CN208102311U - A kind of air curtain sawtooth spout for undercarriage noise reduction - Google Patents
A kind of air curtain sawtooth spout for undercarriage noise reduction Download PDFInfo
- Publication number
- CN208102311U CN208102311U CN201820606234.4U CN201820606234U CN208102311U CN 208102311 U CN208102311 U CN 208102311U CN 201820606234 U CN201820606234 U CN 201820606234U CN 208102311 U CN208102311 U CN 208102311U
- Authority
- CN
- China
- Prior art keywords
- air curtain
- noise
- spout
- noise reduction
- undercarriage
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Landscapes
- Curtains And Furnishings For Windows Or Doors (AREA)
Abstract
The invention discloses a kind of air curtain sawtooth spout for undercarriage noise reduction, including air curtain jet pipe, broached-tooth design is set as on the jet lip of the air curtain jet pipe；When high-speed air is sprayed from common air curtain spout, it can blow and hit orifice rim and generate shear layer, generate lip noise；Meanwhile being mixed in mixed zone shear layer with jet flow and can generate mixed noise, the two is the main sound source of jet noise；The expected spout shear layer structure that can change of zigzag spout of the present invention reduces lip noise；Mixed zone is acted on simultaneously, is inhibited mixed noise, can be reduced air curtain overall noise amount.
Description
Technical field
The invention belongs to aircraft landing gear aerodynamic noise suppression technology fields, are used for aircraft takeoffs and landings more particularly to one kind
The air curtain sawtooth spout of frame noise reduction.
Background technique
Aircraft noise is the airliner development major issue to be considered, whether noise emission is up to standard big as China
Aircraft enters a key technology problem that international market must solve.Airliner noise source can be divided into dynamical system noise and
Body aerodynamic noise, wherein dynamical system refers mainly to engine.It is continually striving to by industry with academia, engine noise has been
It being significantly reduced, this makes body aerodynamic noise is opposite to the noise spectrum contribution of entire aircraft to increase, become potential main sound source,
And obstacle is caused to the development of the following novel large passenger plane.When body aerodynamic noise is due to aircraft high-speed flight in the sky,
It can cause backset bed on its surface with air effect, to cause stress fluctuation, form noise.The distribution of noise sources of engine body noise
In each position of aircraft, wherein undercarriage is one of Main Noise Sources.According to statistics, in the aircraft landing stage, undercarriage is made an uproar
Sound accounts for 30% or so of overall noise discharge amount.Undercarriage noise-reduction method becomes the emphasis of aircraft noise area research.Based on system knot
Structure stability is set out, and Landing Gear Design shape is extremely complex, and aeroperformance is poor.Air-flow can generate strong flowing point when flowing through
Gu from whirlpool-interference, Noise Mechanism is complicated；Its wake flow and the interference of rear airframe components also will form quadratic noise source simultaneously.Cause
This, undercarriage noise reduction also becomes a difficulties in Study of Aerodynamic field.
Since undercarriage is the component for carrying all quality of aircraft in landing, safety of structure is most important.Especially
It is that can generate huge collision in landing, it is careless slightly, it may occur that serious accident.Traditional noise reduction technology（Such as radome fairing）,
It needs to modify to undercarriage self structure or installing accessory component, easily structural stability is had an impact, therefore there is office
It is sex-limited.In contrast, contactless noise reduction technology is small to landing gear structure stability influence, and advantage is more obvious, it would be highly desirable to develop.
Air curtain is being put forward for the first time as a kind of active control technology, Wickerhoff and Sijpkes by air curtain application
In the concept of aircraft landing gear noise reduction.Its scheme is to load the air of an almost plane jet stream in aircraft landing gear upstream
Gas curtain, the gas curtain can be formed about a phase in undercarriage with deviation high speed direction of flow to prevent it from impacting undercarriage
To the region of low speeds flow.Since Landing gear noise and incoming flow flow velocity have an approximate 6 power relationship, Landing gear noise can be with
It is greatly lowered.For air curtain as a kind of contactless Active Control Method, carrying out pneumatic noise reduction using air curtain has uniqueness
Advantage：1. deviation high speed incoming flow, fundamentally removes noise source, noise reduction effect is obvious；2. not needing to pacify in undercarriage itself
Any part is filled, does not influence landing gear structure stability and electric power function；3. can open and close at any time, adjustable flow
And then air curtain size is adjusted, it is easily controllable.4. with air effect in air, gas source convenient sources, without any disposal of pollutants.
But air curtain is as a kind of high-speed plane jet stream, it will generates a large amount of jet noises, limits its Future Projects
Using.
