Aircraft engine and its guide valve sealing structure

Abstract

The present invention discloses an aircraft engine and a guide vane sealing structure thereof, wherein the guide vane sealing structure includes a guide vane and a casing, the guide vane including a lower edge plate and a plurality of guide vanes arranged on the lower edge plate, the guide vane being integrally formed, the lower edge plate being provided with a plurality of expansion joints equidistantly arranged along its circumference, the expansion joints being provided between two corresponding adjacent guide vanes to divide the lower edge plate into a plurality of segments, the casing being provided with cold air flow ducts at both ends along its axial direction, the casing being provided with a gas baffle on its outer wall facing the lower edge plate, the gas baffle being spaced apart relative to the lower edge plate and used to shield the expansion joint along the radial direction of the guide vane. The guide vane sealing structure provided by the present invention is quick and easy to assemble, has a simple structure, can ensure the structural strength and stability of the guide vane, enables the guide vane to better release thermal stress, and also has a better sealing effect.

Description

Technical Field

[0001] The present invention relates to the technical field of guide rails of aircraft engines, and in particular to a guide rail sealing structure and an aircraft engine using the guide rail sealing structure. Background Art

[0002] In aircraft engines, the guide vane is installed at the front end of the engine rotor. It serves as an annular stationary blade grid composed of inner and outer rings and a set of guide blades. When the high-temperature combustion gas passes through the convergent flow channel of the guide vanes, it converts part of the thermal energy of the combustion gas into kinetic energy and meets the inlet airflow direction required by the working blades.

[0003] like Figure 1 As shown, since the guide works directly in a high-temperature gas environment and needs to withstand large thermal stress, the existing guide usually adopts a segmented design, which divides the entire ring structure into multiple arc segments 100 along the circumference and processes them separately, and then assembles them into an entire ring structure. At the same time, it is necessary to consider the sealing between two adjacent arc segments 100 to reduce the power loss caused by gas leakage. It is necessary to process a sealing groove 101 on the end face of each arc segment 100, and then insert a sealing piece 200 into the sealing groove 101. The sealing between two adjacent arc segments 100 is achieved by the sealing piece 200. This not only makes the overall structure complicated, but also requires the design of special assembly tooling to complete the installation of the entire circle of blades and sealing pieces. The assembly steps are cumbersome, and the misalignment of each arc segment 100 during the assembly process will bring great difficulties to the entire assembly, and even multiple assembly failures will occur, requiring repeated trial assembly. Summary of the Invention

[0004] The present invention primarily provides a guide sealing structure to solve the technical problems of the existing guide having a complex structure and difficult assembly.

[0005] The present invention also provides an aero-engine, which adopts the guide sealing structure.

[0006] According to a first aspect of the present invention, a guide sealing structure is provided, comprising a guide and a casing, wherein the guide is mounted on the outer periphery of the casing, the guide comprising an upper edge plate and a lower edge plate, and a plurality of guide vanes disposed between the upper edge plate and the lower edge plate, the guide being integrally formed, the lower edge plate being provided with a plurality of expansion joints equidistantly arranged along its circumference, each expansion joint being provided between two corresponding adjacent guide vanes to divide the lower edge plate into a plurality of segments;

[0007] The casing is provided with cold flow ducts for circulating cooling gas at both ends along its axial direction, and a gas baffle is provided on the outer wall of the casing facing the lower edge plate. The gas baffle is spaced relative to the lower edge plate and is used to shield the expansion gap along the radial direction of the guide, so that the gas in the guide can be blocked by the gas baffle when it leaks along the expansion gap, and the gas can be prevented from flowing back into the turbine disc under the action of the gas pressure of the cooling gas in the cold flow duct.

[0008] Preferably, the gas baffle includes a main baffle arranged along the axial direction of the casing and a secondary baffle arranged at the edge of the main baffle and extending in the direction toward the guide, and the vertical projection of the secondary baffle on the plane where the lower edge plate is located is located outside the lower edge plate.

[0009] More preferably, an arc transition surface is provided between a surface of the main baffle facing the lower edge plate and a surface of the secondary baffle facing the middle of the main baffle. The arc transition surface is used to guide the gas in the guide device to the secondary baffle when the gas leaks onto the main baffle along the expansion joint, so that the gas flows back to the guide device along the secondary baffle under the action of the gas pressure of the cooling gas in the cold air flow duct.

