Imported adjustable guide vanes and aero engines

Abstract

This invention discloses an adjustable guide vane and an aero-engine. The guide vane includes a blade body with a leading edge and a trailing edge. It also includes a journal at a first end of the blade body and a support boss at a second end. An adjustment assembly is connected to the journal for adjusting the guide vane angle. An inner cavity is provided within the blade body. The journal has a first air bleed structure for introducing external hot air into the inner cavity. A partition structure is provided within the inner cavity, located at the outlet end of the first air bleed structure and positioned near the trailing edge of the blade body. This partition divides the inner cavity into a front cavity near the leading edge and a rear cavity near the trailing edge, allowing the front and rear cavities to connect near the second end of the blade body. This allows the hot air introduced into the inner cavity to flow from the first end of the blade body to the second end within the front cavity and then into the rear cavity. An exhaust structure is provided within the blade body for discharging the hot air introduced into the inner cavity.

Description

Technical Field

[0001] This invention relates to the field of compressor technology, and in particular, to an adjustable guide vane. Furthermore, this invention also relates to an aero-engine comprising the aforementioned adjustable guide vane. Background Technology

[0002] As a crucial component of aero engines, the performance of the compressor directly impacts the overall performance of the entire engine. Instabilities such as stall and surge in the compressor severely affect the stability of the entire engine. Therefore, most aero engines use adjustable guide vanes at the compressor inlet to improve the overall stability of the engine.

[0003] When a helicopter equipped with an aero-engine flies in icing clouds, the adjustable guide vanes at the inlet are highly susceptible to icing. Icing alters the blade profile and reduces the flow cross-sectional area, leading to decreased engine performance and potentially causing engine damage or shutdown. Therefore, anti-icing design is necessary. Currently, the most widely used method is air-heated anti-icing, which involves introducing high-temperature, high-pressure gas from the compressor's rear end through pipes / air intake chambers into the guide vane cavity for heating and anti-icing. For ease of manufacturing, adjustable guide vanes are all welded structures, consisting of the guide vane blade body, guide vane cover, and guide vane inlet pipe. See [link to documentation]. Figure 1 The guide vane cover is welded to the guide vane body, forming a cavity between them. The guide vane body is provided with an exhaust port that communicates with the cavity for exhaust. The guide vane body and the intake pipe are welded together to form an intake air flow path. Existing technologies use relatively uniform air distribution, but icing of guide vanes occurs from the leading edge to the trailing edge, with the leading edge experiencing more severe icing. Therefore, the uniform air distribution methods in existing technologies suffer from the problem of excessive air volume and difficulty in meeting demand. For example, the structure and assembly method of the engine intake casing disclosed in patent number 202010451070.4, which uses an anti-icing ring to uniformly introduce hot air into the inner cavity, suffers from the aforementioned problem. Another example is the hot air anti-icing structure for composite material engine guide vanes with a metal leading edge disclosed in patent number 201611176267.1. Hot air is introduced from one end of the guide vane and then distributed to various branch pipes by a flute-shaped main pipe located at the leading edge, and then uniformly introduced into the anti-icing cavity and blown out from the air film slit to prevent icing at the leading edge. In this technical solution, all the hot air is guided to the leading edge of the blade, which maximizes the anti-icing effect at the leading edge, but completely ignores the anti-icing problem at the trailing edge of the blade. In practical applications, it is still necessary to add an air distribution structure to solve the problem of anti-icing at the trailing edge of the blade.

[0004] On the other hand, in order to improve the anti-icing effect, the guide vane blade and guide vane cover plate materials must be selected from beryllium bronze alloy with higher thermal conductivity. Based on the existing structural form, other materials cannot achieve the required anti-icing effect. Furthermore, beryllium bronze alloy has obvious corrosion problems after long-term use and does not meet the requirements for long-term use.

