through the film holes, so as to cool the turbine guide vane. This technical solution has low cooling efficiency, and a large amount of cooling gas is required. Correspondingly, a large number of film holes need to be formed in the side wall of the blade body, which will seriously damage the integrity of the fibers in the ceramic matrix composite material and greatly weaken the strength and toughness of the turbine guide vane.

[0007] 2) The turbine guide vane manufactured from ceramic matrix composite material is designed as a hollow structure, a plurality of film holes are formed in the side wall of the blade body, and a flow guide pipe is arranged in the hollow cavity. The flow guide pipe and the side wall of the blade body form an impingement cavity, and a plurality of impingement holes are formed in the side wall of the flow guide pipe to form a double-wall structure. When the aero-engine is working, cooling gas is introduced into the flow guide pipe, and the cooling gas enters the impingement cavity through the impingement holes to impact and cool the side wall of the blade body and is then discharged through the film holes. This technical solution has high cooling efficiency, and the number of film holes formed in the side wall of the blade body can be correspondingly reduced. Only a small number of film holes are formed in the side walls of the leading edge and trailing edge of the blade body to reduce the damage to the integrity of the fibers in the ceramic matrix composite material and ensure the strength and toughness of the turbine guide vane. However, the turbine guide vane manufactured from ceramic matrix composite material has a double-wall structure, which is difficult to process and manufacture and has high cost.

[0008] The present application is proposed in view of the above technical defects.

[0009] It should be noted that the disclosure of the foregoing background art is only used to assist in understanding the inventive concept and technical solutions of the present application, and does not necessarily belong to the prior art of the present patent application. In the absence of explicit evidence that the above-mentioned content has been disclosed on the filing date of the present application, the above-mentioned background art should not be used to evaluate the novelty and inventiveness of the present application. SUMMARY

[0010] The purpose of the present application is to provide a turbine guide vane to overcome or alleviate at least one aspect of the technical defects known to exist.

[0011] The technical solutions of the present application are:

[0012] A turbine guide vane, comprising:

[0013] A blade body made of a ceramic matrix composite material, which is a hollow structure with a plurality of film holes in the side wall;

[0014] A flow guide pipe made of a metal material, having a plurality of impact holes in the side wall, arranged in the hollow cavity and forming an impact cavity with the side wall of the blade body, and having a plurality of Ω-shaped corrugated protruding parts in the side wall;

[0015] Each Ω-shaped corrugated protruding part extends axially along the flow guide pipe and abuts against the side wall of the blade body.

[0016] According to at least one embodiment of the present application, the turbine guide vane described above has a plurality of bulges on the flow guide pipe;

[0017] Each bulge is distributed circumferentially along the flow guide pipe and abuts against the side wall of the blade body.

[0018] According to at least one embodiment of the present application, the turbine guide vane described above has a partition rib in the hollow cavity, which divides the hollow cavity into a leading edge cavity and a trailing edge cavity; wherein the leading edge cavity is close to the leading edge of the blade body and forms an opening at the root of the blade body; the trailing edge cavity is close to the trailing edge of the blade body and forms an opening at the tip of the blade body;

[0019] The flow guide pipe comprises:

[0020] A front flow guide pipe, one end of which extends into the leading edge cavity, and the other end has a front flow guide pipe connecting edge on the outer wall;

[0021] A rear flow guide pipe, one end of which extends into the trailing edge cavity, and the other end has a rear flow guide pipe connecting edge on the outer wall;

[0022] The turbine guide vane further comprises:

[0023] A first bolt fastener for connecting the front flow guide pipe connecting edge to the root of the blade body;

[0024] A second bolt fastener connects the aft shroud connection edge to the tip of the blade.

[0025] According to at least one embodiment of the present application, in the turbine guide vane as described above, the Ω-shaped corrugated protruding part on the front shroud has two parts, one of which abuts against the side wall of the blade near the leading edge, and the other of which abuts against the side wall of the blade near the trailing edge.

[0026] The Ω-shaped corrugated protruding part on the aft shroud has two parts, one of which abuts against the side wall of the blade near the trailing edge, and the other of which abuts against the side wall of the blade near the trailing edge.