[0010] More preferably, a bending section is provided on the edge of the lower edge plate facing the air inlet end of the guide, the first end of the bending section is located in the corner space enclosed by the auxiliary baffle and the main baffle, and the second end of the bending section is flush with one end of the guide blade facing the lower edge plate.

[0011] Preferably, the guide valve sealing structure further comprises a first working blade provided at the air inlet end of the guide valve and a second working blade provided at the air outlet end of the guide valve, as well as a first turbine disc for mounting the first working blade and a second turbine disc for mounting the second working blade;

[0012] A guide edge plate is provided between the second working blade and the second turbine disc, and the guide edge plate is provided between the lower edge plate and the gas baffle, so that an S-shaped gas flow channel is formed by the gas baffle, the guide edge plate and the lower edge plate.

[0013] Preferably, the guide also includes a mounting plate provided on a side of the lower edge plate away from the guide blade, the casing includes a first casing and a second casing arranged coaxially, the first casing and the second casing are respectively provided on two opposite sides of the mounting plate and clamp the mounting plate to each other, and the guide sealing structure also includes a connecting component that is sequentially passed through the first casing, the mounting plate and the second casing and connects the first casing, the mounting plate and the second casing into a whole.

[0014] More preferably, a U-shaped hole is provided on the mounting plate, the U-shaped hole passes through two opposite sides of the mounting plate and is provided with an opening on a side of the mounting plate away from the lower edge plate, and the connecting component is passed through the U-shaped hole.

[0015] More preferably, the first casing includes a first connecting plate arranged in a radial direction, the first connecting plate is provided with a first connecting hole, and the second casing includes a second connecting plate arranged in a radial direction, the second connecting plate is provided with a second connecting hole, and the aperture of the first connecting hole is larger than the aperture of the second connecting hole;

[0016] The connecting assembly includes a bushing and a rivet. The bushing includes a coaxially arranged sleeve portion and a limiting portion. The sleeve portion is sequentially inserted into the first connecting hole and the mounting plate. The axial length of the sleeve portion is 0.1-0.3 mm larger than the sum of the thicknesses of the first connecting plate and the mounting plate. The limiting portion is provided at one end of the sleeve portion away from the mounting plate and is used to abut against the first connecting plate. The rivet is sequentially inserted into the bushing and the second connecting hole and rivets the bushing and the second connecting plate into a whole.

[0017] More preferably, the first casing further includes a support plate connected to the first connecting plate and arranged axially, and the second connecting plate is supported on the support plate.

[0018] According to a second aspect of the present invention, there is also provided an aircraft engine comprising the above-mentioned guide valve sealing structure.

[0019] The present invention has the following beneficial effects:

[0020] The guide in the guide sealing structure provided by the present invention is integrally formed. Compared with the segmented structure, it has a simple structure and high processing precision, and is easy and quick to assemble. By providing an expansion joint on the lower edge plate of the guide, the guide can expand to a certain extent along the expansion joint when heated during operation, thereby releasing thermal stress and avoiding cracks in the guide under the action of internal thermal stress. Secondly, the cold air flow duct and the gas baffle on the casing cooperate with each other to redirect the gas leaked along the expansion joint into the interior of the guide, effectively avoiding the gas backflow into the turbine disc. Compared with the method of relying on sealing plates for sealing, while ensuring the sealing effect, the sealing structure will not directly contact the guide, so that the guide has more flexibility and can fully expand to release thermal stress when heated, further ensuring the structural strength and stability of the guide.

[0021] In addition to the above-described objects, features and advantages, the present invention has other objects, features and advantages. The present invention will be further described in detail below with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] The accompanying drawings, which constitute part of this application, are intended to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are intended to explain the present invention and do not constitute an undue limitation of the present invention. In the accompanying drawings:

[0023] Figure 1 It is a schematic diagram of the local structure of the existing guide;

[0024] Figure 2 A schematic diagram of a partial structure of a guide provided in an embodiment of the present invention;

[0025] Figure 3 A schematic diagram of the assembly structure of the guide sealing structure provided in an embodiment of the present invention, wherein arrows indicate the direction of airflow;

[0026] Figure 4 for Figure 3 Schematic diagram of the assembly structure of the connecting components in the guide sealing structure shown.

