CN102434384A - Novel composite material blade of horizontal shaft wind generating set - Google Patents

Novel composite material blade of horizontal shaft wind generating set Download PDF

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Publication number
CN102434384A
CN102434384A CN2011103941925A CN201110394192A CN102434384A CN 102434384 A CN102434384 A CN 102434384A CN 2011103941925 A CN2011103941925 A CN 2011103941925A CN 201110394192 A CN201110394192 A CN 201110394192A CN 102434384 A CN102434384 A CN 102434384A
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Prior art keywords
blade
pneumatic
section
aerofoil profile
composite material
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Pending
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CN2011103941925A
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Chinese (zh)
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张向增
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Individual
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Individual
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Priority to CN2011103941925A priority Critical patent/CN102434384A/en
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Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03DWIND MOTORS
    • F03D1/00Wind motors with rotation axis substantially parallel to the air flow entering the rotor 
    • F03D1/06Rotors
    • F03D1/065Rotors characterised by their construction elements
    • F03D1/0675Rotors characterised by their construction elements of the blades
    • YGENERAL 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
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02EREDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00Energy generation through renewable energy sources
    • Y02E10/70Wind energy
    • Y02E10/72Wind turbines with rotation axis in wind direction

Abstract

The invention relates to a novel composite material blade of a horizontal shaft wind generating set; a pneumatic function part and a bearing structure part of the blade are designed to be separated from each other respectively, the bearing structure breaks the geometric limit of a pneumatic airfoil shape contour profile and extends out of a pneumatic molded surface, an outer bearing structure and a pneumatic structure part act on together to form a main bearing structure of the blade. A pneumatic airfoil shape can be a combination of a hollow structural section with a constant cross section which is formed by protrusion process. By the design concept, a large blade can be easily realized, and a large sectional type blade can be produced, the power can be ensured, and the flexural rigidity of the blade is increased, the material efficiency is greatly increased and the cost of the blade is reduced.

