A noise reduction structure for an aviation pipeline and a bionics noise reduction pipeline
Patent Information
- Application Number
- CN202522194465.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-10-16
- Publication Date
- 2026-10-27
- Estimated Expiration
- 2035-10-16
AI Technical Summary
[0006]本实用新型的目的在于提供一种用于航空管路的降噪结构及仿生学降噪管路，以解决现有技术中存在的目前降噪管路的降噪结构设计存在缺陷，降噪效果不佳且未充分考虑轻量化设计的技术问题
[0017]本实用新型有效避免了现有技术中存在的目前降噪管路的降噪结构设计存在缺陷，降噪效果不佳且未充分考虑轻量化设计的技术问题。本实用新型提供了一种用于航空管路的降噪结构，降噪结构设置在管道的流体分离区域，包括多层环形且同心设置的降噪组件，降噪组件沿平行于管路的轴向延伸，降噪组件包括前缘为锯齿状或波浪状凸起，凸起沿管路的周向周期性分布排列形成环形结构。
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Figure CN224904401U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of aviation technology, and in particular to a noise reduction structure and a biomimetic noise reduction pipeline for aviation pipelines. Background Technology
[0002] In aviation, the aircraft's piping system plays a crucial role, with the recirculated air system being a key component. The recirculated air system recovers a portion of the used air (characterized by low oxygen and high carbon dioxide content). This recovered air is then filtered and conditioned before being mixed with fresh air and reintroduced into the cabin, improving passenger comfort and controlling ambient temperature.
[0003] However, due to the complexity of aircraft structures, their internal piping systems are diverse and intricately routed. When fluid flows through curved or expanding pipes, the adverse pressure gradient phenomenon becomes particularly pronounced; that is, the pressure gradually increases along the direction of fluid flow, causing a decrease in fluid kinetic energy. In certain stages, the fluid stagnates and detaches from the pipe wall, forming separation zones, such as... Figure 4 , Figure 5 As shown. Behind the separation zone, due to the instability of fluid flow, vortices will be generated, causing pressure pulsations and flutter, resulting in radiated noise.
[0004] To address the aforementioned issues, existing noise reduction structures are typically designed in a general and rudimentary manner, without optimization for specific flow field characteristics. Consequently, their noise reduction effectiveness is limited. Furthermore, the synergistic design of noise reduction and lightweighting is not adequately considered, making it difficult to meet application requirements.
[0005] In view of the above, this utility model is hereby proposed. Utility Model Content
[0006] The purpose of this invention is to provide a noise reduction structure and a biomimetic noise reduction pipeline for aviation pipelines, to solve the technical problems of existing noise reduction pipelines having defects in design, poor noise reduction effect, and insufficient consideration of lightweight design. The various technical effects of the preferred technical solutions provided by this invention are detailed below.
[0007] To achieve the above objectives, the present invention provides the following technical solution:
[0008] This utility model provides a noise reduction structure for aviation pipelines. The noise reduction structure is set in the fluid separation area of the pipeline and includes multiple ring-shaped and concentrically arranged noise reduction components. The noise reduction components extend along the axial direction parallel to the pipeline. The noise reduction components include serrated or wavy protrusions at the leading edge. The protrusions are periodically distributed and arranged along the circumference of the pipeline to form a ring structure.
[0009] Preferably, the protrusions in adjacent layers are staggered.
[0010] Preferably, the height of the noise reduction component gradually decreases from the outside to the inside along the radial direction of the pipeline.
[0011] Preferably, the radius of curvature of the leading edge of the wavy protrusion is ≤0.5mm, and the spanwise twist angle is maintained at 5°-8.
[0012] Preferably, the maximum thickness of the wavy protrusion along the chord is located at a position 70% of the chord length from its leading edge.
[0013] Preferably, the protrusion includes a variable density protrusion, wherein the material retention rate at the root of the variable density protrusion is >80%, and the material retention rate at the leading edge of the variable density protrusion is ≤30%.
[0014] A biomimetic noise reduction pipeline includes the aforementioned noise reduction structure for aviation pipelines, wherein the noise reduction structure is disposed on the interface end face of the noise reduction pipeline.
[0015] Preferably, the noise reduction pipeline and the noise reduction structure are integrally formed.
[0016] The preferred technical solution of this utility model can also produce at least the following technical effects:
[0017] This invention effectively avoids the technical problems of existing noise reduction structures in pipelines, such as poor noise reduction effect and insufficient consideration of lightweight design. This invention provides a noise reduction structure for aviation pipelines. The noise reduction structure is located in the fluid separation region of the pipeline and includes multiple layers of annular and concentrically arranged noise reduction components. The noise reduction components extend along an axial direction parallel to the pipeline and include serrated or wavy protrusions at the leading edge. The protrusions are periodically distributed and arranged along the circumference of the pipeline to form an annular structure.
