Abstract: A wind turbine blade including a shell structure defining a leading edge and a trailing edge, and an upwind shell and a downwind shell joined along at least one of the leading edge or the trailing edge. The shell structure includes an assembly of preformed parts processed into a collection of prefabricated laminates. The invention also includes a method of manufacturing a wind turbine blade, the method includes processing a number of preformed parts into a collection of prefabricated laminates and assembling the collection of prefabricated laminates to build a shell structure defining a leading edge and a trailing edge.

Abstract: A method and a device for strengthening the surface of workpieces, in particular of metal ones, by mechanical effects accompanying the impact of small projectiles or by mechanical effects accompanied by the impact of a shockwave induced by plasma created by electric evaporation of a metal foil are described.

Abstract: Described are systems and methods for providing a fault tolerant electrical power system that is configured to continue operating through various fault and/or failure conditions, so as to withstand certain single points of fault and/or failure conditions. Exemplary embodiments of the present disclosure can provide an exemplary electrical power system that includes various components that are electrically coupled to a shared direct current (DC) bus via protection devices that are configured to isolate the various components in the event of certain fault and/or failure conditions. Additionally, the exemplary electrical power system can also include a high-impedance midpoint grounding connection configured to shift the voltages of the shared DC bus in view of certain fault and/or failure conditions, as well as introducing certain separations (e.g., physical and/or electrical) to mitigate the possibility of certain faults and/or failure conditions.

Abstract: The present invention relates to a method of performing at least one post-moulding operation on a blade segment (70) of a wind turbine blade. The method comprises the providing a holding device (88) for supporting the blade segment (70) at its spar structure (62), the holding device (88) comprising a coupling member (90) for engaging the spar structure (62). The blade segment (70) is held with the holding device (88) such that the spar structure (62) of the blade segment (70) is engaged by the coupling member (90), and performing at least one post-moulding operation on the shell structure (82) of the blade segment (70).

Abstract: An exemplary embodiment of the present disclosure provides an electric utility pole, comprising a beam, a base, and an arm. The beam can be formed from a retired turbine blade and can comprise a first end and a second end. The base connected to the first end of the beam. The arm can be connected to the beam. The arm can be configured to support at least one electrical conductor.

Abstract: A blade for mounting on a rotor disc of a gas turbine engine includes platform segments between a airfoil and blade root and extending laterally from the blade, the platform segment having a curved profile defining a platform recess on a root side of the platform segment, the recess configured to cooperate with recesses of adjacent blades to define a blade pocket. A recessed region is defined in a rear surface of the blade root, and is configured to receive a complementary projection of the rotor disc upon mounting the blade on the rotor disc. The recessed region has a surface configured to abut a corresponding surface on the projection of the rotor disc to form a face seal. Methods of manufacturing such a rotor disc and of sealing a circumferential joint between such blades and the rotor disc are also disclosed.

Abstract: A stator assembly for an aircraft engine, has: vanes distributed about a central axis, a vane having: an airfoil extending from a first end to a second end along a span and from a leading edge to a trailing edge along a chord, the airfoil having a pressure side and a suction side opposed to the pressure side; a slot within the airfoil, the slot extending in a direction having a component along the chord, the slot located between the pressure side and the suction side; a port at the leading edge, the port fluidly communicating with the slot and with the gaspath; a mass located within the slot, the mass movable within the slot to shift a center of gravity of the vane in a chordwise direction; and a biasing member biasing the mass in a direction opposite a pressure force generated by the flow of fluid.

Abstract: A method for fusing a metal material with control of a melt pool on a substrate is provided. The method consists of providing a plurality of laser sources arranged on an imaginary hemispheric surface, wherein each laser source contains a laser tiltable relative to the longitudinal axis of the laser source housing and/or displaceable in the direction of the longitudinal axis of the housing. The optical axes of the lasers are inclined to the material feed direction toward a substrate. The optical axes of the inclined lasers intersect the material feed direction. The material is fed toward a substrate which is placed on a table that has at least three degrees of freedom for moving the substrate in a space relative to the focal points of the laser beams to impart to the object being printed a desired 3D configuration.

