Sealing structure, diffuser structure, design method and aeroengine

Abstract

The application discloses a sealing structure, a diffuser structure, a design method and an aero-engine. The diffuser structure comprises a diffuser assembly and a diffuser casing. The diffuser assembly comprises a radial diffuser and an axial diffuser. The sealing structure comprises a ring-shaped sealing element. The sealing element is configured with a first axial matching edge, a second axial matching edge and an axial close-fitting edge. The first axial matching edge is used for axial abutting matching with a connecting wall at an inlet position of the axial diffuser. The axial close-fitting edge is used for abutting matching with the diffuser casing. The second axial matching edge is used for axial abutting matching with a side wall at an outlet end of the radial diffuser. The sealing element is further configured with a first elastic edge connected between a first end of the axial close-fitting edge and the first axial matching edge, and a second elastic edge connected between a second end of the axial close-fitting edge and the second axial matching edge. The first axial matching edge and the axial close-fitting edge have a first preset axial interval to be axially interference-fitted between the diffuser casing and the axial diffuser.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aero-engines, in particular, to a sealing structure. In addition, the present application also relates to an aero-engine comprising the sealing structure. BACKGROUND

[0002] Small and medium-sized aero-engines usually adopt an axial-flow centrifugal combined compressor configuration, and a diffuser is an important component part for straightening the high-pressure airflow entering. With the continuous improvement of the thermal cycle parameters and power of the engine, the temperature gradient and size of the diffuser are also increasing, which leads to the continuous increase of the axial deformation of the diffuser. The connection structure of the diffuser casing and the diffuser is particularly critical. If the design is poor, the deformation mismatch of the diffuser and the adjacent parts will be easily caused, resulting in poor structural reliability.

[0003] As shown in the conventional diffuser casing and diffuser structure shown in Figure 1 The diffuser assembly is connected with the diffuser casing through the mounting edge bolts, and is centered by the stop or pin. The mounting edge divides the diffuser outlet and the inlet airflow, forming independent chambers.

[0004] The main disadvantages of the prior art are:

[0005] The diffuser and the diffuser casing are connected by rigid bolts, and there is no damping structure for vibration reduction when vibration occurs.

[0006] The mounting edge between the diffuser and the diffuser casing is located above the diffuser. When there is a large radial temperature gradient in the diffuser itself, the upper part of the diffuser deforms together with the diffuser casing in the inlet direction, and the rear mounting edge of the diffuser deforms in the outlet direction. The axial deformation is not matched, and axial scraping is easily caused. SUMMARY

[0007] The present application provides a sealing structure, a diffuser structure, a design method and an aero-engine to solve the technical problems of the axial deformation mismatch of the existing diffuser structure and the structure easily deformed due to the lack of damping structure.

[0008] According to one aspect of the present application, there is provided a sealing structure applied to a diffuser structure of an aero-engine, the diffuser structure comprising a diffuser assembly and a diffuser casing, the diffuser assembly comprising a radial diffuser and an axial diffuser, the sealing structure comprising a sealing ring configured annularly, the sealing ring being configured with a first axial fitting edge, a second axial fitting edge and an axial abutting edge, the first axial fitting edge being configured to axially abut with a connecting wall at an inlet position of the axial diffuser, the axial abutting edge being configured to abut with the diffuser casing, the second axial fitting edge being configured to axially abut with a side wall at an outlet end of the radial diffuser, the sealing ring being further configured with a first elastic edge connected between a first end of the axial abutting edge and the first axial fitting edge, and a second elastic edge connected between a second end of the axial abutting edge and the second axial fitting edge, the first axial fitting edge and the axial abutting edge having a first preset axial spacing to axially fit between the diffuser casing and the axial diffuser, the second axial fitting edge and the axial abutting edge having a second preset axial spacing to fit a spacing between the diffuser casing and the radial diffuser.

[0009] As a further improvement of the above technical solution, the first elastic edge has a first preset axial stiffness, and the second elastic edge has a second preset axial stiffness.

[0010] As a further improvement of the above technical solution, the first elastic edge comprises a curved portion for providing elastic deformation and a flat portion for controlling the stiffness of the first elastic edge, the flat portion being configured at a first preset angle with the radial direction to make the first elastic edge have the first preset axial stiffness, the second elastic edge being configured at a second preset angle with the radial direction to make the second elastic edge have the second preset axial stiffness, the first preset angle and the second preset angle being respectively 25°-35°, the first preset angle being smaller than the second preset angle.

