Abstract: A method for making a component according to one embodiment of this disclosure includes modeling a response of the component to operating conditions. The model is then mapped to materials that would influence the response of the component to the operating conditions. A component is then fabricated using the materials such that the component includes a graded composition.

Abstract: A method of repairing a damaged notch fillet radius of a turbine blade shroud includes a replacement notch fillet radius and a hardface nugget. The damaged notch fillet radius is blended out and a hardface structure positioned proximate the damaged notch fillet radius is removed. A replacement notch fillet radius is formed with weld filler and the hardface nugget is welded to at least a portion of the replacement notch fillet radius.

Abstract: A method provides for assembling a wind turbine blade from at least two blade segments, with each of the blade segments having a pressure side shell member, a suction side shell member, internal support structure, and ends with joint sections that are offset span-wise from the pressure side shell member to the suction side shell member. The blade segments are aligned in an end-to-end orientation and moved into a mating configuration with relative movement that includes overlapping the respective joint sections of adjacent blade segments. The overlapped joint sections are subsequently moved into engagement with each other and joined along respective joint profiles at a chord-wise joint.

Abstract: An automated technique for finishing gas turbine engine blades or vanes by generating a bespoke tooling path for each blade or vane. The bespoke tooling path is generated by scanning the aerofoil surface to generate a 3-D electronic representation of the surface. The 3-D electronic surface is then analysed to identify imperfections or defects, and then a machining path a generated through which the imperfections can be removed. The machining path is determined so as to smoothly blend the surface back to the underlying surface where the imperfections had been present. In this way, the resulting aerofoil, once machined, has optimized aerodynamic performance.

Abstract: An exemplary method for manufacturing a fan rotor includes the following steps. First, a discoid-shaped metal sheet is provided. Second, the metal sheet is stamped such that the stamped metal sheet includes a hub at a middle thereof, a blade-portion spaced from and surrounding the hub, and supporting bars interconnecting the hub and the blade-portion. The blade-portion includes outer peripheral blades adjacent to each other. Third, a free end of each blade is curled up by force applied along a direction substantially perpendicular to a plane of the blade-portion. Finally, each blade is bent downward about an axis coinciding with a portion of one side of the blade that connects with an inner periphery of the blade-portion.

Abstract: A method of machining a blade in a three-dimensional machining center, the blade including an airfoil, a platform including upstream and downstream supports formed respectively under the upstream and downstream portions thereof for supporting a sealing liner, a blade root, and a stilt interposed between the platform and the blade root, the method including the upstream and downstream supports constituting two bearing points for a six-point positioning system for positioning the blade in the three-dimensional machining center.

Abstract: A blade for a water current turbine rotor, which extends along a radial direction and comprises an outer surface, an inner surface, a leading edge, and a trailing edge. The leading edge is the edge of the blade that extends along the radial direction and is disposed upstream in the direction in which the water flows along the blade, while the trailing edge is the edge of the blade opposite the leading edge and is disposed downstream in the direction of flow. At least one portion of the blade has a profile comprising a thick portion and a thin portion, the cross section being perpendicular to the radial direction. The thick portion and the thin portion each have a maximum thickness along a direction perpendicular to the outer surface, the maximum thickness of the thick portion being at least four times greater than the maximum thickness of the thin portion.

Abstract: A hybrid turbine blade having a box beam assembly structure and method of designing such a hybrid turbine blade are disclosed. The box beam assembly provides the primary structure for supporting loads on the blade, and comprises oppositely positioned spar caps joined by oppositely positioned shear webs. For a portion of the blade, the box beam assembly further comprises a root buildup. In one embodiment, the shear webs comprise foam core sandwiched between two biaxial fiber-reinforced plastic laminates (FRP), the spar caps comprise uniaxial FRP laminates, and the root buildup comprises triaxial FRP laminates. The blades are designed using a novel inside-out method, wherein the box beam is first designed to support expected loads, and an aerodynamic surface is then designed to be supported by the box beam. The blade may be constructed in segments that are joined with connectors that engage the box beam structure.