[0027] According to at least one embodiment of the present application, in the turbine guide vane as described above, the end of the front shroud that extends into the leading edge cavity is sealed.

[0028] The end of the aft shroud that extends into the trailing edge cavity is sealed.

[0029] According to at least one embodiment of the present application, in the turbine guide vane as described above, the area of the blade where the first bolt fastener and the second bolt fastener are located is locally thickened.

[0030] According to at least one embodiment of the present application, in the turbine guide vane as described above, the first bolt fastener is located in the area of the trailing edge cavity in the axial direction of the blade.

[0031] The second bolt fastener is located in the area of the leading edge cavity in the axial direction of the blade.

[0032] According to at least one embodiment of the present application, in the turbine guide vane as described above, the head of the first bolt fastener is located in the trailing edge cavity.

[0033] The head of the first bolt fastener is located in the leading edge cavity.

[0034] According to at least one embodiment of the present application, in the turbine guide vane as described above, it further comprises:

[0035] An upper shroud is connected to the tip of the blade, and has an upper shroud cooling cavity inside, an inner side wall with upper shroud film holes, and an outer wall with upper shroud impingement holes; the upper shroud cooling cavity surrounds the tip of the blade.

[0036] A lower shroud is connected to the root of the blade, and has a lower shroud cooling cavity inside, an inner side wall with lower shroud film holes, and an outer wall with lower shroud impingement holes; the lower shroud cooling cavity surrounds the root of the blade.

[0037] According to at least one embodiment of the present application, in the turbine guide vane as described above, the upper shroud is made of ceramic matrix composite material, and the inner side wall is formed on the tip of the blade and is connected to the outer side wall by adhesive bonding, and the upper shroud cooling cavity is formed therebetween.

[0038] The lower shroud is made of ceramic matrix composite material, and the inner side wall is formed at the root of the blade body and is bonded with the outer side wall, and a cooling cavity of the lower shroud is formed between the inner side wall and the outer side wall. BRIEF DESCRIPTION OF DRAWINGS

[0039] Fig. 1 is a schematic diagram of a turbine guide vane provided by an embodiment of the present application;

[0040] Fig. 2 is an assembly schematic diagram of a turbine guide vane provided by an embodiment of the present application;

[0041] Fig. 3 is a partial sectional view of a turbine guide vane provided by an embodiment of the present application;

[0042] Fig. 4 is a schematic diagram of a flow guide provided by an embodiment of the present application;

[0043] wherein:

[0044] 1-blade body; 2-flow guide; 3-first bolt fastener; 4-second bolt fastener; 5-upper shroud; 6-lower shroud.

[0045] In order to better illustrate the embodiments, some components in the drawings may be omitted, enlarged or reduced, and do not represent the actual product size, and in addition, the drawings are only used for illustrative description and cannot be understood as a limitation of the patent. DETAILED DESCRIPTION

[0046] In order to make the technical solutions of the present application and its advantages clearer, the technical solutions of the present application will be further clearly and completely described below in conjunction with the drawings. It should be understood that the specific embodiments described herein are only part of the embodiments of the present application, and are only used to explain the present application, but not to limit the present application. It should be noted that, in order to facilitate description, only parts related to the present application are shown in the drawings, and other related parts can be referred to the usual design. In the case of no conflict, the embodiments in the present application and the technical features in the embodiments can be combined to obtain new embodiments.

[0047] In addition, unless otherwise defined, technical terms or scientific terms used in the description of the present application shall be understood as having the common meaning to those of ordinary skill in the art to which the present application belongs. The words "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer" and the like, which indicate orientation in the description of the present application, are used only to indicate relative directional or positional relationship, and are not intended to imply that the device or element must have a particular orientation, be constructed and operated in a particular orientation, and the relative positional relationship thereof can also be changed accordingly when the absolute position of the described object is changed, and therefore cannot be understood as a limitation on the present application. The words "first", "second", "third" and the like used in the description of the present application are only for the purpose of description, to distinguish different components, and cannot be understood as indicating or implying relative importance. The words "one", "an" or "the" and the like used in the description of the present application should not be understood as an absolute limitation on the number, but should be understood as the presence of at least one. The words "including" or "containing" and the like used in the description of the present application mean that the elements or objects appearing before the words are encompassed by the elements or objects listed after the words and their equivalents, and do not exclude other elements or objects.