[0011] As a further improvement of the above technical solution, an outer wall at the inlet position of the axial diffuser is provided with a stepped structure, the first axial fitting edge abutting with a radial edge of the stepped structure, the first elastic edge abutting with an inner wall of the diffuser casing in the radial direction, and an end of the first axial fitting edge abutting with an axial edge of the stepped structure.

[0012] As a further improvement of the above technical solution, the sealing ring is provided with a vent structure uniformly distributed circumferentially, the vent structure being arranged at the second elastic edge.

[0013] As a further improvement of the above technical solution, the first axial fitting edge and the second axial fitting edge are respectively configured as arc-shaped structures.

[0014] As a further improvement of the above technical solution, the first preset axial stiffness is , the second preset axial stiffness is , the assembly interference of the sealing structure between the diffuser casing and the axial diffuser is 0.2-0.5mm, and the axial fit of the sealing structure between the diffuser casing and the radial diffuser is a gap of 0.2-0.2mm.

[0015] According to another aspect of the present application, a diffuser structure is also provided, which applies the above sealing structure, the diffuser assembly includes a mounting edge for connecting with the diffuser casing, the first end of the mounting edge is connected to the diffuser assembly near the inlet of the radial diffuser, the second end of the mounting edge is provided with a connecting flange for cooperating with the diffuser casing, the mounting edge is at a third preset angle in the axial direction, the third preset angle is 3-15°, and the third preset angle is used to match the axial deformation inside the diffuser structure with the axial deformation outside the diffuser structure.

[0016] According to another aspect of the present application, a design method is also provided, which is applied to the above diffuser structure, and includes the following contents:

[0017] S101, according to the deformation caused by the aerodynamic load and the temperature load of the diffuser, the diameter of the mounting edge of the diffuser assembly and the third preset angle are designed;

[0018] S102, the basic profile of the sealing ring is determined according to the spatial position of the diffuser casing and the diffuser, including the inner and outer diameters and the axial length;

[0019] S103, the first preset axial stiffness and the second preset axial stiffness of the sealing member are determined according to the deformation amount of the outlet end of the radial diffuser;

[0020] S104, the first preset angle and the second preset angle of the sealing member are obtained according to the first preset axial stiffness and the second preset axial stiffness;

[0021] S105, the deformation results between the diffuser and the sealing ring are obtained by joint calculation to determine the damping effect;

[0022] S106, the diffuser structure matching the deformation and the damping effect is obtained.

[0023] According to another aspect of the present application, an aero-engine is also provided, which includes the above sealing structure.

[0024] The present application has the following beneficial effects:

[0025] The present sealing ring is axially abutted with the diffuser casing through the abutting of the axial abutted edge, the abutting of the first axial abutted edge with the connecting wall of the inlet position of the axial diffuser, and the abutting of the second axial abutted edge with the axial diffuser, and the sealing ring is axially abutted with the diffuser casing and the diffuser assembly in the assembled state and the working state under the action of the first elastic edge, thereby matching the axial deformation of the diffuser structure and being consistent with the deformation amount of the diffuser assembly, ensuring the structural reliability, and the sealing structure is in the elastic change state, and the sealing ring can provide damping effects between the axial diffuser and the diffuser casing and between the radial diffuser and the diffuser casing under the action of the first elastic edge and the second elastic edge, effectively reducing resonance and improving service life; meanwhile, the axial abutted edge and the first axial abutted edge are axially abutted through the first elastic edge, and the air chamber is formed between the sealing ring and the diffuser assembly under the condition of maintaining the axial abutted edge, thereby playing a sealing role to prevent airflow from affecting the engine performance and further strengthening the elastic damping effect.