[0018] The noise reduction component of this invention generates a local high-pressure zone in the fluid through its raised areas and a low-pressure zone through its recessed areas. This pressure gradient induces microscale secondary flow, which effectively delays airflow separation and reduces the separation zone area by injecting high-speed fluid momentum into the boundary layer of the separation zone, thereby reducing flow noise. Simultaneously, the protrusions decompose a single shedding frequency into multi-band small eddies, transforming the eddy energy distribution from a narrow-band peak to a broadband continuous spectrum. Through eddy breaking, the energy of large eddies is transferred to smaller eddies, which decay more rapidly due to viscous dissipation, increasing the energy dissipation rate. Furthermore, the noise reduction component employs a multi-layered concentric ring structure design, effectively controlling the overall weight while ensuring noise reduction performance and meeting lightweight requirements. Attached Figure Description
[0019] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.
[0020] Figure 1 This is a schematic diagram of a noise reduction structure for aviation pipelines provided by this utility model;
[0021] Figure 2 This is a cross-sectional view of a noise reduction structure for aviation pipelines and a protrusion of a biomimetic noise reduction pipeline provided by this utility model.
[0022] Figure 3 This is a schematic diagram of the structure of a biomimetic noise reduction pipeline provided by this utility model;
[0023] Figure 4 This is a schematic diagram of the fluid separation zone formed between pipelines mentioned in the background art;
[0024] Figure 5 yes Figure 4 A magnified view of part A.
[0025] In the picture:
[0026] 1. Noise reduction component; 11. Wavy protrusion; 12. Depression;
[0027] 2. Gas supply branch pipe;
[0028] 3. Fan outlet pipeline. Detailed Implementation
[0029] To make the objectives, technical solutions, and advantages of this utility model clearer, the technical solutions of this utility model will be described in detail below. Obviously, the described embodiments are only a part of the embodiments of this utility model, and not all of them. Based on the embodiments of this utility model, all other implementation methods obtained by those skilled in the art without creative effort are within the scope of protection of this utility model.
[0030] Example 1:
[0031] like Figures 1 to 2As shown, this utility model provides a noise reduction structure for aviation pipelines. The noise reduction structure is installed in the fluid separation area between the fan outlet pipeline 3 and the cabin air supply branch pipe 2, that is, on the interface end face of the air supply branch pipe 2. This location is an area where the fluid flow state changes significantly, and installing a noise reduction structure here can specifically address the noise problem generated by fluid separation. The noise reduction structure includes multiple layers of annular, concentric, and spaced noise reduction components 1. The noise reduction components 1 extend along the axial direction parallel to the pipeline. The noise reduction components 1 include serrated or wavy protrusions 11 at the leading edge, and the protrusions are periodically distributed and arranged along the circumference of the pipeline to form an annular structure.
[0032] The raised region of noise reduction component 1 generates a local high-pressure zone in the fluid, while the recessed region 12 between two adjacent noise reduction component layers 1 forms a low-pressure zone. This pressure gradient induces microscale secondary flow, which effectively delays airflow separation and reduces the separation zone area by injecting high-speed fluid momentum into the boundary layer of the separation zone, thereby reducing flow noise. Simultaneously, the edge of noise reduction component 1 can decompose a single shedding frequency into multi-band small eddies, transforming the eddy energy distribution from a narrow-band peak to a broadband continuous spectrum. Through eddy breaking, the energy of large eddies is transferred to small eddies, which decay faster due to viscous dissipation, increasing the energy dissipation rate. Furthermore, noise reduction component 1 adopts a multi-layered concentric ring structure design, effectively controlling the overall weight while ensuring noise reduction performance and meeting lightweight requirements.
[0033] Furthermore, the noise reduction structure includes four concentric, ring-shaped noise reduction components 1. The outer wall of the outermost noise reduction component 1 is flush with the outer wall of the air supply branch pipe 2.
[0034] As an optional implementation, the protrusions of adjacent layers are staggered.
[0035] This configuration enhances the interaction between the fluid and the noise reduction component 1, making the vortices in the fluid more broken and dispersed.
[0036] As an optional implementation, the height of the noise reduction component 1 gradually decreases from the outside to the inside along the radial direction of the pipeline.
[0037] The highly gradient noise reduction component 1 can achieve a better noise reduction effect.
[0038] As an optional implementation, the radius of curvature of the leading edge of the wavy protrusion 11 is ≤0.5mm.
[0039] With this configuration, the leading edge of the wavy protrusion 11 generates stronger local pressure changes and vortex generation in the fluid, which more effectively induces fluid separation and generates microscale secondary flow.
