Aero-engine sealing element
By introducing support components into the aero-engine seals, including the design of irregular grooves, pulleys, and springs, the deformation problem of the seals under compression was solved, achieving stability and durability of the sealing performance.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-03-13
- Publication Date
- 2026-03-17
AI Technical Summary
Existing aero-engine seals are prone to deformation under pressure compression, resulting in poor sealing performance and potential damage to the seals under high pressure.
The design employs a support assembly, including irregularly shaped grooves, pulleys, connecting rods, and springs. The pulleys and connecting rods are connected by rotation, and the springs provide elastic support, reducing deformation and maintaining sealing performance.
It effectively reduces the deformation of the seal during compression, maintains sealing performance, avoids damage, and ensures the stability and sealing effect of the seal during use.
Smart Images
Figure CN224003153U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of sealing technology, and in particular to an aero-engine sealing component. Background Technology
[0002] Aircraft engine seals are an important component of aircraft engines, and their performance directly affects the engine's fuel efficiency, thrust-to-weight ratio, emissions, durability, and maintenance costs. However, existing aircraft engine seals deform under pressure during use, leading to a decrease in sealing performance. If the pressure is too high, it can also damage the seals. Utility Model Content
[0003] The purpose of this utility model is to solve the technical problems mentioned in the background art.
[0004] The present invention adopts the following technical solution: an aero-engine seal, comprising a seal body, the seal body comprising an outer layer and an inner layer, the outer layer being disposed outside the inner layer, a support assembly being disposed inside the inner layer, the support assembly comprising a shaped groove, a pulley being slidably connected inside the shaped groove, a connecting rod being rotatably connected between the pulleys, and a spring being rotatably connected between the connecting rods.
[0005] Preferably, the pulleys are arranged symmetrically inside the inner layer, and the connecting rods are arranged in a cross pattern.
[0006] Preferably, the inner layer is covered with a force-bearing block, and the force-bearing block is in the shape of a semi-elliptical sphere.
[0007] Preferably, the outer layer is an annular reinforcing member disposed outside the inner layer, and the inner layer is made of rubber material.
[0008] Preferably, the irregular groove is a shape that is flat in the middle and curved on both sides.
[0009] Preferably, the material of the force-bearing block is metal.
[0010] Compared with the prior art, the advantages and positive effects of this utility model are as follows:
[0011] In this invention, by setting a support component, the deformation range can be effectively reduced, avoiding the inability to return to the original shape after deformation when the seal is compressed under pressure. At the same time, it can maintain a small deformation range even when subjected to greater pressure, ensuring the sealing performance of the seal during use. Attached Figure Description
[0012] Figure 1 A schematic diagram of an aero-engine seal is provided for this utility model;
[0013] Figure 2 This utility model provides an internal schematic diagram of an aero-engine seal;
[0014] Figure 3 This utility model provides a side cross-sectional view of an aero-engine seal.
[0015] Figure 4 This utility model proposes a sealing component for an aircraft engine. Figure 3 Enlarged diagram of point A in the middle.
[0016] Legend:
[0017] 1. Sealing body; 11. Outer layer; 12. Inner layer; 13. Force-bearing block; 2. Support assembly; 21. Irregular groove; 22. Pulley; 23. Connecting rod; 24. Spring. Detailed Implementation
[0018] To better understand the above-mentioned objectives, features, and advantages of this utility model, the present utility model will be further described below with reference to the accompanying drawings and embodiments. It should be noted that, unless otherwise specified, the embodiments and features described in these embodiments can be combined with each other.
[0019] Many specific details are set forth in the following description in order to provide a full understanding of the present invention. However, the present invention may also be implemented in other ways different from those described herein. Therefore, the present invention is not limited to the specific embodiments disclosed in the following specification.
[0020] Example 1
[0021] Please see Figure 1-4 This utility model provides a technical solution: an aero-engine seal, including a seal body 1, the seal body 1 including an outer layer 11 and an inner layer 12, the outer layer 11 being disposed outside the inner layer 12, and a support assembly 2 being disposed inside the inner layer 12, the support assembly 21 including a shaped groove 21, a pulley 22 being slidably connected inside the shaped groove 21, the pulley 22 being able to slide inside the shaped groove 21, a connecting rod 23 being rotatably connected between the pulleys 22, when the pulleys 22 slide, they will drive the connecting rod 23 to rotate, and a spring 24 being rotatably connected between the connecting rods 23, the spring 24 being used to provide elastic support force to reset the connecting rod 23.
[0022] Example 2
[0023] Please see Figure 1-4The pulleys 22 are arranged symmetrically inside the inner layer 12, and the connecting rods 23 are arranged in a cross pattern. The inner layer 12 is covered with a force-bearing block 13, which provides a force point for external forces and compresses the pulleys 22. The force-bearing block 13 is a semi-elliptical sphere. The outer layer 11 is an annular reinforcing member set outside the inner layer 12. The annular reinforcing member can provide the inner layer 12 with impact resistance and can also bear force and transmit the force to the force-bearing block 13. The inner layer 12 is made of rubber, and the irregular groove 21 is flat in the middle and curved on both sides. The force-bearing block 13 is made of metal.
[0024] Working principle: When the outer layer 11 is subjected to force and transmits the force to the inner layer 12, the force is received through the force-bearing block 13, and then the irregular groove 21 is squeezed. Then the pulley 22 is subjected to force and slides to both sides, while driving the connecting rod 23 to fold. This causes the spring 24 to apply a reaction force to provide elastic support to the connecting rod 23, so that the folding rod 23 drives the pulley 22 to return to its original shape, thereby providing sufficient elastic support to the inner layer 12 to return it to its original shape. Due to the arc design on both sides of the irregular groove 21, the more the pulley 22 moves to both sides, the greater the force required to apply to the spring 24, thus effectively reducing the deformation range.
[0025] The above description is merely a preferred embodiment of the present utility model and is not intended to limit the present utility model in any other way. Any person skilled in the art may make changes or modifications to the above-disclosed technical content to create equivalent embodiments for application in other fields. However, any simple modifications, equivalent changes, and modifications made to the above embodiments based on the technical essence of the present utility model without departing from the technical solution of the present utility model shall still fall within the protection scope of the technical solution of the present utility model.
Claims
1. An aeroengine seal comprising a seal body (1), characterised in that: The sealing body (1) comprises an outer layer (11) and an inner layer (12), the outer layer (11) is arranged outside the inner layer (12), the inside of the inner layer (12) is provided with a supporting assembly (2), the supporting assembly (2) comprises a special-shaped sliding groove (21), the inside of the special-shaped sliding groove (21) is slidably connected with a pulley (22), the pulleys (22) are rotatably connected with a connecting rod (23), and the connecting rod (23) is rotatably connected with a spring (24).
2. The aeroengine seal of claim 1, wherein: The pulleys (22) are symmetrically arranged in the inner layer (12) in an up-down mode, and the connecting rod (23) is arranged in a cross mode.
3. The aeroengine seal of claim 1, wherein: The inside of the inner layer (12) is covered with a stress block (13), and the stress block (13) is in the shape of a semi-elliptical sphere.
4. The aeroengine seal of claim 1, wherein: The outer layer (11) is an annular reinforcing member arranged outside the inner layer (12), and the inner layer (12) is made of rubber material.
5. The aeroengine seal of claim 1, wherein: The special-shaped sliding groove (21) is in the shape of a flat middle part and arc-shaped two sides.
6. The aircraft engine seal of claim 3, wherein: The stress block (13) is made of metal.