CN208123004U - A kind of ellipse blunt trailing edge aerofoil profile - Google Patents
A kind of ellipse blunt trailing edge aerofoil profile Download PDFInfo
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- CN208123004U CN208123004U CN201820179711.3U CN201820179711U CN208123004U CN 208123004 U CN208123004 U CN 208123004U CN 201820179711 U CN201820179711 U CN 201820179711U CN 208123004 U CN208123004 U CN 208123004U
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- aerofoil profile
- trailing edge
- blunt trailing
- aerofoil
- ellipse
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
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Abstract
A kind of ellipse blunt trailing edge aerofoil profile, for about the symmetrical oval blunt trailing edge aerofoil profile of chord length；The relative thickness of the ellipse blunt trailing edge aerofoil profile is 50%；Rear is with a thickness of 27.27% chord length.Maximum relative thickness position is 54.54% chord length away from leading edge point.The blunt trailing edge that the utility model is taken can effectively improve the rigidity of blade, reduce the barometric gradient of airfoil suction side back segment, delay turbulence separation, be conducive to improve the lift coefficient and stall angle of aerofoil profile, and preceding edge roughness sensibility is low, therefore the utility model can be as the substitute for the pneumatic equipment bladess root aerofoil profile being commonly used.
Description
Technical field
The invention belongs to fan blade section Airfoil Design technical fields, and in particular to a kind of to bear compared with big load, lose
The big thickness pneumatic equipment bladess root aerofoil profile that the fast angle of attack is big and preceding edge roughness sensibility is low.
Background technique
With becoming increasingly conspicuous for energy issue of world, wind energy is grown rapidly as environmental-friendly renewable resource,
Blade design is the core technology of fan design, and Blade Properties determine wind energy utilization, load character, noise level etc.,
Middle blade section aerofoil profile is to determine the most important factor of Blade Properties.Therefore high-performance wind mill airfoil design, for improving leaf
Piece Wind energy extraction ability reduces leaf weight and system load important in inhibiting.
Lot of domestic and international mechanism has all carried out the design studies of the advanced family of aerofoil sections of pneumatic equipment bladess, and US and European is successively sent out
The family of aerofoil sections such as S series, DU series, RIS series, FFA series, AH series are put on display, in these aerofoil profiles, part aerofoil profile lacks Gao Lei
Experimental verification under promise number, aerofoil profile aeroperformance decline when compared with large roughness in part is serious, these family of aerofoil sections are both for leaf
The aerofoil profile for the different-thickness that piece is designed from root to tip difference erect-position.In general the index that wind mill airfoil is mainly investigated
There are architectural characteristic, geometry compatibility, aerodynamic characteristic, stalling characteristics and preceding edge roughness sensibility, specifically, architectural characteristic refers to
The ability of load and fatigue is born, geometry compatibility refers in pneumatic equipment bladess from root to the mistake between the different-thickness aerofoil profile of tip
Crossing property, aerodynamic characteristic refer to that the size of the ascending aorta banding and lift resistance ratio of aerofoil profile in blade, stalling characteristics refer to before and after airfoil stall
The situation of change of aerodynamic characteristic, preceding edge roughness sensibility refer to that aerofoil profile leading edge pollutant makes aerofoil profile that turbulence separation occur in advance simultaneously
The amplitude for causing maximum lift coefficient to reduce.For the aerofoil profile of pneumatic equipment bladess root, offer lift should be provided and held again
The load on entire blade is carried on a shoulder pole, therefore the aerofoil profile at this needs good architectural characteristic and geometry is compatible, higher pneumatic
The features such as characteristic, low slow stalling characteristics and the coarse sensibility of leading edge.
Domestic wind mill airfoil design studies are started late, but absorb foreign advanced experience, and development is very fast.Northwest industry is big
Propose in the patent of invention of Patent No. CN2011100023215.1 a kind of wing for blade of megawatt level wind machine
Type discloses aerofoil profile of the family for blade of megawatt level wind machine, altogether includes 7 aerofoil profiles, the phase of the aerofoil profile for root of blade
To with a thickness of 40%, relative thickness is little.
