Abstract: A composite member comprises first and second elongate composite elements. Each has a wedge shaped end with a complimentary tapered end surface. At least one of the components is formed of a stack of fiber layers impregnated in resin, with the tapered end surface being formed by each fiber layer extending longitudinally progressively further than the adjacent layer towards the thin end of the wedge at which the fiber layers have the greatest longitudinal extent. The components are joined at their tapered ends by an adhesive, and the properties of the cured composite material of the at least one component and/or the properties of the adhesive are different in the vicinity of the thin end of the wedge as compared to the rest of the tapered surface in order to reduce the stress concentrations in this region.

Abstract: An aircraft including a primary-structure connection element for attaching the aircraft skin to the primary structure of the aircraft is provided. The primary-structure connection element is designed as a shearweb, a clip and/or as a frame stabilization element or as a rib stabilization element and is manufactured from a fiber-reinforced thermoplastic material with the use of injection molding. Likewise, an injection molding method for the manufacture of such a primary-structure connection element is provided, in which method the fiber-reinforced thermoplastic material is injected in its melted state into an injection molding device. The manufactured shearweb etc. is removed from the injection molding device. In this method, in particular, chopped carbon fibers and/or glass fibers in combination with polyphenylene sulfide (PPS) and/or polyetherether ketone (PEEK) are used, for example also in pellet form.

Abstract: A rotor blade for a wind turbine, having a longitudinal rotor blade base body extending in a longitudinal axis, with the rotor blade base body defining a leading edge and a trailing edge of the rotor blade is provided, wherein the rotor blade base body has a number of panel elements, wherein at least one panel element includes at least one stiffening structure member embedded within the at least one panel element.

Abstract: A wind turbine rotor blade (14) comprising a root portion (15) having a substantially cylindrical shape and a longitudinal axis (22), the root portion having a mounting face (25); a plurality of bores (26) in a wall of the root portion and extending from the mounting face into the root portion, the bores being configured to receive respective connecting means for connecting the wind turbine rotor blade to a wind turbine hub; wherein the plurality of bores are inclined at an angle relative to the longitudinal axis of the root portion to define a cone angle.

Abstract: A rotor blade of a wind power installation for fixing to a rotor hub and having a rotor blade longitudinal axis, including a rotor blade inner part towards the rotor hub, and a rotor blade outer part away from the rotor hub, wherein the rotor blade inner part and the rotor blade outer part are connected together by means of at least one connecting device and the connecting device includes at least one anchoring element anchored in the rotor blade outer part, at least one counterpart element anchored in the rotor blade inner part, and at least one connecting bolt which extends through the counterpart element and is fixed in the anchoring element.

Abstract: A wind turbine rotor blade is bonded together at the leading and trailing edges, and including a shear web or webs (the main vertical stiffening member that runs the span of the rotor blade) as an integral part, sharing the inner and outer skins of one or both sides of the blade. The integrated shear web(s) is made into the skin shell, and is an uninterrupted, continuous extension of the shell laminate that is joined to the shell component/components without requiring a secondary bond of any sort. The laminates in the shell and the shear web(s) may differ or be the same.

Abstract: The present invention relates to a blade for a wind turbine comprising at least a longitudinal component comprising at least two longitudinal stretches with fibers at different orientations depending on the location of these stretches along the blade, where the orientation of the fibers in the stretches of the blade is adapted to the prevailing load states in each of the stretches.

Abstract: A tiltrotor aircraft includes a fuselage, a wing member extending from the fuselage, an engine disposed relative to the wing member, a rotor hub assembly mechanically coupled to the engine and a plurality of proprotor blade assemblies rotatably mounted to the rotor hub assembly and operable for beamwise folding relative thereto. The proprotor blade assemblies each including a spar and a sheath extending spanwise along a leading edge of the spar. The spar has a root section, a main section and a tip section. The spar has a generally oval cross section at radial stations along the main section of the spar with the root section of the spar forming an integral tang assembly operable for coupling the spar to the rotor hub assembly.