[0040] As an alternative implementation, the spanwise twist angle of the wavy protrusion 11 is maintained at 5°-8° to increase the complexity of the fluid flow.
[0041] It should be noted that the spanwise twist angle refers to the twist angle of the wavy protrusion 11 in the spanwise direction.
[0042] As an optional implementation, the maximum thickness of the wavy protrusion 11 along the chord direction is located at a position 70% of the chord length from its leading edge, and its thickness gradually decreases towards its leading edge, so that a recess 12 is formed between the wavy protrusions 11 of adjacent layers.
[0043] This design allows the wavy protrusions 11 to gradually change their effect on the fluid during the fluid flow process.
[0044] As an optional implementation, the protrusion includes a variable density protrusion, wherein the material retention rate at the root of the variable density protrusion is >80%, and the material retention rate at the leading edge of the variable density protrusion is ≤30%.
[0045] By employing a variable density design, the protrusion achieves structural lightweighting while ensuring structural strength. Furthermore, the lightweight design of the leading edge can more effectively break up vortices, improving energy dissipation and noise reduction.
[0046] Example 2:
[0047] like Figure 2 As shown, this utility model provides a biomimetic noise reduction pipeline, including a noise reduction structure for aviation pipelines as described in Embodiment 1, wherein the noise reduction structure is disposed on the interface end face of the noise reduction pipeline.
[0048] Furthermore, the noise reduction piping includes a cabin air supply branch pipe 2, and a fan outlet pipe 3 is fitted outside the cabin air supply branch pipe 2. The noise reduction structure is installed on the interface end face of the air supply branch pipe 2. This location is an area where the fluid flow state changes significantly, and installing a noise reduction structure here can specifically address the noise problem generated by fluid separation.
[0049] Using the noise reduction structure in Example 1, the fluid in the biomimetic noise reduction pipeline is subjected to noise reduction treatment, and the flow noise is reduced by changing the fluid flow state.
[0050] As an optional implementation, the noise reduction pipeline and the noise reduction structure are integrally molded.
[0051] This setup improves the overall performance and reliability of the noise reduction piping, reduces noise issues caused by connection problems, and further enhances the noise reduction effect.
[0052] It is understood that the same or similar parts in the above embodiments can be referred to each other, and the contents not described in detail in some embodiments can be referred to the same or similar contents in other embodiments.
[0053] In the description of this utility model, it should be noted that, unless otherwise stated, "a plurality of" means two or more; the terms "upper," "lower," "left," "right," "inner," "outer," "front end," "rear end," "head," "tail," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model. Furthermore, the terms "first," "second," "third," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance.
[0054] In the description of this utility model, it should also be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.
[0055] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "a particular example," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of this application. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.
[0056] The above description is merely a specific embodiment of this utility model, but the protection scope of this utility model is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this utility model should be included within the protection scope of this utility model. Therefore, the protection scope of this utility model should be determined by the protection scope of the claims.
Claims
1. A noise reduction structure for aviation pipelines, characterized in that, The noise reduction structure is set in the fluid separation area of the pipeline and includes multiple ring-shaped and concentrically arranged noise reduction components. The noise reduction components extend along the axial direction parallel to the pipeline. The noise reduction components include serrated or wavy protrusions at the leading edge. The protrusions are periodically distributed and arranged along the circumference of the pipeline to form a ring structure.
2. The noise reduction structure for aviation pipelines according to claim 1, characterized in that, The protrusions on adjacent layers are staggered.
3. A noise reduction structure for aviation pipelines according to claim 2, characterized in that, The height of the noise reduction component gradually decreases from the outside to the inside along the radial direction of the pipeline.
4. The noise reduction structure for aviation pipelines according to claim 3, characterized in that, The leading edge curvature radius of the wavy protrusion is ≤0.5mm, and the spanwise twist angle is maintained at 5°-8.
5. A noise reduction structure for aviation pipelines according to claim 4, characterized in that, The maximum thickness of the wavy protrusion along the chord is located at a position 70% of the chord length from its leading edge.
6. A noise reduction structure for aviation pipelines according to claim 5, characterized in that, The protrusion includes a variable density protrusion, wherein the material retention rate at the root of the variable density protrusion is >80%, and the material retention rate at the leading edge of the variable density protrusion is ≤30%.
7. A biomimetic noise reduction pipeline, characterized in that, The invention includes a noise reduction structure for an aviation pipeline according to any one of claims 1-6, wherein the noise reduction structure is disposed on the interface end face of the noise reduction pipeline.
8. The biomimetic noise reduction pipeline according to claim 7, characterized in that, The noise reduction pipeline and the noise reduction structure are integrally formed.