[0026] In addition to the objects, features, and advantages described above, the present application has other objects, features, and advantages. The present application will be further described below with reference to the drawings. BRIEF DESCRIPTION OF DRAWINGS

[0027] The accompanying drawings, which form a part of this application, are included to provide a further understanding of the application, illustrate the preferred embodiments of the application, and assist in the explanation of the application. In the drawings:

[0028] Figure 1 is a structural schematic diagram of a conventional diffuser casing and diffuser assembly;

[0029] Figure 2 is a structural schematic diagram of a diffuser structure of the preferred embodiment of the present application;

[0030] Figure 3 is a structural schematic diagram of a diffuser assembly of the preferred embodiment of the present application;

[0031] Figure 4 is a schematic diagram of the installation of the sealing structure of the preferred embodiment of the present application;

[0032] Figure 5 is a structural schematic diagram of the sealing structure of the preferred embodiment of the present application.

[0033] LEGEND:

[0034] 1, diffuser assembly; 11, axial diffuser; 111, step structure; 12, radial diffuser; 2, diffuser case; 3, connecting bolt; 4, sealing ring; 41, first axial matching edge; 42, first elastic edge; 421, bending part; 422, straight part; 43, axial close edge; 44, second elastic edge; 45, second axial matching edge; 46, air passage structure. DETAILED DESCRIPTION

[0035] The embodiments of the present application will be described in detail below with reference to the accompanying drawings, but the present application can be implemented in various different ways as defined and covered by the following description.

[0036] Figure 2 is a structural schematic view of the diffuser structure of the preferred embodiment of the present application; Figure 3 is a structural schematic view of the diffuser assembly of the preferred embodiment of the present application; Figure 4 is a mounting schematic view of the sealing structure of the preferred embodiment of the present application; Figure 5 is a structural schematic view of the sealing structure of the preferred embodiment of the present application.

[0037] As shown in Figures 2 to 4 , the sealing structure of the present embodiment is applied to the diffuser structure of an aero-engine, the diffuser structure comprising a diffuser assembly 1 and a diffuser case 2, the diffuser assembly 1 comprising a radial diffuser 12 and an axial diffuser 11, the sealing structure comprising a sealing member 4 in the form of a ring, the sealing member 4 being configured with a first axial matching edge 41, a second axial matching edge 45 and an axial close edge 43, the first axial matching edge 41 being used for axial abutting matching with a connecting wall at an inlet position of the axial diffuser 11, the axial close edge 43 being used for abutting matching with the diffuser case 2, the second axial matching edge 45 being used for axial abutting matching with a side wall at an outlet end of the radial diffuser 12, the sealing member 4 being further configured with a first elastic edge 42 connected between a first end of the axial close edge 43 and the first axial matching edge 41, and a second elastic edge 44 connected between a second end of the axial close edge 43 and the second axial matching edge 45, the first axial matching edge 41 and the axial close edge 43 having a first preset axial spacing L1 for axial interference assembly between the diffuser case 2 and the axial diffuser 11, the second axial matching edge 45 and the axial close edge 43 having a second preset axial spacing for matching the spacing between the diffuser case 2 and the radial diffuser 12.

[0038] It can be understood that the seal ring is axially abutted with the diffuser casing 2 through the axial abutting edge 43, the first axial fitting edge 41 is axially abutted with the connecting wall of the inlet position of the axial diffuser 11, and the second axial fitting edge 45 is axially abutted with the radial diffuser 12. Under the action of the first elastic edge 42, the seal 4 is always axially fitted with the diffuser casing 2 and the diffuser assembly 1 in the assembled state and the working state, thereby matching the axial deformation of the diffuser structure and being consistent with the deformation amount of the diffuser assembly 1 to ensure the structural reliability. At the same time, the sealing structure is in an elastic change state. Under the action of the first elastic edge 42 and the second elastic edge 44 on the second axial fitting edge 45, the seal 4 can provide damping action between the axial diffuser 11 and the diffuser casing 2 and between the radial diffuser 12 and the diffuser casing 2, respectively, effectively reducing resonance and improving service life. At the same time, the axial abutting edge 43 and the first axial fitting edge 41 are axially abutted by the first elastic edge 42, and the seal 4 can form an air chamber between the axial fitting condition and the diffuser assembly 1, which not only plays a sealing role to prevent airflow from affecting engine performance, but also further strengthens the elastic damping effect.

[0039] In some preferred embodiments, the first elastic edge 42 has a first preset axial stiffness, and the second elastic edge 44 has a second preset axial stiffness. By respectively designing the axial stiffness of the first elastic edge 42 and the axial stiffness of the second elastic edge 44, the seal 4 can be in an elastic change state in the working state while providing a damping effect.