Abstract: A wind turbine blade comprising a fairing with a rigid structural component (12) which forms the majority of the aerodynamic profile and a non-actively controllable elastically deformable trailing edge component (14) mounted on the structural component to complete the aerodynamic profile. The trailing edge component (14) is formed from a material having an elastic modulus in the range of 0.5 to 2.5 GPa such it will elastically buckle when loading on the trailing edge component exceeds a predetermined threshold. The structural component (12) comprises a unidirectional reinforcing layer adjacent to the trailing edge component with at least one layer of unidirectional fibers (26) extending in a substantially spanwise direction.

Abstract: A wing or blade in at least two sections facing each other. Each section has a longitudinal bearing structure provided with at least one sole of which the link between the sections includes at least one first link plate linking the end of the soles of the sections facing each other. A method of producing such wing or blade.

Abstract: A method of fabricating a blade spar that includes transversely at least one arrangement. A pressure-side mold and a suction-side mold are defined for each arrangement that is to be fabricated. Each mold includes at least one removable slide and a base. Each slide is then removed from a mold and the tape segments of a hank are laid by a fiber-placement method on each mold. Each mold is closed by putting the slides into place on the mold. During a finalizing step, the molds are juxtaposed and the spar is heated.

Abstract: A method for manufacturing a rotor blade, including: a) arranging a first layup of fiber material inside a mold, the first layup corresponding to an airfoil of the rotor blade, b) arranging a second layup of fiber material on a core member before and/or after arranging the core member in the mold, the second layup including the core member corresponding to a web of the rotor blade, the core member comprising a recess configured to ensure a smooth transfer of loads into and out of the web, and c) curing a resin impregnating the fiber material of the first and second layup to form the rotor blade.

Abstract: A method of repairing a core stiffened structure, including removing a damaged portion of the core stiffened structure; bonding a shelf onto a first core member; bonding a second core member to a shelf; and securing a skin patch over the second core member.

Abstract: A spar cap for a rotor blade of a wind turbine is disclosed. The rotor blade includes a blade root and a blade tip, leading and trailing edges, pressure and suction sides, and at least one spar cap configured on an internal surface of either or both the pressure or suction sides. The spar cap includes one or more layers of a first material and a second conductive material contacting at least one of the layers of the first material. Further, the conductive material is different than the first material. Thus, the conductive material is configured with the first material so as to create an equipotential spar cap.

Abstract: A hybrid turbine blade having a box beam assembly structure and method of designing such a hybrid turbine blade are disclosed. The box beam assembly provides the primary structure for supporting loads on the blade, and comprises oppositely positioned spar caps joined by oppositely positioned shear webs. For a portion of the blade, the box beam assembly further comprises a root buildup. In one embodiment, the shear webs comprise foam core sandwiched between two biaxial fiber-reinforced plastic laminates (FRP), the spar caps comprise uniaxial FRP laminates, and the root buildup comprises triaxial FRP laminates. The blades are designed using a novel inside-out method, wherein the box beam is first designed to support expected loads, and an aerodynamic surface is then designed to be supported by the box beam. The blade may be constructed in segments that are joined with connectors that engage the box beam structure.

Abstract: Methods of manufacturing rotor blade components for a wind turbine and rotor blade components produced in accordance with such methods are disclosed. In one embodiment, the method generally includes providing a mold of the rotor blade component; coating at least a portion of an interior surface of the mold with an elastomeric material; inserting impletion material within the mold so as to at least partially reduce an open internal volume within the mold; inserting a foam material within the mold; and, removing the rotor blade component from the mold, wherein the elastomeric material forms a cover skin around at least a portion of the rotor blade component. In an alternative embodiment, the method includes providing at least one support member defining a profile for the rotor blade component on a mold surface; coating at least a portion of the support member with an elastomeric material; and, allowing the elastomeric material to cure on the mold surface so as to form the rotor blade component.

Abstract: Disclosed is a drone having at least one rotor. The at least one rotor comprises a mast and at least two blades having a proximal end and a distal end. The at least two blades are arranged in connection with the mast by their proximal ends. The at least one of the blades comprises an electrically conductive element extending a distance D between its distal end and its proximal end. The electrically conductive element is electrically coupled with means for stopping the blades, thus forming an electrical circuit. The means for stopping the blades is arranged to be actioned when at least one electrical property of the electrical circuit change.

