Abstract: This invention relates to a root end structure, a wind turbine blade comprising such a root end structure and a method of manufacturing such a wind turbine blade. The root end structure comprises a plurality of fastening members distributed along a root end of a blade part, wherein a plurality of pultruded elements are arranged in between the fastening members. Each pultruded element has a second side surface facing a first side surface of an adjacent fastening member. Gaps are formed between the first and second side surfaces in at least the thickness direction, wherein the gaps enable an adaptive positioning of the pultruded elements relative to the outer layers during the vacuum assisted resin infusion process.

Abstract: A wind turbine blade includes a plurality of layered sections coupled together end-to-end. Each section includes a side wall that forms a tubular structure and includes at least one bore. When the sections are coupled together, the bores generally align to form a conduit. A strengthening element extends through the conduit and is configured to reinforce the blade under load during use of the wind turbine. A wind turbine includes a tower, a nacelle, and a rotor including a hub and at least one wind turbine blade including a plurality of layered sections extending from the hub. A method of forming a wind turbine blade through an additive manufacturing process is also disclosed.

Abstract: A tailgate, for a motor vehicle, has a main body made from an injection-molded fiber-reinforced plastics material, and at least one fiber-reinforced plastics material tape that is disposed on the main body. In order for a tailgate having improved load transmission and load distribution properties to be provided, the tailgate has at least one additional component which is at least partially embedded in the main body and which has at least one connection portion around which a loop of the fiber-reinforced plastics material tape is guided.

Abstract: An adapter for a rotor blade assembly including a support member having an outboard surface and an inboard surface; an outboard feature extending laterally from the outboard surface of the support member and including a first lug and a second lug; an inboard feature extending laterally from the inboard surface of the support member and including a first arm and a second arm. The outboard feature and the inboard feature are configured such that a plane defined by an attachment surface of at least one of the first lug and the second lug is non-parallel to a plane defined by an attachment surface of at least one of the first arm and the second arm.

Abstract: A turbine vane assembly adapted for use in a gas turbine engine includes an airfoil, an endwall, and a spar. The airfoil is shaped to interact with hot gases moving axially along a primary gas path of the gas turbine engine. The endwall is shaped to define a boundary of the primary gas path near a radial end of the airfoil. The spar is located in an interior region of the airfoil to carry loads that act on the airfoil during operation of the gas turbine engine.

Abstract: A preform for a turbine engine blade, the preform comprising a main fiber preform obtained by three-dimensional weaving and comprising a first longitudinal segment suitable for forming a blade root (21), a second longitudinal segment extending the first longitudinal segment upwards, and suitable for forming an airfoil portion (22), and a first transverse segment extending transversely from the junction between the first and second longitudinal segments, and suitable for forming a first platform (23), wherein the preform also includes at least one stiffener (40) fitted on the main fiber preform along at least a portion of the distal edge of the first transverse segment.

Abstract: The present disclosure is directed to a rotor blade assembly for a wind turbine having a joint assembly securing first and second blade segments together. For example, the joint assembly releasably couples the first and second blade segments together at a chord-wise extending joint and includes at least one set of interlocking components. As such, the joint assembly is movable between a locked position and an unlocked position by engaging and disengaging the interlocking components. Thus, in the locked position, the first and second blade segments are secured together via the interlocking components, and movement from the locked position to the unlocked position, releases the interlocking components, thereby releasing the first and second blade segments from each other.

Abstract: A rotor blade of a wind turbine having a pultruded spar cap is disclosed. The rotor blade includes a blade root and a blade tip. The blade root includes at least one root insert. The rotor blade also includes at least one spar cap constructed of a plurality of pultruded members grouped together to form one or more layers from the blade tip towards the blade root. Further, the pultruded members separate into one or more pultruded member bundles as the spar cap approaches the blade root. The pultruded member bundles fit within the root insert, along with the blade bolts, such that compression and tension loads of the rotor blade are transferred through the pultruded members.

Abstract: A wind turbine rotor hub attachment that extends inside a one-piece two-bladed wind turbine rotor hub, and secures to its shear web(s). This isolates the attachment from the high strains on the hub exterior, and allows balanced loads to flow across the hub, so that only unbalanced air loads and torque, plus net rotor loads such as thrust and weight, are passed across from the rotor to the wind turbine main shaft. This solves the excess motion problem of central teeter hinges, is mechanically simpler, and reduces overall weight and cost compared to the conventional practice of using individual blades bolted to a separate central hub. A method for connecting a one-piece two bladed wind turbine rotor to a main shaft using a strain isolating attachment to the rotor hub shear web(s) is included.