[0040] In some preferred embodiments, the first elastic edge 42 includes a curved portion 421 for providing elastic deformation and a flat portion 422 for controlling the stiffness of the first elastic edge 42. The flat portion 422 is at a first preset angle a1 with the radial direction to make the first elastic edge 42 have a first preset axial stiffness, and the second elastic edge 44 is at a second preset angle a2 with the radial direction to make the second elastic edge 44 have a second preset axial stiffness. The first preset angle and the second preset angle are respectively 25°-35°, and the first preset angle is smaller than the second preset angle. It should be noted that the first preset axial stiffness is , and the second preset axial stiffness is The assembly interference between the sealing structure and the axial diffuser 11 of the diffuser casing 2 is 0.2-0.5 mm, the axial fit between the sealing structure and the radial diffuser 12 of the diffuser casing 2 is a gap of 0.2-0.2 mm, that is, the second preset distance can be less than or greater than the axial distance between the diffuser casing 2 and the radial diffuser 12; wherein the sealing member 4 is preferably a thin-walled structure with a uniform wall thickness t, the first preset axial stiffness of the sealing member 4 can be controlled by designing the first preset angle, and the second preset axial stiffness can be controlled by designing the second preset angle, the distance L1 between the axial close-fitting edge 43 and the first axial fit edge 41 is greater than the distance L2 between the axial close-fitting edge 43 and the second axial fit edge 45, for example, in a specific embodiment, the distance L1 between the axial close-fitting edge 43 and the first axial fit edge 41 is 3-6 mm, and the distance L2 between the axial close-fitting edge 43 and the second axial fit edge 45 is 1-3 mm, so that the first elastic edge 42 is more easily provided with a bending portion 421 to have a larger axial deformation range and thus ensure that the axial abutting fit is always guaranteed. Based on this, the first preset angle is set to be less than the second preset angle, that is, the first preset axial stiffness is less than the second preset axial stiffness, the main damping effect is provided by the second elastic edge 44, the axial sealing fit is ensured and the secondary damping effect is provided by the first elastic edge 42, and the sealing performance and damping performance of the sealing member are improved.

[0041] In some preferred embodiments, the outer wall of the inlet position of the axial diffuser 11 is provided with a stepped structure 111, the first axial fit edge 41 abuts against the radial edge of the stepped structure 111, the first elastic edge 42 abuts against the inner wall of the diffuser casing 2 in the radial direction, and the end of the first axial fit edge 41 abuts against the axial edge of the stepped structure 111; it should be understood that the bending portion 421 of the first elastic edge 42 can abut against the inner wall of the diffuser casing 2 in the radial direction, by providing the stepped structure 111 on the axial diffuser 11, the radial edge of the stepped structure 111 can be used for abutting against the first axial fit edge 41 in the axial direction, and the axial edge thereof can be used for abutting against the end of the first axial fit edge 41 in the radial direction, thereby realizing radial limiting of the sealing structure, avoiding eccentricity of one side of the sealing ring, and ensuring structural stability.

[0042] In some preferred embodiments, the sealing ring is uniformly distributed with air passage structures 46 in the circumferential direction, and the air passage structures 46 are arranged on the second elastic edge 44. By providing the air passage structures 46, a dead space is avoided in the sealing member 4 after the second axial fit edge 45 abuts against the radial diffuser 12 under axial deformation, and the air passage structures 46 can be circular, elliptical or other shapes of air holes.

[0043] In some preferred embodiments, the first axial fitting edge 41 and the second axial fitting edge 45 are respectively configured as arc-shaped structures. By configuring the two as arc-shaped structures, it can be ensured that when the diffuser is axially deformed, the sealing member 4 can be easily deformed elastically, the axial fitting edges with a certain arc can be easily adapted, close fitting can be ensured, cooperation with the diffuser assembly 1 can be ensured, and the contact area is reduced to avoid scratching when the diffuser is axially deformed.

