CN102011710B - Wind machine blade - Google Patents
Wind machine blade Download PDFInfo
- Publication number
- CN102011710B CN102011710B CN2010105549055A CN201010554905A CN102011710B CN 102011710 B CN102011710 B CN 102011710B CN 2010105549055 A CN2010105549055 A CN 2010105549055A CN 201010554905 A CN201010554905 A CN 201010554905A CN 102011710 B CN102011710 B CN 102011710B
- Authority
- CN
- China
- Prior art keywords
- blade
- circular arc
- pneumatic
- root
- leading edge
- 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.)
- Active
Links
Images
Classifications
-
- Y02E10/722—
Abstract
The invention relates to a wind machine blade, belonging to the field of wind power generation. The wind machine blade comprises a blade front part and a blade back part; the blade front part is the part from the blade tip part to the blade section (12) with the biggest chord length; the blade back part is the part form the blade section (12) with the biggest chord length to the blade root part; the wind machine blade is characterized in that the blade back part comprises a structure component (9) for mounting blade root and bearing loads of the blade and a pneumatic component (10) for capturing wind energy in turn from inner to outer; a cavity is formed between the structure component (9) and the pneumatic component (10); the shape of the pneumatic component (10) is transitioned from the blade section with the biggest chord length to a pneumatic wing section (2) at the blade root; the specific transition form is obtained by lofting each section wing section at front part of the blade and the pneumatic wing section (2) at the blade root. The wind machine blade of the present invention can use the wind energy in a wind wheel fully, improve the use ratio of the wind energy, and increase the generating capacity of the wind machine.
Description
Technical field
The present invention relates to a kind of pneumatic equipment blades made, belong to wind power generation field.
Background technique
Renewable energy sources is the optimal path that solves energy crisis, and wind-power electricity generation be in the renewable energy sources industry development the most rapidly, technology the most ripe, the most wide industry of prospect.China is vast in territory, and wind energy resources is very abundant, and along with continuous progress in science and technology, the Economy of wind-power electricity generation is constantly improved, in addition China the important component part of renewable energy sources as China's energy strategy, wind-power electricity generation has enormous and latent market.
The height of pneumatic equipment blades made pneumatic efficiency has determined the quality of a wind energy conversion system on market, so the design of pneumatic equipment blades made aerodynamic configuration is the wind energy conversion system key for design.Now the large scale wind power machine root of blade of the market mainstream basically all is a cylindrical body, and root of blade all be not utilized in the inner wind energy of wind wheel like this, and cylindrical body also can exert an influence to whole wake flow flow field to radially about 1/5 to locate all be the approximate circle cylinder.All do not pay attention to this problem in the industry at present, think that the root of blade linear velocity is smaller, and the arm of force is also smaller, exerting oneself does not have too big influence.Therefore many people are confined to the middle part and the tip of blade to the optimization of blade, do not remove to consider the root of blade.Utilizing the pneumatic equipment blades made aerodynamic configuration to optimize classical theory is that the result of Glauert theoretical optimization has bigger chord length blade root, but be in structure with consideration on wheel hub is connected, actual blade root employing cylindrical structure, chord length is much smaller than Optimization result.
It is to improve the blade aeroperformance through flow control means that many patents are arranged, as adds wing flap, preceding marginal zone rotating cylindrical body, jet control etc.For present existing pneumatic equipment blades made; The aerodynamic configuration of blade root can be optimized the leeway that can transform in addition; And can great role be arranged, but the at present domestic correlation technique report of also not seeing the raising blade aeroperformance that is directed against the blade root design specially to improving the wind wheel aeroperformance.
Summary of the invention
The purpose of this invention is to provide a kind of wind energy that can make full use of wind wheel inside, improve Wind Power Utilization efficient, increase wind energy conversion system generated energy pneumatic equipment blades made.
A kind of pneumatic equipment blades made is made up of blade front portion and blade rear portion, and the blade front portion is tip segment to blade maximum chord length cross section, and the blade rear portion is blade maximum chord length cross section to leaf root part; It is characterized in that: above-mentioned blade rear portion is made up of with the Pneumatic component that is used for capturing wind energy the interior structure member that is used for the blade root installation and bears blade loading that comprises successively outward; It between said structure parts and the Pneumatic component cavity; The profile of above-mentioned Pneumatic component begins to transit to the pneumatic aerofoil profile of blade root place by blade largest chord strong point, and concrete interim form obtains through anterior each cross section aerofoil profile of blade and the pneumatic aerofoil profile setting-out of blade root.