[0005] On the other hand, the existing structure uses the existing rocker arm connection + self-locking nut locking method. Since the rocker arm slot and the journal are in line contact, the rocker arm and journal are prone to crushing damage due to repeated stress as the usage time increases. At the same time, the uneven tightening of the self-locking nut makes the assembly quality unstable. If it is too tight, the frictional resistance will increase, which will easily cause structural deformation during operation. If it is too loose, it will cause the blade to wobble, affecting the adjustment accuracy. In addition, the self-locking nut may gradually lose its self-locking force, causing the nut to fall off and affecting flight safety. Summary of the Invention

[0006] This invention provides an imported adjustable guide vane and an aero-engine to solve the technical problems of poor anti-icing effect, energy waste, and difficulty in meeting the requirements of anti-icing and anti-corrosion in the prior art.

[0007] According to one aspect of the present invention, an adjustable guide vane is provided for use in an aero-engine. The guide vane includes a blade body having a leading edge and a trailing edge. The guide vane further includes a journal disposed at a first end of the blade body and a support boss disposed at a second end of the blade body. An adjustment assembly is connected to the journal for adjusting the angle of the guide vane. An inner cavity is provided inside the blade body. The journal is provided with a first air bleed structure for introducing external hot air into the inner cavity. A partition structure is provided inside the inner cavity, disposed at the outlet end of the first air bleed structure and arranged on one side near the trailing edge of the blade body, for dividing the inner cavity into a front cavity near the leading edge and a rear cavity near the trailing edge, and for connecting the front cavity and the rear cavity near the second end of the blade body, thereby allowing the hot air introduced into the inner cavity to flow from the first end of the blade body to the second end of the blade body in the front cavity and then into the rear cavity. An exhaust structure is provided on the blade body for discharging the hot air introduced into the inner cavity.

[0008] As a further improvement to the above technical solution, a second air intake structure is provided at the first end of the front cavity near the blade body. The second air intake structure has a gap between itself and the inner wall of the inner cavity and the partition structure. The second air intake structure is used to cause the hot air introduced into the front cavity to generate backflow and / or impact and / or swirling flow on the inner wall of the leading edge near the first end of the blade body.

[0009] As a further improvement to the above technical solution, the second air intake structure has a concave surface arranged toward the inner wall of the first end of the blade, a first inclined surface arranged toward the leading edge, and a second inclined surface arranged toward the separation structure. The concave surface is used to guide hot air to impact the inner wall of the first end of the blade and flow toward the inner wall of the leading edge of the blade. The first inclined surface is used to guide hot air to flow along the inner wall of the leading edge of the blade toward the second end of the blade. The second inclined surface is used to guide hot air to flow toward the second end of the blade.

[0010] As a further improvement to the above technical solution, the exhaust structure includes a plurality of first exhaust ports arranged along the trailing edge. The size of the first exhaust ports gradually increases from the first end to the second end of the blade, so that the amount of exhaust hot gas gradually decreases from the second end to the first end of the blade, thereby making the hot gas in the rear cavity evenly distributed.

[0011] As a further improvement to the above technical solution, the exhaust structure includes a second exhaust port opened at the second end of the blade, and the second exhaust port is arranged close to the leading edge of the blade.

[0012] As a further improvement to the above technical solution, the rear cavity is provided with a plurality of third air intake structures arranged at intervals along a preset direction, which are used to change the flow of the introduced hot air and thus make the hot air introduced into the rear cavity evenly distributed.

[0013] As a further improvement to the above technical solution, the separation structure includes a first inclined section and a second inclined section in sequence from the first end to the second end of the blade. The inclined direction of the first inclined section is towards the leading edge to guide the hot air to flow towards the leading edge, and the inclined direction of the second inclined section is towards the trailing edge to guide the hot air from the front cavity to the rear cavity.

[0014] As a further improvement to the above technical solution, the journal includes a threaded section and a mounting section from the outside to the inside. The adjusting assembly includes a connecting rocker arm for mounting on the mounting section and a self-locking nut for connecting to the threaded section. The connecting rocker arm has a mounting surface, and the mounting surface has a mounting hole for circumferentially engaging with the mounting section. The mounting surface is provided with a flange structure to restrict the rotation of the self-locking nut. The height of the flange structure is greater than the length of the mounting section.

