Aeroengine Fan and Aeroengine

Abstract

The present invention relates to the technical field of aeroengines, and particularly relates to an aeroengine fan and an aeroengine. The aeroengine fan includes: a fan disk; blades disposed on the fan disk; flow channel plates disposed between two adjacent blades; a sealing strip disposed between the flow channel plate and the blade for sealing, and a chamber is provided among the sealing strip, the blade, the fan disk and the flow channel plate; and a sealing ring connected downstream of the fan disk, an air outlet is provided on the sealing ring, and the air outlet is communicated with the chamber for guiding the air flow after flowing through the blade into the chamber. Based on this, an air extraction and sealing method can be realized, and the risk of the sealing strip flying out can be reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engines, and particularly to an aero-engine fan and an aero-engine. Background Art

[0002] A sealing strip is usually provided between the blades and the flow channel plate of an aero-engine fan. The sealing strip is adhesively bonded to the side surface of the flow channel plate to fill and seal the gap between the blades and the flow channel plate.

[0003] In the related art, the installation firmness of the sealing strip completely depends on the adhesive strength. During the actual operation of the aero-engine fan, the sealing strip is likely to fly out, resulting in problems such as sealing failure. Summary of the Invention

[0004] One technical problem to be solved by the present invention is to reduce the risk of the sealing strip flying out.

[0005] To solve the above technical problem, the present invention provides an aero-engine fan, which includes:

[0006] A fan disk;

[0007] Blades, arranged on the fan disk;

[0008] Flow channel plates, arranged between two adjacent blades;

[0009] A sealing strip, arranged between the flow channel plate and the blade for sealing. A chamber is formed among the sealing strip, the blade, the fan disk and the flow channel plate; and

[0010] A sealing ring, connected downstream of the fan disk. An air outlet is provided on the sealing ring, and the air outlet is communicated with the chamber for guiding the airflow after flowing through the blade into the chamber.

[0011] In some embodiments, the air outlet is arranged at one end of the sealing ring facing the fan disk.

[0012] In some embodiments, the aero-engine fan further includes an air inlet, which is located downstream of the blade and communicates the air outlet and the flow channel where the blade is located to guide the airflow after flowing through the blade to flow into the chamber through the air outlet.

[0013] In some embodiments, the air inlet is located on the radial outer wall of the sealing ring, or the air inlet is located between the end of the radial outer wall of the sealing ring and the compression stage of the aero-engine.

[0014] In some embodiments, the sealing strip includes a first sealing section and a second sealing section. The first sealing section extends into the gap between the flow channel plate and the blade, and the second sealing section is connected to the first sealing section at an angle and is located radially inside the flow channel plate.

[0015] In some embodiments, the second sealing section is configured to have a thickness greater than the width of the gap when compressed to the maximum compression amount.

[0016] In some embodiments, an aeroengine fan includes a mandrel disposed inside the sealing strip and radially located inside the flow channel plate, and the diameter of the mandrel is greater than the width of the gap between the flow channel plate and the blade.

[0017] In some embodiments, the mandrel is disposed in the second sealing section of the sealing strip.

[0018] In some embodiments, the mandrel is hollow.

[0019] The present invention further provides an aeroengine, which includes the aeroengine fan according to the embodiments of the present invention.

[0020] In an embodiment of the present invention, the airflow pressurized by the blade and led to the chamber at the air outlet can press the sealing strip against the blade, reducing the risk of the sealing strip flying out.

[0021] Other features and advantages of the present invention will become clear by describing the exemplary embodiments of the present invention in detail with reference to the following drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0023] Figure 1 It is a partial half-sectional view of the aeroengine in the embodiment of the present invention.

[0024] Figure 2 It is an air extraction path diagram in some embodiments.

[0025] Figure 3 For Figure 2 C-C cross-sectional view.

[0026] Figure 4 Showing Figure 3 Local enlarged schematic view of I.

[0027] Figure 5 It is a schematic view of the cooperation between the sealing strip, the flow channel plate and the blade in other embodiments.

[0028] Figure 6 Showing Figure 5 Local enlarged schematic view of II.

[0029] Figure 7 Schematic diagram of the sealing strip cooperating with the flow channel plate and the blade in some other embodiments.

[0030] Figure 8 Show Figure 7 III partial enlarged schematic diagram.

