Abstract: Disclosed is a tip section for a wind turbine blade. The tip section comprises an intermediary blade section comprising a first shell part forming a first side of the intermediary blade section and a second shell part forming a second side of the intermediary blade section, the intermediary blade section having a leading edge and a trailing edge and extending from an intermediary blade section first end to an intermediary blade section second end; a tip part forming an end of the tip section and having been rigidly attached to the intermediary blade section first end, the tip part having an outer surface comprising a metal area; and a number of one or more superficial metal strips extending along an outer surface of the intermediary blade section. A wind turbine blade with such a tip section and the manufacturing of such a wind turbine blade is also disclosed.

Abstract: A guide vane assembly for a nacelle of a gas turbine engine includes a forward vane and an aft vane. The aft vane is located aft of the forward vane and forward of a plurality of fan blades. The forward vane defines a fixed pitch angle and the aft vane is movable between a first pitch angle and a second pitch angle.

Abstract: Provided is a turbine blade, with a first and a second elongated web connected to an upper and a lower half shell, with each web including an upper and a lower flange connecting the respective web to the respective half shell, and with the first and second webs being supported by respective first and second reinforcement structures, which reinforcement structures extend in the lengthwise direction of the blade, wherein each first and second reinforcement structure supporting the first and second web includes at least one stack composed of several pultruded composite strips including carbon fibers with the strips being fixed in a resin matrix, wherein each at least one stack composed of the pultruded composite strips is an integral part of the respective first and second web and builds the respective flange, which is attached to the inner layer of the respective upper and lower shell.

Abstract: An airfoil for a gas turbine engine includes a blade body, a leading edge sheath, and an energy absorbing insert. The blade body has a pressure side and a suction side that each between a forward portion and a trailing edge. The leading edge sheath has a leading edge portion that is spaced apart from the forward portion, a first arm that engages the pressure side, and a second arm that engages the suction side. A cavity is defined between the leading edge portion, the first arm, the second arm, and the forward portion. The energy absorbing insert is disposed within the cavity and improves the impact resistance of the airfoil.

Abstract: A process for manufacturing a blade made of composite material for a turbomachine. The blade includes an airfoil having a pressure side and a suction side which extend from a leading edge to a trailing edge of the airfoil. The blade further includes a metal sheath that extends along the leading edge of the airfoil. The process includes the steps of: placing a preform, produced by three-dimensionally weaving fibers, in a mold, the sheath being positioned on an edge of the preform intended to form the leading edge of the airfoil; and injecting polymerizable resin into the mold to impregnate the preform so as to form the airfoil after solidifying. At least one double-sided adhesive film may be inserted between the sheath and the edge of the preform prior to injection of the resin.

Abstract: A method of manufacturing a rotor blade component for a rotor blade of a wind energy installation, a rotor blade component, and a wind energy installation comprising such a rotor blade component. The method includes manufacturing a layer system including a first layer of a first material and a second layer of a second material. The second material has a smaller modulus of elasticity than the first material, and the second layer extends at least partially along the first layer. The layer system is beveled at least at one end with the aid of at least one separation process such that the second layer projects beyond the first layer at the at least one end of the layer system. The layer system is connected to at least one other such layer system so as to form the rotor blade component.

Abstract: A three-dimensional orthogonal woven composite outlet guide vane and a manufacturing method are provided. Near-net-shaped manufacturing of the outlet guide vane is realized, and a vane profile-platform junction of the outlet guide vane is reinforced by designing a bifurcation of the preform. A basic structure of a three-dimensional orthogonal woven composite and a bifurcation of the vane profile-platform junction are used, so that the ultimate strength under tension, compression and bending of the outlet guide vane structure are significantly improved, and the weight of the outlet guide vane is reduced. Structural load bearing and force transmission functions of a strut are provided by the outlet guide vane while the functions of vane rectification, noise reduction and others are ensured. As a result, the weight and dimensions of an aeroengine, as well as structural complexity, are reduced by removing struts.

