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 composite blade includes a preform and a binder. The preform is a preform of yarns woven in three-dimensions and has a tip region, a root region and an intermediate region. The intermediate region is positioned between the tip region and the root region. The yarns comprise warp yarns and weft yarns. The warp yarns form a longitudinal axis. The weft yarns are positioned at a 90 degree angle to the warp yarns. The weft yarns increase in yarn size as determined by filament count along the longitudinal axis to change the thickness of the preform. The binder maintains the relative positions of the preform yarns.

Abstract: A gas turbine blade includes a hollow-blade-form portion formed by a leading edge on an upstream side of an working fluid of a gas turbine in a flow direction, a trailing edge on a downstream side of the working fluid in the flow direction, and a suction surface and a pressure surface reaching the trailing edge from the leading edge, and a shank portion for supporting the blade form portion. The blade also includes a partition for connecting the suction surface and the pressure surface in a hollow region of the blade-form portion, coolant paths formed by the partition, the suction surface, and the pressure surface, an impingement cooling hole formed in the partition for dividing the first path that is a flow path nearest to the leading edge side among the coolant paths and the second path adjacent to the first path, and first and second converter portions.

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: A method for the milling machining of components is disclosed. The method produces recesses with one or more lateral walls, in particular for the production of integrally bladed rotors for gas turbines, the recesses forming flow channels and the lateral walls forming blade surfaces of an integrally bladed rotor. The component to be machined by milling is clamped in a locating device for the milling machining. To adjust the vibrational properties of the component to be machined by milling, areas of the component are embedded in and/or filled with a machinable plastic.

Abstract: A turbine according to an embodiment includes: a formation object member; a facing member; and a seal part. A formation object member is one of a static part and a rotation part. A facing member is the other of the static part and the rotation part. A seal part at the formation object member is configured to reduce combustion gas leaking between the formation object member and the facing member. The seal part including a ceramics layer. The ceramics layer has a heat conductivity lower than that of the formation object member, and has a concave and convex shape at a surface thereof. The ceramics layer is not in contact with the facing member, or has hardness higher than that of the facing member so that the facing member is preferentially abraded when the facing member and the ceramics layer are in contact with each other.

Abstract: A method for making a ceiling fan blade comprises the steps of cutting, inside drying, surface wetting, surface spraying, and surface forming. The method is capable of reducing production cost and loss rate, reducing the harm to human health, preventing environmental pollution, and preventing the ceiling fan blades from perishing and deformation by dehydrating the ceiling fan blades.

Abstract: A method of fabricating a guide vane. The method produces a fiber preform by 3D weaving a single piece, the preform including a first portion extending along the longitudinal axis and constituting the preform for an airfoil of the vane, and at a longitudinal end of the first portion, a second portion constituting the preform for the platform of the vane, the second portion being produced as a first layer and a second layer facing the first layer and separated from the first layer by unlinking without cutting while producing the preform; folding the first and second layers such that each of them lies in a plane perpendicular to the longitudinal axis, substantially symmetrically to each other relative to the first portion, and such that a first region of the first layer covers a second region of the second layer in front of a front edge of the first portion; conforming the preform in a mold; and densifying the preform with a polymer matrix.

Abstract: The invention relates to a method for manufacturing wind turbine blades, blades for propellers, wings or similar structures, and to a structure in the shape of a blade produced by means of said method, including: use a female mold of the leading edge (5), a female mold of the trailing edge (6), and a third mold (7) for a composite male tool (8) as a lost mold for manufacturing at least an inner crossbeam (4); wherein a demolding agent and an outer protective varnish is applied on the inner sides by robot or a digitally-controlled device; applying prepreg in superimposed layers; coating the prepreg with a vaccum film, and connecting to a pump for extracting air from between the prepreg layers; fitting together the molds and positioning the pieces with the prepreg laminates; and applying pressure and thermal curve for the method of curing or polymerizing the set of pieces in a single stage or all at once.

Abstract: According to one embodiment, a propeller blade includes a carbon foam core and a structural layer that surrounds at least a portion of the carbon foam core.