[0048] In addition, it should be further pointed out that, unless otherwise explicitly specified and limited, the words "mounting", "connecting", "connecting" and the like used in the description of the present application should be understood in a broad sense, for example, the connection can be fixed connection, or detachable connection, or integral connection; can be mechanical connection, or electrical connection; can be directly connected, or indirectly connected through intermediate medium, or the internal communication of two elements, and those skilled in the art can understand the specific meaning of the present application according to the specific circumstances.

[0049] The following will be described in detail in combination with the accompanying drawings Figs. 1 to 4 The present application will be further described in detail.

[0050] A turbine guide vane, comprising:

[0051] A blade 1 made of ceramic matrix composite material, which is a hollow structure with a plurality of film holes in the side wall;

[0052] A flow guide pipe 2 made of metal material, which has a plurality of impact holes in the side wall, is arranged in the cavity, and forms an impact cavity between the side wall of the blade 1, and has a plurality of Ω-shaped corrugated protruding parts in the side wall;

[0053] Each Ω-shaped corrugated protruding part of the flow guide pipe 2 extends axially and abuts against the side wall of the blade 1.

[0054] For the turbine guide vane disclosed in the above embodiments, the person skilled in the art can understand that the guide pipe 2 made of metal is arranged in the cavity of the blade body 1 made of ceramic matrix composite material, forming a double-wall structure, and cooling gas can be introduced into the guide pipe 2 during the operation of the aero-engine. The cooling gas enters the impingement cavity through each impingement hole, impinges on the side wall of the blade body 1, and then is discharged through each film hole, which has a high cooling efficiency, can correspondingly reduce the number of film holes opened on the side wall of the blade body 1, and can greatly reduce the damage to the integrity of the fibers in the ceramic matrix composite material, thereby ensuring the strength and toughness of the turbine guide vane. Moreover, the guide pipe 2 arranged in the cavity of the blade body 1 made of ceramic matrix composite material is made of metal material, which is convenient for processing, manufacturing and assembling. Moreover, the guide pipe 2 is arranged in the cavity of the blade body 1 made of ceramic matrix composite material and does not directly contact the high-temperature gas at the turbine inlet of the aero-engine, so the temperature is relatively low and the guide pipe 2 is not easily damaged by high temperature. Moreover, the guide pipe 2 can be designed to have a relatively thin wall thickness to reduce the overall weight of the aero-engine and improve the thrust-to-weight ratio of the aero-engine.

[0055] The ceramic matrix composite material and the metal material have different thermal expansion coefficients, and the difference between the thermal expansion coefficients is relatively large. Under high-temperature conditions, the blade body 1 made of ceramic matrix composite material and the guide pipe 2 made of metal material are prone to serious uncoordinated deformation and generate a large local stress, which may cause damage. In the turbine guide vane disclosed in the above embodiments, the guide pipe 2 is designed to abut against the side wall of the blade body 1 by the Ω-shaped corrugated protruding part extending along the axial direction on the side wall. On the one hand, the guide pipe 2 can be positioned in the cavity of the blade body 1 to prevent vibration and damage. On the other hand, the Ω-shaped corrugated protruding part has a large deformation capacity, which can absorb the large stress generated by the uncoordinated deformation of the blade body 1 and the guide pipe 2 under high-temperature conditions, thereby protecting the blade body 1 and the guide pipe 2 from damage.

[0056] In some optional embodiments, the turbine guide vane disclosed above has a plurality of bulges on the guide pipe 2.

[0057] The bulges are distributed circumferentially along the guide pipe 2 and abut against the side wall of the blade body 1. In cooperation with the Ω-shaped corrugated protruding parts, the reliability of positioning the guide pipe 2 in the cavity of the blade body 1 is enhanced. Moreover, the bulges make point contact with the side wall of the blade body 1, which can increase the turbulence of the cooling gas flow in the impingement cavity, enhance the cooling effect, and avoid causing a large pressure loss to the cooling gas flow.