[0015] As a further improvement to the above technical solution, the cross-section of the mounting section is waist-shaped and has irregular straight surfaces processed along the axial direction of the mounting section through adjacent arc-shaped surfaces and straight surfaces. The shape of the mounting hole matches the cross-sectional shape of the mounting section. The arc-shaped surface of the mounting section is set with a preset taper.

[0016] According to another aspect of the invention, an aircraft engine is also provided, which includes the aforementioned adjustable guide vanes.

[0017] The present invention has the following beneficial effects:

[0018] This imported adjustable guide vane differs from traditional uniform anti-icing air intake techniques in existing technologies. By setting up a partition structure, the inner cavity of the blade is divided into a front cavity and a rear cavity. The hot air guided into the inner cavity by the first air intake structure first flows through and gathers in the front cavity near the leading edge. Based on the actual working condition that guide vane icing occurs from front to back, the anti-icing effect of the leading edge is effectively enhanced. After the hot air is introduced and fills the front cavity, it flows into the rear cavity and is discharged through the exhaust structure. Through the reasonable inner cavity structure design, the overall structure is simplified, the heat transfer performance of the blade is improved, and the overall anti-icing effect is greatly improved. Based on the significantly improved structure and anti-icing performance of this guide vane, the component materials do not need to rely on beryllium bronze alloy with higher thermal conductivity. Corrosion-resistant stainless steel or high-temperature alloys can be used instead, which improves both the strength level and corrosion resistance of the components.

[0019] In addition to the objectives, features, and advantages described above, the present invention has other objectives, features, and advantages. The invention will now be described in further detail with reference to the figures. Attached Figure Description

[0020] The accompanying drawings, which form part of this application, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings:

[0021] Figure 1 This is a schematic diagram of the guide vane structure in the prior art;

[0022] Figure 2 This is a schematic diagram of the guide vane structure of a preferred embodiment of the present invention;

[0023] Figure 3 This is a schematic diagram of the guide vane installed in an engine according to a preferred embodiment of the present invention;

[0024] Figure 4 This is a schematic diagram of the internal structure of the guide vane according to a preferred embodiment of the present invention;

[0025] Figure 5 This is a partial structural diagram of the guide vanes installed in an engine according to a preferred embodiment of the present invention;

[0026] Figure 6 This is a schematic diagram of the journal structure of the guide vane according to a preferred embodiment of the present invention;

[0027] Figure 7 This is a schematic diagram of the mounting section structure of the journal according to a preferred embodiment of the present invention;

[0028] Figure 8 This is a cross-sectional view of the mounting section according to a preferred embodiment of the present invention;

[0029] Figure 9This is a schematic diagram of the mounting surface of the connecting rocker arm according to a preferred embodiment of the present invention;

[0030] Figure 10 This is a schematic diagram of the connecting rocker arm mounting structure according to a preferred embodiment of the present invention;

[0031] Figure 11 This is a schematic diagram of the double-ear locking plate structure of a preferred embodiment of the present invention;

[0032] Figure 12 This is a schematic diagram of the self-locking nut installation structure according to a preferred embodiment of the present invention.

[0033] Legend:

[0034] 1. Blade body 11. Separation structure 111. First inclined section 112. Second inclined section 12. Second air intake structure 121. Concave surface 122. First inclined surface 123. Second inclined surface 13. Third air intake structure 14. First exhaust port 15. Second exhaust port 2. Journal 21. Air intake hole 22. Air inlet groove 23. Threaded section 24. Mounting section 25. First cylindrical section 26. Second cylindrical section 3. Support boss 4. Connecting rocker arm 5. Self-locking nut 6. Double-ear locking plate 61. Flanged structure Detailed Implementation

[0035] The embodiments of the present invention will be 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.