[0027] Legend:

[0028] 1. Guide; 11. Upper edge plate; 12. Lower edge plate; 121. Expansion joint; 122. Bending section; 13. Guide blade; 14. Mounting plate; 141. U-shaped hole; 2. Casing; 21. Cold air flow duct; 22. Gas baffle; 221. Main baffle; 222. Auxiliary baffle; 23. First casing; 231. First connecting plate; 2311. First connecting hole; 232. Support plate; 24. Second casing; 241. Second connecting plate; 2411. Second connecting hole; 3. First working blade; 4. Second working blade; 5. First turbine disk; 6. Second turbine disk; 7. Guide edge plate; 8. Connecting assembly; 81. Bushing; 811. Sleeve portion; 812. Limiting portion; 82. Rivet. DETAILED DESCRIPTION

[0029] The embodiments of the present invention are described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below.

[0030] Please combine Figure 2 and Figure 3 As a first aspect, an embodiment of the present invention provides a guide valve sealing structure, including a guide valve 1 and a casing 2, wherein the guide valve 1 is mounted on the outer periphery of the casing 2, the guide valve 1 includes an upper edge plate 11 and a lower edge plate 12, and a plurality of guide blades 13 arranged between the upper edge plate 11 and the lower edge plate 12, wherein the plurality of guide blades 13 are arranged at equal intervals and are used to guide the high-temperature combustion gas in the guide valve 1.

[0031] Preferably, the guide vane 1 is integrally formed, and the lower edge plate 12 is provided with a plurality of expansion joints 121 equidistantly arranged along its circumference. Any expansion joint 121 is provided between two corresponding adjacent guide blades 13 to divide the lower edge plate 12 into multiple segments. The casing 2 is provided with cold air flow ducts 21 at both ends along its axial direction for circulating high-pressure cooling gas. A gas baffle 22 is provided on the outer wall of the casing 2 facing the lower edge plate 12. The gas baffle 22 is spaced relative to the lower edge plate 12 and is used to shield the expansion joints 121 along the radial direction of the guide vane 1. When the gas in the guide vane 1 leaks along the expansion joints 121, it can be blocked by the gas baffle 22. Under the action of the gas pressure of the cooling gas in the cold air flow duct 21, the leaked gas is redirected into the interior of the guide vane 1 to prevent the gas from flowing back into the turbine disc.

[0032] Since the guide 1 is integrally formed, compared with a segmented structure, it has a simple structure and high processing precision, and is easy and quick to assemble. By providing an expansion joint 121 on the lower edge plate 12 of the guide 1, the guide 1 can expand to a certain extent along the expansion joint 121 when heated during operation, thereby releasing thermal stress and preventing the guide 1 from cracking under the action of internal thermal stress. Secondly, the cold air flow duct 21 and the gas baffle 22 on the casing 2 can cooperate with each other to redirect the gas leaked along the expansion joint 121 into the interior of the guide 1, effectively preventing the gas from backflowing into the turbine disc. Compared with the method of relying on sealing plates for sealing, while ensuring the sealing effect, the sealing structure will not directly contact the guide 1, so that the guide 1 has more flexibility and can fully expand to release thermal stress when heated, further ensuring the structural strength and stability of the guide 1.

[0033] Furthermore, the width of the expansion joint 121 is between 0.5 and 1 mm, which can effectively reduce the leakage of gas during operation on the one hand, and effectively ensure the release of thermal stress of the guide 1 during operation on the other hand, thereby preventing the guide 1 from cracking due to internal thermal stress. When the width of the expansion joint 121 is less than 0.5 mm, the guide 1 will not be able to fully expand and release thermal stress. When the width of the expansion joint 121 is greater than 1 mm, it will cause excessive gas leakage, making it impossible to guide the gas back into the guide 1 through the cooperation of the cold air flow channel 21 and the gas baffle 22, and will also reduce the structural strength of the guide 1.

[0034] Furthermore, the expansion joints 121 are provided with 6-8, and the specific number can be adjusted according to the actual size of the guide 1 and the expansion requirement. While meeting the expansion requirement, the number of the expansion joints 121 can be reduced as much as possible to reduce the risk of gas leakage and ensure that the guide 1 has a certain structural strength.

[0035] Preferably, the gas baffle 22 includes a main baffle 221 arranged along the axial direction of the casing 2 and a secondary baffle 222 provided at the edge of the main baffle 221 and extending in the direction toward the guide 1. The vertical projection of the secondary baffle 222 on the plane where the lower edge plate 12 is located is located outside the lower edge plate 12, that is, the axial length of the main baffle 221 is greater than the axial length of the lower edge plate 12, so that the main baffle 221 completely covers the lower edge plate 12, and the cavity space enclosed by the secondary baffle 222 and the main baffle 221 completely surrounds the lower edge plate 12, thereby providing a better gas blocking effect. Moreover, after being blocked by the main baffle 221, the gas leaking along the expansion joint 121 can change its flow direction under the guidance of the secondary baffle 222, so that the gas can be more easily reintroduced into the guide 1 by the cooling gas.