It is that the Glauert theory obtains that the anterior profile of above-mentioned blade is optimized classical theory according to the pneumatic equipment blades made aerodynamic configuration, can catch wind energy substantially.The structural component design criterion at blade rear portion is to be designed to mainly with blade structure, and the Pneumatic component design criterion is to be main with the blade pneumatic design.Such design can be brought into play the wind energy capturing ability of blade root, can take into account the powerful bearing capacity of blade root again.
A kind of pneumatic equipment blades made is characterized in that: the pneumatic aerofoil profile chord length of the blade root of above-mentioned Pneumatic component is greater than the leaf and root structure chord length of structure member, simultaneously less than the blade maximum chord length; The profile of the pneumatic aerofoil profile of blade root is determined by following mode: the pneumatic aerofoil profile profile of blade root is by forming with 5 tangent tangent arcs of structural type profile, and these 5 circular arcs are defined as under circular arc on the leading edge, leading edge circular arc, the leading edge under circular arc, the trailing edge circular arc on circular arc, the trailing edge successively; Wherein circular arc and structural type cylindrical inscribe on the leading edge; Circular arc and structural type cylindrical inscribe under the leading edge; Circular arc inscribe all under circular arc and the leading edge on leading edge circular arc and the leading edge, the center of circle of circular arc is on crossing the structural type center of circle and becoming 60 ° straight line with the neutral line, with structural type cylindrical inscribe on the trailing edge; The center of circle of circular arc is on crossing the structural type center of circle and becoming-45 ° straight line with the neutral line under the trailing edge, and is circumscribed with the structural type cylindrical; The above-mentioned neutral line referred to the structural type center of circle, and perpendicular to the circle center line connecting of circular arc under circular arc on the leading edge and the leading edge; Circular arc dovetail place formation trailing edge thickness on circular arc and the trailing edge under the above-mentioned trailing edge, trailing edge thickness is 0.5%～1% of structural type diameter; The relative thickness of the pneumatic aerofoil profile of above-mentioned blade root is less than 100%.
The shape of the pneumatic aerofoil profile of blade root and general thick wing type are similar, and the nonsymmetry of upper and lower surfaces shape produces camber, improve aeroperformance.The tangent connection of 5 arcuate surface has guaranteed the continuity of surface configuration radius of curvature, and the trailing edge home position of circular arc up and down can change, and above-mentioned position is worth as a reference, guarantee that aerofoil profile has camber.Relative thickness is decided according to actual wind field situation, and the pneumatic relative thickness of airfoil of wind field blade root that annual mean wind speed is bigger is big, otherwise then relative thickness is little.Trailing edge thickness is that blade top and bottom trailing edge will inevitably produce thickness when bonding by the decision of the technology of actual production, and the aerofoil profile of thick trailing edge can be good than the airfoil performance of fine stern edge.General blade root all is circular, and blade rear portion major part be cylinder, and when wind wheel rotated, wind energy can not be caught in the blade rear portion, and in the blade wake district output vortex street, the destruction flow field.Adopt the Pneumatic component of the pneumatic aerofoil profile of blade root can catch wind energy, power coefficient is provided, can improve the flow field again.
Said structure parts and blade front portion can be an integral body; Pneumatic component is fixedly connected with structure member and blade front portion in blade largest chord strong point then.Like this simple in structure, and be easy to realize.The integrity that structure member and blade are anterior has guaranteed the continuous of blade power transmission, satisfies structural design criterion.Pneumatic component affixes on the structure member after profile is confirmed to make separately and blade front portion and jointing place, rear portion (being the largest chord strong point).
The leaf and root structure aerofoil profile of said structure parts can be radius and the consistent circle of blade root flange radius.This combination is convenient to install.
Application area of the present invention is wider.Can be when Blade Design blade anterior take all factors into consideration with the rear portion design; Also can be on the basis of existing cylinder blade root type blade; Design the Pneumatic component at blade rear portion separately; Then Pneumatic component is affixed on the existing blade, i.e. the present invention can transform existing blade, improves the aeroperformance of blade.