Abstract: A main laminate forming a load carrying structure for a wind turbine blade, the main laminate extending in a spanwise direction from a proximal end through a transition region to a distal end, wherein the main laminate comprises: a top side, a bottom side, and a thickness direction extending between the top side and the bottom side; a pultrusion portion including a bottom pultrusion element extending to a transition end of a transition portion located in the transition region of the main laminate; a plurality of stacked fibre-reinforced elements including bottom and top fibre-reinforced elements extending to a transition end of a transition portion located in the transition region, wherein the pultrusion portion and the plurality of fibre-reinforced elements are connected by a joint in the transition region of the main laminate.

Abstract: A manufacturing method is provided. During this method, a preform component is provided for a turbine engine. The preform component includes a substrate. A preform meter section and a preform diffuser section are formed in the substrate. An internal coating is applied to at least the preform meter section to provide a meter section of a cooling aperture. External coating material is applied over the substrate. The applying of the external coating material forms an external coating over the substrate. The applying of the external coating also builds up the external coating material within the preform diffuser section to form a diffuser section of the cooling aperture.

Abstract: A method for coating a turbomachine guide vane including a root and a tip, an extrados face and an intrados face connected to one another by a leading edge and a trailing edge, the method including completely covering one of the faces of the vane with a polymer coating of thickness (e1) provided with grooves, removing the grooves from a part of the polymer coating in such a way that the polymer coating includes a grooved zone and a non-grooved zone, coating the non-grooved zone with a coat of paint of thickness (e3) such that the thickness of the coat of paint superimposed on the non-grooved zone is substantially equal to the thickness (e1) of the grooved zone.

Abstract: In one exemplary embodiment of the present disclosure an airfoil is provided. The airfoil defines a spanwise direction, a root end, and a tip end. The airfoil includes: a body defining a pressure side and a suction side and extending along the spanwise direction between the root end and the tip end, the body formed of a composite material; and a spar enclosed in the body of the airfoil extending along the spanwise direction, the spar comprising a plurality of spar segments arranged in an overlapping configuration along the spanwise direction.

Abstract: A method of manufacturing a wind turbine blade shell part is described. Fibre mats and a root end insert are laid up in a mould part in a layup procedure by use of an automated layup system. The fibre mats are laid up by use of a buffer so that the fibre mats may continuously be laid up on the mould surface, also during a cutting procedure. The root end insert is prepared in advance and mounted on a mounting plate. The root end insert is lowered onto the mould by use of the mounting plate and a lowering mechanism. After the wind turbine blade shell has been moulded, the mounting plate is removed.

Abstract: A method of assembling a member and a cap of a vane using a tool which allows the application of a pressing force of the cap against the member during a step of polymerisation by heating a resin for bonding these components. To this end, the tool includes an inflatable bladder and a pocket which surrounds the bladder and the vane so that the inflated bladder applies the pressing force. The heating can be carried out by resistors which are mounted in the bladder and/or using a device for supplying external heat.

Abstract: The invention relates to a blade of a fan of a turbomachine, comprising a structure made from composite material, including a fibrous reinforcement obtained by means of the three-dimensional weaving of strands and a matrix in which the fibrous reinforcement is embedded,—the fibrous reinforcement comprising a first portion forming the leading edge and a second portion forming all or part of the trailing edge,—the strands of the fibrous reinforcement comprising first strands having a predetermined elongation at break and second strands having an elongation at break higher than that of the first strands, the first portion comprising all or some of the first strands while the second portion comprises all or some of the second strands.

Abstract: The present invention relates to a fan blade (3) having a structure made from a composite material, comprising a fibrous reinforcement (5), which is obtained by three-dimensional weaving of warp strands and weft strands, and a matrix in which the fibrous reinforcement (5) is embedded, wherein—the fibrous reinforcement (5) comprises a first portion (14) forming the trailing edge (9) of the structure made from a composite material and a second portion (15) forming its leading edge (8), and wherein—the warp strands of the fibrous reinforcement (5) comprise first strands (12) having a predetermined stiffness and second strands (13) having a greater stiffness than that of the first strands (12), the first portion (14) comprising all or part of the first strands (12) and being devoid of second strands (13) while the second portion (15) comprises all or part of the second strands (13).