[0031] Explanation of reference numerals:

[0032] 100, aeroengine;

[0033] 10, aeroengine fan; 20, booster stage; 30, fan shaft; 40, transmission shaft;

[0034] 1, inlet cone; 11, front section; 12, rear section;

[0035] 2, blade;

[0036] 3, flow channel plate;

[0037] 4, fan disk;

[0038] 5, sealing strip; 51, first sealing section; 52, second sealing section; 53, chamber;

[0039] 6, sealing ring; 62, air inlet; 63, air outlet;

[0040] 7, gap;

[0041] 8, mandrel;

[0042] 9, boss. Detailed implementation manners

[0043] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. The following description of at least one exemplary embodiment is actually only illustrative and in no way constitutes a limitation on the present invention and its application or use. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts fall within the scope of protection of the present invention.

[0044] For technologies, methods, and devices known to those of ordinary skill in the relevant art, detailed discussions may not be made, but where appropriate, the said technologies, methods, and devices should be regarded as part of the specification.

[0045] In the description of the present invention, it should be understood that using words such as "first" and "second" to limit components is only for the convenience of differentiating the corresponding components. Without further statement, the above words have no special meaning and thus should not be construed as limiting the scope of protection of the present invention.

[0046] In addition, the technical features involved in different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0047] Figure 1 The partial structure of the aeroengine 100 in the embodiment of the present invention is shown. Refer to Figure 1 , in some embodiments, the aeroengine 100 includes an aeroengine fan 10, a booster stage 20, a fan shaft 30, and a drive shaft 40. The aeroengine fan 10 and the booster stage 20 are arranged in sequence along the air flow direction and are both provided on the fan shaft 30. The fan shaft 30 is drivingly connected to a low-pressure turbine (not shown in the figure) of the aeroengine 100 through the drive shaft 40. During operation, the low-pressure turbine drives the aeroengine fan 10 and the booster stage 20 to rotate around the rotation axis through the drive shaft 40 and the fan shaft 30.

[0048] Among them, as Figure 1 shown, the aeroengine fan 10 includes an inlet cone 1, a fan disk 4, a sealing ring 6, blades 2, and a flow channel plate 3.

[0049] The inlet cone 1 and the sealing ring 6 are arranged at intervals along the axial direction. The inlet cone 1 is generally conical and includes a front section 11 and a rear section 12 connected in sequence along the air flow direction. The sealing ring 6 is located downstream of the inlet cone 1 along the direction of the air flow through the aeroengine fan 10 and is connected to the booster stage 20.

[0050] The fan disk 4 is axially arranged between the inlet cone 1 and the sealing ring 6 and is connected to the fan shaft 30 to realize the driving connection between the aeroengine fan 10 and the fan shaft 30. Among them, the sealing ring 6 is connected downstream of the fan disk 4.

[0051] Both the blades 2 and the flow channel plate 3 are provided on the fan disk 4. A plurality of blades 2 are circumferentially distributed at intervals from each other. A flow channel plate 3 is provided between any two adjacent blades 2, that is, the flow channel plate 3 is provided between two adjacent blades 2. Thus, an intake section flow channel of the engine is formed between the flow channel plate 3, the inlet cone 1, the sealing ring 6, and the blades 2.

[0052] Among them, refer to Figures 2 - 3 , in some embodiments, the front and rear ends of the flow channel plate 3 are respectively limited by the rear section 12 and the sealing ring 6. And, in some embodiments, the lower end (i.e., the end close to the fan disk 4) of the flow channel plate 3 is limited by the fan disk 4. For example, in some embodiments, a boss 9 is provided on the flow channel plate 3. The boss 9 protrudes radially inward from the inner wall of the flow channel plate 3 and connects the flow channel plate 3 and the fan disk 4 to realize the limitation of the flow channel plate 3. The boss 9 and the flow channel plate 3 can be integrally formed.

[0053] Unless otherwise specified, the circumferential, radial, and axial directions all refer to the circumferential, radial, and axial directions of the aeroengine fan 10, which are defined based on the rotation axis. At the same time, "front", "rear", "upstream", and "downstream" are defined based on the direction of the airflow passing through the aeroengine fan 10. The side where the airflow enters is "front" and "upstream", and the side where the airflow exits is "rear" and "downstream". The direction of the airflow passing through the aeroengine fan 10 is generally along the axial direction of the aeroengine fan 10. The axial, circumferential, and radial directions of the aeroengine fan 10 are consistent with the axial, circumferential, and radial directions of the aeroengine 100.

