• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    A joint sleeve (102) for assembling together a first blade section (104) and a second blade section (106) of a rotor blade assembly (100) is disclosed. The joint sleeve (102) may include an outer surface (146) and an inner surface (134) defining a cavity (136). The cavity (136) may be configured to receive a joint end (130) of the first blade section (104) and a joint end (131) of the second blade section (106). The joint sleeve (102) may also include a plurality of openings (144) defined between the outer (146) and inner (134) surfaces. The openings (144) may be configured to received fasteners (142) for securing the joint ends (130, 131) of the first and second blade sections (104, 106) withint the cavity (136). Additionally, a profile of the outer surface (146) may be configured to generally correspond to an aerodynamic profile of the first and second blade sections (104. 106) such that a substantially continous aerodynamic profile is defined between the first and second balde sections (104, 106) when the joint ends (130, 131) are inserted with the cavity (136).
    公开号:DK201170668A
    申请号:DKP201170668
    申请日:2011-12-05
    公开日:2012-06-09
    发明作者:Bell Eric Lee
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    JOINT SLEEVE FOR A ROTOR BLADE ASSEMBLY ΟΓ A WIND TURBINE
    FIELD OF TUT INVENTION I oou 11 The prosemic subject mallei 'generally relates to rotor blades of a wind turbine and, more particularly. 10 a joint sleeve I'or joining blade sections of a rotor blade assembly BACKGROUND OF THE INVENTION 100021 Wind power is considered one of the cleanest, most environmentally friendly energy sources presenlly available, and wind Inrhines have gained increased all ni ion in this regard. Λ modern wind turbine typically includes a lower, generator, gearbox, nacelle, and one or more rotor blades. Hie roior blades capture kinetic energy from wind using known foil principles and transmit the kinetic energy through rotational energy lo turn a shaft coupling the rotor blades to a gearbox, or if a gearbox is not used, directly to the generator. The generator then converts the mechanical energy to electrical energy that may be deployed to a utility grid. I () 0 () 21 To ensure that the wind power re mains a viable energy source, e floris have made lo improve the overall performance of wind turbines by modifying 1 he si ^ e. shape and configuration of wind turbine rotor blades. One such modification lias been to alter the configuration of the lip of the rotor blade. In particular, blade lips may be specifically designed to enhance or improve various aspects (if a rotor blade's performance. For example, certain blade tips may be designed to operate efficiently in specific wind classes. Additionally, blade lips may be configured to enhance specific operating conditions. of the wind turbine, such as by being configured to lower lore) or reduce noise. 10004] Thus, given that different operating advantages may be provided to a wind turbine depending on the configuration of the blade lip, it would be advantageous to have an attachment device lhai allowed for the quick and efficient assembly and disassembly of blade tips on and off a roior blade However, known aunchmcnl devices are typically complex and are manually intensive to install. Additionally, such attachment devices make it difficult to accurately align the blade tip with the remainder of the rotor blade. IOlMiij Accordingly. there is a need for a simple and efficient attachment device for joining two lilads sections of an iolor blade assembly. RRTr.r nr.SCR ΓΡΤΤΟΚ ΟΓ ΤΤ! Γ 1NVFNTJQN I (jfKK> | Aspects and advantages of the invention will be set Ibi'lh in part in the following description, or may be obvious from the description, or may be learned through practice of this invention I ntK) 71 In one as peel, the present subject matter discloses a zero blade assembly for a wind turbine. The rotor blade assembly gen end includes a first blade section having a joint end and defining an aerodynamic prolile and a second blade seel ion having a joint end and defining an aerodynamic profile. The rotor blade assembly also includes a joint sleeve having an inner surface and an outer surface. The inner surface may generally define a cavity configured to receive the joint ends of the first and second blade sections. Additionally, the rotor blade assembly may include a plurality of fasteners configured to secure the joint ends of the first and second blade sections within the cavity; further, a profile of tire outer surface of the joint sleeve may generally correspond to the aerodynamic profiles of the first and second blade sccli011s such thai a suhslaiitially cnnlinnous aerodynamic profile is distinguished between the lirsl and second blade sections when ihc joint ends arc inserted within the cavity. I () IK) K | In another aspect, the present subject matter discloses a joint sleeve for assembling together a first blade section and a second blade section of a rotor blade assembly. The joint sleeve may include an outer surface and an inner surface defining a cavity. The cavity may have a root end configured to receive a joint end of the first blade section and a tip end configured to receive a joint end of the second blade section. The joint sleeve may also include a plurality of openings defined between the outer and inner surfaces The openings may be configured to receive a plurality of fasteners for securing the joint ends of the first and second blade seel ions within the cavity. Additionally, an outer stir lace profile may be configured to generally correspond to an aerodynamic profile ofihe firsl mid second blade sec Lions such 1 has a substantially continuous aerodynamic profile defined between the first and second blade sections when (lie jo ini ends arc inserted wiUun Lhe cavity. _G009J [τι: in further aspect, the present subject matter discloses η I ip assembly for a ro lor blade of il wind turbine, '[' he Lip assembly LtLay generally include a joint sleeve Lia 'iπul an inner The joint assembly may also include a lip end and a root end.The up assembly may also include a tip section extending between a joint end disposed within the cavity and a blade tip. The Up section may define an aerodynamic profile generally corresponding to (he aerodynamic profile of the joini sleeve at the up end. Additionally, lip assembly may include a plurality of fasteners configured to see cure the joint end of the tip section within the cavity; further, a portion of the cavity disposed at all of the mole ends of the joint sleeve may be configured to receive an end of a separate section of the rotor blade. I (Hi · 10) These and other fca 1 tires. Aspects and advantages of the present invention will be better understood with reference to the following description and appended claims. The accompanying drawings, which are incorporated in and constitute a portion thereof. specification, illustrate embodiments of the invention and together with the description, serve to explain the principles of the inveaiLion.