Northwestern Polytechnical University proposes a kind of suitable for 5-10 in the innovation and creation application No. is 201610164779.X
The aerofoil profile of megawatt pneumatic equipment bladess includes 8 aerofoil profiles altogether, and the relative thickness of the transition aerofoil profile for root is 50% and 60%,
Trailing edge has high-lift and high lift-drag ratio, biggish maximum lift system is also possessed under high reynolds number with a thickness of 12% and 15%
Several and lift resistance ratio, but stalling characteristics are general.
Institute of Engineering Thernophysics, Academia Sinica proposes in the innovation and creation application No. is CN201020677153.7
A kind of wind turbine blade airfoil family, application No. is CN201310234549.2] innovation and creation in propose the big thickness of family
Blunt trailing edge wind mill airfoil and its design method are spent, which includes that relative thickness is followed successively by 45%, 50%, 55% and
60%, trailing edge thickness is followed successively by 7%, 9%, 12% and 16% four kinds of aerofoil profiles, is designed to root of blade to replace tradition
Cylindrical structure, to improve Blade Properties, the maximum stall angle of these four aerofoil profiles only has 8 degree.
A kind of thick wing of large scale wind power machine blade is proposed in the innovation and creation application No. is CN201610546194.4
Type race includes altogether 8 aerofoil profiles, and relative thickness is respectively 35%, 40%, 45%, 50%, 55%, 60%, 65% and 70%, tail
Edge thickness is followed successively by 2.8%, 4.5%, 8.0%, 12%, 16%, 20%, 24% and 28%, wherein the wing of relative thickness 35%
Type stall angle is maximum, can achieve 12.5 °, the followed by aerofoil profile of relative thickness 50%, and stall angle is 11.5 °.
Beijing State Electric United Power Technology Co., Ltd mentions in the innovation and creation application No. is CN201310283675.7
The big thickness aerofoil with blunt tail edge blade for having gone out a kind of large fan discloses a root relative thickness of airfoil up to 65%-75%
Pneumatic equipment bladess, for the aerofoil profile trailing edge with a thickness of 25%-35%, stall angle is 10 °.Above-mentioned big thickness wind mill airfoil, by
In having camber or negative load, required precision is higher, and production is difficult, once there is deviation, can generate one to the aeroperformance of aerofoil profile
Fixed influence, and universal stall angle is smaller.
Aeronautical engineering institute of Northwestern Polytechnical University height teacher at prime delivers for 2008 on " Aeronautics Computing Technique " the 3rd phase of volume 38
's《Oval aerofoil profile low speed aerodynamic characteristic research》, the oval aerofoil profile that relative thickness is 16% is had studied, which has symmetrical, bent
The advantage that rate is continuous, production is simple, and relative thickness is bigger, and stall angle is bigger.Pneumatic equipment bladess root aerofoil profile is due to thickness
Spend larger, flowing is usually in the flow separation flow regime of the big angle of attack at this, therefore big stall angle is conducive to wind energy conversion system
The raising of root Airfoil Aerodynamic Performance.But lift coefficient can decline rapidly after pure oval airfoil stall, and it is special not have slow stall
Property, and the aerofoil profile due to thickness it is small, stall angle only has 8 °, and maximum lift coefficient is also smaller.
Summary of the invention
To overcome the stall angle of thick wing type existing in the prior art smaller, and lift system after pure oval airfoil stall
Number can decline rapidly, not have slow stalling characteristics, and maximum lift coefficient also lesser deficiency, the invention proposes a kind of ellipse
Round blunt edge airfoil.
Ellipse blunt trailing edge aerofoil profile proposed by the present invention is symmetrical about chord length；The relative thickness of the ellipse blunt trailing edge aerofoil profile is
50%；Rear is with a thickness of 27.64% chord length.Maximum relative thickness position is 54.54% chord length away from leading edge point.
The ellipse blunt trailing edge aerofoil profile top airfoil yupWith lower aerofoil ydownCoordinate points in dimensionless coordinate system are shown in Table 1.
Coordinate points of the lower aerofoil in dimensionless coordinate system in 1 aerofoil profile of table
In table 1, C is the chord length of aerofoil profile, and x/C indicates the dimensionless abscissa point of aerofoil profile top airfoil or lower aerofoil, yup/ C table
Show the dimensionless ordinate point of top airfoil, ydownThe dimensionless ordinate point of/C expression lower aerofoil.