Abstract: Variable length blade tip molds include standard tip mold sections having a tapered profile and variable length joint mold sections having first ends and second ends with a constant cross section, wherein the variable length blade tip molds can each produce a plurality of tip assemblies of various lengths.

Abstract: The rotor hub can include a rotor blade; a rotor yoke; a grip member having an inboard portion, an upper extension, and a lower extension; and a rotor blade having a root end coupled to the upper extension and the lower extension of the grip member with a first bolt, a second bolt, and a third bolt. The first bolt is located on a spanwise axis of the rotor blade. The second bolt is offset from the spanwise axis by a first chordwise distance and is offset from the first bolt by a first spanwise distance. The third bolt is offset from the spanwise axis by a second chordwise distance and is offset from the first bolt by a second spanwise distance.

Abstract: An airfoil includes a main portion formed of a base material. Also included is a trailing edge region of the main portion. Further included is a trailing edge supplement structure comprising at least one pre-sintered preform (PSP) material operatively coupled to the base material proximate the trailing edge region.

Abstract: A blade, in particular a rotor blade or a stator vane, for a gas turbomachine, in particular a turbojet engine, the blade having an airfoil (1) for deflecting a flow of working fluid and a first platform (3) connected thereto, in particular integrally connected thereto, to radially bound a flow duct for the working fluid, the airfoil having a suction side and a pressure side (1.1) which are connected at a leading edge (1.2) and at a trailing edge (1.3). The trailing edge has a first minimum wall thickness in a first region (A) of a radial longitudinal extent (R) of the airfoil proximal to the first platform (3), and a maximum wall thickness that is smaller than the first minimum wall thickness in a platform-distal region (C) of the radial longitudinal extent.

Abstract: A turbojet fan blade in which a leading edge presents a sweep angle greater than or equal to +28° in a portion of the blade that is situated at a radial height lying in a range of 60% to 90% of a total radial height of the blade measured from its root towards its tip, and the leading-edge sweep angle presents a difference of less than 10° between a minimum sweep angle measured at a radial height of minimum sweep angle situated in the portion of the blade lying in a range of 20% to 90% of the radial height of the blade, and a sweep angle measured at a radial height that is 10% greater than the radial height of minimum sweep angle.

Abstract: Vertical axis wind turbines are provided having foil design and geometry that facilitates lift, torque and laminar flow along a 360 degree radial. Contemplated foils are non-planar, and have a chord length that is at least three times greater than a distance between a trailing end of a leading foil, and a leading end of a trailing foil. Additionally or alternatively, the foils are located away from a turbine axis at a distance that is about 2.9-3.5 times greater than a chord length of the foils. In some embodiments, the foils are circumferentially distributed via one or more laminar stall vanes.

Abstract: Rotor blade or rotor blade segment for a wind turbine, having at least one cable for fixing the rotor blade or rotor blade segment to a rotor hub or to a further rotor blade segment, wherein the at least one cable is redirected in a U-shaped manner within the rotor blade or rotor blade segment.

Abstract: One embodiment of the present invention is a unique turbine blade for a gas turbine engine. Another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and turbine blades for gas turbine engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Abstract: Large diameter axial Super Low Noise flow fans and commercial air cooled apparatuses incorporating such fans are provided. The large diameter axial flow fan is mounted on the air cooled apparatus for generating an axial air flow in the air cooled apparatus for accomplishing the cooling. The fan has a diameter of at least four feet. The fan has plurality of blades. Each blade includes a leading edge opposite a trailing edge. The entire of the leading edge of each of the blades is linear and forward swept, and each blade includes a metallic outer surface.

Abstract: A marine surface propeller, and blade therefore, which is surface piercing and partially submerged, and includes a blade geometry that improves distribution of pressure and control to wetted and ventilated regions. Preferably, the feature has a positive step (ramp, cup, interceptor, indent or other geometric addition or intervention) between one fifth and four fifths chord length so as to create a high pressure peak or zone in what is now a low pressure zone on either the blade face or back or both and to create speed controllable wetted and ventilated regions.

Abstract: A squealer tip formed from a pressure side tip wall and a suction side tip wall extending radially outward from a tip of the turbine blade is disclosed. The pressure and suction side tip walls may be positioned along the pressure sidewall and the suction sidewall of the turbine blade, respectively. The pressure side tip wall may include a chamfered leading edge with film cooling holes having exhaust outlets positioned therein. An axially extending tip wall may be formed from at least two outer linear surfaces joined together at an intersection forming a concave axially extending tip wall. The axially extending tip wall may include a convex inner surface forming a radially outer end to an inner cavity forming a cooling system. The cooling system may include one or more film cooling holes in the axially extending tip wall proximate to the suction sidewall, which promotes increased cooling at the pressure and suction sidewalls.