    FfRlFF DFSCRIPTION ΤΠΓ RA DRAWINGS 101) 1 I A full and enabling disclosure of the present invention, including (he bcsl mode thereof, directed lo one of ordinary skill in the an, is set forth in this specification, which makes reference to the appended figures, in which: I 0012 I Kit j_ I ilustrines a perspective view of a wind turbine of conventional construction; I () <> n I FIG. 2 illustrates a perspective view of one embodiment of a roior blade assembly m in accordance with aspects of the present submanager; 10014] FIG 2 illustrates a partial, perspective view of the rotor blade assembly shown in FIG, 2 ', | (iOloJ FIG. 4 illustrates a perspective view of one embodiment of a joint sleeve st i liable for use will; ihe disclosed roLnr blade assembly in accordance with aspecls of the present subject matter; I mu 61 Π0> illustrates a panel cross-sectional view of one embodiment ο lie lie at La dime nl of several components of the disclosed your lor blude assembly in accordance with aspects of the pressnl subject matter; | 0fH7 | Hfj 6 illustrates, in partial. cross-sectional view of another embodiment of the attachment of several components of the disclosed roior blade assembly in accordance with aspects of the present subject matter; and, 11) 01 ft In FIG. 7 illustrates a perspective view of an embodiment of a lip assembly in accordance with aspects of the presen l subject matter. DF.TAII.rrj DF.SCRIPTJON ΟΓΤΙΙΓ INVFNTIOM I 00101 Reference will now be made in detail to embodiments of the invention, one or more examples of which arc illustrated in the drawings. Case example is provided by way of explanation of the invention, not limitation of the invention. In a nutshell, it will be apparent to those skilled in the art that various modifications and variations can be made in the present invention without departing from the scope or spirit of that invention. For instance, features illustrated or described as part of one embodiment can be used with another embodiment to yield a still further emlmdimern. Tints, iL is intended lhal ihc present, invention covers such modi ileal ions and variations as come within the scope of the appended claims and their equivalents. 106201 In general, the present subject matter is directed to a joint sleeve for joining together blades sect torts of a rotor blade assembly. In particular, the joint sleeve may define a cavity configured to receive an end of each blade section. For example, the cavity may generally have a shape corresponding to the shape of the ends of the blade sections, such as having a tapered, aerodynamic profile corresponding to the tapered, aerodynamic profiles of the blade section ends. Suitable rasl eners may then be inserted around the periphery of the joint sleeve 10 secure ihe ends of the blade sections within the cavity, 10021J The disclosed joint sleeve may generally provide lor the quick and efficient assembly and disassembly of a roior blade As such, blade seel ion may be easily removed from and re-assembled onto the roLur blade for purposes of maintenance, repairs and tor for upgrading the performance of the rotor blade. For example, it may be preferable to vary the lip section of the rotor blade depending on the wind turbine operating conditions and / or the desired performance of the rotor blade assembly. Thus, using the disclosed joint sleeve, lip section * having differences, dimensions, configurations and / or aero dynamic features may be efficiently assembled oulo the rotor blade and replaced as desired For example, a slraighi lip sec I ion (cg. a tip section extending in a substantially span wise direction) may be replaced with a wine let-Lytic tip section or vice versa. Similarly, a wing having a particular configuration may be replaced wnh a winglet having a different con figuration. I Of> 221 Inferring now7 to the drawings, FIG. I illustrates perspective view ·· of a wind Liirbinc U> of conventional construe lion. The wind turbine Id includes a tower 12 with a nacelle 14 mounted thereon. A plurality of rotor blades 16 are mounted to a rotor hub IS. which is. a turn connected to a main long thai turns a main rotor shaft. J'he wind turbine power generation and control components are housed within nacelle 14. It should be appreciated that the wind turbine 10 of FIG. I am provided for illustrative purposes only to place the present subject matter in an exemplary Hero of Use. Thus, one of ordinary stall in the art shouted readily appreciate that the scope of the present subject mailer is not limited to any particular type of wind turbine con ilgu ration. Referring now to FIGS. 2-4, embodiments of a rotor blade assembly 100 and a joint sleeve 102 for joining the train her first and second blade sections 164, Hid of the rotor blade assembly Hit) are illustrated in accordance with aspects of the present subject matter. In particular. J-'Ki. 2 illustrates a perspective view for one embodiment of the roLor blade assembly 100. FIG. 3 illustrates a paiLial, perspective view of the rotor blade assembly 100 illustrated in FIG. 2. Particularly illustrating the joint sleeve 102 disposed between the blade sections 104, 106 of the rotor blade assembly 100 Additionally, FIG. 4 illustrates a perspective view of one embodiment of the joint sleeve ml 10024J As shown, the rotor blade assembly 100 includes a first blade section 104, a second blade sedition I 06 and a joint sleeve 102 configured to join the blade sections 104, 106 together. In general, lire rotor blade assembly 100 may be configured such that when I first and second blade sections 104, 1 () 6 arc attached within ihc joint sleeve 102, a complete rotor blade, defining a substantially aerodynamic profile, is formed Tims , the comp 1 cl c roior binder assembly 1 () () may generally include a blade root HIK (defined by the first blade seel ion 104) configured Lo be mounted to the hub l H (HG. Π of a wind turbine M) and blade tip 1 10 (defined by the second blade seel ion 1 06) disposed opposile l lie blade root I OK. The rolov blade assembly 100 may also include a span I 12 defining the total length between the blade rool I OK and the blade lip I 10 and a chord L M defining the total length between the Leading edge 1 Id and 1 he trailing edge I IK. As is generally researched. the chord 114 may vary in length wtlh respect to ihe span I 12 as the rotor blade extends from the blade root I OK to the blade lip 1 U>. | 06201 in general, the first and second blade sections 104, I () 0 of ihe roll or blade assembly lot) may be configured similarly to any suitable blade section and / or blade segment known in ihe an. For example, each blade section 104, 100 may include a body shell 120 serving as the greater eusiiig / cuvering of the blade seal 104, LOO and one or more structural components (not shown) to provide stiffness and / or strength to the blade section 104, 106 (eg, a shear web-cap assembly). Additionally, each blade section 106, 106 may generally define an aerodynamic profile. For instance, Ihe body shells 120 of each blade section 104, 106 may be configured to define an airloil shaped cross-section, such as a symmetrical or cambered airfoil shaped cross-section Thus, as shown in FIG. 3, each body shell 120 may generally define a pressure side 122. and a suelIon page 124 extending between a leading edge 126 and trailing edge 12K. I 0026J ll be appreciated lhal the body shells 120 may genera IIv h e formed from any suitable material. For instance, in one embodiment, each body shell 120 may be formed entirely from a laminate composite material, such as a carbon fiber-re in lb reed composite or a glass fiber-reinforced composite Aliernadvely. one or more portions of each body shell 120 may be configured as a layered consi ruction and may include a core material formed from a lightweight maierial such as wood (eg, balsa), loam (extruded polystyrene loam) or combination of such materials, disposed between layers of laminaic composite maierial. 100271 Additionally, the first and second blade sections 104, 106 may each include a joint end 13-0, 131 terminating within the joint sleeve 102, Thus, in (lie illustrated embodiment, the first blade section 104 may generally extend from the