[0036] Figure 2 This is a schematic diagram of the guide vane structure of a preferred embodiment of the present invention; Figure 3 This is a schematic diagram of the guide vane installed in an engine according to a preferred embodiment of the present invention; Figure 4 This is a schematic diagram of the internal structure of the guide vane according to a preferred embodiment of the present invention; Figure 5 This is a partial structural diagram of the guide vanes installed in an engine according to a preferred embodiment of the present invention; Figure 6 This is a schematic diagram of the journal structure of the guide vane according to a preferred embodiment of the present invention; Figure 7 This is a schematic diagram of the mounting section structure of the journal according to a preferred embodiment of the present invention; Figure 8 This is a cross-sectional view of the mounting section according to a preferred embodiment of the present invention; Figure 9 This is a schematic diagram of the mounting surface of the connecting rocker arm according to a preferred embodiment of the present invention; Figure 10 This is a schematic diagram of the connecting rocker arm mounting structure according to a preferred embodiment of the present invention; Figure 11 This is a schematic diagram of the double-ear locking plate structure of a preferred embodiment of the present invention; Figure 12 This is a schematic diagram of the self-locking nut installation structure according to a preferred embodiment of the present invention.

[0037] like Figures 2 to 12As shown, the adjustable guide vane of this embodiment is applied to an aero-engine. The guide vane includes a blade body 1, which has a leading edge and a trailing edge. The guide vane also includes a journal 2 disposed at the first end of the blade body 1 and a support boss 3 disposed at the second end of the blade body 1. An adjustment component is connected to the journal 2 for adjusting the angle of the guide vane. The specific adjustment method can be implemented with reference to existing adjustable guide vanes. An inner cavity is provided inside the blade body 1. A first air bleed structure is provided on the journal 2 for introducing external hot air into the inner cavity. A partition structure 11 is provided inside the inner cavity, disposed at the outlet end of the first air bleed structure and arranged on one side near the trailing edge of the blade body 1. It is used to divide the inner cavity into a front cavity near the leading edge and a rear cavity near the trailing edge, and to connect the front cavity and the rear cavity near the second end of the blade body 1, so that the hot air introduced into the inner cavity flows from the first end of the blade body 1 to the second end of the blade body 1 in the front cavity and is then introduced into the rear cavity. An exhaust structure is provided on the blade body 1 for discharging the hot air introduced into the inner cavity.

[0038] The journal 2 is coaxial with the support boss 3, and the axis is close to the center of gravity of the guide vane to reduce resistance during adjustment. The first air intake structure includes an air intake hole 21 and an air inlet groove 22 provided on the journal 2. The connection method between the air intake hole 21 and the external hot air source is implemented with reference to the prior art. The external hot air is introduced into the inner cavity through the air intake hole 21 and the air inlet groove 22. The shape of the air intake hole 21 is set according to actual needs, and its area determines the air intake volume. Its diameter is larger than the inner diameter of the air inlet groove 22.

[0039] Understandably, this imported adjustable guide vane differs from the traditional uniform anti-icing air intake technology in existing technologies. By setting a partition structure 11, the inner cavity of the blade body 1 is divided into a front cavity and a rear cavity. The hot air guided into the inner cavity by the first air intake structure first flows through and gathers in the front cavity near the leading edge. Based on the actual working condition that the guide vane icing is from front to back, the anti-icing effect of the leading edge is effectively enhanced. After the hot air is introduced and fills the front cavity, it flows into the rear cavity and is discharged through the exhaust structure. Through reasonable inner cavity structure design, the overall structure is simplified, the heat transfer performance of the blade is improved, and the overall anti-icing effect is greatly improved.

[0040] In one embodiment, a second air intake structure 12 is provided at the first end of the front cavity near the blade 1. The second air intake structure 12 has a gap with the inner wall of the inner cavity and the partition structure 11. The second air intake structure 12 is used to cause the hot air introduced into the front cavity to generate backflow and / or impact and / or swirling flow on the inner wall of the leading edge near the first end of the blade 1. Due to the centrifugal force, the first end of the leading edge of the blade 1 is the first to freeze and is also the easiest to freeze. By providing the second air intake structure 12, the direction of the hot air flow into the front cavity is guided. After the hot air enters the front cavity through the first guide structure, it is divided by the second air intake structure 12. Part of it flows along the partition structure 11 to the second end of the blade 1, and part of it flows around the second air intake structure 12 through the inner wall of the first end of the blade 1 and the inner wall of the leading edge to the second end of the blade 1. This strengthens the amount of hot air at the leading edge of the first end of the blade 1, improves the anti-icing effect at this position, optimizes the layout of the anti-icing air intake cavity, enhances the diffusion of hot air into the circumferential space, improves the mixing effect, and effectively improves the anti-icing effect.