[0036] More preferably, an arc transition surface is provided between a side of the main baffle 221 facing the lower edge plate 12 and a side of the auxiliary baffle 222 facing the middle of the main baffle 221. The arc transition surface is used to guide the gas in the guide 1 to the auxiliary baffle 222 when the gas leaks along the expansion joint 121 to the main baffle 221, so that the gas flows back to the guide 1 along the auxiliary baffle 222 under the action of the air pressure of the cooling gas in the cold air flow duct 21, so that the gas reversal is smoother, a circulation can be automatically formed, and the reflux effect is enhanced.

[0037] More preferably, a bent section 122 is provided on the edge of the lower edge plate 12 facing the air inlet end of the guide vane 1. The first end of the bent section 122 is located within the corner space enclosed by the auxiliary baffle 222 and the main baffle 221, and the second end of the bent section 122 is flush with the end of the guide vane 13 facing the lower edge plate 12. Because the bent section 122 is provided at the air inlet end of the guide vane 1, the direction from the first end to the second end of the bent section 122 is aligned with the direction of the main airflow within the guide vane 1. As a result, under the high-speed guidance of the main airflow, the bent section 122 can be used to draw the gas in the corner space enclosed by the auxiliary baffle 222 and the main baffle 221 back into the guide vane 1, further enhancing the gas recirculation effect and preventing gas leakage into the turbine disk.

[0038] Preferably, the guide valve sealing structure further includes a first working blade 3 provided at the air inlet end of the guide valve 1 and a second working blade 4 provided at the air outlet end of the guide valve 1, as well as a first turbine disc 5 for mounting the first working blade 3 and a second turbine disc 6 for mounting the second working blade 4. A guide edge plate 7 is provided between the second working blade 4 and the second turbine disc 6. The guide edge plate 7 is provided between the lower edge plate 12 and the gas baffle 22, so that an S-shaped gas flow channel is formed by the gas baffle 22, the guide edge plate 7, and the lower edge plate 12. This allows the cooling gas flowing from the cold gas flow channel 21 to collide with the backflowing gas to form a vortex, allowing the vortexing gas to flow back into the guide valve 1 more smoothly, further preventing gas leakage and providing the guide valve 1 with a better sealing effect.

[0039] Please combine Figure 2 and Figure 4 The guide 1 shown further includes a mounting plate 14 disposed on a side of the lower edge plate 12 away from the guide vanes 13. The casing 2 includes a coaxially arranged first casing 23 and a second casing 24. The first casing 23 and the second casing 24 are disposed on opposite sides of the mounting plate 14 and mutually clamp the mounting plate 14. The guide sealing structure further includes a connecting assembly 8 that sequentially penetrates the first casing 23, the mounting plate 14, and the second casing 24 to connect the first casing 23, the mounting plate 14, and the second casing 24 into a whole.

[0040] Specifically, the gas baffles 22 are provided on both the first and second casings 23, 24. The gas baffles 22 on each of the first and second casings 23, 24 respectively surround the axial ends of the lower edge plate 12. When the first and second casings 23, 24 are assembled into a single unit, a complete baffle structure is formed that completely covers the lower edge plate 12, ensuring a sealing effect. More importantly, by clamping the guide 1 between the two casing sections, the assembly difficulty of the guide 1 is greatly reduced, making assembly more convenient and quick. It also facilitates centering and circumferential anti-rotation of the guide 1, improving the installation accuracy of the guide 1.

[0041] Preferably, a U-shaped hole 141 is formed on the mounting plate 14. The U-shaped hole 141 passes through two opposite sides of the mounting plate 14 and is provided with an opening on the side of the mounting plate 14 away from the lower edge plate 12. The connecting assembly 8 is passed through the U-shaped hole 141. Through the one-to-one matching of multiple connecting assemblies 8 and multiple U-shaped holes 141, not only can the guide 1 be accurately installed, but also, under the common limitation of the multiple U-shaped holes 141, the guide 1 can be allowed to expand radially and automatically maintain a centered state relative to the casing 2 after radial expansion, without causing stress concentration, avoiding expansion in a high temperature environment and causing extrusion deformation of the guide vanes 13, and avoiding eccentricity of parts or scraping of the rotor, thereby ensuring the stable performance of the aircraft engine.