[0054] Figures 3 - 8 Further shown is a schematic diagram of the cooperation between the blade 2 and the flow channel plate 3. Refer to Figures 3 - 8 , a sealing strip 5 is provided between the blade 2 and the flow channel plate 3. The sealing strip 5 is made of an elastic material such as rubber and has elasticity. The sealing strip 5 fills and seals the gap 7 between the blade 2 and the flow channel plate 3. The space between the sealing strip 5, the blade 2, the fan disk 4, and the flow channel plate 3 forms a chamber 53. In other words, a chamber 53 is provided between the sealing strip 5, the blade 2, the fan disk 4, and the flow channel plate 3,

[0055] The sealing strip 5 provided between the blade 2 and the flow channel plate 3 can, on the one hand, play a sealing role to prevent gas in the flow channel from leaking, causing airflow loss and affecting the engine efficiency. On the other hand, it can play a buffering role to prevent the flow channel plate 3 and the blade 2 from rubbing against each other and damaging the blade 2.

[0056] In the related art, the sealing strip 5 is installed and fixed by bonding to the side of the flow channel plate 3, and its installation firmness completely depends on the bonding strength. However, the material properties of the sealing strip 5 are inactive. When bonding to the flow channel plate 3 made of composite materials, not only a special glue is required, but also the bonding effect is generally poor. This results in that during the operation of the aeroengine fan 10, the sealing strip 5 is easily thrown out under the action of centrifugal force and flies outside the flow channel plate 3.

[0057] The flying out of the sealing strip will cause various problems. For example, on the one hand, after the sealing strip 5 flies out, its sealing effect fails, resulting in the gas in the flow channel leaking through the gap 7, causing airflow loss and affecting the engine efficiency. On the other hand, after the sealing strip 5 flies out, there is no longer a buffering medium between the blade 2 and the flow channel plate 3, which may cause the flow channel plate 3 and the blade 2 to rub against each other, damaging the blade 2. On the other hand, the flying out of the sealing strip 5 becomes a foreign object, causing a safety hazard.

[0058] It can be seen that the flying out of the sealing strip affects the structural reliability, operating efficiency, and working safety of the aeroengine fan 10 and the aeroengine 100.

[0059] In view of the above situation, the structure of the aeroengine fan 10 of the present invention is improved to reduce the risk of the sealing strip 5 flying out.

[0060] Refer to Figure 2 , in some embodiments, an air outlet 63 is provided on the sealing ring 6. The air outlet 63 communicates with the chamber 53 and is used to lead the airflow flowing through the blade 2 into the chamber 53. Specifically, in some embodiments, the air outlet 63 is provided at one end of the sealing ring 6 facing the fan disk 4.

[0061] Based on the above settings, an air bleeding and sealing method can be realized. Since the pressure of the airflow increases after flowing through the blade 2, the air outlet 63 leads the airflow flowing through the blade 2 into the chamber 53, as shown by the arrow in Figure 4 . This part of the gas can exert pressure on the sealing strip 5, pressing the sealing strip 5 tightly against the blade 2. During the operation of the aeroengine fan 10, the sealing strip 5 can be tightly attached to the blade 2 under the action of the pressure exerted by the gas in the chamber 53, effectively reducing the risk of the sealing strip 5 flying out. Reducing the risk of the sealing strip 5 flying out, on the one hand, enables the sealing strip 5 to play a more reliable sealing and buffering role, so as to prevent air leakage, affect the engine efficiency, or cause rubbing between the flow path plate 3 and the blade 2, affecting the structural reliability. On the other hand, it can prevent the sealing strip 5 from flying out and becoming foreign objects, affecting the working safety.

[0062] At the same time, since the sealing strip 5 can be tightly attached to the blade 2 under the action of gas pressure, the sealing performance is also better, and the sealing effect can be effectively improved.

[0063] It can be seen that based on the air bleeding and sealing method of the air outlet 63, the sealing effect can be enhanced and the risk of the sealing strip flying out can be reduced.