Abstract: A process for manufacturing a metal part such as a metal reinforcement for the blade of a turbine engine, which includes: manufacturing a three-dimensional metal structure made up of an insert which exhibits properties which allow superplastic forming and diffusion welding to be carried out, and of multiple metal wires encircling the periphery of the insert, where the metal structure forms a preform of the metal part; positioning the metal structure in a forming tool and hot-pressing the three-dimensional metal structure which causes agglomeration of the metal structure so as to obtain the compact metal part.

Abstract: A method of attaching first and second aerofoil sections to each other is disclosed. The method comprises the steps of: positioning one aerofoil section in an initial assembly orientation with respect to the other aerofoil section so that hinge elements on each aerofoil section are in alignment with each other, inserting a hinge shaft through said aligned hinge elements to initially couple the aerofoil sections together whilst the aerofoil sections are in their initial assembly orientation; and rotating one aerofoil section relative to the other aerofoil section about a compound angle defined by the hinge shaft into a second orientation in which the aerofoil sections are in their final, assembled orientation relative to each other. An aerofoil assembly is also disclosed.

Abstract: A method for producing a coated turbine blade, with which the frequency property thereof can be particularly easily adjusted to the required boundary conditions is provided. Recesses are introduced into a blade tip of the blade leaf of the turbine blade after coating of turbine blade. In one aspect a plurality of bores are made which are distributed along the blade leaf center line.

Abstract: A method for producing a protective layer for a rotor blade of a turbomachine is proposed. The rotor blade has a wear cap wall that in relation to the axis of the turbomachine protrudes radially towards the exterior of the turbomachine beyond a body of the rotor blade. The method enables the entire rotor blade to have a comparatively long service life and at the same time allows the wear cap wall to be thermally insulated in an especially simple manner. For the purpose, a profile producing a positive fit effective in the radial direction is inserted in a radially located region of the wear cap wall, a slip containing metal powder and/or a ceramic slip is applied to the region and the slip in sintered.

Abstract: The invention relates to the use of layer structures in the production of rotor blades for wind power plants, and to rotor blades for wind power plants.

Abstract: A ceramic matrix composite blade for use in a gas turbine engine having an airfoil with leading and trailing edges and pressure and suction side surfaces, a blade shank secured to the lower end of each airfoil, one or more interior fluid cavities within the airfoil having inlet flow passages at the lower end which are in fluid communication with the blade shank, one or more passageways in the blade shank corresponding to each one of the interior fluid cavities and a fluid pump (or compressor) that provides pressurized fluid (nominally cool, dry air) to each one of the interior fluid cavities in each airfoil. The fluid (e.g., air) is sufficient in pressure and volume to maintain a minimum fluid flow to each of the interior fluid cavities in the event of a breach due to foreign object damage.

Abstract: A method for producing a reinforced metal part, includes: cutting out a plurality of metal foils from at least one flexible metal sheet, the foils substantially corresponding to the blank of said metal part to be produced; rigidly connecting at least one metal reinforcing wire to at least one metal foil, the metal wire being positioned depending on the orientation of the desired structural reinforcement; making a plurality of reinforced metal pockets, each metal pocket being made from two reinforced metal foils; positioning the plurality of reinforced metal pockets in shaping equipment; performing a isostatically hot-pressing of the reinforced metal pockets, causing the metal pockets and the metal reinforcing wire to be bonded together so as to produce the metal part incorporating the structural reinforcement.

Abstract: A metal reinforcing piece for mounting on a leading edge or trailing edge of a composite blade for a turbine engine is made by shaping two metal sheets, positioning them on either side of a core, assembling the two sheets together around the core under a vacuum, shaping them on the core by hot isostatic compression, and cutting them to separate the reinforcing piece and release the core. A predetermined roughness is given to at least a portion of the surface of the core and is transferred to a corresponding portion of an inside surface of the reinforcing piece by the hot isostatic compression.

Abstract: A composite turbine blade and a method of manufacture thereof is disclosed. The composite turbine blade comprises a turbine blade portion comprising a first material and a first tip plate comprising a second material. The turbine blade portion has an exterior wall and an interior wall surrounding a hollow interior cavity, and a top surface extending from the exterior wall to the interior wall bounding an orifice that is fluidly connected to the hollow interior cavity. The first tip plate may be attached to the turbine blade along the top surface and extending from proximate the exterior wall of the turbine blade across the orifice to cover the orifice.

