CN103629055B - A kind of dismountable pneumatic equipment blades made and assembly method thereof - Google Patents
A kind of dismountable pneumatic equipment blades made and assembly method thereof Download PDFInfo
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- CN103629055B CN103629055B CN201310690643.9A CN201310690643A CN103629055B CN 103629055 B CN103629055 B CN 103629055B CN 201310690643 A CN201310690643 A CN 201310690643A CN 103629055 B CN103629055 B CN 103629055B
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Abstract
The present invention discloses a kind of demountable pneumatic equipment blades made and assembly method thereof, this type blade adopts clamping bolt to connect main bearing beam cap, sizing wing plate, front/trailing edge bearing beam skeletal structure, flexible covering aerodynamic configuration, the structure of the blade that achieve and the efficiency utilization of material complete with the formation of sizing wing plate is connected by outstanding rope tensioning.The blade of this structural type has detachably, convenient transport, can Assembling convenient, structure efficiency is high, safeguards simple, has broad application prospects and stronger structure designability.
Description
Technical field
The present invention relates to a kind of blade of wind-driven generator, particularly relate to a kind of dismountable blade and assembly method thereof, belong to the component of wind power plant.
Background technique
Along with the minimizing of fossil energy, renewable energy sources becomes more and more important, will progressively become the main power in future source of energy structure, it is lower that wind energy has development cost as a part of renewable energy sources, technology maturation, the advantage such as widely distributed, becomes the emphasis of Renewable Energy Development in recent years.Along with the continuous progress of technology, wind energy conversion system also progressively moves towards to maximize, and its length of blade also constantly increases, and the rugged ridge of some physical features or the sea often, place that wind-resources is abundant, traffic is severe, and transporting blade is quite difficult, safeguards not easily.
Current wind machine blade generally adopts fibre reinforced composites manufacture, and composite material blade produce to environment and technological requirement harsh especially, a lot of wind energy turbine set is all in the serious or humidity of nearly dust storm, place that salinity is very high.In such a case, the pneumatic equipment blades made quality of production is difficult to control, and the super sized type pneumatic equipment blades made in future can use carbon fiber, this material to technique and environment more responsive.Compare traditional most of metallic material, composite material price is relatively costly, reclaim difficulty, composite material once-through pneumatic equipment blades made out has the continuity of good structure, but to factory installation condition, technical merit proposes higher requirement, there is larger operational risk in one-shot forming technique, whole blade rejection is very likely caused once go wrong, when length of blade is to certain limit, traditional integral blade is in production, also there is many deficiencies in transport and installation and maintenance process, thus, variety of problems is there is in order to solve blade maximization, adopt detachable pneumatic equipment blades made, by main for the pneumatic equipment blades made of complexity load-carrying member in original plant produced, dispersion transport, Assembling is the effective ways solving wind energy conversion system maximization.
This dismountable blade has the advantages that to break the whole up into parts, for situation and the required function had of blade different parts bearing load, optimize the combination of materials and structures, realize that blade structure is lighter, cost is lower, transport, safeguard object more easily, this blade adopts metal or the composite material of high strength and rigidity in the position that stand under load is maximum, lightweight, flexible composite shell or cloth covering is used at the covering position of bearing local blast, both can save manufacture cost, and effectively can alleviate again leaf weight, reduce blade loading.Therefore, detachable pneumatic equipment blades made can fundamentally solve current large scale wind power machine composite material blade technological problems, reduce cost of transportation and maintenance difficulties.Contribute to wind energy industry development and technological progress.
Summary of the invention
For the above-mentioned shortcoming and defect of prior art, technical problem to be solved by this invention is to provide a kind of portable construction, structural reliability is high, designability is strong, manufacture, the simple pneumatic equipment blades made of transportation, installation, maintenance and assembly connection method thereof.
According to an aspect of the present invention, the technological scheme that the present invention takes for its technical problem of solution is: a kind of dismountable pneumatic equipment blades made, comprise blade framework structure and covering, it is characterized in that, described covering is flexible covering, described blade framework structure comprises along blade exhibition to spaced apart at least two sizing wing plates and the main bearing beam cap that is arranged on described sizing wing plate, leading edge bearing beam and trailing edge bearing beam, described main bearing beam cap is assemblied on blade sizing wing plate, lower slotting position, and respectively at least arrange main bearing beam cap described at the suction surface of blade and pressure side, described leading edge bearing beam is assemblied in leading edge bearing beam position of opening on blade sizing wing plate, described trailing edge bearing beam is assemblied in trailing edge bearing beam position of opening on blade sizing wing plate, described covering is connected on described sizing wing plate by the tensioning of outstanding rope.