    Li Inde rool l OK or li li rolor Lilad c assembly 1 ϋΟ lo ils joint end 13 i) widnn die joim sleeve 102. Similarly, the sea o roll blade section 1 (12 rnay generally extend from ils ioinl end 13 1 wilhin joint sleeve] U2 to ibe blade lip 110 or ibe rotor blade assembly I Of). Further. as will be described in sweater detail below wiih reference lo TICS. 3 and 6, the joint ends 1.5 (), 131 ol blade sections 104. 1 () 6 may define a particular profile in order Lo insertion insert, of the jo ml ends 130, 131 within the joint sleeve 102, For insiance. in several embodiments, (he | oiitl ends 130, 131 of each blade section 104, 106 may define a tapered or stepped profile corresponding to a tapered or stepped profile defined in ihe joint sleeve 102. | t) U2Nj Moreover, as shown in FIGS. 2 and 3, the flrsl blade seel ion 1 () 4 may generally extend lengthwise along a substantial portion of the span I 12 of the rotor blade assembly KM) such thai the joint sleeve 102 is disposed in an outboard position on the lotor blade generally. proximal to the blade lip 110. As such, the second blade section 106 may generally be configured as a tin outboard or lip section of the rotor blade assembly 100. Thus, in its illustrated embodiment, the second blade seel ion 106 may be configured similar to the outboard portion of a conventional tonal rotor blade 16 (FIG. such, such as by cxlending in a substantially spantvisc direction with the join) than I3l of the blade seel ion 106 and 1 he blade lip I It).
    Alternatively, as will be described below with reference to FIG. 7, the second blade sec lion 106 may be configured as a wing Let-type lip sec lion or may oiherwise have any other suitable lip configuration know it. I 06291 ll shnLild be appreciated Lhal. In embodiments in which the second blade section 106 is configured as an ouLboard or tip section of the rotor blade assembly 10 (1, ihe second blade section 1 () 6 may generally define a relatively short length 132 For example, with several embodiments, the second blade seel ion 106 may define a lettgih 132 which is less than 10 meters (m) long, such as less than 3 m long or less than 3 in long and all other subranges therebetween, However, in an Item a live embodiments, the second blade section 106 need not be configured as a lip section of the mlnr blade assembly KKJ and, ihus, may generally define any suilablc length 132, such as a length greater than or equal to 111 m. In such embodiments, it should be appreciated that the .joint sleeve 102 may generally be disposed of at any suitable location along 1 lie span l 12 ol'thc roior blade assembly 10U such as by being located LU ll wall inboard pusiiion closet Lo the blade root 1 <) M. 100301 Still referring lu FIGS. 2-4, the joint sleeve 102 of the disclosed rotor blade assembly 100 may generally be configured as an attachment device for joining the first and second blade sections 104, 106 Tints, ii should be appreciated that the joint sleeve 102 may generally have any suitable configuration lhat permits the joint ends 130, 131 of I He blade sections li) 4, 100 to be received within the joint sleeve [02. Fur example, in several embodiments, the joint sleeve 102 may have a hollow or a substantial hollow configuration for receiving the joint ends 130, 131 of the blade sections 104, 1 () 6 In particular, as shown in FTG 4. the joint sleeve 102 may generally include an inner perimeter or inner surface 134 defining a cavity 136 extending between a root end 138 and a tip end 140 of the joint sleeve 162. As such, the joint end 130 on the first blade section 104 may be configured to be received within the portion of the cavity 136 defined all the rout end 13h of the joint sleeve 162 and the joint end 131 of the second blade section [¢) 6 may be configured to be received within the portion of the cavity 136 defined all the lip end 14U of the joint sleeve 162. I 063 I] The shoLtld be appreciated dial ihe joint ends 13 (), 13 I of the blade sections 104, 106 may generally be inched within the cavil y 136 of the joint sleeve 102 using ativ suitable betyder. For example, in one embodiment, ihe joint ends 13d. 131 may be bonded within the joint sleeve 102 using any suitable adhesive. In another embodiment, a plurality of bearings 142 may be utilized to secure the joint ends 130, 131 within the joint sleeve 102. For example, as shown in FIGS. 3 and 4. the joint sleeve 102 may define a plurality of openings 144 extending its inner and outer surfaces 134. 146. with each opening 144 being configured to receive a fastener 142. Specifically, a plurality of openings 144 may be defined proximate lo the root end 1.38 oflhe joint sleeve 1 () 2 to permit a number of loaders 142 to be inserted through the openings 144 and attached to the joint, end 130 of the first blade section 104. Similarly, a plurality of openings 144 may he defined proximate ihe tip end 140 oflhe joint sleeve 102 to permit an equal number of fasteners 142 to be inserted through the openings 144 and attached lo the jo ini end 131 of the second blade section 1 () 6. It should be readily appreciated that the openings 144 may be defined in the joint sleeve 102 so as not to form any suitable boll hole paitem. Exampleογ example, in one embodiment, ilie openings 144 imiy futiii a single row along the mole and tips ends 1 38. [4 (1 of the joint sleeve 102. In another embodiment, multiple rows fe.g., two or more rows) or openings 144, beins ^ alienated or offset from one anollier. may be defined in ihe oil and lip ends 13N, 140 of the joint sleeve 102, 10032 I II should also be appreciated that the fasteners 142 described herein may generally comprise any suiiabJe fasteners known in the art, for example, in several embodiments , the fasteners 142 may be configured as threaded fasteners, such as threaded bolls, screws and other suitable threaded 1 listening devices. In other embodiments, the fasteners may comprise suitable fastening and / or allaclimem devices, such as pins, dips, brackets, rods, rivets, bonded fasLeners and the hke. 10033] The disclosed joint sleeve 102 may also define a substan tally aerodynamic profile. For example, as shown in FIG. 4, the joint sleeve Ii> 2 may define an airfoil-shaped cross-section. Thus, similar to the first and second blade sections Ifi4, 106, the outer surface 14G of the joint sleeve 102 may generally define a pressure side 148 and a suction side 150 extending between a leading edge 152 and a trailing edge L52. Additionally, in several embodiments of the present subject matter, the aerodynamic profile dclincd by the joining sleeve lt> 2 may generally correspond to or otherwise match the aerodynamic profiles of the firsi and second blade seelions 104. 