Abstract: A method of manufacturing a reinforcing edge for attachment to a turbo machine aerofoil, wherein the reinforcing edge comprises a relatively thick nose portion contoured for fitting along the edge of the turbo machine aerofoil, and a pair of opposing, relatively thin, tail portions for overlapping the suction surface and pressure surface respectively of the aerofoil, the method comprising: pressure forming a predefined hollow workpiece under fluid pressure from a respective pre-form, the hollow workpiece incorporating the reinforcing edge; and cutting out said reinforcing edge from the hollow workpiece, wherein the pre-form is created by bonding a pair of relatively thin metal sheets to opposite faces of a relatively thick inner plate or bonded stack of inner plates, the inner plate or stack of inner plates having an opening which defines a closed cavity between the metal sheets for introducing said fluid pressure, each tail portion of the reinforcing edge being constituted by part of a respective one of the

Abstract: The present invention relates to a wind turbine rotor blade comprising a lightning protection system. The lightning protection system comprises a lightning receptor for capturing lightning strikes. The receptors are arranged in the rotor blade. The lightning receptors comprise carbon nanotubes. In embodiments, the nanotubes are at an exterior surface is provided with a layer of carbon nanotubes and/or at least part of the lightning receptor is of a carbon nanotube metal composite material, such as a carbon nanotube metal matrix composite material. Moreover, the exterior surface of the receptor may in embodiments be provided with one or more electric field enhancing protrusions.

Abstract: A method of producing a shear web for a wind turbine blade includes providing a mold generally conforming to a shape of at least a portion of a shear web; and filling the mold with a closed cell structural foam.

Abstract: The present invention relates to an automatic method for manufacturing a stator or rotor blade preform for a turbine engine, comprising at least the following successive steps: a) a step for the helical braiding of a plurality of interlocked tubular braids (1), called nested braids, said step being conducted on braiding machines (2) placed in a row in a braiding direction; b) a step for flattening the nested braids (1); c) a step for stitching the nested braids (1) together in a direction perpendicular to the braiding direction; d) a step for winding the nested braids (1) on a transport mandrel (3); e) a step for cutting the nested braids (1) unwound from the transport mandrel (3), said cut being performed in a direction perpendicular to the braiding direction.

Abstract: An inventive self-aligning blade joint structure is provided to facilitate assembly and clamping of wind turbine blade sections carried on a transporter. The blade joint structure includes alignment pins on one end bulkhead of a blade body section at the joint and complimentary female bushings on a bulkhead of an adjacent blade body section to permit fine alignment of the joint. The blade joint structure also includes through holes in the end bulkheads for the adjacent blade body sections to permit clamping of the sections in preparation for application of adhesive bonding to the joint. A pair of male scarfed surfaces of spar caps extend from one blade section into the second blade section and engage female scarfed surfaces of spar caps formed in the second blade section and recessed from the joint. An inventive method is provided to utilize the self-aligning blade joint structure for assembly of the blade sections.

Abstract: A quantity of particles (28) may be cold-sprayed toward the distal surface (22) of a turbine blade (6) at a temperature below a melting point of the particles at a velocity sufficiently high to cause at least a portion of the particles to adhere to the surface to form squealer ridge (24) with a desired cutting profile. The cutting profile may be defined by a face (52) and a land (54) disposed at a relief angle (38) relative to a direction of motion (58) of a cutting edge (48). The ridge may be built by multiple passes of a cold spray gun depositing sequential layers (30, 32, 34) of varying widths. An in-service blade having worn distal surface may be repaired using this technique.

Abstract: A wind turbine blade including a number of segments attached together end-to-end in a predetermined arrangement so that the respective covering subassemblies of the segments cooperate to form a substantially smooth surface of the wind turbine blade. Each segment includes a number of fiber tubes extending along preselected lengths of the segment respectively, the fiber tubes being laterally spaced apart from each other respectively to define gaps therebetween. The segment also includes a covering subassembly at least partially supported by the fiber tubes and at least partially defining an internal cavity.

Abstract: A metal leading edge of a turbine fan blade is manufactured by cutting and shaping an elongated metal part. The metal part has front and rear edges extending lengthwise of the part, and has a generally wedge-shaped transverse cross-section with opposite sides diverging from the front edge toward the rear edge. A cavity is cut inward from the rear edge toward the front edge. This provides the part with a generally V-shaped transverse cross-section having opposite side walls diverging rearwardly from the front edge. A mandrel is inserted into the cavity, and the side walls of the V-shaped part are deflected toward each other to constrict the cavity into the configuration of the mandrel. The part is then mounted as a metal leading edge by inserting a turbine fan blade component into the constricted cavity and fastening the part to the component.

