CN103541856A

CN103541856A - Vane intersegment link structure of horizontal shaft wind generating set

Info

Publication number: CN103541856A
Application number: CN201210249420.4A
Authority: CN
Inventors: 张向增
Original assignee: Individual
Current assignee: Individual
Priority date: 2012-07-17
Filing date: 2012-07-17
Publication date: 2014-01-29

Abstract

The invention relates to a vane intersegment link structure of a horizontal shaft wind generating set. Aiming at a vane segmenting condition in which an externally-arranged lengthwise girder is arranged, the scheme of introducing an intersegment link flange solves the problem of intersegment link, and smooth transition and transmission of force of the cross section of a vane are achieved. In terms of the characteristic that a shell body of mutually-connected vane segments is an interlayer structure, a specially-manufactured connection bolt handle is in glue joint with the four walls of a homocentric-square-shaped sandwich pipe of the shell body. In terms of the characteristic that an externally-arranged tension rod bears tension loads, an inner-cone metal adapter is designed and applied to reliable connection between the externally-arranged tension rod and the flange. A sufficient bolt connection matching surface is constructed between a bolt handle and a bolt pillar of a specially-manufactured connection bolt, so that the glue joint surface between the bolt handle and the homocentric-square-shaped sandwich pipe does not bear the tension force after the connection bolt exerts pre-tightening force. Due to the technical schemes, connection of the vane is simple, economic and reliable. Transportation of a large vane can be achieved due to segmentation of the vane and effective intersegment link.

Description

Linkage structure between horizontal axis wind-driven generator group blade sections

Affiliated technical field:

The present invention relates to a kind of intersegmental linkage structure of horizontal axis wind-driven generator group composite material blade, pneumatic funtion part and the bearing structure of this blade are partly separated from each other design, feature is to be furnished with the situation of external longitudinal beam in the front side of the pneumatic wing type profile of blade or bi-side, front and back, and keeps between pneumatic wing type and external beam enough sectional-type blades of pneumatic clearance.The present invention's proposition is applicable to intersegmental Placement and the linkage structure of the sectional-type blade of this structure.

The invention belongs to horizontal axis wind-driven generator group composite material blade technical field.

Background technique:

The above large-scale horizontal axis wind-driven generator group composite material blade of MW class, cantilever is installed and is born wind-force flexural load, and no matter length of blade, in 40m-80m level, is considered from the angle of transportation, or, there is sectional formula blade in the needs of blade self technique or structure.This must relate to the key technology of the intersegmental connection of blade.Reliability, life-span, Economy that the quality level of linkage structure design and manufacture cost have all determined blade.

Traditional blades, because bearing structure is strapped in the inside of blade aerodynamic profile profile, is all the structural type that girder adds covering substantially, so the connecting means that is also limited to beam of the principle that connects of subsection blade and method, will not launch to tell about.What the present invention relates to is mainly for patent application: the blade of the class new structure that ZL201210207846.3 " a kind of horizontal shaft wind-driven generator vane and forming method thereof and equipment " is mentioned, its pneumatic function and bearing structure separate design, bearing structure is broken through the restriction of aerodynamic configuration, be provided with external bearer beam, carry in other words pull bar.This structure, as accompanying drawing figure mono-signal, the load mode of blade connection part and traditional blades are completely different.External bearer pull bar bears tension load longitudinally forever, blade pneumatic wing type part Bending load and the longitudinally resultant load of compressive stress, intersegmental adpting flange born compressed, the complicated applied force such as warping force, bending force, so, be born for distinctive connecting means and the linkage structure of this structure.

Summary of the invention:

The object of the invention is for above-mentioned new blade, realize a kind of succinct, lightweight, cheap, reliable linkage structure, thereby realize the industrialization use of the blade product of this segmentation combination.If there is no effective intersegmental interconnection technique, blade section is fantasy certainly.Yet, the blade of fibrous composite, the weakest the most complicated, not the main body of material or structure, but attachment portion.Blade fragment cans be compared to people's trunk, and attachment portion cans be compared to the joint of human body, and articulation structure is more complex.Therefore, the linkage structure of subsection blade is extremely important.