Abstract: The present invention relates to a method of manufacturing a wind turbine blade comprising the steps of manufacturing a pressure shell halves and arranging a spar structure (62) within one of the shell halves. The spar structure (62) comprises two parts releasably coupled to each other. The method results in a segmented wind turbine blade for easy transportation and re-assembly.

Abstract: A propeller includes a rotatable hub and at least two propeller blades coupled to the rotatable hub. Each of the propeller blades is formed from a combination of a first material having a negative Poisson's ratio (NPR) and a second material having a positive Poisson's ratio (PPR). The first material and the second material can be layered or can be formed as a matrix with one of the first or second material embedded in the other. In a layered configuration, a layer of the first material is positioned between adjacent layers of the second material, and the layers can be connected by tabs of NPR material. The combination of the NPR and PPR materials improve the strength and impact resilience of the propeller blades compared to conventional materials.

Abstract: A mounting tool includes a base component and an attachment means. The base component includes a mounting portion defining an attachment location for receiving and securing a repair tool so as to maintain the repair tool at a desired repair location and a first receiving portion defining a first cavity for receiving a portion of a wind turbine so as to be externally secured to the wind turbine. The attachment means may be adjustably secured to the first receiving portion of the base component and securable to the portion of the wind turbine so as to secure the mounting tool to the wind turbine at the desirable repair location.

Abstract: The present disclosure relates to wind turbine blades (22) configured to receive a peripheral device (250a, 250b, 250c) at a portion of the outer surface (211) of the blade (22), and wherein the wind turbine blade (22) is configured to magnetically couple to the peripheral device (250a, 250b, 250c). The present disclosure also relates to wind turbine blade assemblies (200) and methods (700) to provide the same.

Abstract: Provided is a method of shaping an initial edge seal along a longitudinal edge step of an add-on part mounted on the outer surface of a rotor blade, which method includes the steps of providing an initial edge seal along a longitudinal edge step of an add-on part mounted on an outer surface of a rotor blade, and removing a top layer of the initial edge seal. Further provided is wind turbine rotor blade.

Abstract: The present disclosure is directed to a method and system for repairing a blade for a turbomachine that has been damaged due to foreign object impact. Machine learning algorithms are used to determine an amount of material to be removed from one or more damage locations and determine an amount of material addition to the damaged portion(s) and/or at other locations on the blade to keep the natural frequencies of the repaired blade within design limits during operation.

Abstract: An internally cooled turbine blade for use in a gas turbine engine includes a serpentine channel extending within the turbine blade for flowing cooling air through the interior of the blade. The turbine blade includes turbulators positioned within the serpentine channel to cause or increase turbulence of the cooling air flowing through the serpentine channel, increasing the heat transfer between the turbine blade and the cooling air before exiting a plurality of air outlets within the turbine blade.

Abstract: The present invention is directed to a method for coating a component, wherein the component has a first and a second surface, and wherein the first and the second surface adjoin each other at an edge, in which method i) first of all, the edge between the first and the second surface is rounded, and ii) subsequently, a coating is applied to the first surface.

Abstract: An apparatus for 3D laser printing and a method for fusing a metal material with control of a melt pool on a substrate are provided. The apparatus contains a metal wire or powder feed unit and a plurality of laser sources symmetrically arranged on the surface of an imaginary hemisphere. Each laser source contains a laser with a laser beam focusing lens that focuses the laser beam in a focal point at a given distance from the focusing lens. The laser source is also provided with CPU/GPU-controlled devices for independently shifting each laser or a group of lasers along the optical axis and/or for tilting the lasers relative to the longitudinal axis of the source housing so that heating or fusing can be performed by placing the focal points of the lasers selectively at any point of the material or on a substrate for forming and controlling the melt pool.

Abstract: The present invention relates to a method of processing a component, wherein the component comprises at least one opening in a surface thereof, the method comprising: placing the component in an electrophoretic fluid comprising particles of a masking material as an electrode, applying a voltage to the component and a counter electrode of the component, depositing particles of the masking material in the electrophoretic fluid into the at least one aperture through electrophoresis to mask the at least one aperture; processing a surface of the component; and removing the masking material in the at least one opening.