Description

A kind of horizontal axis wind-driven generator group advanced composite material (ACM) blade
Affiliated technical field:
The present invention relates to a kind of horizontal axis wind-driven generator group advanced composite material (ACM) blade.The pneumatic funtion part and the bearing structure of blade partly are separated from each other design, and bearing structure has been broken through the geometric limitations of pneumatic aerofoil profile and extended to pneumatic profile outside.External bearer structure and pneumatic structure division acting in conjunction construct the main bearing structure of blade.The blade that this design concept forms, under the prerequisite that ensures pneumatic power, the flexural rigidity that has greatly promoted blade also reduces the cost of blade significantly, and material use efficient promotes significantly.
The invention belongs to horizontal axis wind-driven generator group composite material blade and make the field.
Background technique:
No matter modern horizontal axis wind power generating set composite material blade is to adopt the pre-bending structure or carbon fibre material strengthens structure, has all ultimately optimized blade and can't break through once again.Its basic reason is exactly the geometric limitations that is limited by the pneumatic aerofoil profile of blade, makes the structural behaviour performance of material not come out.Blade bears maximum aerodynamic lift and produces huge bending moment waving direction specifically; But blade receives the restriction of airfoil geometry at the thickness of this direction; Thereby make blade be restricted in the flexural rigidity of this direction; Even adopt the carbon fibre material of high-modulus to strengthen, insufficient rigidity still seems for large-scale blade.Blade pre-bending technology just changes the initial position of blade deflection deformation, can not increase the flexural rigidity of blade self.
We know that " worker " word beam has the most excellent transverse property and material efficiency.From the rectangular cross-section bending resistance deformation characteristic analysis of overhang we know that the flexural rigidity of beam and depth of beam cube first power proportional and material modulus is proportional.So the thickness ratio that increases blade structure selects for use high modulus material more effective.Therefore, the method that promotes the blade flexural rigidity just is how to ensure the thickness that strengthens the load-carrying construction of blade under the prerequisite of pneumatic function.Answer is exactly the restriction that breaks through the pneumatic profile thickness of blade, makes bearing structure external with respect to pneumatic aerofoil profile.
The blade that wind power generating set is used has maximum speed of incoming flow at the blade tip place of blade, can reach the level of 65m/s, is equivalent to 1/5 velocity of sound.This belongs to the pneumatic scope of low speed in aerodynamics, this just makes the blade bearing structure with respect to the external possibility that becomes of pneumatic aerofoil profile.
Summary of the invention:
The objective of the invention is to realize design and manufacturing technology a kind of lightweight, cheap, the reliable large-scale blade of horizontal axis wind-driven generator group.
So-called major diameter impeller and large-scale blade, be appreciated that into diameter at the impeller more than the 80m, more than the length of blade 40m.
Thinking of the present invention is exactly to break through the restriction of the pneumatic profile thickness of blade, makes bearing structure external.
Similar general deflection of beam deformation principle, during the blade buckling deformation, the material that is positioned at curved axle one side bears compressive stress, and the material of opposite side bears tensile stress.For different materials and structure shape, it is different with the ability that stretches to bear compression.This patent is designed to pneumatic aerofoil profile side and bears compressive stress, and external longitudinal beam bears tensile stress, when promoting flexural rigidity, makes full use of the crooked stability that the airfoil geometry size promotes blade.For pneumatic airfoil section, the section bar that nature can adopt pultrude process to make uniform section comes the combined pneumatic aerofoil profile.From the blade root to the blade tip, need the chord length of vane airfoil profile different in theory; Scheme of the present invention is to adopt segmentation combination approximate processing method, is promptly formed the pneumatic aerofoil profile of whole blade by the constant cross-section blade fragment combination pultrude process moulding, different chord lengths and thickness.For external longitudinal beam part, longitudinal beam bears tensile stress, and it is optimal selection that unidirectional fibre strengthens resin composite materials; Owing to there is not the flexing stability problem; Sectional dimension can be very little, for reducing windage and wind disturbance, promotes the overall pneumatic efficiency of blade; The geometrical shape of longitudinal beam also needs aerodynamic characteristic, adopts the flat pattern of axisymmetric profile to be advisable.And longitudinal beam adopts carbon fiber composite more suitable.
Certainly, the connecting arrangement between external longitudinal beam and pneumatic aerofoil profile also will have aerodynamic characteristic, reduces windage and wind disturbance.Can be sandwich foam sandwich structure.
Every blade must can be realized independent feathering control, and this is the prerequisite ability of modern horizontal axis blower fan.The aerodynamic center axis that the change oar axle of blade of the present invention and pneumatic aerofoil profile form overlaps basically, like this, when the blade revolution becomes oar, can realize fully that the pneumatic angle of attack of blade diverse location is regulated.
Set forth specific embodiment of the present invention below in conjunction with accompanying drawing.
Description of drawings:
