CN106938696A - A design method for saber-shaped low-noise propeller blades - Google Patents
A design method for saber-shaped low-noise propeller blades Download PDFInfo
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- CN106938696A CN106938696A CN201710088817.2A CN201710088817A CN106938696A CN 106938696 A CN106938696 A CN 106938696A CN 201710088817 A CN201710088817 A CN 201710088817A CN 106938696 A CN106938696 A CN 106938696A
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- 238000013461 design Methods 0.000 title claims abstract description 58
- 238000000034 method Methods 0.000 title claims abstract description 16
- 230000007423 decrease Effects 0.000 claims description 3
- UPMXNNIRAGDFEH-UHFFFAOYSA-N 3,5-dibromo-4-hydroxybenzonitrile Chemical compound OC1=C(Br)C=C(C#N)C=C1Br UPMXNNIRAGDFEH-UHFFFAOYSA-N 0.000 description 10
- 238000004519 manufacturing process Methods 0.000 description 5
- 238000005457 optimization Methods 0.000 description 3
- 238000004088 simulation Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000002474 experimental method Methods 0.000 description 2
- 239000004744 fabric Substances 0.000 description 2
- 230000008707 rearrangement Effects 0.000 description 2
- 238000004458 analytical method Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
- 238000012163 sequencing technique Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/18—Aerodynamic features
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
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Abstract
本发明公开了一种马刀型低噪声螺旋桨桨叶设计方法，采用直线作为各截面翼型安插基准，但直线和展向各设计平面的交点与平面上和翼型的后缘点重合。首先绘制一条平直的直线，固定一个原点，在距离原点不同相对半径距离上沿桨叶旋转方向布置各设计平面，确定各设计平面与直线的交点即设计平面与直线互相垂直；然后将不同设计平面上对应的翼型插入，保证翼型后缘上下点与设计平面、直线的交点重合，并进行翼型扭转角的绘制,且同一桨叶各设计平面上下要求相同；之后再对各截面进行连接，最终成为一条后缘平直的螺旋桨。并且在大部分截面处获得同时脱落的尾涡，可对螺旋桨桨叶的声源点进行重新排布，实现对螺旋桨桨叶噪声的降低。
The invention discloses a design method of a saber-shaped low-noise propeller blade, which adopts a straight line as the reference point for the placement of each cross-section airfoil, but the intersection point of the straight line and each design plane in the span direction coincides with the trailing edge point on the plane and the airfoil. First draw a straight line, fix an origin, arrange the design planes along the direction of blade rotation at different relative radius distances from the origin, and determine the intersection of each design plane and the straight line, that is, the design plane and the straight line are perpendicular to each other; The corresponding airfoil on the plane is inserted to ensure that the top and bottom points of the trailing edge of the airfoil coincide with the intersection of the design plane and the straight line, and the twist angle of the airfoil is drawn, and the requirements for the top and bottom of each design plane of the same blade are the same; connected, eventually becoming a propeller with a straight trailing edge. And the wake vortex that falls off at the same time is obtained at most of the cross-sections, and the sound source points of the propeller blades can be rearranged to reduce the noise of the propeller blades.
Description
Technical field
Propeller technology field is used the present invention relates to airborne vehicle, specifically, is related to a kind of sabre type low noise propeller
Blade design method.