1 () 6, In particular , the aerodynamic profile of the joint sleeve H> 2 at the root end 13 They may generally correspond to the aerodynamic profile of the first blade section 102 in an area adjacent to its joint end 130. Similarly, the aerodynamic profile of the joint sleeve 102 at the tip end 140 may generally correspond to the aerodynamic profile of the second blade section 106 in an area adjacent to its joint end 131. As such, when the blade sections 104. 106 are assembled together within jo ini sleeve 102, i lie roior blade assembly 100 may generally define a substantially continuous aerodynamic profile along its entire span 112 For instance, as shown in FIGURE 3. ihejoim sleeve 102 may be configured such that a substantially flush, aerodynamic surface is dclined at the interlace oflhc first blade scclion I 04 and 1 he root end I 3X ol'lhc joinl sleeve 102 and at the interface oJThe second blade section 100 and the Up end 140 of the join «sleeve 102. Thus, 1 lie rotor blade assembly loo may generally define a continuous aerodynamic surface between the first and second blade sections [04, 106. I () (34) should be appreciated that, in several embodiments, an additional slit fate feature may be applied Lls ui positioned ovet the seams at the interfaces of the blade sections 104, 100 and the ends 13 ^, 140 of the joint sleeve 102 to ensure that a substantially smooth aerodynamic surface is achieved. For example, in a particular embodiment, several plies of a laminar composite material may be applied around the outer perimeter of the rotor blade assembly 1) at the joint seams, such as by using a wet lay-up process, to provide a substantial flush aerodynamic surface between (he blade sections 104, lflbtind the joint sleeve Lrt2. | 003 | It should also be appreciated that the joint sleeve If> 2 may generally be formed from any steel material. Tor example, in one embodiment, ihc joint Sleeve 102 may be formed from a metal such as alum mum, steel and Lire like. In other embodiments, the join sleeve 1 () 2 may be formed from a laminate composite material], such as various fiber-reinforced composites, or any other suitable non-metal lie material 10030] Referring now to KIGS 3 and 6, there is illustrated partial, cross-sectional views of two embodiments of the disclosed rotor blade assembly UK), particularly illustrating the attachment of the first and second blades sections 104, 106 within the joinl sleeve 1 () 2 As indicated above, 1 lie joinl ends lot). IA I ol'lhc blade seclions 104, 100 may generally be configured to be alt ached within cavity 13 b defined by joint sleeve 102 such that a substantially continuous aerodynamic profile is defined along span 1 12 (FIG. 2) of the rotor blade assembly 1 Off and, patlicly, all the interfaces between Lire mole and lip ends I 3M "140 of the joint sleeve 102 and the blade shells 120 of the blade sections If) 4, 106. Thus, in several embodiments, an eross -seciional height I 06 ofcttch blade section 104. 106 may generally be reduced ai [he joinl ends 130, 131 to permit (he joint ends 130. 131 to be inserted within the joint sleeve 102 and to ensure thai a substantially continuous or Hush surface is defined between the blade sections 1 () 4, 106 and the joint sleeve 102. I () () 37J For example, as show n in TIG.5, in one embodiment, at least a portion of the join ends 13 () Ί.ί I of the blade sections 104, 1 () 6 may define a tapered pmlllc, such as by configuring the blade shells 120 lo have a tapered thickness 158, in order to perntii the joinl ends 13d, 131 lo be positioned with the joinl sleeve 1 () 2, Additionally, the joinl sleeve 102 may define a corresponding tapered profile so that the orner surface 146 of the joim sleeve 102 is positionccl substantially Hush with the unlfc ] surfaces [Oil uf the binder shells Ι2Π. Thus, as shown, the joint sleeve 102 may generally define lapered widths 102 at its root and tip ends L3S, 140 corresponding to the lapered l hick nesses I of the blade shells 120. Ti should be appreciated that, all hough ihe tapered widths 162 of the joint sleeve 102 are shown defining a substantially sharp or knife edge at the root and tip ends L3H, 110, the tapered widths I 62 need not define such sharp or knife edges. For example, in one embodiment, the tapered profile of joint sleeve 102 may be configured to extend only partially along the tapered profiles of blade sections 104. 106 such that relatively thin, blunt edges may be defined al ihc root and lip ends I3S . 140 of'lhc joiul sleeve 1 () 2. In such an embodiment, an additional surface feature, such as the laminate plies described above, may be applied at the root and lip ends 138, 140 to ensure a substantially continuous aerodynamic surface is defined between the blade sections [04, 106 and the joint sleeve 102. | 0036] Alternatively, as shown in HG. 6, the joint ends 130, 131 of the blade sections 104, 106 may define a stepped profile, such as by configuring the blade shells 120 lo have a stepped reduction in thickness 164 at the rooL and tip ends I3H, 140 of the joint sleeve 102. in such an mho dime ill ihc joint sleeve 102 may generally define a width 166 substantially equal to the reduction in thickness defined in the blade shells 12 () so (the outer surface 146 of the joint sleeve 102 is positioned substantially Hush w ith the outer surfaces 160 of the blade shells 120. In future embodiments, it should be appreciated that the joint sleeve 102 and / or Lire joint ends 130, 131 of the blade sections [04, 106 may generally have any oilier suitable eon figuration ihai permits the joint ends 13 (), 131 to be inserted wiihin the joint sleeve 102. 100301 | 1 general, the tapered or stepped profiles defined at the joint ends 130. I3l of the blade sections 104, 106 may be formed using any suitable means For example, in one embodiment , the tapered or stepped profiles may be a molded feature of the blade shells 120. such as dealing with a mold having a lapcrcd / sLcpped profile defined therein or by placing a mold insert defining the laperedAtepped profile within the mold as (he blade shells 120 arc being formed. In another embodiment, the tapered or stepped profile may be machined into the blade shells 120 after Lite shells 12d have been formed, such as using any suitable machining process and any suitable Hindi tiling equipment. Additionally, il should be appreciated dial the corresponding profile of the joint sleeve 102 may generally be formed using any suitable means For example, in one embodiment, llie | oinl sleeve U) 7 may be [no 1 ded oro 11 ierw i sc fo ri tied to i nc I ute 1 he co rre s po nd i ng pro flic. In any embodiment, the corresponding profile may be machined into the joint sleeve 102 using any suitable machining process and -or any suitable machining equipment I Of MO I In a further embodiment of the present subject matter one of the tapered or stepped profiles of the blade shells 120 or the corresponding profile of the joint sleeve 102 may be initially formed and / or machined and ihcn scanned to permit the exact geometry of such profiles) to be known. For example, in one embodiment, a metrology or oilier 3-D scan may be performed on the la pc red profiles of the .joint ends lit). 131 or each blade section 104, LU6. In a successful embodiment, the tapered width 162 of the joint sleeve 102 may then be formed and / or machined based on the scan to ensure that the tapered width 162 corresponds to the tapered profiles of the blade sections 104. L06. 10041J Referring to two FKi. 5 and 6, in several embodiments, the openings 144 defined in the joint sleeve 102 may include recessed features I 70 for recessing ihc fasteners 142 between the inner and outer stirs I aces 134, 146 often lie joint sleeve 102.