The present invention is directed to the segmentation feature of blade, especially different sections adopt the pultrusion product features of different cross sections, then in conjunction with the feature of outside longitudinal load-bearing joist support Tensile stress.The present invention has provided the preferred case of different connection part different structures.

First, main body for the larger pneumatic wing type of cross section profile (for example: cross-sectional width size reaches 3 meters connects, thickness reaches 1 meter), owing to being that two of connections may be the blade fragments of different cross section, nature can be expected the transition linkage section of a revolution cone curved surface.But further analyze and know, this connection transition structure, if too abundant for what reliably do, just uneconomical, and weight is too large, the existence of the centrifugal force while also causing additional blade rotary; If design thinly, be difficult to again accomplish that highly reliable, complicated stressed and structural instability will threaten the safe operation of blade.And processing technology is complicated.Consider that interconnective two sections of blades are all prismatic situations of pultrusion, and blade shell must be the fact that has the sandwich structure of adequate thickness.The present invention proposes the intersegmental mounting flange concept that a section transitions is used that arranges.This flange plate will transmit stress certainly, comprises local tensile, compressive, bending, cuts, warping stress.

Secondly, for example, for the connection of the tiny external longitudinal stretching beam of cross section profile the pull bar of 5 centimetres (diameter of section), because the stress of its connection part core is exactly tensile stress, stressed relatively simple.But, the blade of this segmental structure, safety rope almost just ties up on this pull bar.Once rod head failure fracture, the bearing structure of blade is run quickly and is burst, and blade is instantaneous will fracture.This requirement to reliability, has naturally comprised and the bearing capacity of limit basic load has also comprised the reliability design of fatigue load.So a kind of super simple and efficient structure for pull bar rod end joint has been born, that is exactly a kind of cone structure.This structure for example, for fibrous composite especially effectively (this special fibrous composite of timber), and this structure has the use of opinion in carpenter's structure.

The connection at above-mentioned two places all relates to an adpting flange, so the adpting flange at this two place can combine together, and is called flange plate.Certainly, flange plate can be fabricated, can be also a monomer, plays transmitted load, distribute loads, homogenizing load.And, this flange plate play one external pull bar Point of Strength is provided and ensure pneumatic profile and external pull bar between the effect of clearance.The setting of flange plate, killing three birds with one stone.

Below in conjunction with accompanying drawing, set forth the specific embodiment of the intersegmental linkage structure of the subsection blade the present invention relates to.

Accompanying drawing explanation:

Fig. 1 is the structure constitutional diagram of pneumatic function new blade separated with bearing structure

Fig. 2 A is that a flat flange is constructed intersegmental linkage structure axial section

Fig. 2 B is that a U-shaped edge mounting flange is constructed intersegmental linkage structure axial section

Fig. 3 A is a flat adpting flange disk component

Fig. 3 B is a U-shaped edge adpting flange disk component

The sandwich structure schematic diagram of Fig. 4 A signal connecting object-blade shell

Fig. 4 B is that housing connects embodiment one: after grip of bolt interplantation crustless sandwich, glued joint

Fig. 4 C is that housing connects embodiment two: grip of bolt interplantation crustless sandwich extending in housing glueds joint after appearance

Fig. 4 D is that housing connects embodiment three: the grip of bolt is embedded in the periphery of subsection blade housing

Fig. 5 A is that external pull bar connects embodiment one: taper joint structure

Fig. 5 B is that external pull bar connects embodiment two: link is embedded in the periphery of pull bar

In Fig. 1,1-pneumatic wing type, the external pull bar of 2-, the intersegmental adpting flange of 3-, 4-truss section, 5-docking wheelboss flange, L-truss segment length, the pneumatic clearance of Lc-, T-profile thickness.