Abstract: A wind turbine rotor blade assembly and associated method include a rotor blade having a pressure side, a suction side, a leading edge, and a trailing edge extending in a generally span-wise direction between a tip and a root. An edge extension panel is attached along either of the leading edge or trailing edge (or along both edges) in a generally span-wise direction from adjacent the root towards the tip. The edge extension panels include a cured and hardened viscous material continuous core formed onto the leading or trailing edge with a contoured generally aerodynamic outer surface.

Abstract: It is described a blade for a wind turbine for converting wind energy into electric energy, including: a blade structure longitudinally extending along a blade axis (X1) and including a blade tip, an opposite blade root, a longitudinal leading edge portion and a longitudinal trailing edge portion which are extended between the blade root and the blade tip; and an outer aerodynamic shell defining an airfoil including an airfoil leading edge, an airfoil trailing edge and an airfoil suction side and an airfoil pressure side between the airfoil leading and trailing edges.

Abstract: A blade (10) for a rotor of a wind turbine having a profiled contour divided into: a root region (30), an airfoil region (34), and a transition region (32) between the root region (30) and the airfoil region (34). A shoulder (40) is located at the boundary between the transition region (32) and the airfoil region (34). The blade's profiled contour comprises a local relative thickness defined as the local ratio between a maximum profile thickness (t) and the chord length (c). The ratio between the shoulder width (W) and the blade length (L) being less than or equal to 0.075, and the relative thickness (t/c) in a blade length interval of 0-0.8 L is at least 22%.

Abstract: Tapered layers of pre-cured composite material are integrated into a tapered, highly stressed laminate structure in order to provide improved compressive strength. The pre-cured composite material can advantageously be cured under tension as pultruded material, to further augment compressive strength. The thickness of composite layers can be tapered on their termination edges by mechanically abrading, chemical abrading, or other methods. Especially preferred embodiments include aircraft structural components such as wings, wing spars, wing skins, fuselage skins, rotor blades, propellers, and propeller blades. Preferred laminates can be constructed to have at least 6, 10, 30, 50, or 100 layers of material, and can have a maximum thickness of at least 0.15, 0.25, 0.5, 1.0, or 5.0 inches.

Abstract: A fluid turbine blade and method of fabrication are provided. The fluid turbine blade includes a centrally disposed longitudinal spar having a substantially circumferential cross section. The fluid turbine blade also includes at least one chord stiffener coupled to the longitudinal spar. The fluid turbine blade further includes a torsionally compliant segmented skin coupled to the at least one chord stiffener. The centrally disposed longitudinal spar and the torsionally compliant segmented skin are functionally decoupled to relieve the torsionally compliant segmented skin of one or more of a flapwise load condition, an edgewise load condition and a torsional load condition.

Abstract: A blade comprises a lightweight core, a composite material disposed on the core, and a skin located on the composite material. The composite material comprises fibers incorporated into a thermoplastic resin matrix in the form of a prepreg sheet or wet layup. The rotor blade may also comprise a front edge member attached along at least a portion of a leading edge of the core, a rear edge member attached along at least a portion of a trailing edge of the core, and a skin located over the core, the front edge member, and the rear edge member. The rotor blade may also comprise a spar extending through the core along a longitudinal axis of the rotor blade, and a skin located over the core and the spar. The edge members and the spars may be fabricated from thermoplastic material.

Abstract: A method for installing a shear web insert between a blade segment and a blade insert of a rotor blade assembly is disclosed. The blade segment may include a first shear web and the blade insert may include a second shear web. The method may generally include coupling a first positioning device along an inner surface of a first side of the rotor blade assembly, inserting the shear web insert horizontally between the first and second shear webs until a first side face of the shear web insert engages the first positioning device and coupling a first retention device along the inner surface of the first side of the rotor blade assembly so that the first retention device is positioned adjacent to a second side face of the shear web insert, wherein the second side face is opposite the first side face.

Abstract: A rotor blade for an aircraft includes a composite portion having fiber-reinforced resin material, the composite portion having an outside surface that forms at least a partial airfoil shape. The weighted portion includes a plurality of weighted material layers and a plurality of fiber-reinforced resin material layers. Weighted material is configured to be compatible with and integrated into composite manufacturing processes used to fabricate the rotor blade. The weighted portion has a higher density than the composite portion and positioned to produce desired mass balance characteristics of the rotor blade.