Abstract: An airfoil assembly for a gas turbine engine includes an airfoil extending radially relative to a central reference axis. A spar is located within the airfoil and spaced from the airfoil at all radial locations along the airfoil such that a gap is maintained between the airfoil and the spar. A foam is located between the airfoil and the spar.

Abstract: A system and method for measuring characteristics, comprising: a directed energy source having an energy output which changes over time, incident on an object undergoing additive manufacturing; a sensor configured to measure a dynamic thermal response of at least a portion of the object undergoing additive manufacturing proximate to a directed location of the directed energy source over time with respect distance from the directed location; and at least one processor, configured to analyze the measured dynamic thermal response to determine presence of a manufacturing defect in the object undergoing additive manufacturing, before completion of manufacturing.

Abstract: This invention relates to a method of manufacturing a wind turbine blade and a wind turbine blade thereof. A central core element and a plurality of side core elements are sandwiched between first layers and second layers of a first fibre material. The central core element is spaced apart from the side core elements to form a first and a second recess. This sandwich structure is then impregnated with a first resin and cured in a first step. Layers of a second fibre material of a first and a second main laminate are laid up in the first and second recesses. The first and second main laminates are then impregnated with a second resin and cured in a second step.

Abstract: A method of manufacturing a component for a gas turbine engine includes applying a thermoplastic polymer sheet over a composite body for the component; applying a shield over part of the composite body, the shield terminating at an end which overlies the thermoplastic polymer sheet and defines an interface between shielded and unshielded regions of the component; and pressing the shield into the thermoplastic polymer sheet so that the thermoplastic polymer sheet deforms around the end of the shield, such that the exterior profile of the component at the interface between the shielded and unshielded regions is flush.

Abstract: Provided is a rotor blade of a wind turbine including a leading edge section with a leading edge and a trailing edge section with a trailing edge, wherein the leading edge and the trailing edge divide the surface of the rotor blade into a suction side and a pressure side. The rotor blade further includes a blade shell for defining the outer shape of the rotor blade and a heating mat for anti-icing and/or deicing purposes which is arranged upon the blade shell. In the outboard region of the rotor blade, the heating mat is substantially or completely covered by a protective shield made of an electrically insulating polymer material. Use of a protective shield made of electrically insulating polymer material for electrical insulation of a heating mat in particular, against lightning strikes is also provided.

Abstract: A method for reducing extreme loads acting on a component of a wind turbine includes measuring, via one or more sensors, a plurality of operating parameters of the wind turbine. Further, the method includes predicting at least one blade moment of at least one rotor blade of the wind turbine based on the plurality of operating parameters. The method also includes predicting a load and an associated load angle of the at least one rotor blade as a function of the at least one blade moment. Moreover, the method includes predicting a pitch angle of the at least one rotor blade of the wind turbine. In addition, the method includes generating a load envelope for the component that comprises at least one load value for the pitch angle and the load angle. Thus, the method includes implementing a control action when the load is outside of the load envelope.

Abstract: Disclosed is a spar beam and a wind turbine blade comprising a spar beam. The wind turbine blade comprising a first blade section extending along a longitudinal axis from a root to a first end and a second blade section extending along the longitudinal axis from a second end to a tip. The spar beam comprises a conductive beam sheath circumscribing at least a beam sheath angular distance of the spar beam about the spar beam axis and longitudinally extending from a fourth beam axis position to a fifth beam axis position.

Abstract: A composite airfoil is disclosed. In various embodiments, a composite airfoil as disclosed herein includes an outer skin comprising one or more layers of carbon fiber composite material, the outer skin defining an aerodynamic surface having a leading edge; and a reinforcement material comprising a roll of fiberglass reinforced fabric positioned behind the outer skin along at least a portion of the leading edge.