In Fig. 2 A, 20-air guide sleeve, the flat mounting flange of 21-, 22-blade tip side PS surface pull rod joint, 23-blade root side PS surface pull rod joint, 24-blade tip side SS surface pull rod joint, 25-blade root side SS surface pull rod joint, 26-blade tip lateral lobe sheet sheet piece housing, 27-blade root lateral lobe sheet sheet piece housing, 28-rod head bolt are paid, 29-housing connecting bolt is paid.

In Fig. 2 B, 20-air guide sleeve, 21-U type edge mounting flange, 22-blade tip side PS surface pull rod joint, 23-blade root side PS surface pull rod joint, 24-blade tip side SS surface pull rod joint, 25-blade root side SS surface pull rod joint, 26-blade tip lateral lobe sheet sheet piece housing, 27-blade root lateral lobe sheet sheet piece housing, 28-pull bar connecting bolt are paid, 29-housing connecting bolt is paid.

In Fig. 3 A, 211-right side blade fragment bolt hole, 212-left side blade fragment bolt hole, stay-bolt hole, 213-right side, stay-bolt hole, 212-left side, the right sectional view of XX-.

In Fig. 3 B, 211-right side blade fragment bolt hole, 212-left side blade fragment bolt hole, stay-bolt hole, 213-right side, stay-bolt hole, 212-left side, the right sectional view of YY-.

In Fig. 4 A, cavity between 1-pneumatic wing type (blade fragment), 261-housing exterior skin, 262-housing inside panel, 263-housing covering.

In Fig. 4 B, between 21-mounting flange, 261-housing exterior skin, 262-housing inside panel, 263-housing covering, in cavity, 264-covering, glued joint surface layer, 291-bolt connection fitting surface, the 292-grip of bolt, 293-bolt column, 294-pad, 295-nut.

In Fig. 4 C, between 21-mounting flange, 261-housing exterior skin, 262-housing inside panel, 263-housing covering, in cavity, 264-covering, splicing surface layer, 265-covering glued joint surface layer outward, 291-bolt connects fitting surface, the 292-grip of bolt, 293-bolt column, 294-pad, 295-nut.

In Fig. 4 D, between 21-mounting flange, 261-housing exterior skin, 262-housing inside panel, 263-housing covering, cavity, the enhancing of 266-fibrous composite lamination, 291-bolt connect fitting surface, the 292-grip of bolt, 293-bolt column, 294-pad, 295-nut.

In Fig. 5 A, 28-pull bar connecting bolt is paid, fill base material between 251-pull bar, 252-internal cones metal joint, 2511-pull bar constituent element, 2522-pull bar constituent element, Lmin-glueds joint face length degree.

In Fig. 5 B, 28-pull bar connecting bolt is paid, the outside lamination of 251-pull bar, 253-metal joint, 2513-fibrous composite strengthens, the inner lamination of 2514-fibrous composite strengthens, Lmax-glueds joint face length degree.

Figure mono-illustrates the blade structure of this segmentation combination.Respectively there is an external pull bar 2 in Pneumatic pressure face (PS face) outside and pneumatic adsorption plane (SS face) outside at the blade of subsection blade pneumatic wing type 1, and the blade composite fragment that illustrates case is divided into three paragraghs.Blade disjunction place relates to the disjunction of the pneumatic wing type 1 of blade, and the disjunction of external pull bar 2.Obviously, the present invention will solve the connectivity problem of two place's different characteristic members here.In addition, the connection of the truss part of composite material blade part and afterbody, has identical construction feature, can understand the rest by analogy.And docking wheelboss flange 5 connects pitch variable bearings, do not belong to mission category of the present invention.