    In particular, the openings 144 may be configured such that the fasteners 142 are recessed partially or fully within the joint sleeve 102. For example, as shown in FIGS. 5 and 6. the recessed openings 144 may be configured such that llie top surface 168 of each fastener 142 is positioned substantially Hush until the outer surface 146 of the joint sleeve 102. As such, the joint sleeve 102 may generally define a substantially continuous aerodynamic profile belw-een its root and tip ends 138. 140. 100421 11 should be appreciated that ihe si / .e, shape and / or configuration of the recessed features 17 (> often openings 144 may generally vary depending on the si / e , shape and / or configuration of the loadeners 142 being used lo attach the joint ends 130, 131 of the blade sccl inns 104, I Of j within the joint sleeve lt> 2 For example, as shown in Fltr. i, the fasteners 142 may generally comprise threaded fasteners having a fastener head 172 defining a tapered diameter.In such an embodiment, the openings 144 formed in the joint sleeve 102 may generally define a corresponding capered di, if such dial l lie fastener head 172 may be lully recessed within i he j oint sleeve 1 (12. In another embo din Lent, shown in FIG. (>, the openings 144 mny are configured as counterbored holes having a shape and / or configuration corresponding to the shape and'dr configuration of I he fastener head I 77. I () (> 431 Referring to FIGS. 5 and (> 10. Ensure proper attachment of'the blade sec lions wit, I od wit lun the joint sleeve 102, l lie dtsc lotted rotor blade assembly 100 may also include lea (hours for retaining the disclosed fasteners 142 wi the joint ends lit). 131 of the blade sections L (> 4;] ClG. For example, in embodiments in which the fasteners 142 are configured as a threaded fasteners (eg, threaded bolls), the rotor blade assembly Kid may include a plurality of female ihrcadcd members 174 configured lo receive Lhe threaded fasteners 142 such that a damped interface is provided between the inner surface 134 of lhe joint sleeve l!> 2 and the joint ends LMi. L3L of the blade sections 1 ((4, I Oh. Thus, as shown in FIG. FIGS. 3 and 0. a plurality of female threaded members 174 may be configured to be aligned with the openings 144 defined in the joint sleeve 102 such that the fasteners 142 may be inserted through the openings 144 and screwed into the threaded members 174. For instance, in the embodiment shown in FIG. 5. the threaded members 174 may comprise a plurality of threaded channels or pings I 7 configured lo not otherwise disposed within (he joins ends 13 (). 131 of the blade sections 104. I () d, In another embodiment, the threaded members 174 may comprise a plurality of nuts 17M mounted directly or indirectly to an inner surface 182 of the blade shells 120. For example, as shown in FIG. 6, the zero 1 78 mny be mounted onLo a ganged channel or nuL plate 1 MO extending around the inner perimeter of each blade shell 120. It should be appreciated that the null I7N may generally comprise any suitable nut known in the art, including conventional, i breaded nuts and floating nuts Additionally, in alternative embodiments, it should be appreciated that lhe threaded members 174 may have any other suitable configuration thai permits lhe fasteners 142 to be securely attached to the joint ends 130, 131 of the first and second blade sections 104, 106. I 0044] In several embodiments of willic prcse nl subject malter, the disclosed rotor blade assembly 100 may also include a divider 184 configured lo sepamLe Lhe joint end 13 () of the lhe firsi blade section 104 from the joim end 131 of the second blade section 10b within the juinL sleeve 102. L he divider 131 nitty also serve as a slop for locating or positioning ihc.join; ends 13d, 131 or "die blade sections 104. 106 wiihin the joint sleeve 102. Foot example, in one embodiment, ihe divide] '1 * 4 may be positioned wilbin the joint sleeve [02 such that, when Ihe joint ends 130, 131 of the blade section 104. 106 are inserted fully within the joint sleeve UK And contact the divider 1 * 4, the threaded members 174 disposed within or mounted lotlic blade shells 120 may generally be aligned with Lite openings 144 defined in the joint sleeve 102. 1 () 0431 Ti should be appreciated thai the divider IK4 may generally have any suitable configuration that permits the divide] 1 * 4 to function as described herein.