Background technology
In existing Design of Propeller, primary data, i.e. pace are typically determined first, advance ratio, diameter of propeller blade, blade
The technical indicators such as number, followed by the pneumatic design of propeller.It is theoretical using two-dimentional foline, with reference to the primary data of propeller
Determine that blade opens up the aerofoil profile and its corresponding torsion angle to each section.Recycle optimum theory necessarily to be optimized, such as make extensively
Betz methods.Each master data opened up to the aerofoil profile at section, chord length, torsion angle, obtain blade of optimization.Enter promoting the circulation of qi afterwards
Dynamic performance Analysis and Calculation, meets and requires then to carry out next step manufacture, experimental work；It is unsatisfactory for requiring then further to optimize tune
Straightening reaches requirement.After the master data of blade is obtained, the drawing of model is carried out, it is common practice that determine a benchmark
Line, datum line and is opened up to each section, and the intersection point vertical with datum line is as the chord length position of section aerofoil profile 30%, then cloth
Aerofoil profile torsion angle is put, blade is drawn, is processed manufacture.The blade of this form has problems in that and Betz method original intentions
It is not inconsistent.Betz methods emphasize after blade optimization that circular rector change is for the overall pneumatic property of blade caused by each section aerofoil profile change
The influence of energy is identical, i.e., the trailing vortex deviate from after blade can form an equidistant helicoid.But according to previously described tradition
The blade that form is drawn has very big difference due to each section aerofoil profile length, torsion angle, and its trailing edge is that a complicated three-dimensional is bent
Line.The reason for being so designed is to facilitate fabrication design and design experiences for many years.But after the blade of traditional form
Edge is not straight, and the trailing vortex that its each section comes off respectively certainly exists sequencing, and these trailing vortexs can exist certain each other
Interference, cause the increase of blade noise.
In propeller blade design, basic data be it is each open up to section correspondence aerofoil profile and its torsion angle it is selected after, spiral
The Betz methods of oar optimization emphasize that blade afterbody can form isometric helix face, but the blade trailing edge tail of traditional propeller design
Not on the same line, blade is opened up to trailing vortex between each section still can produce certain interference to whirlpool disengaging configuration.
The content of the invention
In order to avoid the deficiency that prior art is present, the present invention proposes a kind of sabre type low noise propeller blade design side
Method.
The present invention thinking be:It is determined that propeller blade master data is each opens up to section correspondence aerofoil profile and its torsion angle
Afterwards, it is embodied on the aerodynamic configuration of propeller, assigns benchmark using straight line as each section aerofoil profile, but straight line and opens up to each
The intersection point of design plane in plane with the trailing edge point of aerofoil profile with overlapping.A straight blade trailing edge can be so obtained, and big
The trailing vortex come off simultaneously is obtained at partial cross section, rearrangement can be carried out to the point source of sound of blade, realization is cut to blade noise
Subtract.
The technical solution adopted for the present invention to solve the technical problems is:
Sabre type low noise propeller blade design method, it is characterised in that comprise the following steps:
Step 1. determines the master data of a blade, draws a straight straight line, and fixes an origin, in distance
Origin difference relative radius arranges each design plane on along blade direction of rotation, determines the friendship of each design plane and straight line
Point, spanwise direction from 0.3 times of relative radius to 1.0 times of relative radius at insert a design plane every 0.1 times of relative radius；
Step 2. inserts corresponding aerofoil profile in different designs plane, it is ensured that put above and below airfoil trailing edge with design plane, directly
The intersection point of line is overlapped, and carries out requiring identical above and below the drafting of aerofoil profile torsion angle, and each design plane of same blade；
Step 3. is attached to each section again according to above-mentioned steps, eventually becomes a straight propeller of trailing edge；Knot
The blade for closing Betz condition optimizings increases with radius of turn, and each section aerofoil profile chord length first increases and then decreases obtains a sabre type
Leading edge；
Each section aerofoil profile parameter is:Propeller profile be sabre type, a length of 800mm of wing chord,
Beneficial effect
Sabre type low noise propeller blade design method proposed by the present invention, is assigned using straight line as each section aerofoil profile
Benchmark, but straight line and intersection point to each design plane is opened up with being overlapped in plane with the trailing edge point of aerofoil profile.Drafting one is straight first
Straight line, fix an origin, each design plane arranged along blade direction of rotation on apart from the different relative radius of origin,
Determine that the intersection point i.e. design plane and straight line of each design plane and straight line are orthogonal；Then will be corresponding in different designs plane
Aerofoil profile is inserted, it is ensured that point is overlapped with the intersection point of design plane, straight line above and below airfoil trailing edge, and carries out the drafting of aerofoil profile torsion angle,
And require identical above and below same each design plane of blade；Each section is attached again afterwards, a trailing edge is eventually become straight
Propeller.And the trailing vortex come off simultaneously is obtained at most of section, the point source of sound of propeller blade can be carried out again
Arrangement, realizes the reduction to propeller blade noise.