Fig. 1 is the general structure schematic representation of a blade;
Fig. 2 is a blade middle part cross-sectional view;
Among Fig. 1, the pneumatic aerofoil profile of 1-, the external longitudinal beam of 2-, 3-supporting plate, 4-brace, 5-blade tip, 6-blade root linkage section, FL-distribution lift, PX1-become the oar axis;
Among Fig. 2, the pneumatic aerofoil profile of 1-, the external longitudinal beam of 2-, 3-supporting plate, 7-leading edge, 8-trailing edge, 9-web, the X1-aerofoil profile string of a musical instrument, the external longitudinal beam string of a musical instrument of X2-, X3-bending resistant section centre of form axis, PS-Pneumatic pressure face, SS-aerodynamic suction face, Lc-clearance, T-profile thickness.
In Fig. 1, the blade body bearing structure is made up of pneumatic aerofoil profile 1 part and external longitudinal beam 2 two-part.Combine by connecting arrangement between the two, become the bearing structure that effectively to resist the bending blade distortion.Connecting arrangement can be the grid structure that is made up of supporting plate 3 and brace 4.
As can beappreciated from fig. 1, external longitudinal beam 2 has been broken through the restriction of the geometric profile of pneumatic aerofoil profile 1, is placed on the outside of pneumatic aerofoil profile 1.Pneumatic distribution lift FL vertically is distributed in the outer surface of pneumatic aerofoil profile 1 along blade.
Certainly, even blade structure must have blade tip 5 and blade root linkage section 6 appendages.Blade root linkage section 6 is accomplished and is connected the wheel hub function, and can carry the huge bending load of blade root.
The aerodynamic center axis that the change oar axis of blade and pneumatic aerofoil profile form overlaps basically, and the two mainly is to overlap in the blade root section when pneumatic aerofoil profile 1 is pre-bending type blade.
Along on the blade longitudinal length; Pneumatic aerofoil profile 1 contains the blade fragment of one section constant cross-section at least, and by the blade that multistage blade fragment is formed, every section blade fragment all has the constant cross section of specific chord length; Blade fragment for every section constant cross-section; To the blade tip direction, each differential cross section reverses several angle continuously around becoming the oar central shaft from the blade root of blade, and the pneumatic angle of attack design of neglecting greatly of this angle is confirmed.Fig. 1 illustrates the blade shape of being made up of three sections pneumatic aerofoil profiles of uniform section.Illustrate on the right side of Fig. 1 the pneumatic aerofoil profile of constant cross section that has adopted different chord lengths at ABC three place's diverse locations, its rule be reduce from blade root to the blade tip chord length, vane thickness also reduces.This is needs of considering blade structure stability.
Certainly; This part can be chord length and thickness continually varying form fully for the pneumatic aerofoil profile 1 of blade; The blade geometry external form of the different blade chord lengths in different radii position that promptly obtain according to the foline theoretical calculation still meets the rule that reduces to the blade tip chord length from blade root.Pneumatic aerofoil profile 1 will meet specific pneumatic torsional angle.
Pneumatic aerofoil profile 1 adopts constant cross-section segmentation combination technological scheme can use the vane section bar by the pultrusion molding process manufacturing to make up, and realizes automatic continuous production, and chord length and thickness continually varying blade then need be used the mould intermittent type manufacturing of distinguish.The former has higher reliability and lower manufacture cost, and the Technological Economy sexual clorminance is obvious.
Also there is more technology to be particular about about supporting plate 3 and brace 4.Supporting plate 3 also should have suitable aerodynamic configuration, reduces resistance of air and the disturbance that reduces air-flow to greatest extent.Supporting plate 3 can adopt the sandwich sandwich structure of foam.From the blade root to the blade tip, the height of supporting plate 3 reduces, and thickness reduces.Brace 4 then is that unidirectional fibre strengthens resin composite materials fully.Because the distribution lift FL load that produces on the pneumatic aerofoil profile of blade is to be distributed on the whole length of blade, so the brace 4 of diverse location can distribute suitable cross-section area according to the size of distributed load.
Because the airspeed of blade tip is the highest, for reducing resistance and noise, external longitudinal beam 2 not necessarily begins in the blade tip position to generate, and for example, can begin in the position apart from blade tip 1/5 length of blade, finish up to the blade root position.
External longitudinal beam 2 can one-body moldedly be made with brace 4.Have a kind of embodiment to be exactly, the continuous fiber of each brace 4 from pneumatic aerofoil profile surperficial initial, cross over the root that always extends to blade behind the supporting plate 3.Like this, all braces 4 extension fiber tufts assemble external longitudinal beam 2.Its result is exactly that external longitudinal beam 2 is that progressively the cross section increases from the blade tip to the blade root.Suppose length of blade 45m; Supporting plate of every 3m 3 and brace 4; The cross-section area of each fibrous composite brace 4 is 5 square centimeters, can bear the pulling force more than 50 tons, so; From the blade tip to the blade root, whenever go forward one by one its sectional area of position of 3m of external longitudinal beam 2 increases by 5 square centimeters, be successively 5 square centimeters, 10 square centimeters, 15 square centimeters ... .., 75 square centimeters.Cross section, external longitudinal beam 2 blade tip position is equivalent to 50mm * 10mm, and cross section, blade root position is equivalent to 300mm * 25mm.