    For ins lance, as shown in FIGS. and 6, the divider 1K4 may be configured as a relatively lhin member extending around the inner peri meler of Ilte jo i nl sleeve 1 () 2 substantially perpendicularly to the inner surface 134. Additionally, as shown in FIG. one, in one embodiment, ihc divider I * 4 may extend inwardly from the inner surface 134 only pat (tally into the cavity 136 defined by the joint sleeve 102. Alternatively, as shown in FIG. 0, liter divider 1N4 may be configured lu extend from the inner surface 134 throughout the entire cavity 13b so as to divide the cavity 13b into two separate cavities 10046J Referring now to FIG. 7, there is illustrated a perspective view of a lip assembly 2 () 0 in accordance with aspects of In general, ihc lip assembly 2tl () may include a joinl sleeve 202 and a lip section 200, the joint sleeve 202 may generally be configured similar to the joinl sleeve 102 described above with reference to FIGS. Thus, joint sleeve 202 may define a cavity 13b [FIG. 4) extending between a tip end 240 and a root end 23 H of the joinL sleeve 202. The pern ion oflhe cavity 130 defined at the tip end 240 may generally be configured to receive a joinl end 231 of the lip section 206. F or example, the joint sleeve 202 and the joinl end 231 of the dp section 206 may define corresponding tapered profiles such that the joint end 231 may be inserted into the joint sleeve 202 and aided therein using a plurality of fasteners 242, In addition, the joint sleeve 202 may define an aerodynamic profile generally corresponding to the aerodynamic profile of the lip section 206. As such, when the lip scclion 2 () 6 is inscrled within the join sleeve 202, the tip assembly 200 may generally define a subsi l L He has continuous aerodynamic profile between the joint sleeve 202 and the Lip section 206. I () (general71 In general, the lip section 206 mny exlend from the joint end 23 I io a blade tip 2 10 titid may have any yuilablt: tip coiifigurHlLort known in the art. For exam μ, in one embodiment, the tip seal 206 may be configured as a straight tip section, such as by being configured similar to the second blade section 106 described above with reference to FIGS. 2 and 3 and extending substantially. spamwise dircciion between the joint end 231 and the blade tip 2 10. In another embodiment, shown in FIG. 7, (he up section 206 may be configured as a wing let-type tip section. As such, a wing let 290 may generally be defined between the joint end 231 and the blade tip 2 10. It should be appreciated that the wing let 290 may have any suitable configuration know n in the an. For example, ihe winglct 290 may have configured ns n suction side wing let or additionally, the wing let 290 mny define any suitable sweep angle, cam angle, loc angle and / or twist angle, all of which arc commonly known terms in the aero dynamic an. Kiuther, the wing let 290 may define tiny suitable radius of curvature and may have any suitable aspect ratio (i.s .. ratio of the span of the wing let 290 to the planform area of the wing let 290}.
    I 004 KJ It should be appreciated that the disclosed tip assembly 200 may generally be configured as a replaceable tip lor a rotor blade. Thus, the tip assembly 200 may be configured to be all acltcd lo any suilahle iithoard blade scgmcnl or section of a rotor blade. For example. Ihe portion of (he cavity 136 (FIG. 4) defined al (lie tool end23of the joint sleeve 202 may be configured to receive an end not shown) of an inboard binding section (not shown), such as by being configured to receive the joint end 130 of the first blade section 104 described above with references Lo KIGS 2-6_ Thus, in one embodiment, the end of the inboard blade section may be formed, machined or otherwise shaped so as to define a tapered profile corresponding to a tapered profile defined in the cavily 136 al ihe root end 23K such that ihe blade section may be inserted into the joint sleeve 202. Similar <o the embodiments described above, 1 he blade seel ion may be attached within the joint sleeve 202 using a plurality of loaders 242 inserted through the openings 244 defined along the root end 23X 100491 Tins written description uses examples Lo disclose the invention, including the best mode, and also enable any person skilled in the art to practice the invention, including The making and use of any devices or systems performed by any incorporated me. The paten table scope of the invem ion is delineated by the claims, LLiid inuy include other examples that occur to those skilled in the art. Such oilier examples are intended to be within the scope of the claims if they include structural elements that do not differ from the literal l.inyuas'e of the claims. or If they include equivalent structural elements with msubsianiial differences from the literal latiituaycs often he claims.
    权利要求:
    Claims (11)
    [1] 2. The rnlor blade assembly (100) of claim I, wherein ihc second blade section ί 106) is configured as a lip section of (he rolor blade assembly (100)
    [2] 3. Lite rotor blade assembly ([()0) of claim 2. wherein the tip section defines a witiglet ¢290).
    [3] 4. The rotor blade assem bly (I DO) of claim I, wherein a tapered profile is defined at the joint ends (130, 131) of Lhe first and second blade sections (104, 106), ihc joint sleeve (102) defining a tapered width (162) generally corresponding to the tapered profile.
    [4] 3. The rotor blade assembly (100) of claim ls wherein a stepped profile is defined at tin joint ends (13(), 131) of the firsi and second blade sections (104, 106).
    [5] 6. The rolor blade assemhly (100) of claim I, wherein ihc plurality of fasteners ¢142) comprises a plurality of threaded fasteners.
    [6] 7. The rotor blade assembly (100) of claim 6, further comprising a plurality of threaded members (174) disposed at the joint ends (130, ] 31) of the firsl and second blade sections (104. lOb). ihc pluralily οΓ threaded, members (174) being eon figured lo receive llie plurality of threaded fasteners. N. Tire rotor blade assembly (10(1) of claim l, further comprising a plurality of openings (144) defined between the inner and outer surfaces (1 44. I 4it) of the joini sleeve (107). each of'thc plumliiy of openings (144) defining a recessed feature (170) configured Lo recess the plurality of fasteners (142) within the joint sleeve (1 ()2) (λ The rotor blade assembly (1()(1) of claim l, further comprising a divider ί 1 K4) configured lo separate the joint ends i 130, 131) of the first and second blade sections (104. KJii) wilhin the cavily (136)
    [7] 10. A joinL sleeve (102) for assembling together a first blade seel ion (1()4) and a second blade section (100) of a roior blade assembly (I <M0, Ihc sleeve (1 02) comprising. an outer surface (140): an inner surface (134) defining a cavily f 13(0, (be cavity (130) having a root end (13fi) configured to receive a joint end (130) of the first blade section (10Ί) and a tip end (14(1) configured to receive a joim cud < L31) oJ the second blade section [ 10b); and. a plurality o['openings (144) defined between the outer and inner surfaces (140, 134). the plurality of openings (144) being configured lo receive a plurality οΓ fasteners (142) for securing the joint ends (130. 131) of the first and second blade sections (104, 100) within I he cavity (136), wherein a profile of the outer surface (146) is configured to generally correspond to an aerodynamic profile of the lirsi and second blade sections (104, 100) such that a substaniially continuous aerodynamic profile is defined beiween I he lirs.1 and second blade sections (1()4. 100} when the joini ends (130, 13 I) are inserted within (he cavily (130), It. A tip assembly [2()0) for a rotor blade (1 f>) of a wind turbine [ 1(f). the Lip assembly (2((()) comprising: a jo ml sleeve (202) including an inner surface (134) defining a cavity (I3(i| and an outer surface (146) defining an aerodynamic profile, the joini sleeve (2(12) further including u lip end (240) and ti tool end (23f<), a lip seel ion (206) cxi ending between a.joint end (231) and a blade lip (210) und defining tm aetodymuuic profile generally corresponding (o (he aerodynamic profile of (he joint sleeve (2((2) at (he tip end (240), the joint end (231) ofthe tip seel ion t!W>) being disposed wiihin the cavity (1 and. a plurality of fasteners (242) configured 10 secure ihe joint end (231) of the lip section (206) within the cavity {136). wherein a pen ion of the cavity (136) disposed at the root end (2.¾) of ihe.ioint sleeve ¢2()2) is configured (o receive an end of a separate section of the rotor blade [ 16).