Abstract: A rotor blade for a wind power installation with a longitudinal direction in which the rotor blade extends, at least one first rotor blade segment with a first end face, and at least one second rotor blade segment with a second end face, wherein the first rotor blade segment is coupled on the end face in the longitudinal direction to the second rotor blade segment, wherein the first and second rotor blade segments each comprise: a blade laminate with a plurality of laminate layers which are arranged stacked in a profile thickness direction, and arranged on the end face, a plurality of mounting elements for coupling the first rotor blade segment to the second rotor blade segment, wherein each of the mounting elements extends in the longitudinal direction and has two contact faces which are arranged transversely, in particular orthogonally to the longitudinal direction at a distance from one another which diminishes in non-linear fashion towards the end.

Abstract: Provided is a method for producing a wind turbine blade having a blade body including a body part and a tip part, the blade being produced by using a mold, wherein a prefabricated tip part having a first connection interface is arranged adjacent to the mold for producing the body part, whereby building elements for building the body part are arranged in the mold providing a second connection interface which corresponds to and connects to the first connection interface, whereafter both connection interfaces are fixed by applying a fixing agent and curing it.

Abstract: A tower and a wind turbine and be able to shoot water from the center point of a three to five blade wind turbine in a concentrated direction and from the blades to disperse water/fire retardant in a light to heavy spray from the tips of the blades covering a wider area for creating clean energy and suppressing wildfires.

Abstract: A guide vane for a vane assembly of a turbo machine, the guide vane can include: an aerofoil body including: a forward portion, a rear portion, and opposite outer surfaces, extending between the forward portion and the rear portion, a liner shaped with a sheet like geometry, the liner being configured for being fixed to the aerofoil body, the liner including: a first portion configured for being connected to the forward portion of the aerofoil body, a trailing edge portion shaped with a convex geometry, a first coupling portion extending between the first portion and the trailing edge portion, and configured for being fixed to an outer surface of the aerofoil body, a second portion extending from the trailing edge portion and configured for being connected to the rear portion of the aerofoil body, wherein when the first coupling portion of the liner is fixed to an outer surface of the aerofoil body: the trailing edge portion of the liner extends from the rear portion of the aerofoil body, and the second porti

Abstract: A method of manufacturing a TiAl alloy impeller includes a blank preparation step in which a blank of the TiAl alloy impeller is prepared, wherein the blank has a shaft portion and a plurality of blades, and a thickness of an outer edge of each of the blades of the blank is set so as to be larger than a thickness of an outer edge of a blade of the TiAl alloy impeller, and an additional work step in which an additional work is performed on each of the blades of the blank. In the additional work step, the additional work is performed on a first surface of a portion that includes at least the outer edge of each of the blades or the first surface and a second surface of the portion thereof.

Abstract: A method for forming large titanium parts includes forming bends into a titanium plate for form a bent part. The bent part is then roll-formed to form contours into the bent part. The surfaces of the contoured part are rough-machined, and the part is then secured to a bladed form fixture. The bladed form fixture comprises a plurality of header boards that secure the part to the fixture. The fixture part is placed in a thermal vacuum furnace and a stress-relieving operation is performed. The part is removed from the fixture and final machining takes place.

Abstract: A bi-metal variable geometry turbocharger (VGT) vane includes a structural, airfoil-shaped flag portion, and a functional, cylindrically-shaped shaft portion connected to the flag portion. The flag portion and the shaft portion are formed of a first metal alloy, and the shaft portion further includes a surface area formed of a second metal alloy different from the first metal alloy.

Abstract: A rotor blade for a wind turbine includes first and second blade segments extending in opposite directions from a chord-wise joint. Each of the first and second blade segments includes at least one shell member defining an airfoil surface and an internal support structure. The internal support structure of the first blade segment includes a beam structure extending lengthwise, whereas the internal support structure of the second blade segment includes a receiving section that receives the beam structure of the first blade segment. Further, the rotor blade includes at least one chord-wise extending pin positioned through the beam structure and the receiving section at the chord-wise joint so as to secure the first and second blade segments together. The rotor blade includes at least one additional support member that receives a portion of the chord-wise extending pin so as to reduce a chord-wise bending deflection of the chord-wise extending pin at the chord-wise joint.