In Fig. 2 A, provide an intersegmental connection embodiment, the left side of figure is blade tip direction, and right side is blade root direction.Supposing is above PS face one side, and bottom is SS face one side.What Fig. 2 A set forth is to do intersegmental mounting flange with one flat plate.The situation that the vane end faces size of the applicable both sides of this situation differs greatly.Its assemble sequence is first little blade fragment and the mounting flange 21 in the cross section in left side to be assembled, then can be in the blade fragment on factory floor or wind energy turbine set assembled in situ right side.It is to do intersegmental connection transition with a U-shaped edge mounting flange that Fig. 2 B has set forth.This situation is applicable to the approximate situation of vane end faces size of both sides.Equally, its assemble sequence is first the blade fragment in left side and mounting flange 21 to be assembled, then can be in the blade fragment on factory floor or wind energy turbine set assembled in situ right side.

Assembly connection is and simply, as long as it is just passable to accomplish fluently Bolt Torque by designing requirement.

Finally air guide sleeve 20 is assembled.Air guide sleeve is a cover that is centered around vane airfoil profile outside, has equally and meets the exterior contour that blade aerodynamic characteristic requires.Object is to eliminate the impact of outstanding bolt head on blade aeroperformance.

While being linked and packed, in the left and right sides of mounting flange 21, rely on housing connecting bolt pay 29 and pull bar connecting bolt 28 pretightening forces that provide are provided, blade fragment and mounting flange are linked together tightly.

The housing connecting bolt that connects pneumatic wing type 1 pays 29 along blade aerodynamic configuration profile line layout (referring to the mounting flange bolt hole layout in accompanying drawing 4).The size of the layout of bolt, quantity, bolt is all determined according to designing and calculating.Owing to disposing the connecting bolt of a circle, large connection surface of contact (referring to Fig. 4) can be provided enough, therefore, the transmission of the change oar moment of torsion of blade is without any problem.

For more clearly expressing bolted layout design, provided the component diagram of two kinds of mounting flanges of Fig. 3 A and Fig. 3 B.In figure, demonstrate, the bolt that connects blade pneumatic wing type 1 housing is along the profile line layout of aerofoil profile, and the bolt that connects external pull bar 2 to be structural type by rod head determine.Point out that mounting flange 21 can be reduced to a special-shaped ring simultaneously, approximate aerofoil profile wire shaped, meanwhile, at blade Pneumatic pressure PS face and pneumatic absorption SS face, respectively there is the arm of an expenditure, for ensureing the clearance Lc (seeing Fig. 1) between aerofoil profile and pull bar.Certainly, when size is larger, be unfavorable for processing and transportation, with regard to Structure of need, decompose, do not repeat.In addition, because the stressed complexity of mounting flange, with regard to reliability, recommendation metal flange, then the factor of the weight of worrying, use cast aluminium alloy should be proper.Certainly, along with the accuracy lifting of computing technique and the real example of design experiences, the selection that mounting flange 21 makes fiberfill layer plywood material be also.

Certainly, mutually dock two sections of blade fragments that connect, must have the phase relationship of cross section docking, specifically, in joint, will guarantee exactly the correct and continuous of blade string of a musical instrument torsional angle.Therefore, require on mounting flange 21, to use perfect number controlled machine to carry out coordinate boring.Point out in passing, boring herein, can also realize the artificial adjusting of twist angle of blade, thus torsional angle discreteness deviation when compensation blade fragment is manufactured.

Come again further to study reliability and the manufacturability of this linkage structure.

Fig. 4 A provides this shell construction enlarged view that has the blade fragment of external pull bar, and according to vane stability design, the housing of blade must be the structure of interlayer, and the shell construction scheme of mentioning as formerly patent application, at this, is expressed by Fig. 4 A.Wherein, between housing covering, cavity 263 is that we will utilize, and is used for implanting connecting bolt handle.For the connection of this shell construction, connection is gluedd joint in optimum selection exactly.Further point out, this shell construction adopts conical section transition connection to be and is difficult, and adopt flat flange plate to connect, is simple possible, and has met the requirement of segmentation transportation.In Fig. 4 A, illustrate between the interior exterior skin of housing, there is the sandwich pipe of a series of " returning " font, just in time for the grip of bolt of every support bolt provides enough splicing in conjunction with wall.Like this, such as implant a grip of bolt in each hole, as two kinds of embodiments that Fig. 4 B and Fig. 4 C provide, be to be all designed to N the bolt of arranging along aerofoil profile line connect and pay, N is according to design value.Because the sandwich pipe of " returning " font is longitudinally to connect blade fragment, therefore, can the corresponding sandwich pipe of " returning " font of each bolt, so just accomplished dispersion, the uniform distribution of power and be reliably connected.