[0044] On the other hand, the preferred embodiments of the present application also provide a diffuser structure applied with the above sealing structure. The diffuser assembly 1 includes a mounting edge for connecting with the diffuser casing 2. The first end of the mounting edge is connected to the diffuser assembly 1 at a position close to the inlet of the radial diffuser 12. The second end of the mounting edge is provided with a connecting flange for cooperating with the diffuser casing 2, and the connecting is realized by connecting bolts 3. The mounting edge is axially at a third preset angle a3, and the third preset angle is 3-15°. The third preset angle is used to match the axial deformation of the inside of the diffuser structure with the axial deformation of the outside of the diffuser structure. It should be noted that the mounting edge is preferably designed at the inlet position of the radial direction of the diffuser assembly 1. The distribution diameter of the mounting edge is about 1-1.1 times the diameter of the inlet position of the radial diffuser 12. The mounting edge is configured to have a certain angle, i.e. the third preset angle, and the design value is 3-15°. The third preset angle is used to match the axial deformation of the inside of the diffuser structure with the axial deformation of the outside of the diffuser structure, so as to ensure that in the case of existing radial temperature gradient, the axial deformation of the outside and the inside of the diffuser can be matched under the action of the sealing structure and the mounting edge, so as to ensure the coordination of the axial deformation.

[0045] On the other hand, the preferred embodiments of the present application also provide a design method applied to the above diffuser structure, which includes the following contents:

[0046] S101, according to the deformation caused by the aerodynamic load and the temperature load of the diffuser, the diameter of the mounting edge of the diffuser assembly 1 and the third preset angle are designed to ensure that the diffuser deformation can meet the design requirements;

[0047] S102, based on step S101, the basic outline of the sealing ring is determined according to the spatial position of the diffuser casing 2 and the diffuser, including the inner and outer diameters and the axial length;

[0048] S103, according to the deformation amount of the outlet end of the radial diffuser 12, the first preset axial stiffness and the second preset axial stiffness of the sealing member 4 are determined to meet the sealing and damping requirements;

[0049] S104, according to the first preset axial stiffness and the second preset axial stiffness, the first preset angle, the second preset angle, the thickness, the material and the like of the sealing member 4 are obtained, and the vent structure 46 is determined based on this;

[0050] S105, the deformation result between the diffuser and the seal ring is obtained by joint calculation, and the sealing, damping and deformation matching effects are met;

[0051] S106, the diffuser structure matching the deformation and damping effect is obtained.

[0052] According to the stress and stress distribution generated by the load of the diffuser itself, the deformation matching is met by designing the diffuser mounting structure including the mounting edge diameter and the third preset angle; the S-shaped seal member 4 is designed by the above method, compared with the sealing ring in the prior art which only has a sealing effect, the different stiffness of the upper and lower segments of the S-shaped seal ring plays different damping, sealing and axial deformation adaptation effects, effectively meeting various needs; through joint calculation, it is determined that the above different effects can meet the requirements.

[0053] On the other hand, the preferred embodiment of the present application also provides an aero-engine applying the above sealing structure.

[0054] Embodiment one

[0055] In this embodiment, referring to Table 1, the sealing structure completes numerical simulation analysis, scheme design, physical processing, and whole machine level verification;

[0056] ;

[0057] The sealing structure of the present embodiment realizes the axial deformation consistency of the diffuser casing and the diffuser assembly, and compared with the conventional structure in the prior art, the relative axial deformation amount is reduced by more than 2 / 3, which proves that the scheme is feasible and the deformation control effect is obvious.

[0058] In the description of the present application, it should be pointed out that the terms "upper", "lower", "front", "rear" and the like indicate the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, therefore cannot be understood as a limitation on the present application.

[0059] In the description of the present application, it should be pointed out that unless otherwise explicitly specified and limited, the terms "mounting", "connection", "connection" should be understood broadly, for example, it can be fixed connection, or detachable connection, or integral connection; it can be mechanical connection, or electrical connection; it can be directly connected, or indirectly connected through intermediate medium, or the communication between two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0060] The above merely provides the preferred embodiments of the present application, and is not used to limit the present application. For those skilled in the art, the present application can have various modifications and changes. Any modifications, equivalent replacements, improvements, etc. made within the principles and technical scope of the present application shall fall into the scope of the present application.