    [8] 12 The tip assembly (20()) of claim I I, wherein the tip seel ion (206) defines a wmgleL (290).
    [9] 13 The tip assembly (2(H)) of claim I I, wherein a i ape red pro file is defined at the joint end (231) of the tip section (206), the joint sleeve (202) defining a tapered width (162} generally corresponding to the tapered profile.
    [10] 14. The tip assembly (200) of claim 11, further comprising a plurality of openings (244) defined along the lip end (240) of the joint sleeve (202} and configured to receive the plurality of fast eners (242), each of the plurality of openings (244) defining a recessed feature (17()) configured lo recess the plum lily of fhsl eners (242) wiihin 1 lie joint sleeve (2()2),
    [11] 15. The tip assembly (200) of claim 11, further comprising a plurality οΓ openings (244) defined along (he root end (23((} of (he joint sleeve (202), the plurality of openings ¢244) being configured to receive a plurality of fasteners (242) for securing the end of the separate section of the rotor blade (16) wiihin the cavity (136).
    类似技术:
    公开号 | 公开日 | 专利标题
    DK201170668A|2012-06-09|Joint sleeve for a rotor blade assembly of a wind turbine
    DK178056B1|2015-04-20|Joint design for rotor blade segments of a wind turbine
    EP2843227B1|2016-06-15|Method for installing a shear web insert within a segmented rotor blade assembly
    ES2757525T3|2020-04-29|Blade insert for a wind turbine rotor blade
    EP2249027A2|2010-11-10|Segmented wind turbine blades
    US8393871B2|2013-03-12|Wind turbine blade shear web connection assembly
    US20120141287A1|2012-06-07|Wind turbine rotor blade joint
    EP2634418B1|2021-03-31|Blade insert for a wind turbine rotor blade and related methods
    US8622707B2|2014-01-07|Root attachment for a rotor blade assembly
    EP3085952A1|2016-10-26|Airflow configuration for a wind turbine rotor blade
    US9638164B2|2017-05-02|Chord extenders for a wind turbine rotor blade assembly
    US10495058B2|2019-12-03|Joint assembly for rotor blade segments of a wind turbine
    US20170145986A1|2017-05-25|Custom fit blade tip for a rotor blade assembly of a wind turbine and method of fabrication
    US20140169978A1|2014-06-19|Rotor blade assemblies and methods for assembling the same
    EP2728169A2|2014-05-07|Structural members for a wind turbine rotor blade
    US10760544B2|2020-09-01|Sealing members for jointed rotor blade assemblies
    US10920743B2|2021-02-16|Misaligned spar cap scarf joint connection
    US20220065218A1|2022-03-03|Segmented rotor blade having maximized overall pre-bend via an increased pre-bend in a blade tip segment thereof
    US20220065219A1|2022-03-03|Jointed rotor blade having a chord-wise extending pin supported via one or more structural members
    US20220010767A1|2022-01-13|Wind turbine jointed rotor blade having a hollow chord-wise extending pin
    KR101541067B1|2015-08-03|Blade for wind turbine
    EP3642477A1|2020-04-29|Sealing members for jointed rotor blade assemblies
    同族专利:
    公开号 | 公开日
    US20110243736A1|2011-10-06|
    CN102536634A|2012-07-04|
    DE102011056176A1|2012-06-14|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    DK178555B1|2010-12-15|2016-06-13|Gen Electric|Wind turbine rotor blade|DE2921152C2|1979-05-25|1982-04-22|Messerschmitt-Bölkow-Blohm GmbH, 8000 München|Rotor blade for wind power plants|
    US5354175A|1992-03-16|1994-10-11|Northern Power Systems, Inc.|Wind turbine rotor hub and teeter joint|
    US5375324A|1993-07-12|1994-12-27|Flowind Corporation|Vertical axis wind turbine with pultruded blades|
    DE19962989B4|1999-12-24|2006-04-13|Wobben, Aloys, Dipl.-Ing.|Rotor blade for wind turbines|
    DK175275B1|2002-03-19|2004-08-02|Lm Glasfiber As|Transition area in wind turbine blade|
    DE10235496B4|2002-08-02|2015-07-30|General Electric Co.|Method for producing a rotor blade, rotor blade and wind energy plant|
    DK1583904T3|2003-01-02|2013-12-16|Wobben Properties Gmbh|Wind turbine rotor blade with reduced acoustic emission|
    DE102004007487A1|2004-02-13|2005-09-01|Aloys Wobben|Rotor blade of a wind turbine|
    CN100410531C|2004-05-13|2008-08-13|株式会社Ipb|Support arm installation structure for vertical axis wind wheel, and vertical axis wind wheel|
    EP1761702B1|2004-06-30|2011-11-23|Vestas Wind Systems A/S|Wind turbine blades made of two separate sections|
    US7690895B2|2005-07-29|2010-04-06|General Electric Company|Multi-piece passive load reducing blades and wind turbines using same|
    AU2007336537B2|2006-12-22|2011-05-26|Vestas Wind Systems A/S|Wind turbine with rotor blades equipped with winglets and blades for such rotor|
    US7891947B2|2008-12-12|2011-02-22|General Electric Company|Turbine blade and method of fabricating the same|
    US7988421B2|2009-03-31|2011-08-02|General Electric Company|Retrofit sleeve for wind turbine blade|US8876036B2|2011-03-08|2014-11-04|Textron Innovations Inc.|Reconfigurable rotor blade|
    DE102012103704A1|2011-04-30|2012-10-31|General Electric Co.|Winglet for a rotor wing of a wind turbine|
    US20120141287A1|2011-08-29|2012-06-07|General Electric Company|Wind turbine rotor blade joint|
    DE102011088025A1|2011-12-08|2013-06-13|Wobben Properties Gmbh|Rotor blade for horizontal axle wind turbine, has anchoring element anchored in blade outer part, counter element anchored in blade inner part, and connecting bolts reaching through counter element and fastened in anchoring element|
    IN2012DE00572A|2012-02-29|2015-06-05|Gen Electric|
    IN2012DE00573A|2012-02-29|2015-06-05|Gen Electric|