[0058] In some optional embodiments, the turbine guide vane disclosed above has a partition rib in the cavity, which divides the cavity into a leading edge cavity and a trailing edge cavity. The leading edge cavity is close to the leading edge of the blade body 1 and forms an opening at the root of the blade body 1. The trailing edge cavity is close to the trailing edge of the blade body 1 and forms an opening at the tip of the blade body 1.

[0059] The flow guide pipe 2 comprises:

[0060] The front flow guide pipe has one end extending into the front edge cavity and the other end having a front flow guide pipe connecting edge on the outer wall;

[0061] The rear flow guide pipe has one end extending into the rear edge cavity and the other end having a rear flow guide pipe connecting edge on the outer wall;

[0062] The turbine guide vane further comprises:

[0063] The first bolt fastener 3 connects the front flow guide pipe connecting edge to the root of the blade body 1 without damaging the main part of the side wall of the blade body 1 and far away from the core high temperature area of the turbine inlet of the aero-engine to avoid high temperature damage;

[0064] The second bolt fastener 4 connects the rear flow guide pipe connecting edge to the tip of the blade body 1 without damaging the main part of the side wall of the blade body 1 and far away from the core high temperature area of the turbine inlet of the aero-engine to avoid high temperature damage.

[0065] In the specific application, the turbine guide vane disclosed in the above embodiment can introduce the cooling gas from the inner ring of the combustion chamber of the aero-engine into the front flow guide pipe, the cooling gas from the inner ring of the combustion chamber of the aero-engine can enter the front edge cavity through the impingement holes on the side wall of the front flow guide pipe to impact and cool the side wall of the front edge cavity, and then flow out from the film holes on the side wall of the front edge of the blade body 1, and the cooling gas from the outer ring of the combustion chamber of the aero-engine can be introduced into the rear flow guide pipe, the cooling gas from the outer ring of the combustion chamber of the aero-engine can enter the rear edge cavity through the impingement holes on the side wall of the rear flow guide pipe to impact and cool the side wall of the rear edge cavity, and then flow out from the film holes on the side wall of the rear edge of the blade body 1.

[0066] For the turbine guide vane disclosed in the above embodiment, the skilled in the art can also understand that the side wall of the blade body 1 of the turbine guide vane of the aero-engine has a large pressure gradient along the chord direction, the pressure at the front edge of the blade body 1 is much larger than the pressure at the rear edge of the blade body 1, the front edge cavity and the front flow guide pipe near the front edge of the blade body 1 are designed to introduce the cooling gas from the inner ring of the combustion chamber, which has a high pressure, to ensure that the cooling gas flowing out from the film holes near the front edge of the blade body 1 has sufficient pressure margin, and the rear edge cavity and the rear flow guide pipe near the rear edge of the blade body 1 are designed to introduce the cooling gas from the outer ring of the combustion chamber, which has a low pressure, to ensure that the cooling gas flowing out from the film holes near the rear edge of the blade body 1 has a relatively low pressure, which is suitable for the relatively low pressure at the rear edge of the blade body 1, and can facilitate the control of the amount of cooling gas flowing out from the film holes in each chord direction of the blade body 1, thereby reducing the temperature gradient of the side wall of the blade body along the chord direction, avoiding large non-uniform deformation of the blade body, and effectively utilizing the space structure of the root and tip of the blade body 1 to avoid weakening the local strength of the blade body 1.

[0067] For the turbine guide vane disclosed in the above embodiments, the person skilled in the art can also understand that the front fairing is connected to the root of the blade body 1 through the front fairing connecting edge by the first bolt fastener 3, and the rear fairing is connected to the tip of the blade body 1 through the rear fairing connecting edge by the second bolt fastener 4. The first bolt fastener 3 and the second bolt fastener 4 can release the stress caused by the high-temperature incoordination deformation between the blade body 1 made of ceramic matrix composite material and the fairing 2 made of metal, thereby avoiding high-temperature damage.

[0068] In some optional embodiments, the turbine guide vane disclosed above, the Ω-shaped corrugated convex part on the front fairing has two parts, one of which abuts against the side wall of the blade body 1 at the leading edge, and the other abuts against the side wall of the blade body 1 near the leading edge suction surface.

[0069] The Ω-shaped corrugated convex part on the rear fairing has two parts, one of which abuts against the side wall of the blade body 1 near the trailing edge suction surface, and the other abuts against the side wall of the blade body 1 near the trailing edge pressure surface, which is the place with a large temperature gradient.