Claims

1. A sealing structure applied to a diffuser structure of an aero-engine, the diffuser structure comprising a diffuser assembly (1) and a diffuser casing (2), the diffuser assembly (1) comprising a radial diffuser (12) and an axial diffuser (11), characterized in that, The sealing structure includes an annular sealing member (4), which has a first axial mating edge (41), a second axial mating edge (45), and an axially close-fitting edge (43). The first axial mating edge (41) is used to axially abut against the connecting wall at the inlet position of the axial diffuser (11), the axially close-fitting edge (43) is used to abut against the diffuser casing (2), and the second axial mating edge (45) is used to axially abut against the side wall at the outlet end of the radial diffuser (12). The sealing member (4) also has a first elastic edge (42) connecting the first end of the axially close-fitting edge (43) and the first axial mating edge (41), and a second elastic edge (44) connecting the second end of the axially close-fitting edge (43) and the second axial mating edge (45). The first axial mating edge (41) and the axially close-fitting edge (43) have a first preset axial distance to be axially interference-fitted to the diffuser. Between the diffuser housing (2) and the axial diffuser (11), the second axial mating edge (45) and the axially close edge (43) have a second preset axial distance to adapt to the distance between the diffuser housing (2) and the radial diffuser (12); the first elastic edge (42) has a first preset axial stiffness and the second elastic edge (44) has a second preset axial stiffness; the first elastic edge (42) includes a bent portion (421) for providing elastic deformation and a straight portion (422) for controlling the stiffness of the first elastic edge (42), the straight portion (422) is at a first preset angle to the radial direction so that the first elastic edge (42) has a first preset axial stiffness, and the second elastic edge (44) is at a second preset angle to the radial direction so that the second elastic edge (44) has a second preset axial stiffness, the first preset angle and the second preset angle are 25°-35° respectively, and the first preset angle is smaller than the second preset angle.

2. The sealing structure according to claim 1, characterized in that, The outer wall of the inlet position of the axial diffuser (11) is provided with a stepped structure (111), the first axial mating edge (41) abuts against the radial edge of the stepped structure, the first elastic edge (42) abuts against the inner wall of the diffuser casing (2) radially, and the end of the first axial mating edge (41) abuts against the axial edge of the stepped structure (111).

3. The sealing structure according to claim 1, characterized in that, The sealing member (4) is provided with ventilation structures (46) evenly distributed in the circumferential direction, and the ventilation structures (46) are arranged on the second elastic edge (44).

4. The sealing structure according to claim 1, characterized in that, The first axial mating edge (41) and the second axial mating edge (45) are respectively constructed as arc-shaped structures.

5. The sealing structure according to any one of claims 1-4, characterized in that, The first preset axial stiffness is 0.5 to 5*10. 7 N / m, the second preset axial stiffness is 0.5~5*10 N / m. 7 N / m, the interference fit between the sealing structure and the diffuser housing (2) and the axial diffuser (11) is 0.2 to 0.5 mm, and the axial fit between the sealing structure and the diffuser housing (2) and the radial diffuser (12) is a clearance of 0.2 to an interference fit of 0.2 mm.

6. A diffuser structure, characterized in that, The application has a sealing structure as described in any one of claims 1-4, wherein the diffuser assembly (1) includes a mounting edge for connecting to the diffuser housing (2), a first end of the mounting edge is connected to a position on the diffuser assembly (1) near the inlet of the radial diffuser (12), a second end of the mounting edge is provided with a connecting flange for cooperating with the diffuser housing (2), the mounting edge forms a third preset angle with the axial direction, the third preset angle being 3-15°, the third preset angle being used to make the axial deformation of the inner side of the diffuser structure match the axial deformation of the outer side of the diffuser structure.

7. A design method applied to the diffuser structure of claim 6, characterized in that, Includes the following: S101. Based on the deformation caused by the diffuser aerodynamic load and temperature load, design and obtain the installation edge diameter of the diffuser assembly and the third preset angle. S102. Determine the basic outline of the sealing component based on the spatial position of the diffuser casing and diffuser, including the inner and outer diameters and axial length. S103. Determine the first preset axial stiffness and the second preset axial stiffness of the sealing element based on the deformation at the outlet end of the radial diffuser. S104. Obtain the first preset angle and the second preset angle of the sealing element based on the first preset axial stiffness and the second preset axial stiffness; S105. Calculate the deformation between the diffuser and the sealing element to determine the damping effect; S106. A diffuser structure that achieves matching deformation and damping effects.

8. An aircraft engine, characterized in that, The application has the sealing structure as described in any one of claims 1-5.

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