    US9086053B2|2012-03-30|2015-07-21|General Electric Company|Enhanced wind turbine blade|
    CN102926945B|2012-11-13|2014-10-29|中国科学院工程热物理研究所|Multi-segment wind turbine blade connected by U-shaped strengthening devices and assembling method thereof|
    US9399919B2|2012-12-31|2016-07-26|General Electric Company|Extension tip sleeve for wind turbine blade|
    US9790919B2|2014-02-25|2017-10-17|General Electric Company|Joint assembly for rotor blade segments of a wind turbine|
    CN106164476B|2014-04-07|2020-08-07|乌本产权有限公司|Rotor blade for a wind turbine|
    EP3142923B1|2014-05-15|2020-05-06|Sikorsky Aircraft Corporation|Metallic dimpled doubler|
    EP2952739A1|2014-06-05|2015-12-09|Siemens Aktiengesellschaft|A root bushing for a blade root of a wind turbine rotor blade, a blade root, a wind turbine rotor blade and a wind turbine|
    GB2527035A|2014-06-05|2015-12-16|Vestas Wind Sys As|Improvements relating to wind turbine blades|
    DK3088295T3|2015-04-28|2019-09-23|Kongsberg Maritime CM AS|MODULAR PROJECT UNIT NOZZLE|
    US9869297B2|2015-05-07|2018-01-16|General Electric Company|Attachment method and system to install components, such as vortex generators, to a wind turbine blade|
    US9869296B2|2015-05-07|2018-01-16|General Electric Company|Attachment method and system to install components, such as tip extensions and winglets, to a wind turbine blade|
    US9869295B2|2015-05-07|2018-01-16|General Electric Company|Attachment method to install components, such as tip extensions and winglets, to a wind turbine blade, as well as the wind turbine blade and component|
    CN107873070B|2015-05-20|2020-11-03|布拉德纳公司|Wind turbine and wind turbine blade|
    US10100805B2|2015-10-12|2018-10-16|General Electric Compant|Tip extension assembly for a wind turbine rotor blade|
    US20170145986A1|2015-11-25|2017-05-25|General Electric Company|Custom fit blade tip for a rotor blade assembly of a wind turbine and method of fabrication|
    CN106884759A|2015-12-16|2017-06-23|北京博比风电科技有限公司|A kind of blade synergy design for low wind speed area wind power generating set|
    GB2547957A|2016-05-24|2017-09-06|Airbus Operations Ltd|Winglet|
    US10451030B2|2016-05-27|2019-10-22|Blade Dynamics Limited|Wind turbine blade and a method of assembling a wind turbine blade and a spar cap connection piece|
    US10760544B2|2016-06-20|2020-09-01|General Electric Company|Sealing members for jointed rotor blade assemblies|
    US10443579B2|2016-11-15|2019-10-15|General Electric Company|Tip extensions for wind turbine rotor blades and methods of installing same|
    EP3333416A1|2016-12-07|2018-06-13|LM WP Patent Holding A/S|A wind turbine blade comprising two blade parts and an aero-dynamic sleeve|
    EP3339640A1|2016-12-21|2018-06-27|Vestas Wind Systems A/S|Control system for a wind turbine|
    US11098691B2|2017-02-03|2021-08-24|General Electric Company|Methods for manufacturing wind turbine rotor blades and components thereof|
    US10830206B2|2017-02-03|2020-11-10|General Electric Company|Methods for manufacturing wind turbine rotor blades and components thereof|
    US10495058B2|2017-02-21|2019-12-03|General Electric Company|Joint assembly for rotor blade segments of a wind turbine|
    US10563636B2|2017-08-07|2020-02-18|General Electric Company|Joint assembly for a wind turbine rotor blade|
    US10961982B2|2017-11-07|2021-03-30|General Electric Company|Method of joining blade sections using thermoplastics|
    US11215161B2|2017-11-13|2022-01-04|Wichita State University|Retrofit winglets for wind turbines|
    US10821652B2|2017-11-21|2020-11-03|General Electric Company|Vacuum forming mold assembly and method for creating a vacuum forming mold assembly|
    US11040503B2|2017-11-21|2021-06-22|General Electric Company|Apparatus for manufacturing composite airfoils|
    US10913216B2|2017-11-21|2021-02-09|General Electric Company|Methods for manufacturing wind turbine rotor blade panels having printed grid structures|
    US10920745B2|2017-11-21|2021-02-16|General Electric Company|Wind turbine rotor blade components and methods of manufacturing the same|
    US10773464B2|2017-11-21|2020-09-15|General Electric Company|Method for manufacturing composite airfoils|
    US10865769B2|2017-11-21|2020-12-15|General Electric Company|Methods for manufacturing wind turbine rotor blade panels having printed grid structures|
    US11248582B2|2017-11-21|2022-02-15|General Electric Company|Multiple material combinations for printed reinforcement structures of rotor blades|
    CN108150344A|2017-12-25|2018-06-12|江苏金风科技有限公司|For the denoising structure, blade and wind power generating set of wind generator set blade|
    US10821696B2|2018-03-26|2020-11-03|General Electric Company|Methods for manufacturing flatback airfoils for wind turbine rotor blades|
    US11035339B2|2018-03-26|2021-06-15|General Electric Company|Shear web assembly interconnected with additive manufactured components|
    CN113137347A|2021-05-08|2021-07-20|上海电气风电集团股份有限公司|Fan sectional type blade connecting structure, fan sectional type blade and manufacturing process|
    CN113339190B|2021-08-04|2021-11-16|常州市宏发纵横新材料科技股份有限公司|High-strength connecting structure and sectional type wind power blade|
    法律状态:
    2014-07-21| PHB| Application deemed withdrawn due to non-payment or other reasons|Effective date: 20131231 |
    优先权:
    申请号 | 申请日 | 专利标题
    US96315910|2010-12-08|
    US12/963,159|US20110243736A1|2010-12-08|2010-12-08|Joint sleeve for a rotor blade assembly of a wind turbine|
    [返回顶部]