[0042] More preferably, the first casing 23 includes a first connecting plate 231 arranged radially, and a first connecting hole 2311 is provided on the first connecting plate 231; the second casing 24 includes a second connecting plate 241 arranged radially, and a second connecting hole 2411 is provided on the second connecting plate 241; the aperture of the first connecting hole 2311 is larger than the aperture of the second connecting hole 2411.

[0043] The connecting assembly 8 includes a bushing 81 and a rivet 82. The bushing 81 includes a coaxially arranged sleeve portion 811 and a limiting portion 812. The sleeve portion 811 is sequentially inserted into the first connecting hole 2311 and the U-shaped hole 141 of the mounting plate 14. The limiting portion 812 is arranged at an end of the sleeve portion 811 away from the mounting plate 14 and is used to abut the first connecting plate 231. The rivet 82 is sequentially inserted into the bushing 81 and the second connecting hole 2411 and rivets the bushing 81 and the second connecting plate 241 into a whole, thereby riveting the first casing 23, the mounting plate 14 and the second casing 24 into a whole. The axial length of the sleeve portion 811 is 0.1-0.3 mm greater than the sum of the thicknesses of the first connecting plate 231 and the mounting plate 14, that is, after riveting and fixing, the axial limiting effect of the sleeve portion 811 allows a certain amount of axial movement between the first casing 23, the second casing 24 and the guide 1, thereby avoiding overly tight fitting, thereby allowing the first casing 23, the second casing 24 and the guide 1 to collide axially when heated during operation, thereby better releasing internal stress.

[0044] It is worth noting that when the axial length of the sleeve portion 811 is less than 0.1 mm greater than the combined thickness of the first connecting plate 231 and the mounting plate 14, the axial play between the first and second casings 23, 24, and the guide 1 will be too small, making it easy for component or assembly errors to cause adjacent parts to fit tightly together and prevent internal stress from being released. When the axial length of the sleeve portion 811 is greater than 0.3 mm greater than the combined thickness of the first connecting plate 231 and the mounting plate 14, the axial play between the first and second casings 23, 24, and the guide 1 will be excessive, making it easy for them to wobble during use and affecting performance.

[0045] More preferably, the first casing 23 further includes a support plate 232 connected to the first connecting plate 231 and arranged axially, and the second connecting plate 241 rests on the support plate 232, with a small clearance fit between the second connecting plate 241 and the support plate 232. The first casing 23 supports the second casing 24 via the support plate 232, thereby achieving radial position limitation between the first casing 23 and the second casing 24, ensuring the coaxiality of the first casing 23 and the second casing 24. Furthermore, since the second connecting plate 241 and the support plate 232 are fitted with a small clearance and are not tightened to each other, they can allow the first casing 23 and the second casing 24 to expand radially when heated, preventing the first casing 23 and the second casing 24 from squeezing each other, thereby avoiding the problem of rotor and stator scraping caused by eccentricity.

[0046] According to a second aspect of the present invention, an aircraft engine (not shown, the same below) is also provided, comprising the aforementioned guide valve sealing structure. Because the aircraft engine employs the aforementioned guide valve sealing structure, it features a simple structure, high machining precision, and convenient and quick assembly. It effectively relieves thermal stress and provides a superior sealing effect, preventing gas leakage and thereby effectively improving the aircraft engine's performance.

[0047] The foregoing description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Those skilled in the art will readily appreciate that various modifications and variations of the present invention are possible. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention are intended to be within the scope of protection of the present invention.