Preferably, described main bearing beam cap, leading edge bearing beam and trailing edge bearing beam are assemblied on described sizing wing plate by fastening piece.Preferably, described fastening piece is clamping bolt.Preferably, described clamping bolt is corrosion resistant metal bolt, can adopt hex head bolt, also can adopt countersunk screw to keep blade conformity aerodynamic configuration.Preferably, each described sizing wing plate is arranged row or multiple row clamping bolt assemble leading edge bearing beam, trailing edge bearing beam, main bearing beam cap.Preferably, described clamping bolt arrangement mode can also can be staggered side by side.
Preferably, described main bearing beam cap be along blade exhibition to variable cross section size continuous beam, its sectional dimension can be determined according to the local load of blade, structure/material property, in order to meet consistent aerodynamic configuration, its outer surface pressure side and suction surface processing meet the requirement of blade integral aerodynamic configuration physical dimension.
Preferably, described main bearing beam cap can be one group on blade, and namely pressure side and each main bearing beam cap of suction surface, also can be many groups.Its sectional shape is stepped shaft, also can be simple rectangular or trapezoidal.
Preferably, the local that described main bearing beam cap is being connected with each sizing wing plate is equipped with tapped through hole, fastening with sizing wing plate by bolt.
Preferably, the cross-sectional geometry of described sizing wing plate is T-shaped, also can be the shapes such as I-shaped, box-shaped; There is a vertical interior edge face in described sizing wing plate, for improving its strength and stability, its surface, outside pressure face and suction surface surface meet blade aerodynamic shape requirement, simultaneously for being connected with main bearing beam cap, facilitate the use bolton of leading edge bearing beam and trailing edge bearing beam.Implementation structure load is from sizing wing plate to the transmission of main bearing beam cap, leading edge bearing beam, trailing edge bearing beam.
Preferably, described sizing wing plate is slotted for being connected main bearing beam cap along blade exhibition to being respectively equipped with suction surface at pressure side, leading edge locus be provided with along blade exhibition to perforate for connecting leading edge bearing beam, be provided with in trailing edge position along blade exhibition to perforate for connecting trailing edge bearing beam.
Preferably, described sizing wing plate is provided with threaded hole in leading edge, trailing edge is provided with threaded hole, pressure side and suction surface are provided with threaded hole, and its axially bored line direction is all parallel to the Normal direction of the local aerofoil profile of blade.
Preferably, described leading edge bearing beam and trailing edge bearing beam are circular cross-section beam, can be square or trapezoidal uniform beam, and described leading edge bearing beam and trailing edge bearing beam are along exhibition to being non-uniform beam, its sectional dimension can be determined according to the local load of blade, structure/material property.
Preferably, described skins front edges be positioned at chord of blade to leading edge locus, and blade exhibition to two sizing wing plates between positions, described trailing edge covering be positioned at chord of blade to trailing edge position, and blade exhibition to two sizing wing plates between positions.
Preferably, described covering is flexible material, can be the flexible thin-walled skin such as corrosion-resistant, high-strength cloth or composite material.Adopt this kind of material can alleviate weight, the reduction blade cost of blade to greatest extent.
Preferably, described covering by high tensile flexible hang rope by sizing wing plate on perforate be connected to sizing wing plate on.Realize Aerodynamic force from covering to the transmission of sizing wing plate.
Preferably, the described outstanding rope for connecting covering and sizing wing plate also can use rivet or bonding connection to realize substituting.