Abstract: The invention relates to a fan blade (1) comprising: —an aerofoil (8) made of a composite material comprising a fibrous reinforcement densified by a polymer matrix, a leading edge (4) and a trailing edge (5), and —a structural shield (10) fitted and attached to the leading edge (4) or the training edge (5), and —at least one stiffener (20) formed integrally and in one piece with the structural shield (10), said stiffener (20) extending in a cavity (15) formed between the shield (10) and the leading edge (4) or the trailing edge (5) so as to increase a stiffness of the blade (1).

Abstract: The invention refers to a blade for a turbomachine comprising a shroud which is positioned on a tip side of the blade having an outer surface having at least one circumferential web arranged thereon, at least one pocket recessed in the outer surface and a hardfacing provided on at least one edge of the shroud wherein a pocket recessed in the outer surface is arranged adjacent to the hardfacing and a side face of the pocket joins the supporting wall with a radius corresponding at least to the length of the shorter extension of the supporting wall and at most to 1.5 times the length of the larger extension of the supporting wall.

Abstract: A turbine engine blade having an aerodynamic surface extending a first direction between a leading edge and a trailing edge and in a second direction, perpendicular to the first direction, between a root of the blade and a tip of the blade, the aerodynamic surface being made of a fiber-reinforced organic matrix composite material, and a metallic structural reinforcement bonded by an adhesive joint to the leading edge whose shape it follows and which has over its entire height a substantially V-shaped section with a base extended by two lateral flanks having a thinned profile at free ends directed toward the trailing edge, the adhesive joint being locally supplemented below the free ends of the lateral flanks by an elastomeric polymer introduced in the form of solid particles into the adhesive joint and adhered to the aerodynamic surface and/or the free ends of the lateral flanks during a polymerization phase.

Abstract: The present invention relates to a method for producing a component of a ?-TiAl alloy, in which, in a first step, a forging blank made of a ?-TiAl alloy is built up from a powder material by an additive method, and subsequently, in a second step, the forging blank is reshaped into a semi-finished product, wherein the degree of reshaping over the entire forging blank is high enough that, in a third step, the structure is recrystallized during a heat treatment. In addition, the invention relates to a component produced therefrom.

Abstract: A free-tipped axial fan assembly features a shroud barrel comprising an inlet, the radius of said inlet at its upstream end being greater than the radius of said inlet at its downstream end. An angle, in a plane including the fan axis, between the surface of said inlet and the direction of the fan axis varies non-monotonically with respect to a surface coordinate which increases with distance along the surface of the inlet.

Abstract: A system (24) and method are described herein for manufacturing a wind turbine blade (22) proximate to the final installation site of a wind turbine (10). The system (24) includes a creel (72) of feeders (74) configured to apply strengthening elements (62) onto a plurality of shell core sections (26) coupled together and fed through the creel (72). The shell core sections (26) include an external surface (56) with a plurality of external grooves (58) recessed into the external surface (56) such that the strengthening elements (62) are laid into the external grooves (58). The system (24) also includes a deposition station (78) configured to apply an outer surface material layer (82) in fluid form to cover the external surface (56) and the plurality of strengthening elements (62).

Abstract: After a free-form surface is machined on an elongated material 1 with a projection 3 and a blade root 4 held, the holding of the projection 3 is released to release strain generated during machining. Upon release of the holding, the entire elongated material 1 deforms, and the projection 3 moves from a holding position A to a strain-released position B. A re-holding position C obtained by correcting the position B by the deformation amount of the elongated material 1 due to the weight of the elongated material 1 is determined, and the projection 3 is held again at the re-holding position C for further machining the free-form surface on the elongated material 1.