The grip of bolt 292 in Fig. 4 B is implanted between housing covering and is formed and coordinate in cavity 263, and relies on splicing surface layer 264 in covering to form powerful engaging force.If think and be necessary, the grip of bolt 292 can also be deformed into the form of Fig. 4 C, and the two-sided splicing of formation and housing exterior skin 261 and housing inside panel 262 forms splicing surface layer 264, covering in the covering in Fig. 4 C and glued joint surface layer 265 outward.Certainly, the grip of bolt can be also " returning " word metal tube with certain wall thickness, and the glass steel sandwiched pipe of " returning " word of housing forms cooperation and wall glueds joint.Like this, glued joint area large, and because matching gap I is to save structure glue.

Obviously, the bolt arrangement that Fig. 4 B and Fig. 4 C provide is a kind of special bolt, the grip of bolt 292 and bolt column 293, consists of.Its binding site, also needs to provide an important bolt to connect fitting surface 291.When being linked and packed, bolt is paid while applying pretightening force, mounting flange 21 sides are connected to fitting surface 291 face contact to be closely pressed together with bolt, owing to directly not contacting between the end face area of pneumatic wing type 1 composite material casing and mounting flange, zero distance contacts but bears zero stress in other words, so, this powerful pretightening force can not be delivered to glueds joint interface, and pretightening force can not weaken Joint strength.Therefore, this linkage structure can guarantee that sharf is to the transmission of the power with hoop, connects reliable, effective.Connect technique also relatively simple.

Certainly, the grip of bolt 292 can be metal casting part, can be also the composite material element that adopts SMC compression molding, or the similar structure made of alternate manner.The linkage structure of the grip of bolt 292 and bolt column 293 also can be deformed into other form.

Now according to Fig. 4 B scheme, do Joint strength measuring and calculating: suppose to pay along pneumatic capstan profile layout 2500*2.5/60=104 support bolt, suppose the sandwich tube section 60mm*60mm of " returning " word, glued joint length 200mm, Joint strength is guarded value 10MPa, single bolt can provide 60*4*200*10=480kN=48 ton force, suppose that bolt pretightening is 300kN, this pretightening force can not subdued the Joint strength of 48 ton forces.All bolt stacks can provide the combination force of 5000 tons, can carry longitudinal stretching power or the compressive force of 5000 tons.Suppose bonding layer thickness 1mm, use the about 8kg of structure glue.Economical, reliable.Fig. 4 C scheme can promote the splicing power doubling.

Certainly, the connection that Fig. 4 B provides with Fig. 4 C is not the sole mode being connected, can also resemble the connection Fig. 4 D, it is exactly the outside at script blade shell, even inside and outside, along aerofoil profile line layout buried metal bolt or the similar metal connecting piece of housing, outside reprocess fibre composite material lamination strengthens 266.This so-called pre-embedded bolt linkage structure, is widely used at the root of blade of prior art and the connection area of pitch variable bearings.Repeat no more.In figure, illustrate metal embedded part, the grip of bolt 292 is embedded between fibrous composite lamination 266 and housing exterior skin 261.In addition, this structure need to provide flange plate to connect carrying junction plane 291 equally.

So far, the connection that blade fragment relates to pneumatic wing type part has just solved.