[0064] In order to facilitate the airflow flowing through the blade 2 to flow to the air outlet 63 and further flow into the chamber 53 to realize the air bleeding and sealing method, refer to Figure 2 , in some embodiments, the aeroengine fan 10 further includes an air inlet 62. The air inlet 62 is located downstream of the blade 2 and communicates the air outlet 63 with the flow path where the blade 2 is located, so that the airflow flowing through the blade 2 can flow to the air outlet 63 through the air inlet 62 and further flow into the chamber 53 through the air outlet 63. It can be seen that the air inlet 62 can conveniently guide the airflow flowing through the blade 2 to flow into the chamber 53 through the air outlet 63, realizing the air bleeding and sealing method.

[0065] Among them, the setting position of the air inlet 62 is not specifically limited, as long as it is located downstream of the blade 2 and communicates with both the air outlet 63 and the flow path where the blade 2 is located. For example, in some embodiments, the air inlet 62 can be provided on the radial outer wall of the sealing ring 6. For another example, refer to Figure 1 and Figure 2, in some other embodiments, the air inlet 62 may be located between the end of the radially outer wall of the sealing ring 6 and the boosting stage 20, that is to say, the air inlet 62 may be an opening located between the end of the radially outer wall of the sealing ring 6 and the boosting stage 20. During operation, since the sealing ring 6 does not rotate while the boosting stage 20 rotates, in order to prevent direct rubbing between the sealing ring 6 and the boosting stage 20, generally there is originally an opening between the end of the radially outer wall of the sealing ring 6 and the boosting stage 20, and this opening is communicated with the flow passage where the blade 2 is located. In the related art, this opening is either sealed by a labyrinth sealing structure or directly open. However, whether this opening is sealed or open, since the air outlet 63 is not provided on the sealing ring 6 in the related art, the sealing ring 6 blocks the gas communication between this opening and the chamber 53. Therefore, the aforementioned air extraction and sealing method is not realized in the related art. In the illustrated embodiment, this originally existing opening is directly used as the air inlet 62, so that there is no need to provide another opening as the air inlet, and the modification is less. Therefore, it is beneficial to simplify the structure and reduce the cost.

[0066] In addition, in order to further reduce the risk of the sealing strip 5 flying out, some embodiments also improve the structure of the sealing strip 5.

[0067] For example, referring to Figures 7 - 8 , in some embodiments, a mandrel 8 is added to the sealing strip 5 to further reduce the risk of the sealing strip 5 flying out. Among them, as Figures 7 - 8 shown, the mandrel 8 is arranged inside the sealing strip 5 and is located radially inside the flow channel plate 3. And the diameter of the mandrel 8 is greater than the width of the gap 7 between the flow channel plate 3 and the blade 2. It can be understood that the width of the gap 7 refers to the circumferential dimension of the gap 7.

[0068] Since the diameter of the mandrel 8 is greater than the width of the gap 7 and the mandrel 8 is located radially inside the flow channel plate 3, when the sealing strip 5 is thrown outwards due to the centrifugal force, the mandrel 8 can be stuck inside the gap 7 radially, preventing the sealing strip 5 from flying out to the outside of the flow channel plate 3, thereby reducing the risk of the sealing strip 5 flying out.

[0069] Moreover, the mandrel 8 arranged inside the sealing strip 5 can also support the sealing strip 5, enhance the overall rigidity of the sealing strip 5, so that the sealing strip 5 can be more closely attached to the blade 2, improving the sealing performance and the sealing effect.

[0070] At the same time, by setting the mandrel 8 to reduce the risk of the sealing strip 5 flying out, the modification to the original structure of the aeroengine fan 10 is small, the processing is convenient, and the transformation cost is low.

[0071] It can be seen that by adding a mandrel 8 inside the seal strip 5, the sealing effect of the seal strip 5 can be effectively enhanced, and the risk of the seal strip 5 flying out can be reduced. In this way, on the basis of air extraction sealing, the mandrel 8 can be further used to enhance the sealing effect and reduce the flying out risk, so as to more effectively improve the sealing effect and more effectively reduce the flying out risk.

[0072] Among them, the mandrel 8 can be made of a relatively hard material. For example, it can be made of titanium alloy, a relatively hard composite material or a relatively hard rubber material, so that the mandrel 8 has a relatively large hardness, for example, greater than the hardness of the seal strip 5, so that the mandrel 8 can be more reliably stuck on the radial inner side of the flow channel plate 3 to prevent the seal strip 5 from flying out, and can more effectively enhance the rigidity of the seal strip 5 and improve the sealing performance.