Abstract: In one aspect, a flexible fan blade for use in a centrifugal fan impeller having at least one of a rear plate and a front plate with an air inlet is provided. The flexible fan blade comprises a fixed central portion fixedly coupled to at least one of the front plate and the rear plate of the centrifugal fan impeller. The flexible fan blade also includes a trailing edge extending from the fixed central portion and being moveable between a first position and a second position. The trailing edge is fabricated from a compliant material. Furthermore, the trailing edge is flexible in relation to the fixed central portion between a first position and a second position. The flexible fan blade also includes a leading edge extending from the fixed central portion in opposed relation to the trailing edge.

Abstract: A rotor blade assembly for a wind turbine having a rigid root insert is disclosed. The rotor blade assembly includes a blade root section having an end face with a substantially annular cross-section defined by an outer sidewall surface and an inner sidewall surface. The end face is configured to attach the rotor blade assembly to a hub. The rotor blade assembly includes a radial bore hole provided a predetermined span-wise distance from the end face and extending between the sidewall surfaces and a longitudinal bore hole provided between the sidewall surfaces and extending from the end face to the radial bore hole. The rigid root insert is disposed within the longitudinal bore hole and extends from the end face to the radial bore hole. As such, the rigid root insert is configured to increase the stiffness of the blade root section when the rotor blade assembly is attached to the hub with bolts that extend into and through the radial bore hole and the longitudinal bore hole.

Abstract: Provided is a radial vane with which manufacturing is possible with superior economy, without incurring a cut loss associated with vane separation in a weld part of a thread bundle With a longitudinal intermediate part of a contiguous bundle of threads being a fold-over part, both end parts of the fold-over part of the thread bundle are opened into radial shapes and superpositioned, leaving a space in the center part of the fold-over part, a ring-shaped fold-over part (12) is formed within the circumference of the space in the center part thereof. The outer part of the ring-shaped fold-over part (12) is welded in a ring shape, forming a ring-shaped core part (13). A through hole (11) is formed in the inner side of the fold-over part (12), and radial vane parts (14) are formed in which a plurality of thread materials (21) extend outward from the core part (13) toward the outer circumference side from all regions of the circumference direction.

Abstract: A method is provided of non-destructively inspecting titanium alloy articles in the as-cast condition using ultrasonic waves to detect internal flaws, comprising modification of grain structure in the as-solidified ingot structure by the addition of trace boron to various titanium alloys. The ability to ultrasonically inspect as-cast billets combined with improved hot workability provided by trace boron enhancement permits an economical method of manufacture of titanium alloy articles destined for high performance applications.

Abstract: A blade (1) for a turbomachine, including an impact chamber (2), a single impulse body (3) being situated in the impact chamber, a clearance (S1+S2) between the impulse body and the impact chamber being at least 10 ?m and/or at most 1.5 mm in at least one direction.

Abstract: A wind turbine blade comprising a lightning protection system is provided. The lightning protection system comprises a lightning conductor located along a longitudinal portion of the wind turbine blade and is coupled to an electrical ground. A lightning receptor module is arranged on an external surface of the wind turbine blade and electrically coupled to the lightning conductor. An elongate receptor band is installed on the external surface of the wind turbine blade, over the lightning receptor module, and the receptor band is arranged to receive a stroke of lightning and transfer electrical current from the lightning stroke to the lightning conductor through the lightning receptor module. Further, the elongate receptor band comprises a crease in a longitudinal cross-sectional profile of the elongate receptor band. A method of installing a lightning protection system on a wind turbine blade is further provided.

Abstract: Methods for modifying a turbine buckets include removing at least an original outer edge for an entire length of the slash face of the turbine bucket and adding a new material to the slash face to build a new outer edge, wherein the new outer edge extends the entire length of the slash face.

Abstract: A method of modifying an end wall contour is provided. The method includes creating a weld pool using a laser, adding a metal or a ceramic powder or a wire filler to the melt pool and modifying the part of the turbine in a manner that results in a change of about 0.005 to about 50 volume percent in the part of the turbine. The weld pool is created on a turbine component and contains molten metal or ceramic derived as a result of a heat interaction between the laser and the turbine component.

Abstract: A method for designing an air cooled turbine airfoil includes selecting a number of different internal cooling air circuits, forming a ceramic core for each of the different cooling air circuits, forming a metal airfoil over each of the ceramic cores, leaching away the ceramic cores, mounting the airfoils in a stage of a turbine, passing a hot gas stream through the turbine, passing cooling air through each of the airfoils, and measuring a pressure and temperature differential across each of the airfoils to determine which cooling air circuit has the best performance.