Abstract: A method of manufacturing an aerofoil structure capable of being diffusion bonded and superplastically formed to create a substantially hollow cavity within the aerofoil structure, the method comprising: providing a metallic plate for forming the aerofoil structure; joining mounting elements to opposing end surfaces of said metallic plate; dividing said plate along a plane extending substantially in a span-wise direction so as to produce two metallic panels each with one of said mounting elements joined thereto; assembling the two metallic panels so that the surfaces of the panels opposite to the surfaces which have been divided are facing each other; and joining the two metallic panels to one another to form the aerofoil structure; wherein the mounting elements are joined to one another to form the root of the aerofoil.

Abstract: The invention relates to a wind turbine blade comprising one or more electric powered modules. The modules have power supply means converting an energy source to electrical power for said one or more modules, wherein said energy source is light beams transmitted to the power supply means in the blade structure and/or interior from an external light source. The invention also relates to wind turbine and a method for manufacturing a wind turbine blade.

Abstract: A manufacturing system and manufacturing method for adjusting the performance of manufacturing operations or steps in manufacturing components having three-dimensional external structural characteristics. An embodiment of the system broadly comprises: (a) a plurality of manufacturing operations for processing a component having three-dimensional external structural characteristics; (b) at least one analytical device for analyzing at least one characteristic of the component after the performance of one or more manufacturing operations to generate a component data set; (c) at least one data storage device for storing the generated component data sets and for providing at least a relevant portion of accumulated component data; and (d) a communication mechanism for transmitting at least a relevant portion of accumulated component data to one or more manufacturing operations so that the performance thereof can be adjusted in response to the transmitted portion of accumulated component data.

Abstract: The invention relates to a method for the manufacture of wind vanes, consisting of: formation of a single foam core (2), with numerical control machines, application of reinforcing layers (3) pre-impregnated with resin (4), curing of the layers (3) as part of the application process itself by means of UV (ultraviolet) instant curing and thermal curing, polishing of the vane surface, also by use of an automatic numerical control machine, and final painting. Alternatively, the core is made using a mould, is a single piece or two shells (2a) and (2b) which are subsequently joined with adhesive, is solid or, at least in the root thereof, hollow, or formed by two solid or lightened shells and can contain a central inner tube (6) made of composite as a rigidizing element, and other smaller tubes (7) inside the leading and trailing edges.

Abstract: A method of manufacturing a turbine engine component is disclosed. The method includes the steps of providing a plurality of ceramic cloth plies, each ply having woven ceramic fiber tows and at least one fugitive fiber tow, laying up the plurality of plies in a preselected arrangement to form a turbine engine component shape, oxidizing the fugitive fibers to produce fugitive fiber void regions in the ply, rigidizing the component shape to form a coated component preform using chemical vapor infiltration, partially densifying the coated component preform using carbon-containing slurry, and further densifying the coated component preform with at least silicon to form a ceramic matrix composite turbine engine component having matrix rich regions.

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 lift device for a wind turbine blade. The lift device includes a first sidewall and an opposing second sidewall. The lift device is configured to be coupled to the wind turbine blade along a leading edge of the wind turbine blade, and to generate lift when airflow is directed across a surface of the lift device.

Abstract: A sparcap for a wind turbine rotor blade. The sparcap includes a first carbon material layer coupled to an inner surface of the wind turbine rotor blade. The first carbon material layer extends along at least a portion of a length of the wind turbine rotor blade. A core material is coupled to the first carbon material layer. The core material is positioned with respect to a buckling prone region of the wind turbine rotor blade. A second carbon material layer covers the core material and is coupled to the first carbon material layer and/or the core material. The second carbon material layer extends along at least a portion of the length of the wind turbine rotor blade.

Abstract: A rotor blade for a wind turbine having a first blade section and a second blade section coupled to the first blade section to form the rotor blade. Each of the first blade section and the second blade section has a leading edge and a trailing edge. A first sparcap including a carbon material is positioned on an inner surface of the first blade section. A second sparcap including a glass material is positioned on the first blade section. The second sparcap is positioned with respect to the first sparcap in a leading edge direction or a trailing edge direction.