Abstract: The invention concerns a blade (1) designed to be fitted to the rotor of a rotating machine, said blade being characterized in that it exhibits a modular construction including: a rigid, median module (4) formed by a coffer (12), which is itself formed by joining two side panels (13, 14) that are connected to one another by at least one side rail (15), the side panels (13, 14) being connected by at least one weld executed on an internal protuberance on the said side panels that is set back from the intrados (11) and the extrados (1E) of the blade (1), an upstream module (7) forming a leading edge and added onto the upstream portion of the median module, a downstream module (8) forming a trailing edge and added onto the downstream portion of the median module Blades for rotating machines and corresponding fabrication methods.

Abstract: A compressor blade for a gas turbine engine is disclosed. The compressor blade may have a root configured to engage a hub of the gas turbine engine, and an airfoil radially extending a distance from the root to a tip. The airfoil may have a suction side, a pressure side, a leading edge connecting the suction and pressure sides, and a trailing edge connecting the suction and pressure sides opposite the leading edge. The distance that the airfoil extends from the root to the tip may be divided into a plurality of radially adjacent regions. At least one, but not all, of the plurality of radially adjacent regions away from the base and the tip may have a substantially constant thickness.

Abstract: A composite article including composite component extending heightwise from a component base to a component tip and lengthwise between spaced apart component first and second edges. Component plies having widthwise spaced apart ply first and second sides and ply edges therebetween. Component mounted on a spar which includes a shank extending heightwise into the composite component, tab at upper end of shank and substantially or fully embedded in the composite component, and tab tip. Ply edges of at least a first portion of the plies directly or indirectly contacting or pressing against the tab. Ply edges of at least a second portion of the plies may directly or indirectly contact or press against the tab tip. Ply edges of first portion may press against one or more indented or recessed surfaces in the tab. The composite article may be a composite blade or vane including a composite airfoil.

Abstract: A wind blade is provided. The wind blade includes a self-supporting structural framework, having multiple chord-wise members and one or more span-wise members. Each of the multiple chord-wise members and the one or more span-wise members have an aerodynamic contour. The wind blade also comprises a fabric skin located over the self-supporting structural framework. Further, the wind blade includes a tensioning mechanism configured for providing pretensioning in the fabric skin. The tensioning mechanism includes multiple mechanical force elements coupled with the fabric skin for providing a predetermined force for maintaining an aerodynamic surface of the fabric skin during operation of the wind blade.

Abstract: A rotor blade for a wind turbine is disclosed. The rotor blade includes a blade root, a blade tip and a body extending between the blade root and the blade tip. The body has a pressure side and a suction side extending between a leading edge and a trailing edge. The body also defines an inner surface. The rotor blade also includes a spar member extending between a portion of the inner surface defined on the pressure side of the body and a portion of the inner surface defined on the suction side of the body. In addition, the rotor blade includes a plurality of structural members extending adjacent to the inner surface. The structural members are configured to intersect one another along the inner surface.

Abstract: A rotor blade assembly for a wind turbine is disclosed. The rotor blade assembly includes a rotor blade having surfaces defining a pressure side, a suction side, a leading edge, and a trailing edge extending between a tip and a root. The rotor blade assembly further includes a mounting plate and a noise reducer. The mounting plate is configured on a surface of the rotor blade. The noise reducer may include a base plate and a plurality of noise reduction features. The base plate is mounted to the mounting plate. The plurality of noise reduction features extend from the base plate.

Abstract: Provided is a blade for a rotor of a wind turbine having a substantially horizontal rotor shaft, said rotor comprising a hub, from which the blade extends substantially radially when mounted, said blade having a chord plane extending between a leading edge and a trailing edge of said blade, a root area closest to the hub, an airfoil area furthest away from the hub, a transition area between the root area and the airfoil area, a first airfoil extending substantially along the entire airfoil area, and a second airfoil separately mounted to the blade, said second airfoil arranged at a mutual distance transverse to the chord plane and extending along the root area of the blades.

Abstract: The present invention provides a transonic blade that concurrently achieves reduction in shock loss at a design point and improvement in stall margin in blades operating in a flow field of transonic speed or higher in an axial-flow rotating machine. A cross-sectional surface at each of spanwise positions of the blade is shifted parallel to a stagger line connecting a leading edge with a trailing edge of the blade. A stacking line is shifted toward an upstream side of working fluid. The stacking line connects together respective gravity center positions of blade cross-sectional surfaces at spanwise positions in a range from a hub cross-sectional surface joined to a rotating shaft or an outer circumferential side casing of a rotating machine to a tip cross-sectional surface lying at a position most remote from the hub cross-sectional surface in a spanwise direction.

