CN203175769U - Thin wing type blade of large-scale fan - Google Patents
Thin wing type blade of large-scale fan Download PDFInfo
- Publication number
- CN203175769U CN203175769U CN2013201419193U CN201320141919U CN203175769U CN 203175769 U CN203175769 U CN 203175769U CN 2013201419193 U CN2013201419193 U CN 2013201419193U CN 201320141919 U CN201320141919 U CN 201320141919U CN 203175769 U CN203175769 U CN 203175769U
- Authority
- CN
- China
- Prior art keywords
- chord length
- maximum
- wing type
- type blade
- distance
- 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 - Lifetime
Links
Images
Classifications
-
- Y02E10/722—
Landscapes
- Wind Motors (AREA)
Abstract
The utility model relates to a thin wing type blade of a large-scale fan. The outer contour of the cross section of a blade tip of the thin wing type blade is a front edge, a tail edge, a suction surface shaped line and a pressure surface shaped line. The distance of the front edge and the tail edge is chord length, the thickness of the end face of the tail edge is 0%-5% of the chord length, and the radius of the front edge is 2.5%-3.5% of the chord length. The maximum thickness of the cross section is 17.5%-18.5% of the chord length, and the distance of the position with the maximum thickness and the front edge is 25%-35% of the chord length. The maximum camber of the cross section is 3.0%-4.0% of the chord length, and the distance of the position with the maximum camber and the front edge is 40%-60% of the chord length. The comprehensive performance of the thin wing type blade is superior to the comprehensive performance of a traditional DU thin wing type blade with the same relative thickness and the comprehensive performance of a traditional NACA thin wing type blade with the same relative thickness, the utilization efficiency of wind power is improved, structural weight is lightened, fatigue loads are lowered, and the thin wing type blade of the large-scale fan becomes an important technical base for developing large-scale high-efficiency low-cost wind machines.
Description
Technical field
The utility model relates to wind power generation field, particularly relates to a kind of thin airfoil blade of large fan.
Background technique
Along with the energy and environmental problem become increasingly conspicuous, abundant, the pollution-free and reproducible wind energy of reserves is subject to people's attention gradually.The core component of wind-powered electricity generation unit-----blade has the aerofoil section of different-thickness and torsional angle distribution, and operational efficiency and the reliability of its airfoil aerodynamic performances and complete machine are closely related.Early stage wind energy conversion system when blade design first-selection be to develop comparative maturity, lifting resistance characteristic aviation aerofoil profile preferably, but the design that facts have proved this class aerofoil profile is not well positioned to meet blower fan design and use requirement, as for the Stall Type wind energy conversion system, can produce too high peak energy and peak load in the stall zone, not only damaged generator, and increased the weight of the load of blade, reduced the life-span of blade, work in the open air for a long time owing to wind energy conversion system simultaneously, be subjected to sand and dust, effect such as raindrop blade surface roughness increases, and the aerofoil profile aeroperformance worsens the energy loss that causes rapidly can reach 20%-30%.
The research work of present domestic wind energy conversion system special airfoil is at the early-stage, domestic partial blade factory can only survey and draw imitated to the fan blade of external production, in default of geometry and the pneumatic performance data of aerofoil profile, directly influenced the autonomous Design level of Chinese large-sized wind energy conversion system.Therefore how to found the new thin airfoil fan blade of a kind of Wind Power Utilization efficient height, lightweight construction, the task of top priority of China's wind energy conversion system development.
The model utility content
The technical problems to be solved in the utility model provides a kind of thin airfoil blade of large fan, its weight attenuating, blower fan combination property is improved, thereby overcome the deficiency that existing structure weight is heavy, wind energy utilization is low.
For solving the problems of the technologies described above, the utility model provides a kind of thin airfoil blade of large fan, the cross section external frame of its tip segment is divided into leading edge, trailing edge, suction surface molded lines and pressure side molded lines, the distance of leading edge and trailing edge is chord length, the end surface thickness of described trailing edge is the 0%-5% of chord length, and the radius of described leading edge is the 2.5%-3.5% of chord length; The maximum ga(u)ge of described cross section is the 17.5%-18.5% of chord length, and the distance of maximum ga(u)ge place and leading edge is the 25%-35% of chord length; The maximum camber of described cross section is the 3.0%-4.0% of chord length, and the distance of maximum camber place and leading edge is the 40%-60% of chord length.
As a kind of improvement of the present utility model, the utility model also can be realized by following proposal:
A kind of thin airfoil blade of large fan, wherein, described maximum ga(u)ge is 18.05% of chord length, the distance of maximum ga(u)ge place and leading edge is 31.3% of chord length, maximum camber is 3.48% of chord length, the distance of maximum camber place and leading edge is 49.2% of chord length, and leading-edge radius is 3.049% of chord length, and the trailing edge end surface thickness is 0.
A kind of thin airfoil blade of large fan, wherein, described pressure side molded lines and suction surface molded lines are Bezier curve.