Abstract: In order to create titanium components with a titanium composite insert, a method is provided whereby an initial pre form 1 has a groove 2 formed in it. An encapsulating member 4 is then provided about the groove 2 in order to create a cavity 5 which is filled with titanium alloy powder 6. This titanium alloy powder 6 is densified and then accurately machined in order to create a groove insert form 7 which can accommodate a titanium composite material pre form insert 8 and further titanium alloy powder 9 such that through a high temperature isostatic pressing (HIP) process, the insert 8 is embedded. The original component form 1 can then be machined in order to create the final component elements such as aerofoils 13.

Abstract: An insert and method for altering a through-hole in a body, such as a steam balance hole in a steam turbine rotor wheel. The insert has a body with oppositely-disposed first and second ends, a flange radially extending from the second end of the body, and an outer surface at a perimeter of the body between the first end and the flange. A first bore within the body defines a first opening at the first end, and the first bore and outer surface of the body cooperate to define therebetween a wall capable of being plastically deformed in a radially outward direction. A second bore within the body communicates with the first bore and has a smaller cross-section than the first bore. The installation method entails installing the insert in a through-hole and flaring the wall to clamp the axial thickness of the body between the flange and flared wall of the insert.

Abstract: The invention introduces a reinforcement of a box girder of a wind turbine blade. The reinforcement prevents the transverse shear distortion of the blade structure, when the blade is loaded during operation. The reinforcement connects the corners diagonally opposite inside the girder, and fixes them in relation to each other. The reinforcement increases the blade's resistance to overall collapse. The reinforcement comprises one or more individual element, such as rods or plates.

Abstract: The invention relates to a blade for a wind turbine, particularly to a blade that may be produced by an advanced manufacturing process for producing a blade with high quality structural components. Particularly, the structural components, which are preferably manufactured from fibre reinforced plastic material, will have a high level of stretched fibres as well as a far better controlled resin distribution and content and also a low void content.

Abstract: International regulations for aerofoils within gas turbine engines require the safe containment of a released aerofoil. The blade fragments must be contained within an engine casing. Smaller fragments will generally be easier to contain within the casing and therefore reduce the weight of that casing. However introducing lines of weakness may result in cavities and holes which are subject to moisture ingress and problems associated therewith. By providing a root section which incorporates a core having shear surfaces, blades can be designed which in normal use are subject to compressive loads and remain operational, but when subject to impact loads or bending forces create tension forces which cause fragmentation along the shear surfaces after initial energy losses by slippage. By providing the shear surfaces in cores their location is encapsulated avoiding problems with moisture ingress.

Abstract: A method of improving an erosion resistance at the leading edge of a compressor blade includes: a) cleaning a leading edge portion of the compressor blade airfoil; and b) attaching one or more erosion or corrosion-resistant shims to the leading edge portion.

Abstract: A sectional wind turbine rotor blade is provided, the sectional wind turbine rotor blade having first and second blade sections, wherein the first and second blade sections are fixedly mountable to each other via a connector. Furthermore, a method for assembling a sectional wind turbine rotor blade is provided.

Abstract: A vane has an airfoil shell and a spar within the shell. The vane has an outboard shroud at an outboard end of the shell and an inboard platform at an inboard end of the shell. The shell includes a region having a coefficient of thermal expansion (CTE) varying with depth.

Abstract: The present invention relates to the prevention of deformations in an aerodynamic profile caused by lack of resistance to the bending moment forces that are created when such a profile is loaded in operation. More specifically, the invention relates to a reinforcing element inside an aerodynamic profile and a method for the construction thereof. The profile is intended for, but not limited to, use as a wind turbine blade, an aerofoil device or as a wing profile used in the aeronautical industry.

Abstract: An acoustical vibration dampening system for a rotatable blade comprises at least one section of a rotatable blade and a layer of acoustic damping material coupled to a portion of the at least one section of a rotatable blade. A fan blade comprises a first structural section of a fan blade, a second structural section of the fan blade, and a layer of acoustic damping material provided between the first structural section and the second structural section of the fan blade. A method of making a fan blade with acoustic damping comprises forming at least two sections of a fan blade, and disposing an acoustical vibration dampener between the at least two sections of the fan blade.

Abstract: A strengthening structure for a wind turbine blade includes at least one first reinforcement part adapted to be connected to a first blade part of the wind turbine blade, and at least one second reinforcement part adapted to be connected to a second blade part of the wind turbine blade. The strengthening structure is characterized in that the at least one first reinforcement part and/or the at least one second reinforcement part includes an adjusting mechanism enabling that the first reinforcement part and the second reinforcement part are displaceable in relation to each other, at least during the assembly of the wind turbine blade and wherein the adjusting mechanism includes a force mechanism capable of forcing the first reinforcement part and the second reinforcement part away from each other. A wind turbine blade, a method for assembling a wind turbine blade and a use thereof are also contemplated .

