CN103010459B - Method for reducing pneumatic noise of leading edge slat based on trailing edge micro-perforation - Google Patents
Method for reducing pneumatic noise of leading edge slat based on trailing edge micro-perforation Download PDFInfo
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- CN103010459B CN103010459B CN201210531873.6A CN201210531873A CN103010459B CN 103010459 B CN103010459 B CN 103010459B CN 201210531873 A CN201210531873 A CN 201210531873A CN 103010459 B CN103010459 B CN 103010459B
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- slat
- trailing edge
- small holes
- leading edge
- line segment
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Abstract
The invention discloses a method for reducing the pneumatic noise of a leading edge slat based on trailing edge micro-perforation. The method particularly comprises the steps as follows: setting a row of small holes at equal intervals in the wing unfolding direction at the trailing edge of the leading edge slat, wherein the perforation rate of the small holes in the unfolding direction is 2%, namely a line segment is made in the slat unfolding direction through the center of the small holes and the length of the line segment is the thickness of the slat in the unfolding direction; the sum of the lengths of all the small holes on the line segment is 2% of the whole thickness of the slat in the unfolding direction; the diameters of the small holes are 0.8-1 mm; and the distance between the center of the small holes and the trailing edge is 3-5 mm. According to the method, part of energy of sound waves is consumed in the small holes, a small amount of air stream on the lower surface of the slat flows to the upper surface of the slat through the small holes due to the pressure difference of the upper surface and the lower surface, and the vortex-shedding behavior of the trailing edge is influenced by locally changing the flow direction of the air stream in front of the trailing edge, so that the purpose of reducing the high-frequency sharp-frequency pneumatic noise generated by the slat is achieved, the pneumatic force is guaranteed to be not influenced basically at the same time; and the method is convenient to realize in engineering application.
Description
Technical field
The present invention relates to a kind of method reducing leading edge slat aerodynamics noise based on trailing edge micropunch, belong to aviation engine body noise technical field.
Background technology
Along with the development of society and the progress of industrial technology, people propose more and more stricter environmental demands to Civil Aviation Industry.International Civil Aviation Organization has formulated the recommended standard of aircraft noise certification, and a series of aircraft noise air worthiness regulation has been formulated based on this in the U.S., Europe etc., is limited seating plane noise level.These are for challenge huge beyond doubt the large-scale seating plane that China is developing, and can noise level becomes it obtain airworthiness certificate and future in one of world's aviation field key factor occupying one seat.
Modern large-scale civil aircraft is in the take-off and landing stage, and after considering lift-rising effect and mechanism complexity, the three sections of wing formulas generally adopted are to reach lift-rising effect.Wherein, high lift device comprises leading edge slat and trailing edge flap.Fig. 1 shows the wing composition of three sections of wing configurations, comprises leading edge slat 1, main wing 2 and trailing edge flap 3 three parts.
Nowadays, take off and landing phases at large-scale civil aircraft, along with motor noise reduces gradually, engine body noise is dominate gradually, and its noise source comprises high-lift device of airplane and alighting gear.High lift device aerodynamics noise is primarily of leading edge slat aerodynamics noise and source, trailing edge flap side aerodynamics noise composition.Flight test is consistent with wind tunnel experiment to be shown, in the aircraft landing stage, leading edge slat aerodynamics noise can not be ignored.
Leading edge slat aerodynamics noise frequency spectrum is typical broadband noise spectrum, contains the single-tone noise of different frequency therebetween.Wherein, in high frequency pneumatic noise composition, in noise pattern, there is obvious spike.For the appearance of high frequency pneumatic noise spike value, nowadays general owing to the behavior of slat trailing edge vortex shedding.Therefore, change the behavior of slat trailing edge vortex shedding to have an impact to high frequency pneumatic noise.
Summary of the invention
The object of the invention is to solve the problem, proposing a kind of method reducing leading edge slat aerodynamics noise based on trailing edge micropunch.
Reduce a method for leading edge slat aerodynamics noise based on trailing edge micropunch, be specially: at the trailing edge place of leading edge slat, along wing exhibition to arranging row's aperture, spaced set between aperture.
Described aperture exhibition is 2% to punching rate, namely does a line segment along slat exhibition to direction by small hole center, line segment length be slat exhibition to thickness, wherein, the length that all hole diameters are occupied on this line segment and be that whole exhibition is to 2% of thickness.
Described hole diameter is 0.8 ~ 1mm, and the distance of small hole center and trailing edge is 3 ~ 5mm.
The invention has the advantages that:
(1) the present invention is opened up to getting through row's aperture by edge near leading edge slat trailing edge, due to slat upper and lower surface pressure reduction, make a small amount of air-flow of lower surface flow to upper surface by aperture, local changes the air current flow before trailing edge, and then affects the behavior of trailing edge vortex shedding.
(2) in the present invention, not only sound wave can consume portion of energy in aperture, and the object reducing the high frequency point frequency aerodynamics noise produced by slat is reached mainly through changing slat trailing edge vortex shedding behavior, ensure that aerodynamic force is substantially unaffected simultaneously, and be convenient to realize on engineer applied.
Accompanying drawing explanation
Fig. 1 is three sections of wing mechanism schematic diagrams of the prior art;
Fig. 2 is the aperture schematic diagram near slat trailing edge of the present invention;
Fig. 3 a is that wing of the present invention exhibition is to hole knockout overall schematic;
The close-up schematic view of Fig. 3 b Fig. 3 a.
In figure: 1-leading edge slat; 2-main wing; 3-trailing edge flap; 4-aperture.
Detailed description of the invention
Below in conjunction with drawings and Examples, the present invention is described in further detail.