Study again the connection of external pull bar.From the blade stress analysis of this structure, know, pull bar is born tensile stress forever.But according to calculating, the sectional dimension of pull bar is less, such as only need diameter be 100mm with interior numerical value, and the chord length size of blade pneumatic wing type part at 1000mm between 3000mm, thickness size at 300mm between 1000mm.Obviously, external pull bar 21 adopts unidirectional fibre enhancing resin drawing and extruding section bar the most suitable.As long as it is just passable to handle joint problem well.

Fig. 5 A provides a kind of joint structure schematic diagram, and internal cones metal joint 252 is paid 28 by pull bar connecting bolt and is connected with mounting flange 21, can realize enough surface of contact and be connected pretightening force between the two.Key is the validity connecting between metal joint and fiber composite tie rod.Apply a kind of cone interconnection technique herein and replace simple straight sticklac connection technology.Namely pull bar 251 will be resolved into a plurality of little drawing and extruding bars, be called for short pull bar constituent element 2511, while being positioned at bar body part, pull bar constituent element 2511 boundlings combine; The pull bar constituent element 2511 that is positioned at pull bar termination spreads and comes each other, forms a tubaeform cone, fills hard colloid base material between pull bar constituent element, after dependence base material solidifies, is bonded together.The cone head of pull bar and the internal cones of metal joint 252 form fitting surface.This cone linkage structure, can guarantee that joint can effectively carry stretching and compressive stress.The joint of this structure, joint glueds joint face length degree Lmin and can do very littlely, for example just passable in 100mm-300mm scope.Rule of thumb infer, 5 °-30 ° of cone angle values are just passable, unsuitable excessive or too small.Certainly, the filling base material in cone will have enough bond properties and intensity, hardness, and not so, pull bar constituent element, like the steel nail of putting into mud, has just been pulled out easily.This cone interconnection technique is comparatively common in porcelain body and the connection between metal cap of insulator.Facts have proved it is reliable.

Pull bar constituent element 2511 can be glass fibre reinforced plastics pultrusion rod, carbon fiber pultrusion rod, cold drawn wire etc.

Equally, other connection embodiment is also provided herein, as Fig. 5 B signal, if pull bar 251 is solid or hollow barred bodies of a single pultrusion, equally can be peripheral with fibrous composite lamination enhancing 2514 at it, then buried metal joint 253, and then externally the outside lamination of shaping fiber composite material strengthens 2513 again.Because the characteristic of fibrous composite is anisotropic, between the fibrous composite of follow-up introducing and the original pull bar body of rod, certainly exist the weak resin glue junction of a relative thin, so, must have enough splicing areas just can bear huge longitudinal stretching stress.So needing to strengthen splicing face length degree Lmax partly can be very large, such as surpassing the connection of 1 meter of length.Certainly, by accurate Calculation, design, place enough reinforcing materials, also can realize reliable connection.

So far, intersegmental two places connection has just satisfactorily completed.By this assembling type bolt, connect, realized the segmentation of blade, facilitated transport of blades.

At this, particularly point out, intersegmental connection case of the present invention, is equally applicable to possess the outside one-sided situation that external longitudinal beam (or becoming external longitudinal tie) leaf characteristic is set of blade pneumatic wing type.

In theory, the linkage structure the present invention relates to is highly reliable, and economical, can adapt to the use of the large-scale huge blade of wind power generating set.Following hundred meters long horizontal axis fan blades, will lean on this fragmentation technique and interconnection technique to realize.

Claims

1. the intersegmental linkage structure of composite material subsection blade for a horizontal axis wind-driven generator group, especially pultrusion has a constant cross-section, pneumatic wing type outer installment has the intersegmental linkage structure of the sectional-type blade of longitudinal tie structure, this linkage structure comprises the linkage structure of pneumatic wing type (1) main body and two constituent elements of linkage structure of external longitudinal tie (2), this linkage structure comprises transit joint, connecting bolt, flange plate, the structural members such as air guide sleeve, it is characterized in that: between two sections of blades of interconnection, have a mounting flange playing a transition role (21), mounting flange (21) connects pneumatic wing type (1) and (2) two connection parts of external longitudinal tie simultaneously.