[0070] For the turbine guide vane disclosed in the above embodiments, the person skilled in the art can also understand that the blade body 1 and the fairing 2 are designed to contact at the place with a large temperature gradient through the Ω-shaped corrugated convex part, that is, through the line contact of the Ω-shaped corrugated convex part at the most serious incoordination deformation part. This can efficiently absorb the large stress caused by the incoordination deformation of the blade body 1 and the fairing 2, thereby avoiding direct contact of the corresponding parts under high-temperature conditions and protecting the blade body 1 and the fairing 2 from damage.

[0071] In some optional embodiments, the turbine guide vane disclosed above, the end of the front fairing extending into the leading edge cavity is sealed.

[0072] The end of the rear fairing extending into the trailing edge cavity is sealed.

[0073] In some optional embodiments, the turbine guide vane disclosed above, the area of the blade body 1 where the first bolt fastener 3 and the second bolt fastener 4 are located is locally thickened to compensate for the strength damage caused by the bolt hole.

[0074] In some optional embodiments, the turbine guide vane disclosed above, the first bolt fastener 3 is located in the area of the trailing edge cavity in the axial direction of the blade body 1, and this area has sufficient space to allow multiple first bolt fasteners 3 to be connected.

[0075] The second bolt fastener 4 is located in the area of the leading edge cavity in the axial direction of the blade body 1, and this area has sufficient space to allow multiple second bolt fasteners 4 to be connected.

[0076] In some alternative embodiments, the turbine guide vane as described above, the head of the first bolt fastener 3 is located in the trailing edge cavity, in order to avoid installation interference, the head of each first bolt fastener 3 can be designed as a special shape, such as flat;

[0077] The head of the first bolt fastener 3 is located in the leading edge cavity, in order to avoid installation interference, the head of each second bolt fastener 4 can be designed as a special shape, such as flat.

[0078] In some alternative embodiments, the turbine guide vane as described above, further comprising:

[0079] The upper shroud 5 is connected to the tip of the blade body 1, and has an upper shroud cooling cavity therein, the inner side wall has upper shroud film holes, and the outer wall has upper shroud impingement holes; the upper shroud cooling cavity surrounds the tip of the blade body 1;

[0080] The lower shroud 6 is connected to the root of the blade body 1, and has a lower shroud cooling cavity therein, the inner side wall has lower shroud film holes, and the outer wall has lower shroud impingement holes; the lower shroud cooling cavity surrounds the root of the blade body 1.

[0081] The turbine guide vane disclosed in the above embodiments can introduce cooling air into the upper shroud cooling cavity through the upper shroud impingement holes when the aero-engine is working, the cooling air entering the upper shroud cooling cavity can cool the inner side wall of the upper shroud 5, and then flow out through the upper shroud film holes, which can avoid damaging the upper shroud 5 by high temperature, has a higher cooling efficiency for the upper shroud 5, and can block the high temperature effect of the high temperature gas at the turbine inlet of the aero-engine on the second bolt fastener 4.

[0082] For the turbine guide vane disclosed in the above embodiments, the design of the lower shroud 6 can refer to the explanation of the design of the upper shroud 5, and further description is not given here.

[0083] In some alternative embodiments, the turbine guide vane as described above, the upper shroud 5 is made of ceramic matrix composite material, the inner side wall is formed on the tip of the blade body 1, and is adhesively connected with the outer side wall, and the upper shroud cooling cavity is formed therebetween, which can facilitate the processing of the upper shroud cooling cavity;

[0084] The lower shroud 6 is made of ceramic matrix composite material, the inner side wall is formed on the root of the blade body 1, and is adhesively connected with the outer side wall, and the lower shroud cooling cavity is formed therebetween, which can facilitate the processing of the lower shroud cooling cavity.

[0085] Each embodiment in the specification is described in a progressive manner, and each embodiment focuses on the difference from other embodiments. The same or similar parts of each embodiment can be referred to each other.

[0086] The technical scheme of the present application has been described in combination with the preferred embodiments shown in the drawings, and those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments, and those skilled in the art can make equivalent changes or replacements to the related technical features without departing from the principles of the present application, and the technical schemes after the changes or replacements will fall within the protection scope of the present application.