Abstract: The present invention provides a gas turbine nozzle capable of reducing stress related to thermal elongation caused by a rise in gas turbine nozzle temperature and thus reducing stress produced when thermal deformation occurs in the gas turbine nozzle. The gas turbine nozzle according to the present invention includes nozzles formed integrally through an inner perimeter end wall and an outer perimeter end wall. The inner perimeter end wall has an upstream connection portion and a downstream connection portion. The upstream connection portion extends radially inward to be connected to an inner perimeter diaphragm. The downstream connection portion is located downstream from the upstream connection portion and extends radially inward to be connected to the inner perimeter diaphragm.

Abstract: A method of forming a wind turbine blade is provided which includes upper and lower blade mold halves, and a shear web having at least one aperture formed therein. A plurality of bulkheads are attached to the shear web and the shear web can be lifted and rotated, without need for a complex gantry/galactica apparatus, to be placed inside the lower blade mold. The upper mold half can then be closed with the shear web and bulkhead(s) disposed within the blade interior. A heating fluid can be pumped into the interior to pass through the bulkheads, circulating around the shear web and exiting the blade root with the assistance of a sump to pull the cold air outside the blade.

Abstract: Methods for manufacturing composite components having complex geometries are provided. In one exemplary aspect, a method includes laying up each of a plurality of laminates to an initial shape with a substantially planar geometry or a gently curved geometry. Then, a laid up laminate is formed to a final shape for each predefined section defined by the composite component to be manufactured. Thereafter, the laminates formed to their respective final shapes are stacked to build up the complex geometry of the composite component. Next, the composite component can be cured and finish machined as necessary to form the completed composite component.

Abstract: A wind turbine blade and associated method of manufacture is described. The blade comprises an outer shell formed of first and second half shells joined together. A shear web is arranged inside the outer shell. The shear web has a web panel disposed between first and second longitudinally-extending mounting flanges. The shear web is bonded to inner surfaces of the respective half shells via a first adhesive bond line between the first mounting flange and the inner surface of the first half shell and a second adhesive bond line between the second mounting flange and the inner surface of the second half shell. One or more bond spacers are provided in the second bond line, and optionally in the first bond line. The bond spacers are compressed between a shear web mounting flange and an inner surface of a half shell and are plastically deformed. The method of making the shear web involves compressing and the one or bond spacers in the bond line(s) such that they undergo plastic deformation.

Abstract: A method for manufacturing a blade, the method includes casting a nickel alloy blade precursor having an airfoil and a root. The airfoil and the root are solution heat treating differently from each other. After the solution heat treating, the root is wrought processed. After the wrought processing, an exterior of the root is machined.

Abstract: A process includes applying a slurry to a surface of a metallic article to produce a slurry film on the surface. The slurry is composed of a liquid carrier, chromium and aluminum, and an agent that is reactive with the chromium and aluminum to form intermediary compounds. The article and slurry film are then thermally treated at an activation temperature at which the agent reacts with the chromium and aluminum to form the intermediary compounds. The intermediary compounds deposit the chromium and aluminum on the surface. The thermal treating also diffuses the chromium and aluminum into a sub-surface region of the article such that the sub-surface region becomes enriched with chromium and aluminum.

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, a first portion welded to a second portion along an interface such that at least the first portion establishes an airfoil section and the second portion establishes a root section mountable to a rotatable hub. The airfoil section includes an airfoil body extending between leading and trailing edges in a chordwise direction, extending between pressure and suction sides separated in a thickness direction, and extending from the root section in a spanwise direction to a tip portion. A recessed region extends inwardly from at least one of the pressure and suction sides. The airfoil body includes at least one rib bounding a respective pocket within a perimeter of the recessed region. A cover skin is welded to the airfoil body along the at least one rib to enclose the recessed region. A method of forming a gas turbine engine component is also disclosed.

Abstract: A coaxial laser metal deposition head includes a wire guide and a plurality of laser optical units. The wire guide defines a wire guide axis. The laser optical units are distributed around the wire guide axis. Each of the laser optical units is connected to a separate laser and each defines a beam axis. The optical units are fixed relative to the wire guide and in a first condition are positioned to allow each of the beam axes to intersect the wire guide axis at a common point.