Abstract: The invention relates to a propeller blade which comprises a hollow casing (1) forming an extrados (5) and an intrados (4) which extend from a blade shank to a free end in the direction of the span, and a framework which is arranged in the hollow casing (1) and comprises a box spar (8), having a plurality of soles (9a, 9b, 10a, 10b) in surface contact with the hollow casing (1) so as to provide structural support for the hollow casing (1), and at least two cavities (15, 16) which are spaced apart in the direction of the chord (25), wherein the propeller blade further comprises at least two reinforcing spars (6, 7) which extend between the framework and the hollow casing.

Abstract: A method of the present disclosure includes of repairing a core stiffened structure with structural foam. Another method includes splicing core members together using structural foam. Another method includes joining a core member to a structure using structural foam. Another method includes using structural foam to stabilize a core member during a machining process. Another method includes stabilizing a core member with structural foam to prevent the core member from crushing in autoclave pressure. The present disclosure further includes a core stiffened structure have a core member with structural foam therein.

Abstract: A blade (1) provided with a fitting (2) for fastening to a hub and with an airfoil element (10) having a spar (20) extending spanwise from an attachment zone (21) towards a distal zone (22), said attachment zone (21) surrounding a centrifugal force transmission bushing (31) that is connected to said fitting (2) by a through pin (3). The blade comprises a twisting force transmission member (40) provided with a first half-shell (41) and with a second half-shell (42) that together surround said attachment zone (21), each half-shell (41, 42) having a perforated first portion (43?, 43?) giving visual access to said bushing (31) when said airfoil element is removed from the fitting, and a second portion (44?, 44?) co-operating with a torsion box (50) surrounding said distal zone (22), said transmission member (40) being secured to said fitting in rotation about a torsion axis (AX) of the blade (1).

Abstract: A modular fiber reinforced plastic flange for a structural composite beam which comprises a body formed of a plurality of elongate elements arranged in an array, wherein the dimensions of the body are substantially determined by the number and arrangement of the elongate elements in the array, and a skin member at least partially surrounding the array. Also, a structural composite beam comprising the modular fiber reinforced plastic flange and a shear web connected to the skin member of the modular flange. A method of making the modular flange and beams, and a kit of parts for making the modular flange are also disclosed.

Abstract: A method and apparatus for reducing a vibratory response in a structure using a tuning object. A selected mass may be identified for the tuning object. A plurality of channels may be formed in a workpiece having a mass greater than the selected mass to form the tuning object having the selected mass. The tuning object may be bonded to the structure using an adhesive bond to reduce the vibratory response of the structure.

Abstract: An airfoil includes, among other possible things, a main body extending between a leading edge and a trailing edge. Channels are formed into the main body, with a plurality of ribs extending intermediate the channels. A cover skin is attached to the main body. The cover skin is welded to the main body at outer edges. An adhesive is placed between inner surfaces of the cover skin and the main body. The adhesive is deposited inwardly of the outer edges of the cover skin.

Abstract: A wind turbine blade may include a plurality of longitudinal composite members each having a fiber and resin layer around a predetermined cross-sectional shape and each comprising at least one longitudinal outer surface and at least one longitudinal mounting surface, each of the outer surfaces of the plurality of longitudinal composite members corresponding to a different portion of a desired airfoil shape, the plurality of longitudinal composite members assembled such that the outer surfaces of the composite members form at least a majority of the airfoil shape. An outer skin may be provided. The composite members may be made up of transportable segments. A method of assembly may include transporting the segments to a desired location such as an installation site for assembly of the wind turbine blade at the installation site.

Abstract: A propeller blade includes a foam core having a slot formed through it from a camber side to a face side, an internal stiffener disposed through the slot and including flanges in contact with both the camber and face sides and a structural layer that surrounds at least a portion of the foam core and in contact with the flanges on both the camber and face sides.

Abstract: A method and apparatus comprising a composite spar. The composite spar has a root section and a main section. The root section is closed and has a shape configured to be connected to a blade retention system. The main section has an open channel. The composite spar is configured for placement inside of a blade.