Abstract: The present invention includes an apparatus for protecting an aerodynamic surface from erosion including a screen capable of being applied to a leading edge of the aerodynamic surface; and an erosion protection coating applied to the screen before or after the screen is applied to the leading edge, wherein the erosion protection coating protects the aerodynamic surface from erosion.

Abstract: An airfoil defining a span extending between a root and a tip. The airfoil includes a frangible airfoil portion extending between a leading edge and a trailing edge and extending between the tip and a fusion line along the span. The frangible airfoil portion includes a first material defining a first modulus of elasticity and further defines an internal cavity. The airfoil includes a residual airfoil portion coupled to the frangible airfoil portion extending from the fusion line to the root along the span and including a second material defining a second modulus of elasticity greater than the first modulus of elasticity. The residual airfoil portion meets the frangible airfoil portion at the fusion line.

Abstract: A method of manufacturing a spar for a propeller blade comprises forming a hollow inner core from a composite material, and then braiding carbon fibres around the inner core to form an outer spar structure. The hollow inner core may be formed using an inflatable bladder and a mould defining an outer shape of the spar. This construction avoids the need for a foam core to be provided within the spar.

Abstract: A joint for a metallic skin structure includes a first end portion of the metallic skin structure and a second end portion of the metallic skin structure, wherein the first end portion and the second end portion of the metallic skin structure are secured together along a line of securement. The joint further includes at least one reinforcing fiber embedded within at least one of the first end portion of the metallic skin structure or the second end portion of the metallic skin structure extends orthogonal relative to the line of securement.

Abstract: A fan blade for a gas turbine engine is disclosed. The disclosed fan blade includes an airfoil having a leading edge, a trailing ling edge, a convex side, a concave side and a distal tip. The leading edge, trailing edge, convex side and concave side of the airfoil is at least partially coated with an erosion resistant coating. The distal tip of the airfoil is coated with a bonded abrasive coating. The bonded abrasive coating engages the abradable coating disposed on the fan liner and, because of its low thermal conductivity, reduces heat transfer to the distal tip of the fan blade. The reduction in heat transfer to the distal tip of the fan blade preserves the integrity of erosion resistant coatings that may be applied to the body or the airfoil of the fan blade.

Abstract: A propeller blade comprises a root, a tip distal from the root, a trailing edge extending from the root to the tip, a trailing edge, e.g. foam, insert, a shell forming an outer surface of the propeller blade and a plurality of stitches of yarn extending through two parts of the shell adjacent the trailing edge, wherein the yarns do not extend through the trailing edge insert.

Abstract: A method for manufacturing a vane from a composite material with a fitted metal leading edge includes the successive draping, on a template of the leading edge of the vane to be manufactured, of a first layer of a base material and of a second layer of an adhesive material, the transfer of the first and second draped layers in the recess of a metal foil, the positioning of the foil including the first and second draped layers alongside the leading edge of a vane preform including a fiber reinforcement impregnated with a precursor of a matrix, the co-curing of the vane preform and of the first and second draped layers so as to obtain a vane made of composite material including on its leading edge a bonded metal foil.

Abstract: A platform for a gas turbine engine according to an example of the present disclosure includes, among other things, a platform body that has a gas path surface extending axially between a leading edge and a trailing edge and extending circumferentially between opposed mate faces. A plurality of platform flanges extend from the platform body to define one or more slots. The one or more slots are dimensioned to receive a respective flange of a rotatable hub, and each platform flange has a retention member dimensioned to receive a retention pin to mount the platform body. The platform body includes a composite wrap extending about a perimeter of the platform body to define an internal cavity. At least one honeycomb core has a plurality of cells that is disposed in the internal cavity.

Abstract: Various embodiments provide methods in which a metal matrix composite (MMC) material is incorporated into a metallic structure during a one-step near-net-shape structural forming process. Various embodiments provide in-situ selective reinforcement processes in which the MMC may be pre-placed on a forming tool in locations that correspond to specific regions in the metallic structure. Various embodiment near-net-shape structural forming processes may then be executed and result in various embodiment metallic structural components with selectively-reinforced regions that provide enhanced mechanical properties in key locations.