Abstract: According to one embodiment, a propeller blade includes a metallic foam core and a structural layer that surrounds at least a portion of the metallic foam core.

Abstract: A blade includes an airfoil having a base and a free, tip end. The tip end includes at least one porous, abradable element.

Abstract: A core has a body that includes a cooling passage portion with a film cooling passage portion extending there from to a film cooling hole portion. An exterior airfoil portion is connected to the film cooling hole portion and is spaced apart from the cooling passage portion to provide a space surrounding the film cooling hole portion that corresponds to an exterior airfoil wall.

Abstract: An airfoil includes a leading edge, a trailing edge, a suction surface, a pressure surface, a cooling passageway, and a plurality of oblong pedestals. The suction surface and the pressure surface both extend axially between the leading edge and the trailing edge, as well as radially from a root section to a tip section of the airfoil. The cooling passageway is located between the suction surface and the pressure surface. The oblong pedestals connect the suction surface to the pressure surface at the trailing edge of the airfoil.

Abstract: A rotor manufacturing apparatus includes a pusher and multiple blades. The pusher presses multiple magnets that are temporarily attached to a rotor core and arranged side by side in a circumferential direction of the rotor core from an outer side in a radial direction of the rotor core. The multiple blades are individually inserted into gaps between the magnets pressed by the pusher.

Abstract: A turbomachine blade made of composite material including a fiber reinforcement obtained by three-dimensional weaving of yarns and densified by a matrix, comprises a first portion constituting an airfoil and a blade root. The first portion constitutes a single part with at least one second portion constituting a blade inner platform, said blade then lacking a blade anti-tilting wall, or a blade anti-tilting wall, said blade then lacking a blade inner platform. The first portion also constitutes a single part with at least one third portion constituting a blade outer platform spoiler plate, said blade then lacking a blade outer platform wiper plate, or a blade outer platform wiper plate, said blade then lacking a blade outer platform spoiler plate.

Abstract: A method of making an aerofoil comprises the steps of providing first and second skin panels and first and second web-forming membranes. The web-forming membranes each have a series of elongate slots formed longitudinally therein so as to define a series of alternating wide and narrow strips. The wide strips of one membrane are arranged against the narrow strips of the other membrane and the skin panels are arranged either side of the two web-forming membranes. Parts of the web-forming membranes and parts of the skin panels are treated with a release layer and the sub-assembly is compressed and heated so as to effect diffusion bonding between those parts of the membranes and skin panels which are not treated with the release layer. The sub-assembly is then heated and inflated so as to draw the first and second skin panels apart and that, in turn, causes the web-forming membranes to form webs internally.

Abstract: Vibration damping is important with regard to such components as hollow turbine blades in gas turbine engines. Traditionally damping has occurred through damping elements secured at the root or tip of such blades. Such damping is not optimised and results in potential problems with wear in operational life. By providing a tube of deformable material which can be located within a hollow cavity it is possible to provide an element which through friction engagement can absorb vibration energy and therefore damp such vibration. The tube incorporates a number of cuts and/or grooves in an appropriate pattern in order to define a deformation profile once the tube is expanded in location. The tube is secured in position internally upon an expandable element which is typically an inflatable device. Once in position the tube is retained in its expanded deformable profile and the engagement between the tube and the hollow cavity wall surface results in energy absorption through vibration episodes.

Abstract: A method of forming a fan blade includes the step of positioning a piece of low density filler in a cavity of an inner exposed surface of a fan blade body. An upper surface of the piece of low density filler is located above the inner exposed surface of the fan blade body, and the low density filler has a density lower than a density of a material of the fan blade body. The method further includes the steps of positioning the fan blade body in a lower die of a press and applying pressure to the inner exposed surface of the fan blade body with an upper die of the press to compress the low density filler such that the upper surface of the piece of low density filler is approximately flush with the inner exposed surface of the fan blade body.