Abstract: Apparatus and methods are disclosed for manufacture of a composite rotor blade spar having non-uniform wall thickness. Tooling for manufacturing include a first mold defining a first mold surface and a second mold comprising a rigid layer and a heated layer secured to the rigid layer and defining a second mold surface. A plurality of heating elements embedded in the second mold are activated according to a plurality of different temperature progressions effective to cure portions of the uncured composite blade spar positioned between the first and second mold surfaces coextensive with each heating element of the plurality of heating elements. In some embodiments, the second mold defines a root portion and first and second branch portions. A shear web is placed between the first and second branch portions and is bonded to a blade spar skin surrounding the second mold during curing of the blade spar skin.

Abstract: The invention relates to a rotor blade for a wind turbine. The rotor blade comprises a shell and a spar forming a longitudinally extending hollow structure within the shell and comprising: a leading web, a trailing web, and one or more additional webs. Each additional web defines an intermediate portion between a hub end and a tip end. The intermediate portion of each additional web is spaced apart from the leading and trailing webs and at least one of the tip and the hub ends is connected to or integral with the leading or the trailing web. The invention further relates to a wind turbine comprising the rotor blade, and a method for manufacturing the rotor blade.

Abstract: A rotor blade (1) provided with an outer covering (2) and with at least one load take-up spar (10) associated with at least one pin-receiving bushing (3). Each spar (10) is a compartmentalized spar comprising centrifugal force take-up means (20) incorporated within a twisting stress take-up casing (30), said centrifugal force take-up means (20) comprising at least two boxes (21, 22), each having said pin-receiving bushing (3) of the spar (10) passing therethrough, each box (21, 22) including a closed retention belt (23) extending in the spanwise direction of the blade, the retention belt (23) of one box (22) surrounding the retention belt (23) of another box (21), each retention belt (23) being provided with unidirectional fibers (24) wound around said pin-receiving bushing (3), said casing (30) being provided with inclined fibers (31) presenting an angle relative to said unidirectional fibers (24).

Abstract: Wind turbine rotor blades with a reduced radar cross sections include a shell having a leading edge opposite a trailing edge, a structural support member that supports the shell and is disposed internal the wind turbine rotor blade between the leading edge and the trailing edge and extends for at least a portion of a rotor blade span length, wherein the structural support member comprises fiberglass, one or more cavities internal the wind turbine rotor blade, and a lightweight broadband radar absorbing filler material disposed in at least one of the one or more cavities to provide the reduced radar cross section.

Abstract: Wind turbine rotor blades include a shell having a leading edge opposite a trailing edge, a structural support member that supports the shell and is disposed internal the wind turbine rotor blade between the leading edge and the trailing edge and extends for at least a portion of a rotor blade span length, and a resistive cellular support structure disposed at least partially about the wind turbine rotor blade that physically supports at least a portion of the wind turbine rotor blade and at least partially absorbs radar energy.

Abstract: An elongate web is attached to the root end of a spar of a wind turbine rotor blade to provide additional support along the width of the blade. The root end is formed by a winding operation, and a recess is then cut into the surface of the spar. The recess is defined by a relatively large first, cylindrical surface, which is coaxial with the longitudinal axis of the root end, and a relatively small second, conical surface. A tapered end of the elongate web is attached within the recess of the root end using a layer of suitable adhesive and an array of pins. Resilient spacer elements are arranged within the recess so as to surround the pins. The large area of the cylindrical surface causes the tensile and compressive stresses which arise along the elongate web in use to be transmitted to the spar as shear stresses.

Abstract: A blade (1) having a working shell (10) defining an inner space (16). The blade has a leading-edge space (31) and at least one filler means (40, 50) in said inner space (16) and a leading-edge fairing (20) protecting the working shell (10). The fairing (20) extends from a pressure-side part (21) to a suction-side part (22) via a central part (23). The working shell (10) has in the first zone (13): a pressure-side portion (131), a central portion (133), and a suction-side portion (132). The pressure-side portion (131) is secured to the pressure-side part (21). The suction-side portion (132) is secured to the suction-side part (22). The blade (10) includes first damper means (60) with damping material.