[0041] Specifically, the second air intake structure 12 is an irregularly shaped protrusion formed radially within the inner cavity of the blade 1. It has a concave surface 121 facing the inner wall of the first end of the blade 1, a first inclined surface 122 facing the leading edge, and a second inclined surface 123 facing the separating structure 11. The concave surface 121 is used to guide hot air to impact the inner wall of the first end of the blade 1 and flow to the inner wall of the leading edge of the blade 1. The first inclined surface 122 is used to guide hot air to flow along the inner wall of the leading edge of the blade 1 to the second end of the blade 1. The second inclined surface 123 is used to guide hot air to flow to the second end of the blade 1. Furthermore, the distance between the first inclined surface 122 and the inner wall of the leading edge of the blade 1 gradually increases from the first end to the second end, and the distance between the second inclined surface 123 and the separating structure 11 gradually increases from the first end to the second end of the blade 1. This effectively reduces the flow rate of hot air at the location of the second air intake structure 12, thereby further enhancing the anti-icing effect at the leading edge of the first end.

[0042] In one embodiment, the exhaust structure includes a plurality of first exhaust ports 14 arranged along the trailing edge. The size of the first exhaust ports 14 gradually increases from the first end to the second end of the blade 1, so that the amount of hot gas discharged gradually decreases from the second end to the first end of the blade 1, thereby making the hot gas distribution in the rear cavity more uniform. The hot gas flowing into the rear cavity flows from the second end to the first end of the blade 1. Therefore, changing the exhaust capacity of the trailing edge exhaust ports can make the hot gas distribution in the rear cavity more uniform, improve the anti-icing effect, and make the anti-icing performance more stable. Among them, the first exhaust port 14 is a square groove exhaust port. In this embodiment, the width of the square groove exhaust port is the same, while the length gradually changes with the arrangement direction. In other embodiments, the size change method is not limited.

[0043] In one embodiment, a plurality of third air-drawing structures 13 are provided in the rear cavity at intervals along a preset direction to change the flow of the introduced hot gas and thus make the hot gas in the rear cavity more evenly distributed. The third air-drawing structure 13 is preferably a cylindrical boss. The gas entering the rear cavity is mixed with the hot gas introduced into the rear cavity after being impacted by the third air-drawing structure 13, and the rear cavity is filled more evenly. The arrangement direction of the third air-drawing structure 13 matches the length dimension change of the first exhaust port 14, and the number of third air-drawing structures 13 matches the number of first exhaust ports 14. They are arranged approximately between two adjacent first exhaust ports 14. Combined with the exhaust volume distribution of the first exhaust ports 14, the air-drawing effect is effectively improved, and the hot gas distribution in the rear cavity is more even.

[0044] In one embodiment, the exhaust structure includes a second exhaust port 15 located at the second end of the blade 1. The second exhaust port 15 is arranged near the leading edge of the blade 1. The second exhaust port 15 is a waist-shaped exhaust port. The hot air flows from the first end to the second end in the front cavity and is divided into two parts. A small part is discharged through the second exhaust port 15, and the other part flows into the rear cavity. The hot air discharged through the second exhaust port 15 impacts other components located outside the second end of the blade 1 at the leading edge of the blade 1, forming a hot air backflow and accumulation, thereby enhancing the anti-icing effect at the leading edge of the second end of the blade 1. The size of the waist-shaped exhaust port is designed according to actual needs.