Fig. 2 illustrates the sectional view in a cross section of certain position, blade middle part, utilizes this counter-bending characteristic of scheming to analyze this cross section, provides bending resistant section centre of form axis X 3 among the figure; In X3 axle left side; External longitudinal beam 2 bears tensile stress, and on X3 axle right side, pneumatic aerofoil profile 1 is born compressive stress.Because the structure that pneumatic aerofoil profile 1 is a hollow, enveloping outer enclosure has bigger geometric area, and therefore, it is stronger to resist the stable ability of vertical compression; And external longitudinal beam 2 carries tensile stress, so sectional area can be less, can be solid structure, such as the variable cross section solid construction of above-mentioned example.Consider the structure efficiency of material, the wall thickness of the aerodynamic suction face SS in pneumatic aerofoil profile 1 outside is much larger than the wall thickness of the Pneumatic pressure face PS of inboard.Consider the flexural rigidity requirement of the shimmy direction of blade; In this shimmy direction, load-carrying construction can't be broken through the restriction of pneumatic aerofoil profile, and the theory of this invention is inapplicable in shimmy direction; So, all be assigned the long grain fiber enhancing of capacity at the leading edge 7 and the trailing edge 8 of pneumatic aerofoil profile 1.In order to promote flexing stability, the pneumatic aerofoil profile of blade 1 inside has web 9 to link the aerodynamic suction face SS and the Pneumatic pressure face PS of pneumatic aerofoil profile 1.Numeral is given an example and is described and understand this notion; Cross section, blade certain for example, chord length is the pneumatic aerofoil profile 1 of 1.6m, outside aerodynamic suction face SS wall thickness 3mm; Inboard Pneumatic pressure face PS wall thickness 1.5mm; Leading edge 7 inboard reinforcement increase by 10 square centimeters of sectional areas, and trailing edge 8 inboard reinforcement increase by 20 square centimeters of sectional areas, web 9 thickness 2mm.Certainly, on aerodynamic suction face SS, Pneumatic pressure face PS and the web 9 of blade, need rational deployment certainly and be designed with waling, stiffening rib can be a foam sandwich structure.
For the blade that the present invention relates to,, so, also only be that external longitudinal beam 2 uses carbon fiber-reinforced resin composite materials if want to adopt carbon fibre material to promote the flexural rigidity of whole blade.Though graphite fiber modular ratio glass fibre exceeds more than 4 times; But elongation at break is very low; The flexibility of deformable blade is limited; If want to adopt high-strength S type glass fibre to promote the flexibility of whole blade, so, also only be that external longitudinal beam 2 uses high-strength S type galss fiber reinforced resin composite material.
Among Fig. 2, the pneumatic aerofoil profile 1 that centers on string of a musical instrument X1 must satisfy the aerodynamic characteristic requirement.And also to possess pneumatic profile around the external longitudinal beam 2 of string of a musical instrument X2, reduce resistance of air and the disturbance that reduces air-flow to greatest extent.External longitudinal beam (2) can be to have thin plate symmetrical pneumatic profile structure, that reduce to the blade tip cross-section area from blade root.And the clearance Lc between external longitudinal beam 2 and the pneumatic aerofoil profile 1 preferably is greater than the profile thickness T of pneumatic aerofoil profile 1, could effectively reduce the disturbance to air-flow like this.Clearance between external longitudinal beam 2 and the pneumatic aerofoil profile 1 is more little, and the blade flexural rigidity is more little, and pneumatic efficiency is poor more.
The lift efficiency variation even the stall of blade are normally owing to the reason of separating appears in the air-flow of aerodynamic suction face SS side.Because external longitudinal beam 2 is positioned at the Pneumatic pressure face PS side rather than the aerodynamic suction face SS side of pneumatic aerofoil profile 1, and has kept clearance Lc, and is though the existence of external longitudinal beam 2 can cause the local air flow disturbance, limited to the influence of blade aerodynamic lift.
Know that through embodiment's analysis traditional blades produces when crooked bearing aerodynamic force, always aerodynamic suction face SS side is born compressive stress and Pneumatic pressure face PS side is born tensile stress, and the height of bending sections is profile thickness T.And blade according to the invention is that compressive stress is born in the whole cross section of pneumatic aerofoil profile 1 and external longitudinal beam 2 bears tensile stress substantially, and the height of bending sections is Lc+T.Rough measuring and calculating, if Lc+T=2T, flexural rigidity can promote 2 so 3Doubly.In other words, if keep flexural rigidity constant, bending resistant section can be reduced to original 1/8 so; If keep the constant flexural rigidity that makes of material consumption to promote 2 3Doubly, mean that blade can prolong one times at least, accomplishes the manufacturing of large-scale blade easily.It is thus clear that the saving of material and cost just is embodied in here.
The blade that the present invention relates to obviously, can break off in the segmentation joint of pneumatic aerofoil profile 1 fully naturally, adopts the flange bolt structure to connect combination.Like this, whole blade can be transported with remote by sectional forming, assembles in the blower fan erecting bed to link together again, and reduces length, difficulty and the cost of blade transportation.
The present invention adopts and to let the blade bearing structure technical conceive external with respect to pneumatic aerofoil profile; Though aspect pneumatic efficiency, lose; But can prolong blade easily; Realize large diameter impeller and significantly increase wind sweeping area, guaranteed to catch wind power, realized a kind of low cost, highly reliable, legerity type large scale horizontal axis wind-driven generator group blade.