According to an aspect of the present invention, present invention also offers the assembly method of above-mentioned detachable blade, it is characterized in that, comprise following installation step:
(1) manufacture blade each several part assembly respectively, surface anticorrosive process or coating process carried out to assembly, and partial pressure face and suction surface the roughness process on surface, the aerodynamic configuration making it to meet design requires and matching requirements;
(2) according to designing requirement, sizing wing plate is placed in each exhibition to position, the placing height of adjustment sizing wing plate and chordwise location;
(3) leading edge bearing beam is packed into each sizing wing plate along exhibition to order, with leading edge clamping bolt pretension, tentatively fixing; Use the same method and trailing edge bearing beam is assembled on each sizing wing plate, adopt similar approach to be assembled to by main bearing beam cap on each sizing wing plate;
(4) clamping bolt, leading edge bearing beam clamping bolt, the trailing edge bearing beam clamping bolt of main bearing beam cap are tightened in classification in order (3-5 level);
(5) packed into respectively in order by the outstanding rope on covering in the perforate of sizing wing plate, adjustment, alignment posttension taut envelope fix outstanding rope;
(6) according to design screw-down torque, check each parts connecting bolt Tightening moment, so far namely the detachable blade of wind energy conversion system installs;
(7) when needs dismounting blade, then according to the contrary dismounting realizing blade smoothly, the assembling of parts, replacing, maintenance and recovery is completed.
With prior art contrast, the detachable blade of wind energy conversion system of the present invention and assembly method thereof have following significant technique effect:
1, the detachable blade of wind energy conversion system of the present invention can realize the dispersion manufacture of pneumatic equipment blades made, transport and Assembling, greatly reduces transport and manufacture difficulty.
2, the detachable blade of wind energy conversion system of the present invention is independently manufactured according to parts, compares conventional composite materials integral blade, significantly reduces vane manufacturing to the requirement of factory condition, number quality and technical difficulty and manufacture risk.
3, the rigidity that the detachable blade of wind energy conversion system of the present invention adopts metal or high-strength composite material main bearing beam cap, leading edge bearing beam, trailing edge bearing beam significantly can promote blade, avoids the interference between blade and pylon.
4, the detachable blade of wind energy conversion system of the present invention courageously adopts lightweight, flexible cloth covering or shell composite material skin obviously can reduce the weight of blade.
5, the detachable blade of wind energy conversion system of the present invention adopts steel sizing wing plate, and ratio of rigidity composite material is large, can better ensure the aerodynamic configuration of blade.
6, the thinking of the detachable blade of wind energy conversion system of the present invention combines blade structure and function is considered, and can adopt the component of multiple material, various ways, considerably increase the designability of blade, simultaneously also for follow-up improvement, improve and reserved space.
Accompanying drawing explanation
Fig. 1. patent of the present invention detachable blade wing panel partial view;
Fig. 2. wing panel partial top view;
Fig. 3 wing panel partial elevation view;
Fig. 4 wing panel part sectioned view;
Fig. 5 shapes wing plate front view;
Fig. 6 main bearing beam cap cross section geometric appearance schematic diagram.
Embodiment
For making object of the present invention, technological scheme and advantage clearly understand, to develop simultaneously embodiment referring to accompanying drawing, the present invention is described in more detail.
As shown in Figure 1, dismountable pneumatic equipment blades made of the present invention, comprise blade framework structure and covering 2, described covering 2 is flexible covering, described blade framework structure comprises along blade exhibition to spaced apart at least two sizing wing plates 3 and the main bearing beam cap 1 that is arranged on described sizing wing plate 3, leading edge bearing beam 5 and trailing edge bearing beam 6, described main bearing beam cap 1 is assemblied on blade sizing wing plate 3, lower fluting 21 position, and respectively at least arrange main bearing beam cap 1 described at the suction surface of blade and pressure side, described leading edge bearing beam 5 is assemblied in leading edge bearing beam perforate 16 position on blade sizing wing plate 3, described trailing edge bearing beam 6 is assemblied in trailing edge bearing beam perforate 17 position on blade sizing wing plate 3, described covering 2 is connected on described sizing wing plate 3 by the tensioning of outstanding rope.
As Figure 1-4, described main bearing beam cap 1, leading edge bearing beam 5 and trailing edge bearing beam 6 are assemblied on described sizing wing plate 3 by fastening piece 4.Described fastening piece 4 is preferably clamping bolt.Preferably, described clamping bolt 4a, 4b, 4c are corrosion resistant metal bolt, can adopt hex head bolt, also can adopt countersunk screw to keep blade conformity aerodynamic configuration.Preferably, each described sizing wing plate 3 is arranged row or a multiple row clamping bolt 4a, 4b, 4c assemble leading edge bearing beam 5, trailing edge bearing beam 6, main bearing beam cap 1.Preferably, described clamping bolt 4a, 4b, 4c arrangement mode can also can be staggered side by side.