Abstract: A method of making a fan blade includes: a) providing a blade body having a top surface, a bottom surface opposite to the top surface, and a peripheral wall interconnecting the top and bottom surfaces; b) drilling a blind hole in the blade body that extends from one side of the peripheral wall of the blade body and between the top and bottom surfaces of the blade body; and c) inserting a reinforcing rib into the blind hole.

Abstract: The invention relates to a method for producing a rotor for a Francis turbine, comprising a rotor base, a rotor ring and rotors.

Abstract: A method for manufacturing integrally bladed rotors by laser brazing a rotor disk (1) made of a nickel or titanium-base material to blades (3) made of titanium aluminide. A brazing metal similar to the blade material is used, which is introduced into the laser beam (4) as brazing power jet (5) and whose heat capacity, which is controlled by the melting temperature and the volume of the molten metal bath This provides for melting of the disk material and alloying with this material, but not for melting of the blade material, to which it is connected by adhesion. Such blisk features a low blade weight, reduced centrifugal effects and enhanced service life.

Abstract: The invention relates to a rotor blade (60) of a wind energy plant with a top side (suction side) and a bottom side (pressure side) wherein profiles (21, 22, 23, 24, 25) with a front edge and a back edge (62) in cross-section are designed along a longitudinal axis between a rotor blade root and a rotor blade tip, one designed-based direction of air inflow (31, 32, 33, 34, 35) is predetermined for each profile (21, 22, 23, 24, 25) and the profiles (21, 22, 23, 24, 25) in the outer area facing the rotor blade tip are designed with a relative thickness of less than 30%.

Abstract: A ceiling fan including a motor having a rotatable rotor, a plurality of ceiling fans blades having a thickness, the blades connected to the rotor to rotate therewith and each of the ceiling fan blades comprising a thin edge along its leading edge that is thinner than the thickness of the ceiling fan blade to present less resistance and produce less turbulence and achieve high efficiencies.

Abstract: A wind turbine blade has at least one lightning receptor, wherein at least part of a surface of the wind turbine blade close to the lightning receptor is covered by a protective layer having electrical and thermal insulating material. Moreover, a method for protecting the surface of a wind turbine blade close to a lightning protector against temperature increase resulting from lightning impact is disclosed. At least part of the surface of the wind turbine blade is covered with a protective layer having electrical and thermal insulating material.

Abstract: An aerofoil (35) for example a fan blade (26) comprises a leading edge (36), a trailing edge (38), a concave pressure surface extending (40) from the leading edge (36) to the trailing edge (38) and a convex suction surface (42) extending from the leading edge (36) to the trailing edge (38). The aerofoil (35) comprises a metal foam (50) arranged within a cavity defined by metal workpieces (52, 54). The metal foam (50) of the aerofoil (26) ideally has a density of less than 1g/cm3, is cheaper to manufacture and has improved fatigue behaviour and impact capability.

Abstract: A turbine blade with a tip squealer and method of rebuilding a turbine blade for a gas turbine engine. The blade is of the type including an airfoil having first and second spaced-apart sidewalls defining an interior void and joined at a leading edge and a trailing edge. The first and second sidewalls extending from a root disposed adjacent the dovetail to a tip cap for channeling combustion gases, and a squealer tip including at least one tip rib extending outwardly from the tip cap. The method includes the steps of removing the squealer tip, including the at least one rib tip, from the tip cap and adding new material to the tip cap to serve as a new squealer tip. A plurality of spaced-apart notches is formed in the new material between the leading edge and the trailing edge of the airfoil. At least one hole is formed in each notch communicating with the interior void of the airfoil for channeling cooling air from the interior void of the airfoil to thereby form a squealer tip.

Abstract: A blade for a wind turbine includes a body adapted for movement in response to wind flow past the blade body. The body has an inner surface defining an interior chamber and an opposite outer surface. At least one damping element extends from the inner surface of the body. The at least one damping element is configured to facilitate reducing an amount of noise generated by and propagating through the blade.

Abstract: A method of constructing a turbine blade for a gas turbine engine is provided. The method includes casting the blade, forming a plurality of spaced-apart notches in the airfoil proximate the tip on the pressure sidewall and forming at least one hole in each tip shelf communicating with the interior void of the airfoil for channeling cooling air from the interior void of the airfoil to thereby form a squealer tip.