Abstract: The blade body of the present invention is provided with a main body which has a dorsal face and a ventral face and also provided with a trailing edge portion which connects the dorsal face to the ventral face with a continuous curved face. The curved face of the trailing edge portion is gradually decreased in curvature radius from one of the dorsal face and the ventral face toward the rear end portion which is positioned most downstream in a direction at which a fluid flows, decreased to the greatest extent in curvature radius at the rear end portion, thereafter, gradually increased in curvature radius from the rear end portion toward the other of the dorsal face and the ventral face and arrives at the other of the dorsal face and the ventral face.

Abstract: A propeller (10,110) has a hub (20,120) with blades (40,140). A safety member (50,150) is provided along at least a portion of the leading edge (43,143) of each blade (40,140); and the blades (140) may incorporate anti-cavitation slots (160).

Abstract: The invention relates to a roadable aircraft vehicle (100) and related systems. An example roadable aircraft vehicle (100) includes a vehicle drive system (262) including an engine (264) and gearbox (206) selectively engageable with an automotive driveline (266) and at least one propeller (270), a user interface including a display (202) for controlling the drive system (262) in an automotive mode including a steering wheel (204) and in a flight mode including a control stick (272), a control system for switching between the flight mode and the automotive mode, and a system (236) for locking the propeller (270) during the automotive mode. The invention also relates to aircraft systems and elements such as an airfoil (106) having a nominal profile, a folding wing (102), and an occupant crash protection system for an aircraft (100).

Abstract: The invention relates to a radially compressible and expandable rotor for a pump having at least one impeller blade, wherein the impeller blade has an impeller blade body whose material is elastically deformable as well as at least one stiffening strut which is at least partially embedded in the material of the impeller blade body. The struts are designed suitably in size, shape and arrangement and are integrated in suitable hollow spaces of the impeller blade body for stabilizing the impeller blade. Elements with tensile strength can additionally be provided.

Abstract: A turbine blade assembly is disclosed. In one embodiment, the turbine blade assembly may generally include a turbine blade having a root portion and an airfoil. The airfoil may extend radially from the root portion to an airfoil tip. Additionally, the turbine blade assembly may include a composite rod extending within the turbine blade. The composite rod may include a first end coupled to the airfoil at the airfoil tip and a second end coupled to the root portion. Moreover, the coefficient of thermal expansion of the composite rod may be designed to be less than or equal to the coefficient of thermal expansion of the airfoil.

Abstract: An aerofoil having a leading edge point within a leading edge region and a pressure surface with a profile wherein within the leading edge region the pressure surface profile has a local minimum. The local minimum reduces the loss which may be caused by high negative incidence on to the blade.

Abstract: The catheter device comprises a drive shaft connected to a motor, and a rotor mounted on the drive shaft at the distal end section. The rotor has a frame structure which is formed by a screw-like boundary frame and rotor struts extending radially inwards from the boundary frame. The rotor struts are fastened to the drive shaft by their ends opposite the boundary frame. Between the boundary frame and the drive shaft extends an elastic covering. The frame structure is made of an elastic material such that, after forced compression, the rotor unfolds automatically.

Abstract: A multi segment wind turbine blade comprises at least two blade segments. A first blade segment comprises an outer skin, a bulkhead, and first alignment brackets removably coupled to the outer skin of the first blade segment. A first portion of a flange of the bulkhead is bonded to the first blade segment and a second portion of the flange of the bulkhead projects out from the first blade segment. A second blade segment comprises an outer skin and second alignment brackets removably coupled to the outer skin of the first blade segment. The first and second alignment brackets are alignable upon the outer side of the second blade segment being inserted over the second portion of the flange of the bulkhead.

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: A turbine blade for use in a gas turbine engine, the turbine blade being made from a spar and shell construction in which the spar extends from the root and forms a cavity in which cooling air is supplied to the blade. The shell is held between the tip cap and the platform in grooves. A tension rod extends from the root and through the cavity within the spar to engage with the tip cap and secure the tip cap and the shell in place. A pretension nut is secured to the tension rod on the root end and engages a surface of the root to allow for a tension to be applied to the tension rod. Ceramic rope seals are secured within the grooves between the shell ends and the groove to form a seal. An inner seal is secured within a groove of the spar and engages with a projecting member on the tip cap to form a seal. Heat shields are wrapped around the platforms to provide thermal protection to the platforms.