[0045] In one embodiment, the partition structure 11 includes a first inclined section 111 and a second inclined section 112 sequentially from the first end to the second end of the blade 1. The first inclined section 111 is inclined towards the leading edge to guide the hot air to flow towards the leading edge, and the second inclined section 112 is inclined towards the trailing edge to guide the hot air from the front cavity to the rear cavity. The partition structure 11 is a solid rib that protrudes radially into the inner cavity. The first inclined section 111 extends from the first end to the second end in a direction towards the leading edge, and after reaching a preset position, it becomes the second inclined section 112 extending towards the trailing edge. At the same time, under the action of the second air intake structure 12, hot air is fully introduced into the front cavity to form an impact, backflow, and then flow into the rear cavity. The distance between the partition structure 11 and the inner wall of the second end of the blade 1 allows the hot air to flow from the front cavity to the rear cavity. The flow area of ​​this distance should be greater than the size of the inner air inlet groove 22 to ensure the passage of the introduced hot air.

[0046] In one embodiment, the journal 2 includes, from the outside to the inside, a threaded section 23, a mounting section 24, a first cylindrical section 25, and a second cylindrical section 26. The adjusting assembly includes a connecting rocker arm 4 for mounting on the mounting section 24 and a self-locking nut 5 for connecting to the threaded section 23. The connecting rocker arm 4 has a mounting surface with mounting holes for circumferentially engaging with the mounting section 24. The mounting surface is provided with a flange structure 61 to restrict the rotation of the self-locking nut 5. The height of the flange structure 61 is greater than the length of the mounting section 24, so as to restrict the rotation of the self-locking nut 5. After the connecting rocker arm 4 rotates into position with the self-locking nut 5, the flange structure 61 still engages with the mounting section 24 when the connecting rocker arm 4 is engaged with the mounting section 24. That is, before tightening the self-locking nut 5, the connecting rocker arm 4 and the self-locking nut 5 rotate synchronously. After tightening, the mounting surface of the connecting rocker arm 4 is embedded into the mounting section 24, and the flange structure 61 still fits against the self-locking nut 5. By setting the flange structure 61 to limit the circumferential movement of the self-locking nut 5, the self-locking nut 5 cannot rotate circumferentially and will loosen radially, which improves the adjustment accuracy and the reliability of locking.

[0047] To improve reliability and avoid breakage under abnormal operation, the thread specification of threaded section 23 is not less than M5; the flange structure 61 in this embodiment is a double-ear locking plate 6 independently set on the mounting surface. During installation, the mounting surface connecting the rocker arm 4 and the double-ear locking plate 6 are passed through threaded section 23 in sequence and then the self-locking nut 5 is locked; the angles of the two flanges of the double-ear locking plate 6 match the edge angles of the self-locking nut 5.

[0048] Furthermore, the cross-section of the mounting section 24 is waist-shaped and has irregular straight surfaces processed along the axial direction of the mounting section 24 through adjacent arc-shaped surfaces and straight surfaces. The shape of the mounting hole matches the cross-sectional shape of the mounting section 24. The arc-shaped surface of the mounting section 24 is set with a preset taper. During operation, the straight surface bears the force, reducing pressure damage caused by line contact. The tapered circular surface fits tightly to maintain the fitting accuracy.

[0049] On the other hand, the blade body 1 in this embodiment is a blade structure with no margin. The blade body 1, journal 2, and support boss 3 are integrally manufactured. Based on the significant improvement of the guide vane structure and anti-icing performance, the component materials do not need to rely on beryllium bronze alloy with higher thermal conductivity. Corrosion-resistant stainless steel or high-temperature alloys can be used instead. This not only improves the strength level of the parts but also enhances their corrosion resistance. Furthermore, the guide vane is integrally manufactured without welding, which solves the problem of a large number of parts and complex manufacturing in traditional designs. It effectively eliminates the risk of welding failure and improves the reliability of the parts. Moreover, the number of processing steps is reduced, eliminating welding, ultrasonic and other processes, reducing processing costs by more than 50% and effectively improving the economic efficiency of use.

[0050] On the other hand, this embodiment also provides an aero-engine that uses the aforementioned imported adjustable guide vanes.