For the dimensionless coordinate system using leading edge vertex as coordinate origin, string direction is x-axis, and makes the dimensionless coordinate system
Y-axis perpendicular to the x-axis.
The dimensionless two-dimensional coordinate data of oval blunt trailing edge aerofoil profile described in table 1 can make this when zooming in or out
Aerofoil profile keeps shape invariance.When needing to obtain the aerofoil profile of different chord lengths, in table dimensionless x coordinate and y-coordinate multiply respectively
With chord length C, to obtain upper limb areal coordinate (x, the y of the aerofoil profile of different chord lengthsup) and bottom wing areal coordinate
(x,ydown), these coordinate points are connected with B-spline curves can be obtained the aerofoil profile for meeting design requirement.
Compared with prior art, the present invention proposes that aerofoil profile has the following advantages that：
1, the aerofoil profile is oval aerofoil profile, and curvature is smooth, and is blunt trailing edge, and manufacture is substantially reduced from manufacturing process
Difficulty reduces production cost；
2, the aerofoil profile maximum gauge is 50%C, and rear is with a thickness of 27.27%C, and aerofoil section is long-pending, the moment of inertia is larger, can be with
The rigidity for effectively improving blade promotes the structural behaviour of blade, and the U.S. laboratory Sandia is also found under study for action, passes through increase
The thickness of blunt trailing edge aerofoil profile is obviously improved its structural behaviour, can preferably limit the increase of leaf weight, can at most subtract
Weigh 15%；
3, the aerofoil profile has thicker rear, reduces the barometric gradient of airfoil suction side back segment, delays turbulence separation,
Be conducive to improve the lift coefficient and stall angle of aerofoil profile；
4, the preceding edge roughness sensibility of the aerofoil profile is low, and for the pneumatic equipment bladess of field work, leading edge is often stained with
Pollutant can have a significant impact to the aerodynamic characteristic of general aerofoil profile, and the aerofoil profile simulates this state in the position of leading edge 5%C
Rough zone is posted, aerodynamic characteristic is unobvious compared to the variation of original aerofoil profile, and less, aerodynamic characteristic is very steady for maximum lift coefficient variation
It is fixed.
Detailed description of the invention
Fig. 1 is the outline drawing of oval aerofoil profile provided by the invention；
Fig. 2 is the structural schematic diagram of oval aerofoil profile provided by the invention；
Fig. 3 is to twist status diagram for fixed turn in experiment.In figure：
1. leading edge；2. top airfoil；3. lower aerofoil；4. rear；5 rough zones.
Specific embodiment
The present embodiment is a kind of about the symmetrical oval blunt trailing edge aerofoil profile of chord length.
The maximum relative thickness position of the relatively general wind mill airfoil of oval blunt trailing edge aerofoil profile is compared rearward, is made most
Big relative thickness positions are away from 1 vertex of leading edge, 54.54% chord length；Relative thickness is 50%；Rear 4 with a thickness of 27.64% chord length.
In the present embodiment, the chord length C of the ellipse blunt trailing edge aerofoil profile is 0.55m.
The oval blunt trailing edge aerofoil profile is placed in dimensionless coordinate system, the dimensionless coordinate system is using leading edge vertex as coordinate
Origin, string direction is x-axis, and makes the y-axis of the dimensionless coordinate system perpendicular to the x-axis.
The top airfoil 2 and the coordinate points in the dimensionless coordinate system of lower aerofoil 3 of the present embodiment are shown in Table 1.
Coordinate points of the lower aerofoil in dimensionless coordinate system in 1 aerofoil profile of table
In table 1, C is the chord length of aerofoil profile, and x/C indicates the dimensionless abscissa point of aerofoil profile top airfoil or lower aerofoil, yup/ C table
Show the dimensionless ordinate point of top airfoil, ydownThe dimensionless ordinate point of/C expression lower aerofoil.
In order to verify the aerodynamic characteristic of the present embodiment, carried out in the NF-3 low speed dimensional airfoil wind-tunnel of Northwestern Polytechnical University
Experiment.The length of experimental model is 1.6m, and aerofoil profile is the oval blunt trailing edge aerofoil profile of the present embodiment.