Abstract: An investment casting method includes providing a stock investment casting core, bending the stock investment casting core to thereby form a production investment casting core that conforms to a design cooling passage shape, and casting an alloy around the production investment casting core to form a cast article.

Abstract: A fan blade having an opening on one side exposing one or more cavities, and a composite cover that fits over the opening, is provided. The composite cover has a variable thickness resulting from the layering of cover plies having different shapes, and is designed to achieve a lightweight fan blade having an optimal level of stiffness.

Abstract: A rotating component includes an airfoil section with a free end, the airfoil section being formed of a composite core with a metallic skin and an abrasive coating applied to the free end.

Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 2.85-3.15 inch (72.4-80.0 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 1.52-1.82 inch (38.6-46.2 mm). The airfoil element includes at least two of a first mode with a frequency of 506±10% Hz, a second mode with a frequency of 1732±10% Hz, a third mode with a frequency of 2268±10% Hz, a fourth mode with a frequency of 4007±10% Hz, a fifth mode with a frequency of 4851±10% Hz and a sixth mode with a frequency of 6416±10% Hz.

Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 2.13-2.43 inch (54.2-61.8 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 3.56-3.86 inch (90.3-97.9 mm). The airfoil element includes at least one of a first mode with a frequency of 1049±10% Hz and a second mode with a frequency of 1271±10% Hz.

Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 0.63-0.73 inch (16.0-18.5 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 0.61-0.71 inch (15.5-18.0 mm). The airfoil element includes at least two of a first mode with a frequency of 4852±10% Hz, a second mode with a frequency of 11917±10% Hz, a third mode with a frequency of 30842±10% Hz and a fourth mode with a frequency of 35225±10% Hz.

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: A field of rotary blades, and more particularly to a method of fabricating a leading edge shield for protecting such a blade. The method includes at least steps of performing initial plastic deformation on at least one sheet from a pressure side sheet and a suction side sheet, using additive fabrication to add a reinforcement with a fiber insert on at least one of the pressure and suction side sheets, closing the pressure and suction side sheets around a core after the initial plastic deformation and after adding the reinforcement, performing subsequent plastic deformation by pressing the pressure and suction side sheets against an outside surface of the core after the sheets have been closed around the core, and extracting the core.

Abstract: The present disclosure is directed to methods for attaching a plurality of surface features to a rotor blade of a wind turbine. Such methods may include direct molding of the surface features to the rotor blade, bonding arrays of connected components to the rotor blade and subsequently removing connections between components, as well as using a flexible template with or without a tinted adhesive.

Abstract: A hybrid article is disclosed including a coating disposed on and circumscribing the lateral surface of a core having a core material. The coating includes about 35% to about 95% of a first metallic material having a first melting point, and about 5% to about 65% of a second metallic material having a second melting point lower than the first melting point. The coating is sinter-bonded to the core. A method for forming the hybrid article is disclosed including disposing the core in a die, introducing a slurry having the metallic materials into a gap between the lateral surface and the die, and sintering the slurry, forming the coating. A method for closing an aperture of an article is disclosed including inserting the hybrid article into the aperture, and brazing the hybrid article to the article, welding the aperture with the hybrid article serving as weld filler, or both.

Abstract: An airfoil for a gas turbine engine has a first layer forming a cavity having transitioning from a first thickness to a second thickness through a ply drop region. A second layer is secured to the first layer.

Abstract: A composite vane body formed of a composite material of a thermosetting resin or a thermoplastic resin, and reinforced fibers, and a metal sheath that is bonded to a leading edge section of the composite vane body via a soft adhesive to cover the leading edge section are included, and an adhesive filling section in which the soft adhesive is filled, a plurality of leading edge side contact sections that come into contact with a curved section corresponding to a leading edge of the metal sheath, and a plurality of protrusions that come into contact with a planar section corresponding to a vane surface of the metal sheath, with at least a same height as a thickness of a layer of a requisite amount of the soft adhesive filled in the adhesive filling section are formed in the leading edge section of the composite vane body. Attachment of the metal sheath to the leading edge section can be performed easily with high precision.