Brief description of the drawings
A kind of sabre type low noise propeller blade design method of the invention is made with embodiment below in conjunction with the accompanying drawings into
One step is described in detail.
Fig. 1 a are propeller blade plane projected shape of the present invention.
Fig. 1 b are conventional propeller blade plane projected shape.
Fig. 2 a assign datum line schematic diagram for each design plane aerofoil profile of propeller blade aerodynamic configuration of the present invention.
Fig. 2 b assign datum line schematic diagram for each design plane aerofoil profile of conventional propeller blade aerodynamic profile.
Embodiment
The present embodiment is a kind of sabre type low noise propeller blade design method.
This example sabre type low noise propeller blade design method assigns benchmark using straight line as each section aerofoil profile, and
Straight line and intersection point to each design plane is opened up with being overlapped in plane with the trailing edge point of aerofoil profile；A straight straight line is drawn first,
An origin is fixed, each design plane is being arranged along blade direction of rotation on apart from the different relative radius of origin, it is determined that respectively
The intersection point of design plane and straight line is that design plane and straight line are orthogonal；Then corresponding aerofoil profile in different designs plane is inserted
Enter, it is ensured that point is overlapped with the intersection point of design plane, straight line above and below airfoil trailing edge, and carries out the drafting of aerofoil profile torsion angle, and same
Require identical above and below each design plane of blade；Each section is attached again afterwards, a straight spiral of trailing edge is eventually become
Oar.Increase with reference to the blade of Betz condition optimizings with radius of turn, each section aerofoil profile chord length first increases and then decreases obtains a horse
The leading edge of blade type.Due to straight according to the blade trailing edge of this example Design of Aerodynamic Configuration, therefore tailwater system of its abjection is flushed,
Blade point source of sound can be re-started branch, so as to reduce noise.
Fig. 1 a, Fig. 1 b illustrate the contrast of the blade and conventional blade plane projected shape of the present embodiment.Two oars in figure
It is half side on leaf to correspond to blade leading edge, left side correspondence blade tip.The oar for the present embodiment blade aerodynamic form factor of top in figure
Leaf projection of shape, straight portion is blade trailing edge.Due to determining that straight line is corresponding with each section airfoil trailing edge point in design first, institute
It is straight straightway with its blade trailing edge.Straight trailing edge can play a part of rearrangement blade point source of sound, for reduction
Noise is favourable.The blade of lower section for Conventional pneumatic form factor blade compared with this present embodiment difference it is obvious.
Fig. 2 a, Fig. 2 b illustrate each design of the present embodiment blade aerodynamic form factor and conventional blade aerodynamic configuration form
Plane aerofoil profile assigns the difference of datum line.Top is the aerofoil profile arrangement of the blade aerodynamic form factor of the present embodiment in figure,
Aerofoil profile arrangement is carried out on each design plane so that airfoil trailing edge point is as a reference point.Lower section is then the cloth of conventional blade aerodynamic configuration
Form is put, with progress aerofoil profile arrangement as a reference point at the 30% of the aerofoil profile string of a musical instrument on its design plane, with doing for the present embodiment
Method is completely different.
The propeller progress that certain set has designed completion is chosen in experiment, and blade master data is as follows:
Number of blade:2, diameter of propeller blade:800mm, uses height:6KMm, speed of incoming flow:150Km/h,
Rotating speed:5500RPM, efficiency:>0.60
Each section aerofoil profile data are as follows:
The propeller configuration design scheme of table 1, diameter:800mm, number of blade:2
Using this set blade data, the blade aerodynamic form factor and traditional blade aerodynamic profile of the present embodiment are utilized respectively
Form is drawn, processing and manufacturing blade.Experimental verification is carried out, the propeller blade aerodynamic configuration noise reduction of the present invention is verified.Point
Not in propeller oar disk plane, at 3 times of diameters of oar axle；Blade downstream is with oar axle into 45 degree of angles, and 5 times away from propeller center straight
Footpath Liang Ge positions carry out the aerodynamic numerical simulation of blade, experiment measurement.Measuring state is for ground static state, i.e. speed of incoming flow
0。
Numerical simulation result shows, in propeller oar disk plane, according to the pneumatic of the present embodiment at 3 times of diameters of oar axle
The blade of form factor manufacture, its noise is down to 97dB by the 105dB of traditional, pneumatic profile blade, and the result of ground survey is also obtained
Identical conclusion is arrived；And in blade downstream and oar axle into 45 degree of angles, at 5 times away from propeller center diameters, numerical simulation result
Show that noise is down to 93dB by 96dB.At the same time the pneumatic efficiency of blade has no significant change under two kinds of test modes.