Description of drawings
Fig. 1 is an embodiment of the invention blade root aerofoil profile schematic representation.
Fig. 2 is an embodiment of the invention front view.
Fig. 3 is an embodiment of the invention front elevation.
Fig. 4 utilizes the embodiments of the invention blade and the power coefficient of general blade to compare.
Fig. 5 utilizes the embodiments of the invention blade and the thrust coefficient of general blade to compare.
Embodiment
Fig. 1～Fig. 5 is the shape and the performance of one embodiment of the invention blade.This length of blade is 41 meters, rated power 1500kW, and blade maximum chord length position is apart from 7.5 meters of blade roots, and the blade root flange diameter is 1.89 meters.
With reference to Fig. 1, be this embodiment's blade root aerofoil profile, the blade root aerofoil profile is made up of structural type 1 and the pneumatic aerofoil profile 2 of blade root.Structural type 1 is that radius is the circle of R, and R confirms that by the radius of blade root adpting flange structural type 1 is connected through bolt with flange.The pneumatic aerofoil profile 2 of blade root is made up of the part profile of structural type 1,5 tangent arcs and trailing edge thickness 8, and 5 tangent arcs are respectively under circular arc 3 on the leading edge, leading edge circular arc 4, the leading edge on circular arc 5, the trailing edge circular arc 7 under the circular arc 6 and trailing edge.2/5R place under structural type 1 center of circle, the circular arc center of circle of circular arc 3 on the leading edge, radius of arc is 7/5R, with structural type 1 cylindrical inscribe.1/2R place directly over structural type 1 center of circle, the circular arc center of circle of circular arc 5 under the leading edge, radius of arc is 3/2R, with structural type 1 cylindrical inscribe.Circular arc 5 inscribe all under circular arc 3 and the leading edge on leading edge circular arc 4 and the leading edge, radius is 1/2R.The center of circle of circular arc 6 is on crossing structural type 1 center of circle and becoming 60 ° straight line with the neutral line on the trailing edge, and radius is 4R, with structural type 1 cylindrical inscribe.The center of circle of circular arc 7 is on crossing structural type 1 center of circle and becoming-45 ° straight line with the neutral line under the trailing edge, and radius is 2R, and is circumscribed with structural type 1 cylindrical.8 of trailing edge thickness are vertical, and thickness is 0.5%～1% of structural type 1 diameter.This embodiment blade root aerofoil profile air-driven type chord length is 2.83 meters, and relative thickness is 66.7%.
With reference to Fig. 2, be the front view of this embodiment's blade.Part in the middle of blade root and the blade maximum chord length cross section is divided into structure member 9 and Pneumatic component 10.Structure member 9 is a cylindrical section at preceding 0.5 meter (11 places, blade root to cross section), is used for imbedding bolt, and cross section 11 sectional shape backward obtains with blade maximum chord length cross section 12 (blade largest chord strong point) each cross section aerofoil profile setting-out backward through circular.Pneumatic component 10 is to obtain through blade root air-driven type and blade maximum chord length cross section 12 each cross section aerofoil profile setting-out backward.The leaf and root structure type partly is the main bearing part of blade, is one with blade tip in leaf and root structure type part and the leaf, does as a whole manufacturing and obtains.The blade root air-driven type partly is to make separately according to the profile that has designed, and pastes on the structure member it and 12 places, blade maximum chord length cross section then.
With reference to Fig. 3, be the front elevation (seeing) of this embodiment's blade from blade root toward blade tip, blade maximum chord length cross section (12) is apart from 7.5 meters of blade root.Form a cavity in the middle of air-driven type and the structural type.
With reference to Fig. 4, for utilizing the comparison of the present invention embodiment's blade that designs and the general blade power coefficient that does not utilize the present invention to design.Thus it is clear that, utilize the power coefficient of the blade that the present invention designs to improve greatly.Particularly when big tip speed ratio (low wind speed), power coefficient has more significantly to be increased, this just frequently corresponding to the high wind of the whole year, so annual electricity generating capacity also can obviously increase.
With reference to Fig. 5, for utilizing the comparison of the present invention embodiment's blade that designs and the general blade thrust coefficient that does not utilize the present invention to design, blade is identical with above-mentioned blade.After the wind power utilization coefficient improved, thrust coefficient did not but increase, and thrust coefficient slightly reduces when big tip speed ratio (low wind speed).