Abstract: A hybrid article is disclosed including a coating disposed on and circumscribing the lateral surface of a core having a core material. The coating includes about 35% to about 95% of a first metallic material having a first melting point, and about 5% to about 65% of a second metallic material having a second melting point lower than the first melting point. A method for forming the hybrid article is disclosed including disposing the core in a die, forming a gap between the lateral surface and the die, introducing a slurry having the metallic materials into the gap, and sintering the slurry, forming the coating. A method for closing an aperture of an article is disclosed including inserting the hybrid article into the aperture. Closing the aperture includes brazing the hybrid article to the article, welding the aperture with the hybrid article serving as weld filler, or a combination thereof.

Abstract: A spar cap assembly is for a wind turbine rotor blade. The spar cap assembly has a spar cap reinforced with carbon fibers, comprising a lightning conductor, which is arranged so as to run along the spar cap, and at least one potential-equalizing element, which establishes an electrical connection between the spar cap and the lightning conductor. The carbon fibers of the spar cap, the lightning conductor and the at least one potential-equalizing element are embedded in a common polymer matrix and are configured as a prefabricated assembly for integration into a wind turbine rotor blade half-shell after the curing of the polymer matrix.

Abstract: A hybrid article is disclosed including a coating circumscribing the lateral surface of a hollow core having a core material and a channel disposed within the lateral surface. The coating includes about 35% to about 95% of a first metallic material, and about 5% to about 65% of a second metallic material with a lower melting point than the first metallic material. A method for forming the hybrid article is disclosed including disposing the hollow core in a die, forming a gap between the lateral surface and the die, introducing a slurry having the metallic materials into the gap, and sintering the slurry, forming the coating. A method for closing an aperture of an article is disclosed including inserting the hybrid article into the aperture, and brazing the hybrid article to the article, welding the aperture with the hybrid article serving as weld filler, or a combination thereof.

Abstract: The present wind turbine blade comprises an airfoil structure comprising an airfoil shape, an internal support structure arranged spanwise along the length of the blade within the airfoil structure, and an elastic connection joining a portion of an inner surface of the airfoil structure with a portion of the internal support structure. The airfoil structure can be passively pitched relative to the internal support structure according to aerodynamic pressure distribution at different blade locations.

Abstract: A hybrid article is disclosed including a coating disposed on and circumscribing the lateral surface of a core having a core material. The coating includes about 35% to about 95% of a first metallic material having a first melting point, and about 5% to about 65% of a second metallic material having a second melting point lower than the first melting point. A method for forming the hybrid article is disclosed including disposing the core in a die, forming a gap between the lateral surface and the die, introducing a slurry having the metallic materials into the gap, and sintering the slurry, forming the coating. A method for closing an aperture of an article is disclosed including inserting the hybrid article into the aperture. Closing the aperture includes brazing the hybrid article to the article, welding the aperture with the hybrid article serving as weld filler, or a combination thereof.

Abstract: The invention relates to a turbine engine blade, particularly made of composite material, including: on the one hand, an airfoil (10) which exhibits: a leading edge (12), a trailing edge (14) opposite to the leading edge (12), intrados (16) and extrados (18) lateral walls which connect the leading edge (12) to the trailing edge (14), et on the other hand, a structural reinforcement (20) including a base (24) extending into two fins (26, 28) and designed to be applied to the leading edge (12) and the lateral walls (16, 18) of the airfoil (10), characterized in that the fins (26, 28) of the structural reinforcement (20) and/or the lateral walls (16, 18) of the airfoil (10) are shaped to maintain an assembly space (30) with nonzero thickness between at least one of the fins (26, 28) and the airfoil (10) when the structural reinforcement (20) is in place on the airfoil (10), said assembly space (30) extending from a free end (27, 29) of said fin (26, 28) toward the base (24) of the structural reinforcement