Claims (1)
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| CN201710088817.2A CN106938696B (en) | 2017-02-20 | 2017-02-20 | A kind of sabre type low noise propeller blade design method |
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| CN201710088817.2A CN106938696B (en) | 2017-02-20 | 2017-02-20 | A kind of sabre type low noise propeller blade design method |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108545173A (en) * | 2018-06-25 | 2018-09-18 | 北京小米移动软件有限公司 | Blade, propeller and aircraft |
| CN109693807A (en) * | 2018-12-28 | 2019-04-30 | 西北工业大学 | A kind of adaptive pneumatic variable-pitch propeller design method |
| WO2020024488A1 (en) * | 2018-08-01 | 2020-02-06 | 深圳市道通智能航空技术有限公司 | Propeller, power assembly and unmanned aerial vehicle |
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| US20100092299A1 (en) * | 2008-05-22 | 2010-04-15 | Agusta S.P.A. | Helicopter antitorque tail rotor blade |
| CN102887222A (en) * | 2012-09-18 | 2013-01-23 | 北京理工大学 | Paddle with changeable torsion-angle distribution |
| US20130323043A1 (en) * | 2012-02-27 | 2013-12-05 | Eurocopter | Rotor blade, a rotor, an aircraft, and a method |
| CN105235893A (en) * | 2015-10-27 | 2016-01-13 | 深圳市道通智能航空技术有限公司 | Propeller and aircraft |
| CN205652336U (en) * | 2016-03-29 | 2016-10-19 | 丹东市元宝区飓风螺旋桨厂 | High efficiency low noise power umbrella screw |
| CN106114821A (en) * | 2015-05-27 | 2016-11-16 | 深圳市高巨创新科技开发有限公司 | The method for designing of a kind of aircraft with low noise propeller and propeller configurations |
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Patent Citations (6)
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| US20100092299A1 (en) * | 2008-05-22 | 2010-04-15 | Agusta S.P.A. | Helicopter antitorque tail rotor blade |
| US20130323043A1 (en) * | 2012-02-27 | 2013-12-05 | Eurocopter | Rotor blade, a rotor, an aircraft, and a method |
| CN102887222A (en) * | 2012-09-18 | 2013-01-23 | 北京理工大学 | Paddle with changeable torsion-angle distribution |
| CN106114821A (en) * | 2015-05-27 | 2016-11-16 | 深圳市高巨创新科技开发有限公司 | The method for designing of a kind of aircraft with low noise propeller and propeller configurations |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108545173A (en) * | 2018-06-25 | 2018-09-18 | 北京小米移动软件有限公司 | Blade, propeller and aircraft |
| WO2020024488A1 (en) * | 2018-08-01 | 2020-02-06 | 深圳市道通智能航空技术有限公司 | Propeller, power assembly and unmanned aerial vehicle |
| CN109693807A (en) * | 2018-12-28 | 2019-04-30 | 西北工业大学 | A kind of adaptive pneumatic variable-pitch propeller design method |
| CN109693807B (en) * | 2018-12-28 | 2021-11-09 | 西北工业大学 | Design method of self-adaptive pneumatic variable-pitch propeller |
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Inventor after: Zhang Lin Inventor after: Gong Xiying Inventor after: Tao Yujin Inventor after: Zhang Zijian Inventor after: Liang Chenggang Inventor before: Gong Xiying Inventor before: Tao Yujin Inventor before: Zhang Lin Inventor before: Zhang Zijian Inventor before: Liang Chenggang |
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