[0051] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. An imported adjustable guide vane, used in an aero-engine, the guide vane comprising a blade body (1) having a leading edge and a trailing edge, characterized in that, The guide vane also includes a journal (2) disposed at the first end of the blade body (1) and a support boss (3) disposed at the second end of the blade body (1). An adjustment component is connected to the journal (2) for adjusting the angle of the guide vane. An inner cavity is provided inside the blade body (1). A first air intake structure is provided on the journal (2) for introducing external hot air into the inner cavity. A partition structure (11) is provided inside the inner cavity, disposed at the outlet end of the first air intake structure and arranged on one side near the trailing edge of the blade body (1), for dividing the inner cavity into a front cavity near the leading edge and a rear cavity near the trailing edge, and for connecting the front cavity and the rear cavity at a position near the second end of the blade body (1), so that the hot air introduced into the inner cavity flows from the first end of the blade body (1) to the second end of the blade body (1) in the front cavity and is then introduced into the rear cavity. An exhaust structure is provided on the blade body (1) for discharging the hot air introduced into the inner cavity. A second air intake structure (12) is provided at the first end of the front cavity near the blade (1). There is a gap between the second air intake structure (12) and the inner wall of the inner cavity and the partition structure (11). The second air intake structure (12) is used to cause the hot air introduced into the front cavity to generate backflow and / or impact and / or swirling flow on the inner wall of the leading edge near the first end of the blade (1). The second air intake structure (12) has a concave surface (121) arranged towards the inner wall of the first end of the blade (1), a first inclined surface (122) arranged towards the leading edge, and a second inclined surface (123) arranged towards the partition structure (11). The concave surface (121) is used to guide the hot air to impact the inner wall of the first end of the blade (1) and flow to the inner wall of the leading edge of the blade (1). The first inclined surface (122) is used to guide the hot air to flow along the inner wall of the leading edge of the blade (1) to the second end of the blade (1). The second inclined surface (123) is used to guide the hot air to flow to the second end of the blade (1).

2. The adjustable guide vane according to claim 1, characterized in that, The exhaust structure includes a plurality of first exhaust ports (14) arranged along the trailing edge. The size of the first exhaust ports (14) gradually increases from the first end to the second end of the blade (1) so that the amount of hot gas discharged gradually decreases from the second end to the first end of the blade (1) so that the hot gas in the rear cavity is evenly distributed.

3. The adjustable guide vane according to claim 1, characterized in that, The exhaust structure includes a second exhaust port (15) located at the second end of the blade (1), with the second exhaust port (15) positioned near the leading edge of the blade (1).

4. The adjustable guide vane according to claim 1, characterized in that, The rear cavity is provided with a plurality of third air intake structures (13) arranged at intervals along a preset direction, which are used to change the flow of the introduced hot air and thus make the hot air introduced into the rear cavity evenly distributed.

5. The adjustable guide vane according to any one of claims 1-4, characterized in that, The separation structure (11) includes a first inclined section (111) and a second inclined section (112) in sequence from the first end to the second end of the blade (1). The inclined direction of the first inclined section (111) is towards the leading edge to guide the hot air to flow towards the leading edge, and the inclined direction of the second inclined section (112) is towards the trailing edge to guide the hot air from the front cavity to the rear cavity.

6. The adjustable guide vane according to claim 1, characterized in that, The journal (2) includes a threaded section (23) and a mounting section (24) from the outside to the inside. The adjustment assembly includes a connecting rocker arm (4) for mounting on the mounting section (24) and a self-locking nut (5) for connecting to the threaded section (23). The connecting rocker arm (4) has a mounting surface with a mounting hole for circumferentially engaging with the mounting section (24). The mounting surface is provided with a flange structure (61) to restrict the rotation of the self-locking nut (5). The height of the flange structure (61) is greater than the length of the mounting section (24).

7. The adjustable guide vane according to claim 6, characterized in that, The cross-section of the mounting section (24) is waist-shaped and has irregular straight surfaces processed along the axial direction of the mounting section (24) through adjacent arc-shaped surfaces and straight surfaces. The shape of the mounting hole matches the cross-sectional shape of the mounting section (24). The arc-shaped surface of the mounting section (24) is set with a preset taper.

8. An aircraft engine, characterized in that, The application has the inlet adjustable guide vane as described in any one of claims 1-7.

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