Summary of the invention
The purpose of the invention is to overcome above-mentioned the deficiencies in the prior art, design a kind of low from making an uproar based on broached-tooth design
Sound air curtain spout inhibits air curtain self-noise, provides technical support for engineering practice.
To achieve the above object, the present invention adopts the following technical scheme that：
A kind of air curtain sawtooth spout for undercarriage noise reduction, including air curtain jet pipe, the air curtain spray
Broached-tooth design is set as on the jet lip of pipe.
In the above-mentioned technical solutions, the broached-tooth design by several continuous triangulars at.
In the above-mentioned technical solutions, the dimensional parameters of the triangle are adjusted according to noise effects.
In the above-mentioned technical solutions, the gradient of the triangle is adjustable.
In the above-mentioned technical solutions, the gradient is adjusted according to demand, and triangle is to the close gradient of air curtain
Value is positive, and triangle deviates tilt values to air curtain and is negative, and amount of taper is zero when triangle honest to air curtain direction.
In the above-mentioned technical solutions, several described triangles be congruent sides triangular at.
The principle of the present invention is：When high-speed air is sprayed from common air curtain spout, it can blow and hit orifice rim and generate shearing
Layer generates lip noise；Meanwhile being mixed in mixed zone shear layer with jet flow and can generate mixed noise, the two is jet noise
Main sound source.The expected spout shear layer structure that can change of zigzag spout reduces lip noise；Mixed zone is acted on simultaneously, is pressed down
Mixed noise processed.Therefore, air curtain overall noise amount can be reduced.
In conclusion by adopting the above-described technical solution, the beneficial effects of the invention are as follows：
The lip noise of spout shear layer can be effectively reduced using broached-tooth design, inhibited mixed noise, especially used
To high-speed aircraft landing when can play extraordinary effect.
Detailed description of the invention
Examples of the present invention will be described by way of reference to the accompanying drawings, wherein：
Fig. 1 is schematic view of the mounting position of the air curtain in airplane complete machine；
Fig. 2 is air curtain relative to undercarriage installation site side direction visual angle enlarged diagram；
Fig. 3 is air curtain gas path device schematic diagram；
Fig. 4 is air curtain sawtooth jet pipe schematic diagram；
Wherein：1 is airframe, and 2 be nose-gear, and 3 be air curtain, and 4 be air curtain sawtooth jet pipe, 5 jet nozzles saw
Toothing.
Specific embodiment
All features disclosed in this specification or disclosed all methods or in the process the step of, in addition to mutually exclusive
Feature and/or step other than, can combine in any way.
Embodiment one
As shown in figure 3, being structure of the invention, structure is simple, is exactly by the structure of lip by traditional smooth structure
Broached-tooth design in design cost scheme, broached-tooth design should be arranged at air curtain nozzle lip, and broached-tooth design is by continuous congruence
Triangle sets are at triangle dimensional parameters can be adjusted according to noise effects.Tiltable simultaneously, gradient can be arranged according to demand.
Gradient refers to the angle that triangle deviates to air curtain, can be close, can also deviate.Tilt values are positive when close, deviate
When tilt values be negative.Without drift angle, i.e., when sawtooth is honest upward, gradient zero.By continuous sawtooth mouth, to change spout
The shear layer structure at place reduces lip noise, reduces air curtain overall noise amount from realizing.
By the position of notch setting of the invention in such as Fig. 1, Fig. 2, Fig. 4, air curtain jet pipe is arranged on undercarriage
Swim suitable position.Its length should be selected at least more than undercarriage local width, width according to flow and required air curtain intensity
It selects.
When high-speed flow is ejected from nozzle, an air curtain vertically downward will form, because of aircraft
High-speed flight avoid incoming air from directly impinging on undercarriage so that air curtain stops the shock of incoming air, thus
Bring huge noise.
The invention is not limited to specific embodiments above-mentioned.The present invention, which expands to, any in the present specification to be disclosed
New feature or any new combination, and disclose any new method or process the step of or any new combination.
Claims (6)
1. a kind of air curtain sawtooth spout for undercarriage noise reduction, including air curtain jet pipe, it is characterised in that described
Air curtain jet pipe jet lip on be set as broached-tooth design.
2. a kind of air curtain sawtooth spout for undercarriage noise reduction according to claim 1, it is characterised in that institute
State broached-tooth design by several continuous triangulars at.
3. a kind of air curtain sawtooth spout for undercarriage noise reduction according to claim 2, it is characterised in that institute
The dimensional parameters for stating triangle are adjusted according to noise effects.
4. a kind of air curtain sawtooth spout for undercarriage noise reduction according to claim 2, it is characterised in that institute
The gradient for stating triangle is adjustable.