Claims

1. A turbine guide vane, characterized by, Comprise: A blade body (1) made of ceramic matrix composite material, which is a hollow structure with a plurality of film holes on the side wall; A flow guide pipe (2) made of metal material, which has a plurality of impact holes on the side wall, is arranged in the cavity, and forms an impact cavity with the side wall of the blade body (1), and has a plurality of Ω-shaped corrugated protruding parts on the side wall; Each of the Ω-shaped corrugated protruding parts extends along the axial direction of the flow guide pipe (2) and abuts against the side wall of the blade body (1); The flow guide pipe (2) has a plurality of bulges; Each of the bulges is distributed circumferentially along the flow guide pipe (2) and abuts against the side wall of the blade body (1); The cavity has a partition rib, which divides the cavity into a leading edge cavity and a trailing edge cavity; wherein the leading edge cavity is close to the leading edge of the blade body (1) and forms an opening at the root of the blade body (1); the trailing edge cavity is close to the trailing edge of the blade body (1) and forms an opening at the tip of the blade body (1); The flow guide pipe (2) comprises: A front flow guide pipe, one end of which extends into the leading edge cavity, and the other end has a front flow guide pipe connecting edge on the outer wall; A rear flow guide pipe, one end of which extends into the trailing edge cavity, and the other end has a rear flow guide pipe connecting edge on the outer wall; The turbine guide vane further comprises: A first bolt fastener (3) for connecting the front flow guide pipe connecting edge to the root of the blade body (1); A second bolt fastener (4) for connecting the rear flow guide pipe connecting edge to the tip of the blade body (1); The leading edge cavity and its front flow guide pipe introduce cooling gas into the inner ring of the combustion chamber; The trailing edge cavity and its rear flow guide pipe introduce cooling gas into the outer ring of the combustion chamber; The Ω-shaped corrugated protruding parts on the front flow guide pipe have two parts, one of which abuts against the side wall of the leading edge of the blade body (1), and the other of which abuts against the side wall of the blade body (1) close to the leading edge of the blade body (1); The Ω-shaped corrugated protruding parts on the rear flow guide pipe have two parts, one of which abuts against the side wall of the blade body (1) close to the trailing edge of the blade body (1), and the other of which abuts against the side wall of the blade body (1) close to the trailing edge of the blade body (1).

2. The turbine guide vane according to claim 1, wherein: The end of the front flow guide pipe extending into the leading edge cavity is sealed; The end of the rear flow guide pipe extending into the trailing edge cavity is sealed.

3. The turbine guide vane according to claim 1, wherein: The area of the blade body (1) where the first bolt fastener (3) and the second bolt fastener (4) are located is locally thickened.

4. The turbine guide vane according to claim 1, wherein: The first bolt fastener (3) is located in the area of the trailing edge cavity in the axial direction of the blade body (1); The second bolt fastener (4) is located in the area of the leading edge cavity in the axial direction of the blade body (1).

5. The turbine guide vane according to claim 4, wherein: The head of the first bolt fastener (3) is located in the trailing edge cavity; The head of the first bolt fastener (3) is located in the leading edge cavity.

6. The turbine guide vane according to claim 1, further comprising: ​ An upper shroud (5) is connected to the tip of the blade (1), and has an upper shroud cooling cavity in the interior, an inner side wall with upper shroud film holes, and an outer wall with upper shroud impingement holes; the upper shroud cooling cavity surrounds the tip of the blade (1); A lower shroud (6) is connected to the root of the blade (1), and has a lower shroud cooling cavity in the interior, an inner side wall with lower shroud film holes, and an outer wall with lower shroud impingement holes; the lower shroud cooling cavity surrounds the root of the blade (1).

7. The turbine guide vane of claim 6, wherein: The upper shroud (5) is made of ceramic matrix composite material, and the inner side wall is formed on the tip of the blade (1) and is adhesively connected to the outer side wall, with the upper shroud cooling cavity formed therebetween; The lower shroud (6) is made of ceramic matrix composite material, and the inner side wall is formed on the root of the blade (1) and is adhesively connected to the outer side wall, with the lower shroud cooling cavity formed therebetween.

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