Abstract: A turbine rotor blade with a spar and shell construction, where the shell has an airfoil shape and is formed of two shell segments with an upper shell half and a lower shell half. The upper shell half is radially supported by a tip of the spar while the lower shell half is radially loaded by an attachment so that its load is not carried by the upper shell half and the tip of the spar in order to reduce overall stress levels.

Abstract: A blade segment is disclosed for a rotor blade formed from a plurality of blade segments, the blade segment having a span and a chord. The blade segment includes a shell segment having a pressure side and a suction side extending between a leading edge and a trailing edge, the shell segment further having a tip end and a root end. The blade segment further includes at least one joint portion projecting from the shell segment at one of the tip end or the root end and defining a generally span-wise extending joining surface. The joint portion allows the blade segment to be coupled to an adjacent blade segment with a mating joint portion.

Abstract: The invention provides a sectional blade for a wind turbine. The blade comprises at least a first blade portion and a second blade portion extending in opposite directions from a joint. Further each blade portion comprises a spar section forming a structural member of the blade and running lengthways. The first blade portion and the second blade portion are structurally connected by at least one spar bridge extending into both blade portions to facilitate joining of said blade portions and the spar bridge joins the spar sections.

Abstract: A torsionally loadable wind turbine blade, includes a loading member secured to a body of the wind turbine blade; and an adjuster for actively displacing the loading member and torsionally deforming the blade on a spanwise axis.

Abstract: A turbine blade includes at least two blade segments. Each blade segment includes first and second shells joined together, a base region, at least one joint region including a mating face. Each of the first and second shells includes an outer skin, a base spar cap attached to an inner surface of the outer skin in the base region, a joint spar cap attached to the inner surface of the outer skin in the joint region and adjacent to at least a portion of the base spar cap. The joint spar cap includes holes in the mating face of the joint region. The turbine blade further includes fasteners within the holes for securing the at least two blade segments together.

Abstract: A turbine blade for use in a gas turbine engine, where the turbine blade is made from a spar and shell construction in which a thin walled shell is held in place between the blade tip and the platform by only a mechanical fastener without using any bonding, welding or brazing. The spar is connected to an attachment by a tie bolt, and a separate platform is secured, over the attachment t in which the shell is held against. This provides for a thermally free platform and shell connection. With this arrangement, the shell is held under compression within the 2% yield stress range such that the turbine blade shell can have an infinite life. Also, the turbine blade is much lighter than prior art blades. As a result, the spar and shell blade produces less stress on the rotor disk during engine operation.

Abstract: The invention relates to a wind turbine comprising a rotating part including a rotor with at least one blade and a wind turbine hub with at least one enclosure structure or similar wall structure, and a stationary part including a nacelle with at least one enclosure structure or similar wall structure. At least one of said parts comprises a conductive film layer of said enclosure structure with connection to a ground potential, where said film layer forms a shield enclosing said part or parts and protects against electromagnetic fields. The invention also relates to a method to manufacture said enclosure structure.

Abstract: A method of assembling a gas turbine engine includes providing at least one blade assembly. The method also includes forming at least one blade tip fuse within at least a portion of the at least one blade assembly. The method further includes coupling the at least one blade assembly into the gas turbine engine. The blade assembly includes an airfoil and a metal leading edge (MLE) coupled to at least a portion of the airfoil. The MLE includes the at least one blade tip fuse.

Abstract: A method of reducing crack propagation includes: providing a metallic component having an exterior surface, and using a burnishing element to apply a varying to the exterior surface within a selected area, within which the component has a varying thickness, so as to create a region of residual compressive stress of surrounded by an interior boundary. The distance from the interior boundary to the exterior surface at any location within the selected area is independent of the thickness of the component at that location, and may be controlled by changing the pressure and/or an amount of overlap between burnished segments.

Abstract: A butt connection of divided hollow profile members, which is suitable in particular for rotor blades of wind power installations, comprises a multiplicity of straps which are arranged along the joint and which bridge over same and which are respectively fixed with their ends to one of the profile members to be connected. In this respect the arrangement is preferably such that one of the two bolts fixing the strap at the ends thereof has a wedge-shaped flattening, by means of which a tensile prestressing can be imparted to the strap.

Abstract: A method for making a blade includes stacking a plurality of modular segments having formed conduits, threading and tensioning cables through the conduits of the stacked segments, and clamping the cables to hold the modular segments together.

Abstract: In a wind turbine (104, 500, 704) having a plurality of blades (132, 404, 516, 744) and a blade rotor hub (120, 712), a lightning protection system (100, 504, 700) for conducting lightning strikes to any one of the blades and the region surrounding the blade hub along a path around the blade hub and critical components of the wind turbine, such as the generator (112, 716), gearbox (708) and main turbine bearings (176, 724).