Abstract: In a method for manufacturing a hollow blade for a turbomachine, the blade is made from a preform derived from external primary parts. Each primary part comprising a root part is formed by flattening a blank cut out from a ring with a large diameter provided with a protuberance, in order to reduce costs.

Abstract: A system and method of constructing a system for delivering cargo by airdrop are provided. In short, the system uses rotor blades to slow the descent of cargo dropped from an aircraft. In one example of one embodiment, a frame is secured to a cargo pallet and at least one rotor blade is secured to the frame. The rotor blade is secured to the frame in a position such that it causes the cargo pallet and the frame to rotate in air when dropped from an elevation. In another embodiment, the rotor blade may be extendable and extend during flight.

Abstract: A method for forming a bucket for a steam turbine includes forming a leading edge on at least one airfoil. The leading edge is comprised of an erosion resistant material and is bonded to the airfoil.

Abstract: A method of forming a wind turbine blade includes forming a root portion, a tip portion, and an airfoil portion extending radially outward from the root portion to the tip portion. The method also includes forming a spar cap extending radially outward from the root portion through at least a portion of the airfoil portion. At least a portion of the spar cap is oriented substantially longitudinally and extends generally linearly from a first end of the spar cap to a second end of the spar cap. The method also includes forming at least one spar cap extension that extends from the spar cap, wherein at least a portion of the spar cap extension is oriented nonlinearly relative to the spar cap.

Abstract: Methods and apparatus are provided for making a rotor blade spar from composite material wherein a multi-component mandrel is used to form the composite spar. The mandrel is made using a number of components that are assembled and held in place using a roller assembly. The roller assembly is removed after pre-cure lay up and compaction of the composite material. Once the roller assembly is removed, the remaining mandrel components can be separated from each other and easily removed from the spar. The mandrel components, including the roller assembly, can then be re-assembled and re-used to form additional composite spars.

Abstract: Systems and methods involving localized stiffening of blades are provided. In this regard, a representative a gas turbine engine blade includes: a recess located in a surface of the blade; and material positioned at least partially within the recess such that the material provides a localized increase in stiffness of the blade.

Abstract: A fan, particularly for cooling internal combustion engines for earth moving machines, whose blades have an elastically deformable composite structure including at least one shape memory alloy foil adapted to be heated by means of electric current to vary the geometry of the blade.

Abstract: A method for fabricating a rotor blade includes fabricating a rotor blade that includes a dovetail and an airfoil coupled to the dovetail, the airfoil including a first side, a second side, and a plurality of openings extending therethrough, and weaving a composite material through the openings such that the airfoil has an aerodynamic profile that is substantially smooth from an airfoil leading edge to an airfoil trailing edge.

Abstract: A process for producing a rotor, the rotor formed thereby, as well as turbines in which such a rotor is installed. The rotor is formed by casting an ingot to have first and second regions formed of different alloys that intermix during casting to define a transition zone therebetween. The ingot is forged to yield a rotor forging that contains axially-aligned first and second alloy regions and a transition zone therebetween. The effects of the transition zone can be mitigated by modeling the transition zone and then off-center machining the forging so that the axis of rotation of the machined monolithic rotor is more centrally located with respect to the transition zone.

Abstract: A main rotor blade assembly having a blade skin bonded to a main spar and a tip spar.

Abstract: A method of manufacturing an article by diffusion bonding at least two metal components (30,36) comprises assembling the metal components (30,36) into a stack relative to each other so that the surfaces (34,40) are in mating contact. The edges of the metal components (30,36) are sealed together, except for an aperture (49) where a pipe (50) is to be connected. A connector (51) has a first end (52) and a second end (53). The first end (52) has a smaller diameter than the second end (53) and a bore (54) extends through the connector (51) from the first end (52) to the second end (53). The second end (53) of the connector (51) is joined (57) to the stack. The pipe (50) is joined (58) to the first end (52) of the connector (51). The interior of the sealed assembly is evacuated via the pipe (50) and the pipe is sealed. Heat and pressure are applied to diffusion bond the metal components (30,36) together to form an integral structure.

Abstract: A blade assembly including an outboard blade segment is provided. The outboard blade segment includes an outboard blade shell, first and second outboard bulkheads situated within the outboard blade shell, and an outer box supported by and aligned by the outboard bulkheads. The blade assembly also includes an inboard blade segment including an inboard blade shell, first and second inboard bulkheads situated within the inboard blade shell, and an inner box supported by and aligned by the inboard bulkheads. Further, the inner and the outer boxes are tapered to facilitate insertion of the inner box into the outer box and coupling of the inner and outer boxes.