Abstract: The invention relates to a rotor blade (10) of a wind power plant and a method for fabricating a rotor blade (10) of a wind power plant and a manufacturing mold (54, 50) for a belt (28-31). The invention is characterized by a belt pair (28, 29, 30, 31) in which two belts (28, 29, 30, 31) are connected together in a form-fit and/or force-fit and material fit connection, where the belts (28-31) have a complementary shape in a joining area (50).

Abstract: Prepregs and stacks of prepregs based on reactive epoxy resins that can be cured at lower externally applied temperatures such as from 70° C. to 110° C. with acceptably short cycle times comprise epoxy resins of epoxy equivalent weight from 200 to 500 containing a curing agent but no hardener.

Abstract: A composite assembly has an outer spar component having an outer spar component inner profile, an inner spar component having an inner spar component outer profile substantially complementary to the outer spar component inner profile, and an adhesive disposed between the outer spar component and the inner spar component.

Abstract: A wind turbine blade transversely divided in an inboard module (13) and an outboard module (33) provided on their end sections with connecting means, comprising, respectively, an inboard spar (15), an inboard upper shell (17) and an inboard lower shell (19); an outboard spar (35), an outboard upper shell (37) and an outboard lower shell (39); and arranged so that the aerodynamic profile of said inboard and outboard modules (13, 33) is defined by said upper and lower shells (17, 19; 37, 39), in which the inboard spar (15) is composed of two cap prefabricated panels (21, 23) and two web prefabricated panels (25, 27), and the outboard spar (35) is composed of first and second prefabricated panels (41, 43) integrating its caps (45, 47) and webs (49, 51). The invention also refers to a method of fabricating said wind turbine blade.

Abstract: A rotor blade of a wind power plant in which the rotor blade has a longitudinal extension that extends from a rotor blade root substantially to a rotor blade tip. At least in one region of the rotor blade, an aerodynamic cross-sectional profile is provided, which has a leading edge (nose) and a trailing edge, which are connected via a suction side and a pressure side of the cross-sectional profile. The rotor blade is subdivided at least in a longitudinally extended section into a front rotor blade section with the leading edge and a rear rotor blade section with the trailing edge. The rear region of the front rotor blade section and the adjacent front region of the rear rotor blade section are connected through an I-beam.

Abstract: A fan includes a frame, rotor supported by this frame and having a central hub and a number of blades and a drive mechanism for rotatably driving the rotor, in addition to a ring to which the end zones of the blades are connected. The ring is assembled from two part-rings of the same form which each include a circular strip of sheet material, the free ends of which are mutually connected to form the outer surface of a truncated cone, and a third part-ring which mutually connects the inner edges of the first two part-rings. The end zones of the blades are connected to the third part-ring. The ring has a diameter of more than about 1.50 m. The number of blades amounts to at least eight. The blades are hollow and include a framework structure which is provided with a skin connected thereto.

Abstract: Embodiments of the present application generally provide for wind turbine blade spar caps comprising composite materials prepared using a low viscosity resin system and a high density fabric and methods for their manufacture. In particular embodiment, the low viscosity resin system has a viscosity in the range of about 1 to about 100 centipoises at a temperature in the range of about 0° C. to about 125° C. during the preparation of the composite material. By using low viscosity resin systems, composite materials have been prepared having a fiber volume fraction of greater than about 65% and a composite modulus of greater than 48000 MPa.

Abstract: A rotor blade assembly for a wind turbine, and a method for installing a rotor blade assembly on a wind turbine, are disclosed. The rotor blade assembly includes a rotor blade having exterior surfaces defining an aerodynamic profile including a pressure side and a suction side extending between a leading edge and a trailing edge. The rotor blade further extends in a generally span-wise direction between a root and a tip. The rotor blade assembly further includes a blade extension extending in the generally span-wise direction from the root towards the tip, and a plurality of connection devices connecting the blade extension to the rotor blade. Each of the plurality of connection devices includes a mechanical fastener extending through the root in the generally span-wise direction for connecting the rotor blade to a hub of the wind turbine.

Abstract: A turbine vane for a gas turbine engine may include a composite airfoil structure. The composite airfoil structure may have an opening. The turbine vane may include a spar. The spar may have a body, which may be disposed within the opening. A standoff structure may be disposed within the opening. In some non-limiting embodiments, a cooling air gap may be defined between the body and an internal surface of the composite airfoil structure.