Claims (8)

1. a horizontal axis wind-driven generator group advanced composite material (ACM) blade has independently pneumatic aerofoil profile and bearing structure, it is characterized in that: blade has one to be positioned at pneumatic aerofoil profile (1) external longitudinal beam (2) outside, that promote the vertical flexural rigidity of blade.
2. composite material blade according to claim 1 is characterized in that: external longitudinal beam (2) is positioned at Pneumatic pressure face (PS) side of pneumatic aerofoil profile (1).
3. composite material blade according to claim 1; It is characterized in that: along on the blade longitudinal length, pneumatic aerofoil profile (1) contains the blade fragment of one section constant cross-section at least, the blade of being made up of multistage blade fragment; Every section blade fragment all has the constant cross section of specific chord length; For the blade fragment of every section constant cross-section, to the blade tip direction, each differential cross section reverses several angle continuously around becoming the oar central shaft from the blade root of blade.
4. composite material blade according to claim 1; It is characterized in that: the pneumatic aerofoil profile of blade (1) has the variation of successively decreasing continuously of the geometrical shape of different chord lengths and thickness, chord length from blade root to the pneumatic aerofoil profile of blade tip blade (1) and thickness by the different radii position that obtains according to the foline theoretical calculation.
5. composite material blade according to claim 1 is characterized in that: external longitudinal beam (2) is to have thin plate symmetrical pneumatic profile structure, that progressively reduce to the blade tip cross-section area from blade root.
6. according to claim 1 or 5 described composite material blades, it is characterized in that: resisting diastrophic external longitudinal beam (2) is carbon fiber-reinforced resin composite materials.
7. composite material blade according to claim 1 is characterized in that: the aerodynamic center axis that the change oar axis of blade and pneumatic aerofoil profile (1) form overlaps basically, and the two mainly is to overlap in the blade root section when pneumatic aerofoil profile (1) is pre-bending type blade.
8. composite material blade according to claim 1 is characterized in that: the segmentation joint in pneumatic aerofoil profile (1) is broken off naturally, adopts the flange bolt structure to connect combination.
CN2011103941925A 2011-11-11 2011-11-22 Novel composite material blade of horizontal shaft wind generating set Pending CN102434384A (en)

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CN201120446769.8 2011-11-11
CN201120446769 2011-11-11
CN2011103941925A CN102434384A (en) 2011-11-11 2011-11-22 Novel composite material blade of horizontal shaft wind generating set

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WO2013004156A1 (en) * 2011-07-04 2013-01-10 Zhang Xiangzeng Blade with constant cross section, forming method thereof, and horizontal axis wind turbine impeller comprised of the same
WO2013067916A1 (en) * 2011-11-11 2013-05-16 Zhang Xiangzeng New blade of composite material for horizontal-axis wind power generator
CN103470445A (en) * 2013-10-09 2013-12-25 南京风电科技有限公司 Device for increasing rigidity of blades of wind turbine generator
CN103726710A (en) * 2013-12-31 2014-04-16 国家电网公司 Lattice type derrick of electric transmission line
CN105649868A (en) * 2016-01-22 2016-06-08 清华大学 Large wind power blade face outside enhancing device based on winged knife pull rod structure
WO2017076096A1 (en) * 2015-11-03 2017-05-11 周方 Reinforced blade for wind-driven generator

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Publication number Priority date Publication date Assignee Title
WO2013004156A1 (en) * 2011-07-04 2013-01-10 Zhang Xiangzeng Blade with constant cross section, forming method thereof, and horizontal axis wind turbine impeller comprised of the same
WO2013067916A1 (en) * 2011-11-11 2013-05-16 Zhang Xiangzeng New blade of composite material for horizontal-axis wind power generator
CN103470445A (en) * 2013-10-09 2013-12-25 南京风电科技有限公司 Device for increasing rigidity of blades of wind turbine generator
CN103726710A (en) * 2013-12-31 2014-04-16 国家电网公司 Lattice type derrick of electric transmission line
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WO2017076096A1 (en) * 2015-11-03 2017-05-11 周方 Reinforced blade for wind-driven generator
CN105649868A (en) * 2016-01-22 2016-06-08 清华大学 Large wind power blade face outside enhancing device based on winged knife pull rod structure
CN105649868B (en) * 2016-01-22 2018-06-15 清华大学 Intensifier outside a kind of wind turbine blade face based on wing fence Tiebar structure

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