Abstract: A wind turbine blade used in a wind power generator that receives wind and rotates a rotating shaft of a generator includes at least two layers on a surface of a blade body, one of the layers being colored with a coating material different in color from the blade body and the rest of the layers. The layers are provided at least on a tip, particularly at a front edge of the wind turbine blade. A wind turbine blade monitoring system that monitors the wind turbine blade includes: an imaging unit that images the wind turbine blade in a predetermined position over a predetermined period at timing when the wind turbine blade passes through the predetermined position; and an indication unit that chronologically indicates imaging results of the wind turbine blade imaged by the imaging means.

Abstract: A method for retrofitting a rotor blade of a wind turbine is disclosed.

Abstract: A method includes joining an integral bulkhead and a blade shell to form a blade and separating the blade into two blade segments at a location including the integral bulkhead such that each blade segment comprises a portion of the integral bulkhead and a portion of the blade shell.

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: A wind turbine rotor blade assembly includes 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 is attached along the trailing edge and includes a first strip member having a span-wise attachment section attached to pressure side, and a second strip member having a span-wise attachment section attached to the suction side. Each of the first and second strip members has an outboard edge and an extension section that projects chord-wise beyond the trailing edge. The extension sections are adhesively attached to each other outboard of the trailing edge along a span-wise length of the first and second strip members and define an adhesively bonded closure edge of the edge extension. A method is also provided for forming an edge extension on a wind turbine rotor blade.

Abstract: A method of manufacturing a turbine blade is provided. The described method includes providing an elongate core, surrounding the elongate core with a textile structure, arranging the elongate core surrounded by the textile structure in a mold, pressing at least a part of the textile structure against the mold, and injecting a curing agent into the mold to interact with the textile structure, thereby forming the turbine blade. Also, a system and an intermediate member for manufacturing a turbine blade by means of the described method is provided.

Abstract: A composite blade has a root and a tip in a spanwise direction and a leading edge and a trailing edge in a chordwise direction. The composite blade includes a three-dimensional woven preform having weft yarns and warp yarns. The weft yarns extend in the spanwise direction of the composite blade. The warp yarns interweave the weft yarns and extend in the chordwise direction of the blade.

Abstract: A process for manufacturing a metal part reinforced with ceramic fibers, in which: a housing is formed for an insert in a main metal body having an upper face; an insert formed from a bundle of fibers with a metal matrix is placed in the housing; a metal cover is placed on the main body so as to cover the insert; the cover is welded onto the metal body; a hot isostatic pressing operation is carried out; and the part obtained is machined to the desired shape. The housing has the shape of a notch of L-shaped cross section with a face perpendicular to the upper face and a face parallel to the upper face, the cover having an internal notch of L-shaped cross section, this having a shape complementary to that of the metal body with said insert, the cover being shaped on the outside so that the pressure forces are exerted perpendicular to said faces of the notch.

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 method for making a metallic part, includes positioning at least one metallic coil formed from flexible metal foil including a plurality of notches, on a shaping tool, the at least one coil being manually deformable when cold along three directions in space (X, Y, Z); hot isostatic pressing the at least one metallic coil in a tool causing compaction of the metallic coil so as to obtain the metallic part.

Abstract: A masking system for an airfoil comprises a locator for positioning along the trailing edge of the airfoil, and first and second mask sections. The first mask section has a trailing edge portion with locator pins for cooperating with a positioning tab on the locator to position the first mask section along the trailing edge of the airfoil, and a leading edge portion for extending around the leading edge of the airfoil to locate the first mask section along the convex surface. The second mask section has a retainer portion for cooperating with a retainer process on the first mask section to retain the second mask along the leading edge of the airfoil, and a flange portion for extending between the locator pins to locate the second mask along the concave surface.

Abstract: A method is provided for treating turbine blades having holes for discharging cooling air. A protective layer is provided and then the holes that are partly or completely closed by the protective layer are opened again. Coordinates concerning the position of the holes are acquired before the protective layer is applied using a laser triangulation sensor using a light source generating a light beam and a light detector. The data obtained is used after application of the protective layer to control a removal device for removing protective layer partly or wholly covering the holes. Each hole is measured by the light beam being shone into the hole in different positions in relation to the longitudinal mid-axis of the latter. The light beam is shone into the respective hole in a plane at at least three different angles to the longitudinal mid-axis thereof.