5. a kind of air curtain sawtooth spout for undercarriage noise reduction according to claim 4, it is characterised in that institute
It states gradient to be adjusted according to demand, triangle is positive to the close tilt values of air curtain, and triangle inclines to air curtain deviation
Amount of taper is negative, and amount of taper is zero when triangle honest to air curtain direction.
6. a kind of air curtain sawtooth spout for undercarriage noise reduction according to claim 2, it is characterised in that institute
State several triangles be congruent sides triangular at.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820606234.4U CN208102311U (en) | 2018-04-26 | 2018-04-26 | A kind of air curtain sawtooth spout for undercarriage noise reduction |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820606234.4U CN208102311U (en) | 2018-04-26 | 2018-04-26 | A kind of air curtain sawtooth spout for undercarriage noise reduction |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208102311U true CN208102311U (en) | 2018-11-16 |
Family
ID=64117064
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820606234.4U Expired - Fee Related CN208102311U (en) | 2018-04-26 | 2018-04-26 | A kind of air curtain sawtooth spout for undercarriage noise reduction |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208102311U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109850129A (en) * | 2019-04-18 | 2019-06-07 | 中国空气动力研究与发展中心低速空气动力研究所 | Denoising structure and its aircraft and its control method for undercarriage and cabin |
| CN117740308A (en) * | 2024-02-19 | 2024-03-22 | 中国空气动力研究与发展中心高速空气动力研究所 | Jet micro-embedded turbulence method and device for controlling large-scale high-speed jet noise |
-
2018
- 2018-04-26 CN CN201820606234.4U patent/CN208102311U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109850129A (en) * | 2019-04-18 | 2019-06-07 | 中国空气动力研究与发展中心低速空气动力研究所 | Denoising structure and its aircraft and its control method for undercarriage and cabin |
| CN117740308A (en) * | 2024-02-19 | 2024-03-22 | 中国空气动力研究与发展中心高速空气动力研究所 | Jet micro-embedded turbulence method and device for controlling large-scale high-speed jet noise |
| CN117740308B (en) * | 2024-02-19 | 2024-04-19 | 中国空气动力研究与发展中心高速空气动力研究所 | Jet micro-embedded turbulence method and device for controlling large-scale high-speed jet noise |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8083171B2 (en) | Supersonic aircraft for reducing sonic boom effects at ground level | |
| RU2522539C2 (en) | Aircraft with fin assembly of "codfish tail" type and with rear-mounted engine | |
| CN208102311U (en) | A kind of air curtain sawtooth spout for undercarriage noise reduction | |
| US7900433B2 (en) | Fan exhaust nozzle for turbofan engine | |
| CA2737893C (en) | Fuselage shaping on a supersonic aircraft for controlling and reducing sonic boom | |
| CN104118557B (en) | Low-Reynolds-number airfoil section with multi-seam synergetic jet flow control and control method | |
| US3881669A (en) | Method and apparatus for elimination of airfoil trailing vortices | |
| CN108216617B (en) | Method for suppressing helicopter propeller-vortex interference noise | |
| CN108706092B (en) | Sawtooth-shaped aircraft weapon cabin noise suppression device | |
| JP6254437B2 (en) | Variable width aerodynamic device | |
| CN108001669B (en) | Leading edge slat noise suppression method based on zero-mass jet control | |
| CN208134602U (en) | A kind of air curtain spout device for undercarriage noise reduction | |
| US20140131514A1 (en) | Nose landing gear arrangement for aircraft and method of assembly | |
| JP2013520360A (en) | A device for reducing noise generated from the interaction between jet jets and pylon in jet engines | |
| CN103332288B (en) | Edge strip at trailing edge of airplane and design method thereof | |
| US8516824B2 (en) | Gas ejection cone for an aircraft turbojet equipped with a device for generating turbulence in a primary flow limiting jet noise | |
| US20150361823A1 (en) | Methods and apparatus for passive thrust vectoring and plume deflection | |
| JPWO2008093447A1 (en) | Low noise aircraft | |
| CN207607638U (en) | Flying-wing's aircraft course control device based on active Flow Control technology | |
| CN105464838A (en) | Methods and apparatus for passive thrust vectoring and plume deflection | |
| US4452266A (en) | Air aspiration device of aircraft-mounted gas-turbine engine | |
| EP2610170A1 (en) | Air drag reduction for an undercarriage with skids of a rotary wing aircraft | |
| CN207565865U (en) | A kind of aircraft is in wing skid pad deflector | |
| CN104960585A (en) | Method and system for performing active resistance reduction control on automobile based on jet actuators | |
| US20140076419A1 (en) | Self adjusting deturbulator enhanced flap and wind deflector |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20181116 Termination date: 20210426 |