After adopting such design, the utility model has the following advantages at least:
1, the vane airfoil profile combination property that provides of this programme is better than traditional DU, the NACA aerofoil profile of identical relative thickness, and wherein relative thickness is that 18% aerofoil profile (called after UP18) improves 4% than traditional NACA63618 combination property.
2, new aerofoil profile has not only improved Wind Power Utilization efficient, and has alleviated structure weight, has reduced fatigue load, has become the important technology basis of the large-scale high efficiency, low cost wind energy conversion system of development.
Description of drawings
Above-mentioned only is the general introduction of technical solutions of the utility model, and for can clearer understanding technological means of the present utility model, the utility model is described in further detail below in conjunction with accompanying drawing and embodiment.
Fig. 1 is the leaf tip cross-sectional structure schematic representation of the thin airfoil blade of a kind of large fan of the utility model.
Fig. 2 is the partial enlarged drawing of trailing edge among Fig. 1.
Fig. 3 is the cross section external frame plotted curve of the thin airfoil blade of a kind of large fan of the utility model.
Fig. 4 is the thin airfoil blade of a kind of large fan of the utility model and the lift coefficient comparison diagram of NACA63618.
Fig. 5 is the thin airfoil blade of a kind of large fan of the utility model and the ratio of lift coefficient to drag coefficient comparison diagram of NACA63618.
Embodiment
With reference to Fig. 1, Fig. 2, it is 18% vane airfoil profile (called after UP18) that the utility model provides relative thickness, the leaf tip cross section of the thin airfoil blade of large fan that the utility model provides is made of leading edge 1, trailing edge 2, suction surface molded lines 3 and pressure side molded lines 4, wherein leading edge 1 is circular arc, leading edge 1 is connected with suction surface molded lines 3, pressure side molded lines 4 respectively, the curvature at tie point place is continuous, and suction surface molded lines 3 terminal 11 and pressure side molded lines 4 ends 13 are connected to form trailing edge 2.
At first, the name to each several part among Fig. 1 is called following definition:
1, mean camber line 10: do the incircle of a series of suction surface molded lines 3 and pressure side molded lines 4 in aerofoil profile, the line of these incenters is called the mean camber line 10 of aerofoil profile.
2, chord length: the line of mean camber line 10 rear and front end points is called wing chord, and the length of wing chord is called for short chord length.
3, camber C: the maximum normal distance between mean camber line 10 and the wing chord is called the maximum camber of aerofoil profile, is called for short camber, and it is called relative maximum camber with the ratio of chord length.
4, leading-edge radius: the apothem of the leading edge 1 by aerofoil profile is called leading-edge radius, and it is called relative leading-edge radius with the ratio of chord length.
5, maximum ga(u)ge D: maximum inscribe diameter of a circle is called the maximum ga(u)ge of aerofoil profile in the aerofoil profile incircle, and it is called relative maximum ga(u)ge with the ratio of chord length.
6, maximum ga(u)ge position: be called maximum ga(u)ge position by leading edge point to the distance at maximum ga(u)ge place along wing chord, it is called relative maximum ga(u)ge position with the ratio of chord length.
7, maximum camber position: be called the maximum camber position by leading edge point to the distance of maximum camber place chordwise, it is called relative maximum camber position with the ratio of chord length.
8, the trailing edge end face 12: the line segment that end 13 lines of the end 11 of suction surface molded lines 3 and pressure side molded lines 4 constitute is trailing edge end face 12, and its thickness becomes relative trailing edge end surface thickness with the ratio of chord length.
With reference to shown in Figure 3, pressure side molded lines 4 of the present utility model and suction surface molded lines 3 adopt be the Bezier(shellfish now) curve, the relative thickness of this programme design is that the geometric data of 18% aerofoil profile (UP18) is as follows:
The scope of UP18 each several part parameter value:
Through experimental verification repeatedly, most preferred embodiment data of the present utility model are as follows:
The aerodynamic configuration that can carry out the large scale wind power machine blade according to geometry and the pneumatic performance data of above-mentioned aerofoil profile designs.
The aerodynamic data comparison diagram of UP18 and NACA63618 aerofoil profile sees that with reference to Fig. 4, Fig. 5 the aeroperformance of UP18 obviously is better than traditional NACA aerofoil profile of stack pile as seen from the figure.The main layout of the utility model large scale wind power machine thin airfoil blade is in close blade tip position, this position is the position that blade is mainly exerted oneself, the aerofoil profile of this position of large scale wind power machine blade needs high coefficient of lift combined, high lift-drag ratio, mild stalling characteristics, low roughness receptance, high reynolds number stability, this programme passes through the performance to the mode comprehensive assessment aerofoil profile of above-mentioned index parameter weighting, obtained traditional DU, NACA aerofoil profile that combination property is better than identical relative thickness, the reynolds number range of the aerofoil profile operation that the utility model provides is at 3*10
6To 6*10
6
The above; it only is preferred embodiment of the present utility model; be not that the utility model is done any pro forma restriction, those skilled in the art utilize the technology contents of above-mentioned announcement to make a little simple modification, equivalent variations or modification, all drop in the protection domain of the present utility model.