2. the intersegmental linkage structure of composite material blade according to claim 1, intersegmental connection for pneumatic wing type (1), it is characterized in that: during the overall size difference of the blade fragment pneumatic wing type of mounting flange (21) both sides great disparity, the housing connecting bolt of both sides is paid (29) and is mutually staggered in radial space, and mounting flange (21) is one flat plate formula mounting flange.

3. the intersegmental linkage structure of composite material blade according to claim 1, intersegmental connection for pneumatic wing type (1), it is characterized in that: when the overall size of the blade fragment pneumatic wing type of mounting flange (21) both sides is close, the housing connecting bolt of both sides is paid (29) position in radial space and is approached overlappingly, and mounting flange (21) is a U-shaped edge mounting flange.

4. the intersegmental linkage structure of composite material blade according to claim 1, intersegmental connection for pneumatic wing type (1), it is characterized in that: corresponding to the connection of the housing of blade pneumatic wing type (1), housing connecting bolt is paid the layout of (29) and is arranged along the circumferential profile line of housing cross section, and bolt is paid quantity and spacing according to different design values.

5. the intersegmental linkage structure of composite material blade according to claim 1, intersegmental connection for pneumatic wing type (1), it is characterized in that: the housing of blade pneumatic wing type (1) is the housing with sandwich structure, housing connecting bolt is paid the sandwich structure of the bolt shank implantation housing of (29) and " is returned " in the middle of the sandwich pipe of word, wall face coordinates, and glueds joint and connects; Or housing connecting bolt is paid the bolt shank of (29) and is implanted the sandwich structure centre of housing simultaneously and extend to covering outside, and wall coordinates, and glueds joint and connects.

6. according to the intersegmental linkage structure of the composite material blade described in claim 1 and 5, intersegmental connection for pneumatic wing type (1), it is characterized in that: the grip of bolt (292) that housing connecting bolt is paid (29) can be metal casting part, can be also the composite material element that adopts SMC compression molding.

7. the intersegmental linkage structure of composite material blade according to claim 1, intersegmental connection for pneumatic wing type (1), it is characterized in that: housing connecting bolt pay between the bolt shank of (29) and bolt column, be configured with one enough large bolt connect fitting surface (291), the pretightening force effect applying by clamping bolt, mounting flange (21) side is connected to fitting surface (291) face contact is closely pressed together with bolt, and not directly contact between the end face area of pneumatic wing type (1) composite material casing and mounting flange.

8. the intersegmental linkage structure of composite material blade according to claim 1, intersegmental connection for pneumatic wing type (1), it is characterized in that: the grip of bolt (292) that housing connecting bolt is paid (29) is embedded between fibrous composite lamination 266 and blade shell exterior skin (261), is configured to a kind of embedding structure.

9. the intersegmental linkage structure of composite material blade according to claim 1, intersegmental connection for external pull bar (2), it is characterized in that: when external pull bar (2) is the pull bar (251) being configured to by many pull bar constituent elements (2511) set, pull bar constituent element (2511) spreads out each other in the end of pull bar (251), gap-fill hard colloid base material therebetween, after solidifying, form trumpet-shaped cone, the outside of cone coordinates suit internal cones metal joint (252), the pull bar (251) of one end of internal cones metal joint (252) and boundling is connected and cone constraint, the other end is paid (28) by pull bar connecting bolt and is connected with mounting flange (21) and bolt pretightening constraint.

10. the intersegmental linkage structure of composite material blade according to claim 1, intersegmental connection for external pull bar (2), it is characterized in that: when external pull bar (2) is the produced hollow or solid fibrous composite body of rod of a pultrusion, in periphery, the body of rod (251) end, along cross section profile contour layout, buried metal joint (253), metal joint (253) is embedded in the outside lamination of fibrous composite to be strengthened between (2513) and the inner lamination enhancing of fibrous composite (2514), is configured to a kind of joint embedding structure.