The experiment turn to twist and fix naturally turn to twist two kinds under the conditions of, Reynolds number is respectively 1 × 106、2×106、3×106
Under three kinds of different experiments states, heart section beats static pressure tap in a model, has carried out static survey compacting to model and has tested, has been somebody's turn to do
The lift efficiency and stalling characteristics of model.
To aerofoil profile respectively turn to twist and fix naturally turn to twist two kinds of different conditions under to carry out wind tunnel experiment be wind mill airfoil
Traditional experimental method, turning to twist naturally is archetype experimental state, it is fixed turn to twist refer to aerofoil profile top airfoil away from leading edge 5%C,
The experimental state of rough zone 5 is pasted in position of the lower aerofoil away from leading edge 10%C, has the case where pollutant for simulating aerofoil profile leading edge,
As shown in Figure 3.In addition to this, Reynolds number is also the parameter that must be simulated in wind mill airfoil experiment, and Reynolds number is a kind of available
The similar parameter that viscous effects are indicated in dimensionless number and hydrodynamics to characterize fluid situations, is indicated with Re, is defined
For：
Wherein, ρ indicates the density of fluid, and v indicates that the flow velocity of fluid, c indicate aerofoil profile chord length, and μ indicates the viscosity of fluid.
With Reynolds number for 1 × 106Experimental result for, turn the stall angle under the conditions of twisting naturally and be up to 25 degree, it is fixed
Turning the stall angle under the conditions of twisting is 23 degree, and the aerofoil profile is symmetrical about chord length, the stall angle of negative angle also 20 degree with
On, more much bigger than the stall angle of normal thick aerofoil profile, lift coefficient does not also decline rapidly after stall, and stalling characteristics mitigate.It removes
Except this, turning the maximum lift coefficient under the conditions of twisting naturally is 1.403, and the fixed maximum lift coefficient turned under the conditions of twisting is
1.068, the fixed maximum lift coefficient turned under the conditions of twisting has dropped 23.88%, i.e., preceding edge roughness sensibility is 23.88%,
For the aerofoil profile of wind energy conversion system root, preceding edge roughness sensibility is generally less than 25%, therefore, again demonstrates the present invention and is mentioned
The aerofoil profile of confession is low to the sensibility of preceding edge roughness, and aerodynamic characteristic is stablized.
Claims (1)
1. a kind of ellipse blunt trailing edge aerofoil profile, which is characterized in that oval blunt trailing edge aerofoil profile is symmetrical about chord length；The ellipse blunt trailing edge wing
The relative thickness of type is 50%；Rear is with a thickness of 27.64% chord length；Maximum relative thickness position is 54.54% string away from leading edge point
It is long.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820179711.3U CN208123004U (en) | 2018-02-02 | 2018-02-02 | A kind of ellipse blunt trailing edge aerofoil profile |
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| CN201820179711.3U CN208123004U (en) | 2018-02-02 | 2018-02-02 | A kind of ellipse blunt trailing edge aerofoil profile |
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| CN208123004U true CN208123004U (en) | 2018-11-20 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114166486A (en) * | 2021-11-23 | 2022-03-11 | 中国直升机设计研究所 | Loading attack angle adjusting method for fatigue test of helicopter tail rotor blade airfoil section |
| CN114754023A (en) * | 2022-03-28 | 2022-07-15 | 约克广州空调冷冻设备有限公司 | Blade, impeller and backward centrifugal fan |
-
2018
- 2018-02-02 CN CN201820179711.3U patent/CN208123004U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114166486A (en) * | 2021-11-23 | 2022-03-11 | 中国直升机设计研究所 | Loading attack angle adjusting method for fatigue test of helicopter tail rotor blade airfoil section |
| CN114166486B (en) * | 2021-11-23 | 2023-05-23 | 中国直升机设计研究所 | Loading attack angle adjusting method for She Yixing-section fatigue test of helicopter tail rotor |
| CN114754023A (en) * | 2022-03-28 | 2022-07-15 | 约克广州空调冷冻设备有限公司 | Blade, impeller and backward centrifugal fan |
| CN114754023B (en) * | 2022-03-28 | 2024-06-07 | 约克广州空调冷冻设备有限公司 | Blade, impeller and backward centrifugal fan |
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| 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: 20181120 Termination date: 20200202 |