[0073] In addition, referring to Figure 8 , in some embodiments, the mandrel 8 is hollow. At this time, the mandrel 8 is a hollow structure. Compared with a solid structure, it has a lighter weight, which is beneficial to reducing the overall weight of the aeroengine fan 10.

[0074] In the foregoing embodiments, the shape of the seal strip 5 is not specifically limited. For example, referring to Figures 3 - 8 , in some embodiments, the seal strip 5 includes a first sealing section 51 and a second sealing section 52. The first sealing section 51 extends into the gap 7 between the flow channel plate 3 and the blade 2. The second sealing section 52 is connected to the first sealing section 51 at an angle and is located on the radial inner side of the flow channel plate 3. Among them, being connected at an angle means that there is an included angle between the first sealing section 51 and the second sealing section 52. For example, the two are perpendicular to each other, or the two are connected into an acute angle structure or an obtuse angle structure. As Figure 4 shown, when the second sealing section 52 is connected between the radial two ends of the first sealing section 51, the seal strip 5 is in a T shape. And as Figure 6 and Figure 8 shown, when the second sealing section 52 is connected to the radial inner end of the first sealing section 51, the seal strip 5 is in an L shape.

[0075] In the embodiments provided with the mandrel 8, for different-shaped seal strips 5, the setting position of the mandrel 8 can be the same or different. For example, when the seal strip 5 is in a T shape, the mandrel 8 can be arranged in the part of the first sealing section 51 located on the radial inner side of the flow channel plate 3, or can also be arranged in the second sealing section 52, so that the mandrel 8 is located on the radial inner side of the flow channel plate 3, facilitating the mandrel 8 to prevent the seal strip 5 from flying out by being stuck on the radial inner side of the gap 7; when the seal strip 5 is in an L shape, the mandrel 8 can be arranged in the second sealing section 52, so that the mandrel 8 is located on the radial inner side of the flow channel plate 3, facilitating the mandrel 8 to prevent the seal strip 5 from flying out by being stuck below the gap 7.

[0076] When the sealing strip 5 includes a first sealing section 51 and a second sealing section 52, in addition to further reducing the risk of the sealing strip 5 flying out by setting the mandrel 8, other measures can also be adopted to further reduce the risk of the sealing strip 5 flying out.

[0077] For example, referring to Figure 6 , in some embodiments, the second sealing section 52 is set to be thicker. For example, the initial thickness of the second sealing section 52 (i.e., the thickness when not compressed) is changed from the conventional less than or equal to 3 mm to greater than or equal to 10 mm, so that when the second sealing section 52 is compressed to the maximum compression amount, the thickness of the second sealing section 52 is still greater than the width of the gap 7 between the runner plate 3 and the blade 2. Wherein, the thickness of the second sealing section 52 refers to the dimension of the second sealing section 52 in the radial direction.

[0078] Based on the above settings, when the sealing strip 5 is thrown outwards, even when the sealing strip 5 is in the extreme compression state, the second sealing section 52 can still be stuck on the radial inner side of the runner plate 3 to prevent the sealing strip 5 from flying out. Therefore, the risk of the sealing strip 5 flying out can be effectively reduced.

[0079] Moreover, setting the second sealing section 52 to be thicker is also beneficial to enhancing the overall rigidity of the sealing strip 5, so that the sealing strip 5 can closely adhere to the blade 2, improving the sealing performance and the sealing effect.

[0080] At the same time, by increasing the thickness of the second sealing section 52 to reduce the risk of the sealing strip 5 flying out, the modification to the original structure of the aeroengine fan 10 is small, the processing is convenient, and the transformation cost is low.

[0081] It can be seen that by redesigning the structure of the sealing strip 5 and increasing the thickness of the second sealing section 52 of the sealing strip 5, not only can the sealing effect of the sealing strip 5 be effectively enhanced, but also the risk of the sealing strip 5 flying out can be effectively reduced. In this way, on the basis of air extraction sealing and / or setting the mandrel 8, the thickened second sealing section 52 can be further used to enhance the sealing effect and reduce the flying out risk, so as to more effectively improve the sealing effect and more effectively reduce the flying out risk.

[0082] Among them, when the three measures of air extraction sealing, thickening the second sealing section 52, and setting the mandrel 8 inside the sealing strip 5 are adopted simultaneously, the sealing strip 5 can be affected by the triple actions of the pressurized gas, the second sealing section 52, and the mandrel 8. Therefore, the flying out risk is lower and the sealing effect is better.