Claims

1. A guide sealing structure, comprising a guide (1) and a casing (2), wherein the guide (1) is mounted on the outer periphery of the casing (2), the guide (1) comprises an upper edge plate (11) and a lower edge plate (12), and a plurality of guide blades (13) arranged between the upper edge plate (11) and the lower edge plate (12), characterized in that: The guide (1) is integrally formed, and the lower edge plate (12) is provided with a plurality of expansion joints (121) arranged equidistantly along its circumference, and any of the expansion joints (121) is provided between two corresponding adjacent guide blades (13) to divide the lower edge plate (12) into a plurality of segments; The casing (2) is provided with cold air flow channels (21) for circulating cooling gas at both ends along its axial direction, and a gas baffle (22) is provided on the outer wall of the casing (2) facing the lower edge plate (12). The gas baffle (22) is spaced apart relative to the lower edge plate (12) and is used to shield the expansion gap (121) along the radial direction of the guide (1), so that the gas in the guide (1) can be blocked by the gas baffle (22) when leaking along the expansion gap (121), and the gas is prevented from flowing back into the turbine disc under the action of the gas pressure of the cooling gas in the cold air flow channel (21); The gas baffle (22) comprises a main baffle (221) arranged along the axial direction of the casing (2) and a secondary baffle (222) arranged at the edge of the main baffle (221) and extending in a direction toward the guide (1), wherein a vertical projection of the secondary baffle (222) on the plane where the lower edge plate (12) is located is located outside the lower edge plate (12); The guide (1) further comprises a mounting plate (14) provided on a side of the lower edge plate (12) away from the guide blade (13); the casing (2) comprises a first casing (23) and a second casing (24) coaxially arranged; the first casing (23) and the second casing (24) are respectively provided on two opposite sides of the mounting plate (14) and clamp the mounting plate (14) with each other; the guide sealing structure further comprises a connecting component (8) which is sequentially provided on the first casing (23), the mounting plate (14) and the second casing (24) and connects the first casing (23), the mounting plate (14) and the second casing (24) into a whole; The first casing (23) includes a first connecting plate (231) arranged in a radial direction, the first connecting plate (231) being provided with a first connecting hole (2311), the second casing (24) includes a second connecting plate (241) arranged in a radial direction, the second connecting plate (241) being provided with a second connecting hole (2411), and the aperture of the first connecting hole (2311) is larger than the aperture of the second connecting hole (2411); The connecting assembly (8) includes a bushing (81) and a rivet (82), the bushing (81) includes a sleeve portion (811) and a limiting portion (812) arranged coaxially, the sleeve portion (811) is sequentially inserted into the first connecting hole (2311) and the mounting plate (14), the axial length of the sleeve portion (811) is 0.1-0.3 mm greater than the sum of the thicknesses of the first connecting plate (231) and the mounting plate (14), the limiting portion (812) is provided at one end of the sleeve portion (811) away from the mounting plate (14) and is used to abut against the first connecting plate (231), the rivet (82) is sequentially inserted into the bushing (81) and the second connecting hole (2411) and rivets the bushing (81) and the second connecting plate (241) into a whole.

2. The guide sealing structure according to claim 1, characterized in that: An arc transition surface is provided between a surface of the main baffle (221) facing the lower edge plate (12) and a surface of the auxiliary baffle (222) facing the middle of the main baffle (221). The arc transition surface is used to guide the gas in the guide (1) to the auxiliary baffle (222) when the gas leaks along the expansion joint (121) to the main baffle (221), so that the gas flows back to the guide (1) along the auxiliary baffle (222) under the action of the gas pressure of the cooling gas in the cold air flow channel (21).

3. The guide sealing structure according to claim 1, characterized in that: A bent section (122) is provided on the edge of the lower edge plate (12) facing the air inlet end of the guide (1), a first end of the bent section (122) is located in a corner space enclosed by the auxiliary baffle (222) and the main baffle (221), and a second end of the bent section (122) is flush with an end of the guide blade (13) facing the lower edge plate (12).

4. The guide sealing structure according to claim 1, characterized in that: The guide valve sealing structure further comprises a first working blade (3) provided at the air inlet end of the guide valve (1) and a second working blade (4) provided at the air outlet end of the guide valve (1), as well as a first turbine disc (5) for mounting the first working blade (3) and a second turbine disc (6) for mounting the second working blade (4); A guide edge plate (7) is provided between the second working blade (4) and the second turbine disc (6), and the guide edge plate (7) is provided between the lower edge plate (12) and the gas baffle (22), so that an S-shaped gas flow channel is formed by the gas baffle (22), the guide edge plate (7) and the lower edge plate (12).

5. The guide sealing structure according to claim 1, characterized in that: A U-shaped hole (141) is provided on the mounting plate (14), the U-shaped hole (141) passes through two opposite sides of the mounting plate (14) and is provided with an opening on a side of the mounting plate (14) away from the lower edge plate (12), and the connecting assembly (8) is passed through the U-shaped hole (141).

6. The guide sealing structure according to claim 1, characterized in that: The first casing (23) further includes a support plate (232) connected to the first connecting plate (231) and arranged axially, and the second connecting plate (241) is supported on the support plate (232).

7. An aircraft engine, characterized in that: The invention comprises a guide sealing structure as claimed in any one of claims 1 to 6.

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