Abstract: A connection and fastening unit for components of a lightning protection system, the connection and fastening unit being realized for the purpose of being integrated in a wind turbine rotor blade and for being connected to the components of the lightning protection system, wherein the connection and fastening unit includes a cavity which can be closed in an airtight manner and in which a connector for connection to at least one of the components of the lightning protection system is arranged.

Abstract: A compressor airfoil of a turbine engine that has a geared architecture includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a trailing edge angle and span position that defines a curve with a non-negative slope from 0% span to 20% span corresponding to a non-decreasing trailing edge angle.

Abstract: The present disclosure is directed to systems and methods for manufacturing a wind turbine rotor blade that can be easily lifted and lowered to and from a rotor installed atop a tower. The method includes providing a plurality of root inserts for a blade root of the blade and securing at least one cylindrical member to one of the root inserts such that the cylindrical member is substantially perpendicular with the root insert. The method also includes arranging the root inserts in a blade mold of the blade and forming a blade shell with the plurality of root inserts laminated therein. The method may further include securing at least one attachment component within each of the cylindrical members so as to provide an attachment location for a pulley cable used to lift and lower the rotor blade to and from the rotor installed atop the tower.

Abstract: A method of forming a gas turbine engine component according to an example of the present disclosure includes, among other things, attaching a cover skin to an airfoil body, the airfoil body and the cover skin cooperating to define pressure and suction sides of an airfoil, and moving the airfoil in a forming line including a plurality of stations. The plurality of stations include a set of heating stations, a deforming station and a set of cool down stations. The moving step includes positioning the airfoil in the set of heating stations to progressively increase a temperature of the airfoil, then positioning the airfoil in the deforming station including causing the airfoil to deform between first and second dies, and then positioning the airfoil in the set of cool down stations to progressively decrease the temperature of the airfoil.

Abstract: A rotor assembly for a gas turbine engine includes a rotor defining an outer periphery; and a plurality of blades attached to the outer periphery. The plurality of blades includes a material property different than the other of the plurality of blades to provide mistuning of the rotor.

Abstract: A steam turbine includes a platform (100) including a front part on an upstream side of the platform, a rear part opposite the front part, and a side part extending between the front part and the rear part; a vane (200) provided on an upper surface of the platform, the vane including a leading edge facing the front part and a trailing edge extending from the front part via the side part to the rear part; and a dovetail (300) formed integrally with the platform. The dovetail slant angle (DSA) is created when the horizon is drawn at an angle formed by a dovetail center axis (DCA) of the dovetail and a rotation axis (RA), and the stagger angle (SA) corresponds to an angle formed by the leading edge and the trailing edge of the vane. The dovetail slant angle is less than the stagger angle.

Abstract: Locking device for locking a movement side of a wind turbine blade mould to a floor at a desired level, the locking device having a first locking component for mounting to a floor surface and a second locking component adapted to be fitted to a movement side of a wind turbine blade mould to be locked by the locking device, wherein one of the first and second locking components includes a clamp engaging member, and the other of the first and second locking components includes an actuator and a clamp member coupled to the actuator, the clamp member being movable by operation of the actuator between a retracted position and an extended position, the clamp member including a clamp surface which in one of the retracted and extended positions is arranged to apply a clamping force on the clamp engaging member.

Abstract: The invention is directed to a method for making an equipotential bonding connection between two components of a lightning protection arrangement of a wind turbine rotor blade. The method includes providing a wind turbine rotor blade having two rotor blade half shells having respective connection and fastening units connected to corresponding ones of the two components of the lightning protection arrangement. A space is present in the interior of the rotor blade between the two connection and fastening units. A connection conductor is introduced from outside of the rotor blade through a through opening in one of the two connection and fastening units into the interior space of the wind turbine rotor blade. The two ends of the connection conductor are fastened to corresponding ones of the connection and fastening units such that the connection conductor bridges the interior space along an essentially linear imaginary line.

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 0.75-0.85 inch (19.1-21.6 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 0.56-0.66 inch (14.2-16.8 mm). The airfoil element includes at least two of a first mode with a frequency of 2740±10% Hz, a second mode with a frequency of 5956±10% Hz, a third mode with a frequency of 6554±10% Hz and a fourth mode with a frequency of 31959±10% Hz.