Preferably, described main bearing beam cap 1 be along blade exhibition to 25 variable cross section size continuous beam, its sectional dimension can be determined according to the local load of blade, structure/material property, in order to meet consistent aerodynamic configuration, its outer surface pressure side 23 and suction surface 24 processing meet the requirement of blade integral aerodynamic configuration physical dimension.
As shown in Figure 6, described main bearing beam cap 1 can be one group on blade, and namely pressure side 23 and each main bearing beam cap 1 of suction surface 24, also can be many groups.Its cross section 10 shape is ladder-type, also can be simple rectangular or trapezoidal.Preferably, the local that described main bearing beam cap 1 is being connected with each sizing wing plate 3 is equipped with tapped through hole 19, fastening with sizing wing plate 3 by bolt 4a.
As shown in Figure 5, the cross-sectional geometry of described sizing wing plate 3 is T-shaped, also can be the shapes such as I-shaped, box-shaped; There is a vertical interior edge face 15 in described sizing wing plate 3, for improving its strength and stability, its surface, outside pressure face 23 and suction surface surface 24 meet blade aerodynamic shape requirement, simultaneously for being connected with main bearing beam cap 1, facilitate use bolt 4b, 4c of leading edge bearing beam 5 and trailing edge bearing beam 6 fastening.Implementation structure load is from the transmission of sizing wing plate 3 to main bearing beam cap 1, leading edge bearing beam 5, trailing edge bearing beam 6.Preferably, described sizing wing plate 3 is respectively equipped with fluting 21 for be connected main bearing beam cap 1 along blade exhibition to 25 with suction surface at pressure side, leading edge 13 position be provided with along blade exhibition to 25 perforate 16 for connecting leading edge bearing beam 5, be provided with in trailing edge 14 position along blade exhibition to 25 perforate 17 for connecting trailing edge bearing beam 6.Preferably, described sizing wing plate 3 is provided with threaded hole 18 in leading edge 13, trailing edge 14 is provided with threaded hole 17, pressure side 23 and suction surface 24 are provided with threaded hole 19, and its axially bored line direction is all parallel to the Normal direction of the local aerofoil profile of blade.
As shown in Figure 1, 2, described leading edge bearing beam 5 and trailing edge bearing beam 6 are circular cross-section beam, it can be square or trapezoidal uniform beam, and described leading edge bearing beam 5 and trailing edge bearing beam 6 are non-uniform beam along exhibition to 25, its sectional dimension can be determined according to the local load of blade, structure/material property.
As shown in Figure 1, described skins front edges 2a is positioned at leading edge 13 position of chord of blade to 26, and blade exhibition is to the positions between 25 two sizing wing plates 3, described trailing edge covering 2a is positioned at trailing edge 13 position of chord of blade to 26, and the positions between two sizing wing plates 3 of blade exhibition to 25.Preferably, described covering 2 is flexible material, can be the flexible thin-walled skin such as corrosion-resistant, high-strength cloth or composite material.Adopt this kind of material can alleviate weight, the reduction blade cost of blade to greatest extent.Preferably, described covering 2 is hanged rope 8 by high tensile flexible and is connected on sizing wing plate 3 by the perforate 7 on sizing wing plate 3.Realize Aerodynamic force from covering 2 to the transmission of sizing wing plate 3.Preferably, the described outstanding rope 8 for connecting covering 2 and sizing wing plate 3 also can use rivet or bonding connection to realize substituting.
According to an aspect of the present invention, present invention also offers the assembly method of above-mentioned detachable blade, it is characterized in that, comprise following installation step:
(1) manufacture blade each several part assembly respectively, surface anticorrosive process or coating process carried out to assembly, and partial pressure face and suction surface the roughness process on surface, the aerodynamic configuration making it to meet design requires and matching requirements;
(2) according to designing requirement, sizing wing plate is placed in each exhibition to position, the placing height of adjustment sizing wing plate and chordwise location;
(3) leading edge bearing beam is packed into each sizing wing plate along exhibition to order, with leading edge clamping bolt pretension, tentatively fixing; Use the same method and trailing edge bearing beam is assembled on each sizing wing plate, adopt similar approach to be assembled to by main bearing beam cap on each sizing wing plate;
(4) clamping bolt, leading edge bearing beam clamping bolt, the trailing edge bearing beam clamping bolt of main bearing beam cap are tightened in classification in order (3-5 level);
(5) packed into respectively in order by the outstanding rope on covering in the perforate of sizing wing plate, adjustment, alignment posttension taut envelope fix outstanding rope;
(6) according to design screw-down torque, check each parts connecting bolt Tightening moment, so far namely the detachable blade of wind energy conversion system installs;
(7) when needs dismounting blade, then according to the contrary dismounting realizing blade smoothly, the assembling of parts, replacing, maintenance and recovery is completed.