Abstract: A method of designing an airfoil for a gas turbine engine according to one embodiment of this disclosure can include localizing a sweep angle at a leading edge of a tip region of the airfoil, and localizing a dihedral angle at the tip region of the airfoil. The dihedral angle can be applied by translating the airfoil in direction normal to a chord of the airfoil.

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: A rotor blade element and a method for improving the efficiency of a wind turbine rotor blade are provided. The wind turbine rotor blade element is adapted for mounting on the wind turbine rotor blade. The wind turbine rotor blade has a trailing edge, a suction side and a pressure side. The blade element has a trailing edge, a first surface and a second surface. The first surface forms a pressure side surface portion. The second surface has a suction side surface portion and a contact surface.

Abstract: Plural saddle shape patches are formed on a blank material for forming a blade using a manufacturing apparatus provided with a punch support having punches each with a holder attached to be opposite with one another at a predetermined interval corresponding to a thickness of the blank material. The punch support is mounted to a second ram via a second rotational mechanism which is rotatable in a direction in which the ram moves. The die is attached to the first ram via the first rotational mechanism. The actuator controls the rotating angles of both the rotational mechanisms.

Abstract: In one aspect, a method for manufacturing a rotor blade for a wind turbine is disclosed. The method may generally include assembling a blade blank comprising a shear member and a volume of core material and removing material from the blade blank to form a body having a pressure side and a suction side extending between a leading edge and a trailing edge. The shear member may have a first end disposed adjacent to the pressure side and a second end disposed adjacent to the suction side. In addition, the method may include positioning a skin around an outer perimeter of the body.

Abstract: A wind turbine blade includes one or more electric powered modules powered by light beams so as to provide a galvanic separation between the electric powered modules and a lightning protection system in a wind turbine blade. The modules have a power supply converting an energy source in the form of light beams to electrical power for the one or more modules. A wind turbine and a method for manufacturing a wind turbine blade are also disclosed.

Abstract: A static structure of a gas turbine engine according to an exemplary aspect of the present disclosure includes a multiple of airfoil sections between an outer ring and an inner ring. A spring biased tie-rod assembly is mounted through at least one of the multiple of airfoil sections.

Abstract: A method for producing a metallic part including inner reinforcements of ceramic fibers, according to which: at least one recess for an insert is machined in a metallic body having an upper surface; at least one insert of ceramic fibers in a metallic matrix is arranged in the recess; the insert is covered with a cover; the gap around the insert is placed under a vacuum and hermetically sealed; the entire metallic body with the cover is treated by hot isostatic compaction; and the treated assembly is machined to produce the part. The insert is rectilinear, and the recess for the insert in the metallic body forms a rectilinear groove, the cover being dimensioned so as to be able to placed on the insert in the recess after having been shrunk by cooling and to establish a tight fit in the groove by dilation such as to close the space.

Abstract: A turbine engine blade made of composite material including fiber reinforcement densified by a matrix is fabricated by a method including: performing three-dimensional weaving to make a single-piece fiber blank; shaping the fiber blank to obtain a single-piece fiber preform having a first portion forming a preform for a blade root and an airfoil, at least one second portion forming a preform for a blade inner platform or for wipers of a blade outer platform, and at least one third portion forming a preform for reinforcing a blade inner platform or for overhangs of a blade outer platform; and densifying the fiber preform with a matrix to obtain a composite material blade having fiber reinforcement constituted by the preform and densified by the matrix, and forming a single piece with an inner and/or outer platform incorporated therein.

Abstract: A method of manufacturing a wind turbine rotor blade includes, in one embodiment, the steps of providing a core, and applying at least one reinforcing skin to the core to form a blade subassembly. Each reinforcing skin is formed from a mat of reinforcing fibers. The method also includes applying a micro-porous membrane over the at least one reinforcing skin, applying a vacuum film over the micro-porous membrane, introducing a polymeric resin to the core, infusing the resin through the core and through the at least one reinforcing skin by applying a vacuum to the blade assembly, and curing the resin to form the rotor blade.