Claims (1)
1. a pneumatic equipment blades made is made up of blade front portion and blade rear portion, and the blade front portion is tip segment to blade maximum chord length cross section (12), and the blade rear portion is blade maximum chord length cross section (12) to leaf root part; Above-mentioned blade rear portion comprises successively outward that by interior being used for the Pneumatic component (10) that blade root installs and bear the structure member (9) of blade loading and be used for capturing wind energy forms; Between said structure parts (9) and the Pneumatic component (10) is cavity;
It is characterized in that: the profile of above-mentioned Pneumatic component (10) begins to transit to the pneumatic aerofoil profile of blade root (2) by blade largest chord strong point to be located, and concrete interim form obtains through anterior each cross section aerofoil profile of blade and the pneumatic aerofoil profile of blade root (2) setting-out;
The pneumatic aerofoil profile of blade root (2) chord length of above-mentioned Pneumatic component (10) is greater than the leaf and root structure chord length of structure member, simultaneously less than the blade maximum chord length;
The profile of the pneumatic aerofoil profile of above-mentioned blade root (2) is determined by following mode:
The pneumatic aerofoil profile profile of blade root is by forming with 5 tangent tangent arcs of structural type profile, and these 5 circular arcs are defined as under circular arc on the leading edge (3), leading edge circular arc (4), the leading edge under circular arc (5), the trailing edge circular arc (6) on circular arc (7), the trailing edge successively;
Wherein circular arc (3) and structural type (1) cylindrical inscribe on the leading edge; Circular arc under the leading edge (5) and structural type (1) cylindrical inscribe; Circular arc (5) inscribe all under circular arc (3) and the leading edge on leading edge circular arc (4) and the leading edge; The center of circle of circular arc on the trailing edge (6) is on crossing structural type (1) center of circle and becoming 60 ° straight line with the neutral line; With structural type (1) cylindrical inscribe, the center of circle of circular arc under the trailing edge (7) circular arc is on crossing structural type (1) center of circle and becoming-45 ° straight line with the neutral line, and is circumscribed with structural type (1) cylindrical; The above-mentioned neutral line referred to the structural type center of circle, and perpendicular to the circle center line connecting of circular arc (5) under circular arc on the leading edge (3) and the leading edge;
Circular arc (6) joining place forms trailing edge thickness (8) on circular arc under the above-mentioned trailing edge (7) and the trailing edge, and trailing edge thickness (8) is 0.5%～1% of structural type (1) diameter;
The relative thickness of the pneumatic aerofoil profile of above-mentioned blade root (2) is less than 100%.
2.According to the described a kind of pneumatic equipment blades made of claim 1, it is characterized in that:
Said structure parts (9) and blade front portion are an integral body; Above-mentioned Pneumatic component (10) is fixedly connected with structure member (9) and blade front portion in blade largest chord strong point.
3.A kind of pneumatic equipment blades made according to claim 1 is characterized in that:
The leaf and root structure type (1) of said structure parts (9) is radius and the consistent circle of blade root flange radius.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010105549055A CN102011710B (en) | 2010-11-23 | 2010-11-23 | Wind machine blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010105549055A CN102011710B (en) | 2010-11-23 | 2010-11-23 | Wind machine blade |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102011710A CN102011710A (en) | 2011-04-13 |
| CN102011710B true CN102011710B (en) | 2012-07-18 |
Family
ID=43842005
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010105549055A Active CN102011710B (en) | 2010-11-23 | 2010-11-23 | Wind machine blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102011710B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103629056B (en) * | 2013-12-23 | 2017-01-04 | 北京天源科创风电技术有限责任公司 | A kind of fan blade and use the blower fan of this blade |
