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Low self-noise airfoil structure having multi-wavelength serrated trailing edge

A low self-noise, multi-wavelength technology, applied in the direction of wings, wing shapes, aircraft parts, etc., can solve the problems of difficulty in ensuring the applicability of different scale vortices, limited noise suppression, increased noise, etc., to achieve the reduction of airfoil Self-noise, simple installation, uniform flow effect

Inactive Publication Date: 2019-02-01
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to solve the current existing trailing edge sawtooth modification design, adopt a single sawtooth shape, and the waveform is a single wavelength and single amplitude, so that the single-scale sawtooth is difficult to ensure the applicability to different scale vortexes, and the noise The suppression effect is limited, and sometimes it will increase the noise problem, thus providing a low self-noise airfoil structure with multi-wavelength sawtooth trailing edge

Method used

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  • Low self-noise airfoil structure having multi-wavelength serrated trailing edge
  • Low self-noise airfoil structure having multi-wavelength serrated trailing edge
  • Low self-noise airfoil structure having multi-wavelength serrated trailing edge

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specific Embodiment approach 1

[0018] Specific implementation mode one: combine Figure 1-10 To illustrate this embodiment, the low self-noise airfoil structure with multi-wavelength sawtooth trailing edge described in this embodiment includes an airfoil body 1 and a noise-reducing trailing edge plate 2, and the airfoil body 1 is connected by Part 3 is detachably connected to the noise reduction trailing edge plate 2;

[0019] The trailing edge of the airfoil body 1 is axially provided with a long slot for inserting the noise-reducing trailing edge plate 2, and the airfoil above the long slot at the tail end of the airfoil body 1 is provided with N fixing holes 1-1, N is a positive integer and N≥2, the noise-reducing trailing edge plate 2 includes two sections, the first section is a rectangular plate 2-1 and the second section is a multi-wavelength sawtooth trailing edge plate 2-2, and the first section is The rectangular plate 2-1 is integrally formed with the second section of multi-wavelength sawtooth ...

specific Embodiment approach 2

[0021] Specific implementation mode two: combination Figure 2-7 To describe this embodiment, two or more types of the Z waveforms in this embodiment are selected from among triangular waveforms, triangular waveforms with rounded corners, sine waveforms, and cosine waveforms. Other compositions and connections are the same as in the first embodiment.

[0022] In this embodiment, the sawtooth shape of the multi-wavelength sawtooth trailing edge plate 2-2 can be processed by laser cutting, electric spark cutting, 3D printing and other manufacturing technologies.

specific Embodiment approach 3

[0023] Specific implementation mode three: combination Figure 2-7 Describe this embodiment, the Z types of waves that constitute the combined sawtooth A described in this embodiment, the value range of the wavelength λ is 0.05L-0.4L, and the value range of the amplitude h of the waveform is 0.02L-0.2L, where L is the chord length, the length from the leading edge to the trailing edge of the airfoil body 1, and other components and connections are the same as those in Embodiment 1 or 2.

[0024] In this embodiment, the wavelength λ represents the distance between peaks of the trailing edge shape, and the amplitude h represents the distance between the peaks and troughs of the trailing edge shape.

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Abstract

The present invention discloses a low self-noise airfoil structure having a multi-wavelength serrated trailing edge, relates to the technical field of hydrodynamic noise, and solves the problem that,in the traditional airfoil trailing edge saw tooth modification design, the single tooth shape is adopted, the waveform has the single wavelength and single amplitude, thus the single-scale saw toothis difficult to guarantee the applicability to vortices of different scales and has limited suppression effect on noise, and on the contrary sometimes the noise is increased. The low self-noise airfoil structure having the multi-wavelength serrated trailing edge comprises an airfoil body and a noise reduction trailing edge plate. The airfoil body is detachably connected with the noise reduction trailing edge plate through a connector; the trailing edge end of the airfoil body is provided with an elongated groove for inserting the noise reduction trailing edge plate in the axial direction, thenoise reduction trailing edge plate comprises two segments, that is, a first segment rectangular plate and a second segment multi-wavelength serrated trailing edge plate, the first segment rectangularplate and the second segment multi-wavelength serrated trailing edge plate are integrally formed, and the multi-wavelength serrated trailing edge plate is a serrated plate. The low self-noise airfoilstructure having the multi-wavelength serrated trailing edge is used for reducing the self-noise of the airfoil.

Description

technical field [0001] The invention relates to the technical field of fluid dynamic noise, in particular to a low self-noise airfoil structure with multi-wavelength serrated trailing edges. Background technique [0002] Airfoil self-noise is an important source of aircraft noise, underwater vehicle noise and wind turbine noise, and the trailing edge of airfoil is one of the key factors for airfoil self-noise. At a high Reynolds number, the airfoil boundary layer is in a fully developed turbulent state. At this time, when the turbulent boundary layer flows over the airfoil trailing edge, the small-scale vortices in the turbulent flow interact with the trailing edge, resulting in pressure scattering, which spreads far away. Broad-band noise with a relatively high radiation frequency; when the Reynolds number is low, the airfoil boundary layer is not completely transformed into turbulent flow, and laminar flow separation bubbles are generated under the action of the reverse pr...

Claims

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Application Information

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IPC IPC(8): B64C3/10
CPCB64C3/10B64C2003/147
Inventor 马瑞贤刘占生张广辉何鹏
Owner HARBIN INST OF TECH