[0083] In the foregoing embodiments, the sealing strip 5 can still be adhesively connected to the flow channel plate 3 to achieve installation and fixation between the flow channel plate 3 and the blade 2. Due to the action of at least one of the air extraction sealing, the mandrel 8, and the thickened second sealing section 52, the setting firmness of the sealing strip 5 no longer depends solely on the bonding strength, but is also restricted by at least one of the pressurized gas, the second sealing section 52, and the mandrel 8. Therefore, compared with the related art where there is no air outlet 63 for air extraction, the thickness of the second sealing section 52 is small, or there is no mandrel 8, and the setting firmness of the sealing strip 5 only depends on the bonding strength, the risk of the adhesively bonded sealing strip 5 flying out can be effectively reduced. At the same time, from another perspective, due to the action of at least one of the pressurized gas, the second sealing section 52, and the mandrel 8, the setting firmness of the sealing strip 5 no longer depends solely on the bonding strength. Therefore, it is also beneficial to reduce the requirements for the selection of the adhesive and the bonding processability of the sealing strip 5, thereby saving costs and improving the processability.

[0084] The foregoing are only exemplary embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention shall be included within the protection scope of the present invention.

Claims

1. An aero-engine fan (10), characterized in that, Comprising: A fan disc (4); Blades (2) disposed on the fan disc (4); A flow path plate (3) disposed between two adjacent ones of the blades (2); A sealing strip (5) disposed between the flow path plate (3) and the blade (2) for sealing, and a chamber (53) is formed among the sealing strip (5), the blade (2), the fan disc (4) and the flow path plate (3); and A sealing ring (6) connected downstream of the fan disc (4), an air outlet (63) is provided on the sealing ring (6), and the air outlet (63) communicates with the chamber (53) for guiding the air flow flowing through the blade (2) into the chamber (53), so that the air flow flowing through the blade (2) applies pressure to the sealing strip (5) to press the sealing strip (5) against the blade (2).

2. The aeroengine fan (10) according to claim 1, characterized in that, The air outlet (63) is disposed at one end of the sealing ring (6) facing the fan disc (4).

3. The aeroengine fan (10) according to claim 1, characterized in that, The aeroengine fan (10) further includes an air inlet (62), the air inlet (62) is located downstream of the blade (2), and communicates the air outlet (63) and the flow path where the blade (2) is located to guide the air flow flowing through the blade (2) to flow into the chamber (53) via the air outlet (63).

4. The aero-engine fan (10) according to claim 3, characterized in that, The air inlet (62) is located on the radially outer wall of the sealing ring (6), or the air inlet (62) is located between the end of the radially outer wall of the sealing ring (6) and the booster stage (20) of the aeroengine (100).

5. The aeroengine fan (10) according to claim 1, characterized in that, The sealing strip (5) includes a first sealing section (51) and a second sealing section (52), the first sealing section (51) extends into a gap (7) between the flow path plate (3) and the blade (2), and the second sealing section (52) is angularly connected to the first sealing section (51) and is located radially inside the flow path plate (3).

6. The aeroengine fan (10) according to claim 5, characterized in that, The second sealing section (52) is configured such that when compressed to the maximum compression amount, its thickness is greater than the width of the gap (7).

7. The aeroengine fan (10) according to any one of claims 1-6, characterized in that, The aeroengine fan (10) includes a mandrel (8), the mandrel (8) is disposed inside the sealing strip (5) and is located radially inside the flow path plate (3), and the diameter of the mandrel (8) is greater than the width of the gap (7) between the flow path plate (3) and the blade (2).

8. The aeroengine fan (10) according to claim 7, characterized in that, The sealing strip (5) includes a first sealing section (51) and a second sealing section (52), the first sealing section (51) extends into a gap (7) between the flow path plate (3) and the blade (2), and the second sealing section (52) is angularly connected to the first sealing section (51) and is located radially inside the flow path plate (3), and the mandrel (8) is disposed in the second sealing section (52) of the sealing strip (5).

9. The aeroengine fan (10) according to claim 7, characterized in that, The mandrel (8) is hollow.

10. An aero-engine (100), characterized in that, Comprising the aeroengine fan (10) according to any one of claims 1-9.

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