The foregoing is only preferred embodiment of the present invention, not in order to limit the present invention, within the spirit and principles in the present invention all, any amendment made, equivalent replacement, improvement etc., all should be included within the scope of the present invention.
Claims (12)
1. a dismountable pneumatic equipment blades made, comprise blade framework structure and covering, it is characterized in that, described covering is flexible covering, described blade framework structure comprises along blade exhibition to spaced apart at least two sizing wing plates and the main bearing beam cap that is arranged on described sizing wing plate, leading edge bearing beam and trailing edge bearing beam, described main bearing beam cap is assemblied on sizing wing plate, lower slotting position, and respectively at least arrange main bearing beam cap described at the suction surface of blade and pressure side, described leading edge bearing beam is assemblied in leading edge bearing beam position of opening on sizing wing plate, described trailing edge bearing beam is assemblied in trailing edge bearing beam position of opening on sizing wing plate, described covering tensioning is connected between adjacent two described sizing wing plates, and the leading edge portion of described covering, trailing edge part lay respectively at chord of blade to leading edge locus and trailing edge position.
2. dismountable pneumatic equipment blades made according to claim 1, is characterized in that, described main bearing beam cap, leading edge bearing beam and trailing edge bearing beam are assemblied on described sizing wing plate by fastening piece.
3. dismountable pneumatic equipment blades made according to claim 2, is characterized in that, described fastening piece is clamping bolt.
4. dismountable pneumatic equipment blades made according to claim 3, it is characterized in that, each described sizing wing plate is arranged row or multiple row clamping bolt assemble leading edge bearing beam, trailing edge bearing beam, main bearing beam cap, described clamping bolt arrangement mode is side by side or is staggered.
5. dismountable pneumatic equipment blades made according to claim 1, it is characterized in that, described main bearing beam cap be along blade exhibition to variable cross section size continuous beam, its sectional dimension is determined according to blade local load, structure or material property, in order to meet consistent aerodynamic configuration, its outer surface pressure side and suction surface processing meet the requirement of blade integral aerodynamic configuration physical dimension.
6. dismountable pneumatic equipment blades made according to claim 1, is characterized in that, described main bearing beam cap is one group on blade, pressure side and each main bearing beam cap of suction surface, or is many groups, and its sectional shape is stepped shaft, rectangular or trapezoidal.
7. dismountable pneumatic equipment blades made according to claim 1, is characterized in that, the local that described main bearing beam cap is being connected with each sizing wing plate is equipped with tapped through hole, fastening with sizing wing plate by bolt.
8. dismountable pneumatic equipment blades made according to claim 1, is characterized in that, the cross-sectional geometry of described sizing wing plate is T-shaped, I-shaped or box-shaped; There is a vertical interior edge face in described sizing wing plate, for improving its strength and stability, its surface, outside pressure face and suction surface surface meet blade aerodynamic shape requirement, simultaneously for being connected with main bearing beam cap.
9. dismountable pneumatic equipment blades made according to claim 1, it is characterized in that, described sizing wing plate is slotted for being connected main bearing beam cap along blade exhibition to being respectively equipped with suction surface at pressure side, leading edge locus be provided with along blade exhibition to perforate for connecting leading edge bearing beam, be provided with in trailing edge position along blade exhibition to perforate for connecting trailing edge bearing beam.
10. dismountable pneumatic equipment blades made according to claim 9, it is characterized in that, described sizing wing plate is provided with threaded hole in leading edge, trailing edge is provided with threaded hole, pressure side and suction surface are provided with threaded hole, and its axially bored line direction is all parallel to the Normal direction of the local aerofoil profile of blade.