Claims (3)
1. the thin airfoil blade of a large fan, the cross section external frame of its tip segment is divided into leading edge, trailing edge, suction surface molded lines and pressure side molded lines, and the distance of leading edge and trailing edge is chord length, it is characterized in that:
The end surface thickness of described trailing edge is the 0%-5% of chord length, and the radius of described leading edge is the 2.5%-3.5% of chord length;
The maximum ga(u)ge of described cross section is the 17.5%-18.5% of chord length, and the distance of maximum ga(u)ge place and leading edge is the 25%-35% of chord length;
The maximum camber of described cross section is the 3.0%-4.0% of chord length, and the distance of maximum camber place and leading edge is the 40%-60% of chord length.
2. the thin airfoil blade of a kind of large fan according to claim 1, it is characterized in that: described maximum ga(u)ge is 18.05% of chord length, the distance of maximum ga(u)ge place and leading edge is 31.3% of chord length, maximum camber is 3.48% of chord length, the distance of maximum camber place and leading edge is 49.2% of chord length, leading-edge radius is 3.049% of chord length, and the trailing edge end surface thickness is 0.
3. the thin airfoil blade of a kind of large fan according to claim 1 and 2, it is characterized in that: described pressure side molded lines and suction surface molded lines are Bezier curve.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013201419193U CN203175769U (en) | 2013-03-26 | 2013-03-26 | Thin wing type blade of large-scale fan |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013201419193U CN203175769U (en) | 2013-03-26 | 2013-03-26 | Thin wing type blade of large-scale fan |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203175769U true CN203175769U (en) | 2013-09-04 |
Family
ID=49072476
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2013201419193U Expired - Lifetime CN203175769U (en) | 2013-03-26 | 2013-03-26 | Thin wing type blade of large-scale fan |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203175769U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103133272A (en) * | 2013-03-26 | 2013-06-05 | 国电联合动力技术有限公司 | Thin airfoil type blade of large-scale fan |
| WO2015165140A1 (en) * | 2014-04-29 | 2015-11-05 | 苏州飞能可再生能源科技有限公司 | Vertical-axis wind turbine-dedicated high-efficiency blade |
-
2013
- 2013-03-26 CN CN2013201419193U patent/CN203175769U/en not_active Expired - Lifetime
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103133272A (en) * | 2013-03-26 | 2013-06-05 | 国电联合动力技术有限公司 | Thin airfoil type blade of large-scale fan |
| WO2015165140A1 (en) * | 2014-04-29 | 2015-11-05 | 苏州飞能可再生能源科技有限公司 | Vertical-axis wind turbine-dedicated high-efficiency blade |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102094769B (en) | Wind machine blade airfoil profile capable of controlling flow stalling through standing vortex | |
| CN203374428U (en) | Family of wind-power airfoil profiles with large thickness and blunt trailing edges | |
| CN203383990U (en) | Large-thickness airfoil blade of large fan | |
| CN103133272A (en) | Thin airfoil type blade of large-scale fan | |
| CN102094767B (en) | Airfoil group for megawatt-class wind turbine blade | |
| CN203685493U (en) | Big-thickness blunt trailing edge blade for wind turbine | |
| CN102003332A (en) | Blade airfoil family of wind turbine | |
| CN102444540B (en) | Wind turbine blade aerofoil of horizontal axis wind turbine | |
| CN106089569A (en) | A kind of Miniature Wind Turbine Blades aerofoil profile being applicable to low reynolds number flow | |
| CN102062044B (en) | Wind machine blade airfoil family | |
| CN203362391U (en) | Wind turbine blade with tip vane | |
| CN104863799A (en) | Method for designing wind turbine airfoil by using Bessel function curve | |
| CN203175769U (en) | Thin wing type blade of large-scale fan | |
| CN103306907B (en) | A kind of heavy thickness aerofoil with blunt tail edge blade of large fan | |
| CN203321756U (en) | Medium-thickness airfoil blade for large turbines | |
| CN104018998B (en) | 21%-thickness main airfoil for megawatt wind turbine blade | |
| CN103321856B (en) | A kind of heavy thickness airfoil fan of large fan | |
| CN203175770U (en) | Thin wing type blade of large-scale fan | |
| CN105781904B (en) | 30% thickness aerofoil suitable for megawatt-grade wind turbine blade | |
| CN203321758U (en) | Medium-thickness airfoil blade for large turbines | |
| CN101886619B (en) | Special airfoil for blade tip of wind driven generator | |
| CN203321757U (en) | Medium-thickness airfoil blade for large turbines | |
| CN103133273B (en) | A kind of thin airfoil type blade of large fan | |
| CN103244359B (en) | A kind of intermediate gauge airfoil fan of large fan | |
| CN103244361A (en) | Moderate-thickness airfoil blade of large-scale fan |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20130904 |
|
| CX01 | Expiry of patent term |