The present invention is a kind of method reducing leading edge slat aerodynamics noise based on trailing edge micropunch, is specially: at the trailing edge place of leading edge slat 1, along wing exhibition to arranging row's aperture 4, spaced set between aperture 4.
Aperture 4 diameter is 0.8 ~ 1mm, the distance of small hole center and trailing edge is 3 ~ 5mm, exhibition is 2% to punching rate, namely a line segment is done along slat exhibition to direction by aperture 4 center, line segment length is that slat exhibition is to thickness, wherein, the length that all aperture 4 diameters are occupied on this line segment and be that whole exhibition is to 2% of thickness.
As shown in Figure 2, near the trailing edge of leading edge slat 1, along wing exhibition to getting through row's aperture 4, because pressure reduction can make a small amount of air-flow of leading edge slat 1 lower surface to be flowed to the upper surface of leading edge slat 1 by aperture 4, local changes the air current flow before trailing edge, and then affects the behavior of trailing edge vortex shedding.Sound wave can consume portion of energy in aperture 4, and the consumption of trailing edge vortex shedding energy also can increase, and reaches the object reducing the high frequency point frequency aerodynamics noise produced by leading edge slat 1 thus.In addition, because punch position distance leading edge slat 1 trailing edge is very near, and position is very little to the contribution of aerodynamic force near leading edge slat 1 trailing edge, and controlling on the less basis of punching rate, be to ensure that aerodynamic force is substantially impregnable by getting through the mode of aperture 4 noise reduction.And, punch aperture 4 and be convenient to realize on engineer applied.
Embodiment:
If leading edge slat 1 trailing edge thickness is 4mm, wing exhibition is 600mm to thickness.Concrete exhibition is shown in Fig. 3 a to hole knockout, and getting aperture 4 diameter is 1mm, every two aperture 4 centers be spaced apart 53mm, 12 apertures 4 altogether.Fig. 3 b is the local punching enlarged drawing of Fig. 3 a, and show position and the size of edge aperture 4, the distance of aperture 4 center and trailing edge is 4mm, is 8mm with the extrorse distance of exhibition.The punching rate obtained thus is 2%.
Invent the method based on the reduction leading edge slat aerodynamics noise of boring a hole near large-scale civil aircraft leading edge slat trailing edge, on the guarantee substantially impregnable basis of aerodynamic force, can reach the object reducing the high frequency point frequency aerodynamics noise produced by slat, and the method is convenient on engineer applied realize.
Claims (2)
1. reduce a method for leading edge slat aerodynamics noise based on trailing edge micropunch, be specially: at the trailing edge place of leading edge slat, along wing exhibition to arranging row's aperture, spaced set between aperture;
Described aperture exhibition is 2% to punching rate, namely does a line segment along slat exhibition to direction by small hole center, line segment length be slat exhibition to thickness, wherein, the length that all hole diameters are occupied on this line segment and be that whole exhibition is to 2% of thickness.
2. a kind of method reducing leading edge slat aerodynamics noise based on trailing edge micropunch according to claim 1, described hole diameter is 0.8 ~ 1mm, and the distance of small hole center and trailing edge is 3 ~ 5mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210531873.6A CN103010459B (en) | 2012-12-11 | 2012-12-11 | Method for reducing pneumatic noise of leading edge slat based on trailing edge micro-perforation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210531873.6A CN103010459B (en) | 2012-12-11 | 2012-12-11 | Method for reducing pneumatic noise of leading edge slat based on trailing edge micro-perforation |
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| Publication Number | Publication Date |
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| CN103010459A CN103010459A (en) | 2013-04-03 |
| CN103010459B true CN103010459B (en) | 2015-02-11 |
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| CN201210531873.6A Expired - Fee Related CN103010459B (en) | 2012-12-11 | 2012-12-11 | Method for reducing pneumatic noise of leading edge slat based on trailing edge micro-perforation |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112949127A (en) * | 2021-03-02 | 2021-06-11 | 西北工业大学 | Interference trailing edge structure of leading-edge slat and design method of interference amount of interference trailing edge structure |
| CN114598983B (en) * | 2022-01-24 | 2023-06-16 | 北京航空航天大学 | Noise microphone array test method for civil aircraft lift-increasing device |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5598990A (en) * | 1994-12-15 | 1997-02-04 | University Of Kansas Center For Research Inc. | Supersonic vortex generator |
| US7396208B1 (en) * | 2005-02-15 | 2008-07-08 | Hussain Mahmood H | Divided blade rotor |
| US8251317B2 (en) * | 2008-04-18 | 2012-08-28 | The Boeing Company | System and method for varying the porosity of an aerodynamic surface |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| BRPI0701438B1 (en) * | 2007-04-13 | 2019-11-19 | Embraer Empresa Brasileira De Aeronautica S A | aircraft control surface in combination in combination with an aerodynamic seal to reduce noise generated by aircraft control surfaces |
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2012
- 2012-12-11 CN CN201210531873.6A patent/CN103010459B/en not_active Expired - Fee Related
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5598990A (en) * | 1994-12-15 | 1997-02-04 | University Of Kansas Center For Research Inc. | Supersonic vortex generator |
| US7396208B1 (en) * | 2005-02-15 | 2008-07-08 | Hussain Mahmood H | Divided blade rotor |
| US8251317B2 (en) * | 2008-04-18 | 2012-08-28 | The Boeing Company | System and method for varying the porosity of an aerodynamic surface |
Non-Patent Citations (1)
| Title |
|---|
| 飞机机体噪声降噪方法研究进展;张浩驰;《噪声与振动控制》;20080430(第2期);全文 * |
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