11. dismountable pneumatic equipment blades mades according to claim 1, it is characterized in that, described leading edge bearing beam and trailing edge bearing beam are circle, square or trapezoid cross section beam, and described leading edge bearing beam and trailing edge bearing beam are along exhibition to being non-uniform beam, its sectional dimension is determined according to blade local load, structure or material property.
The assembly method of the dismountable pneumatic equipment blades made described in 12. above-mentioned any one claims, is characterized in that, comprise following installation step:
(1) manufacture blade each several part assembly respectively, surface anticorrosive process or coating process carried out to assembly, and partial pressure face and suction surface the roughness process on surface, the aerodynamic configuration making it to meet design requires and matching requirements;
(2) according to designing requirement, sizing wing plate is placed in each exhibition to position, the placing height of adjustment sizing wing plate and chordwise location;
(3) leading edge bearing beam is packed into each sizing wing plate along exhibition to order, with leading edge clamping bolt pretension, tentatively fixing; Use the same method and trailing edge bearing beam is assembled on each sizing wing plate, adopt similar approach to be assembled to by main bearing beam cap on each sizing wing plate;
(4) clamping bolt, leading edge bearing beam clamping bolt, the trailing edge bearing beam clamping bolt of main bearing beam cap is tightened in classification in order;
(5) packed into respectively in order by the outstanding rope on covering in the perforate of sizing wing plate, adjustment, alignment posttension taut envelope fix outstanding rope;
(6) according to design screw-down torque, check each parts connecting bolt Tightening moment, so far namely dismountable pneumatic equipment blades made installs;
(7) when needs dismounting blade, then according to the contrary dismounting realizing blade smoothly, the assembling of parts, replacing, maintenance and recovery is completed.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310690643.9A CN103629055B (en) | 2013-12-16 | 2013-12-16 | A kind of dismountable pneumatic equipment blades made and assembly method thereof |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310690643.9A CN103629055B (en) | 2013-12-16 | 2013-12-16 | A kind of dismountable pneumatic equipment blades made and assembly method thereof |
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| CN103629055A CN103629055A (en) | 2014-03-12 |
| CN103629055B true CN103629055B (en) | 2015-11-18 |
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| CN113001995A (en) * | 2021-03-29 | 2021-06-22 | 青岛思恩科技有限公司 | Wind-powered electricity generation blade composite protection film and can dismantle wind-powered electricity generation blade protection device |
| CN114013571B (en) * | 2021-11-15 | 2022-09-13 | 国家海洋技术中心 | Flexible wing for wave glider and wave glider |
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|---|---|---|---|---|
| CN2908843Y (en) * | 2006-05-19 | 2007-06-06 | 王文长 | Blade structure of wind power generation |
| CN102141001A (en) * | 2011-03-25 | 2011-08-03 | 中国科学院工程热物理研究所 | Wind machine blade and method for designing same |
| CN102200100A (en) * | 2011-06-02 | 2011-09-28 | 东方电气集团东方汽轮机有限公司 | Split-assembling-type blade of wind driven generator |
| CN203685489U (en) * | 2013-12-16 | 2014-07-02 | 中国科学院工程热物理研究所 | Detachable wind turbine blade |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7393184B2 (en) * | 2005-11-10 | 2008-07-01 | General Electric Company | Modular blades and methods for making same |
| US7854594B2 (en) * | 2009-04-28 | 2010-12-21 | General Electric Company | Segmented wind turbine blade |
| US8360733B2 (en) * | 2011-09-09 | 2013-01-29 | General Electric Company | Rotor blade for a wind turbine and methods of manufacturing the same |
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2013
- 2013-12-16 CN CN201310690643.9A patent/CN103629055B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2908843Y (en) * | 2006-05-19 | 2007-06-06 | 王文长 | Blade structure of wind power generation |
| CN102141001A (en) * | 2011-03-25 | 2011-08-03 | 中国科学院工程热物理研究所 | Wind machine blade and method for designing same |
| CN102200100A (en) * | 2011-06-02 | 2011-09-28 | 东方电气集团东方汽轮机有限公司 | Split-assembling-type blade of wind driven generator |
| CN203685489U (en) * | 2013-12-16 | 2014-07-02 | 中国科学院工程热物理研究所 | Detachable wind turbine blade |
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