| CN110439743B (en) * | 2019-09-10 | 2021-01-19 | 上海电气风电集团股份有限公司 | Sectional blade of wind turbine |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2869370Y (en) * | 2006-01-20 | 2007-02-14 | 陈向阳 | Wind wheel blade for small-sized wind mill generator |
| CN101300419A (en) * | 2005-10-17 | 2008-11-05 | Lm玻璃纤维制品有限公司 | Blade for a wind turbine rotor |
| EP2187045A1 (en) * | 2007-11-19 | 2010-05-19 | Mitsubishi Heavy Industries, Ltd. | Windmill blade and wind power generator using same |
| CN101737249A (en) * | 2009-12-25 | 2010-06-16 | 阳江市新力工业有限公司 | Wind power blade |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2107235A1 (en) * | 2008-04-02 | 2009-10-07 | Lm Glasfiber A/S | A wind turbine blade with an auxiliary airfoil |
-
2010
- 2010-11-23 CN CN2010105549055A patent/CN102011710B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101300419A (en) * | 2005-10-17 | 2008-11-05 | Lm玻璃纤维制品有限公司 | Blade for a wind turbine rotor |
| CN2869370Y (en) * | 2006-01-20 | 2007-02-14 | 陈向阳 | Wind wheel blade for small-sized wind mill generator |
| EP2187045A1 (en) * | 2007-11-19 | 2010-05-19 | Mitsubishi Heavy Industries, Ltd. | Windmill blade and wind power generator using same |
| CN101737249A (en) * | 2009-12-25 | 2010-06-16 | 阳江市新力工业有限公司 | Wind power blade |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102011710A (en) | 2011-04-13 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN201433856Y (en) | Combined wind driven generator | |
| CN202811194U (en) | Vertical-axis wind turbine blade | |
| CN102011710B (en) | Wind machine blade | |
| AU2011213426A1 (en) | High-efficiency high-power vertical axis wind generator | |
| CN201593480U (en) | Wind turbine blade | |
| CN201635926U (en) | Device for vertical axis wind-driven generator device | |
| CN101560956A (en) | Blade shape-adjustable lift-type wind power generation device | |
| CN105697229A (en) | Blade for vertical axis wind turbine | |
| CN106894948A (en) | Based on bionic vertical axis windmill | |
| CN104033332A (en) | Vertical-axis wind power generation device | |
| CN101571102B (en) | Root adjustable horizontal shaft wind-power blade | |
| CN104214043A (en) | Low-speed-start efficient composite vertical-axis fan wind wheel system capable of providing lift force | |
| CN107859593A (en) | Coupled mode vertical axis aerogenerator and its electricity-generating method | |
| CN104033333A (en) | Point and pocket type fan blades and automatic swing device enabling vertical shaft windmill to be efficient | |
| CN202250596U (en) | Blade of vertical axis wind generator | |
| CN202991343U (en) | Fan blade of vertical-axis wind turbine | |
| CN203441675U (en) | Blade of novel horizontal-axis wind turbine | |
| CN201155424Y (en) | Cross axis wind motor with S -type blade tip winglet | |
| CN207526636U (en) | Coupled mode vertical axis aerogenerator | |
| CN101498275A (en) | Horizontal axle wind mill with S blade tip winglet | |
| CN201461230U (en) | Vertical shaft wind-driven generator blade | |
| CN201396234Y (en) | Super-low specific rotational speed mixed-flow type hydraulic turbine runner dedicated for driving cooling tower fan | |
| CN201650576U (en) | Tidal flow generating device | |
| CN201953577U (en) | Combined wing type fan blade | |
| CN202250643U (en) | Novel wind wheel structure of large scale wind turbine generator system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| ASS | Succession or assignment of patent right |
Owner name: JIANGSU LIVON AUTOMOBILE COMPONENTS TECHNOLOGY CO. Free format text: FORMER OWNER: NANJING UNIVERSITY OF AERONAUTICS AND ASTRONAUTICS Effective date: 20130121 |
|
| C41 | Transfer of patent application or patent right or utility model | ||
| COR | Change of bibliographic data |
Free format text: CORRECT: ADDRESS; FROM: 210016 NANJING, JIANGSU PROVINCE TO: 211178 NANJING, JIANGSU PROVINCE |
|
| TR01 | Transfer of patent right |
Effective date of registration: 20130121 Address after: Jiangning District of Nanjing City, Jiangsu province 211178 Binjiang Development Zone, Jin Road No. 9 Patentee after: Jiangsu Livon Automobile Components Technology Co., Ltd. Address before: Yudaojie Baixia District of Nanjing City, Jiangsu Province, No. 29 210016 Patentee before: Nanjing University of Aeronautics and Astronautics |