Abstract: A method of reshaping a turbine engine blade including at least one deformed zone, the method including peening the deformed zone to be able to restore a shape of the at least one deformed zone.

Abstract: A method for forming at least one cooling channel in a wall which is cooled by cool air flowing in the channel is provided. The channel includes a hole and a diffusion portion, the hole opening out at one end into the inside surface of the wall, and at its other end into the diffusion portion where it forms an orifice. The diffusion portion flares around the orifice and opens out into the outside surface of the wall. The diffusion portion has a bottom whose front end is substantially plane, sloping, and extending in front of the orifice, and also has a margin extending behind, round the sides, and in front of the orifice, the margin joining the sides of the front end.

Abstract: A method reinforcing an axisymmetric annular metal part by including a winding of composite material. A metal blank for the part is prepared, a cavity is formed therein that opens out into a coaxial inside face thereof, and that presents a right cross-section of axial extent that decreases from the inside towards the outside, a reinforcing yarn is wound in the cavity, the cavity is closed, the assembly is subjected to a hot isostatic compression process, and the blank is machined to obtain a final part.

Abstract: A manufacturing process of a monobloc vaned disc including a cutout by abrasive water jet, including: a continuous cutout, with an ejection head of a tool opposite a first face of the block, of a piece passing through the thickness of the block, the continuous cutout revealing a junction line between a second face of the block opposite the first, and the surface of the block cut out by the abrasive water jet; followed by at least one enhancement cutout, with the ejection head opposite the second face of the block, of a piece extending only over part of the thickness of the block, and integrating at least part of the junction line.

Abstract: A wind turbine blade holding arrangement is described comprising a root frame for securing to a root portion of a blade; an airfoil clamp for arranging about an airfoil portion of the blade; and an airfoil frame for supporting the airfoil clamp wherein the root frame and tip clamp are realized for use in a first blade orientation in a first storage and transport stage of the blade and also for use in a second blade orientation in a second storage and transport stage of the blade, wherein the first and second blade orientations are essentially at right angles to each other. A method of handling a number of wind turbine blades is also described.

Abstract: A wind turbine rotor blade and a wind turbine incorporating the rotor blade include a first and second composite skin. A first and a second spar pultrusion having a base and a plurality of integral ribs generally normal to base are attached to the inside surface of the first and second composite skins and extend the span of the rotor blade. At least one shear web connects a rib of the first spar pultrusion to a corresponding rib of the second spar pultrusion. The width of the spar pultrusions decreases in a step-wise fashion along the span of the rotor blade from the root to the tip. The leading or trailing edge of the rotor blade may be selectably opened for inspection and repair.

Abstract: Disclosed are a shroud impeller of a centrifugal compressor and a method of manufacturing the same where the shroud impeller includes a rotary hub connected to a driving shaft, a plurality of blades radially provided about a rotational axis of the rotary hub, and an integral shroud bonded onto top ends of the blades.

Abstract: A rotor blade for a rotary-wing aircraft includes a core member having a first end that extends to a second end, and a spar member positioned about the core member. The spar member includes a first end section that extends to a second end section. A tip core assembly is mounted at the second end section of the spar member. The tip core assembly is formed from a honeycombed material. The rotor blade also includes a rotor blade skin mounted about the spar member and the tip core assembly.

Abstract: A process is provided for forming shaped air holes, such as for use in turbine blades. Aspects of the disclosure relate to forming shaped portions of air holes using a short pulse laser, forming a metered hole corresponding to each shaped portion, and separately finishing the shaped portion using a short-pulse laser. In other embodiments, the order of these operations may be varied, such as to form the shaped portions and to finish the shaped portions using the short-pulse laser prior to forming the corresponding metered holes.

Abstract: A method of manufacturing an aerofoil for a gas turbine engine (10). The method comprises the steps of providing first and second panels (16, 18), providing a web (30) between the first and second panels, deforming the panels by applying internal pressure between the panels so as to form an internal cavity. The method further includes the step of providing a pattern of ribs (60) on the web so as to define a aerofoil having first and second panels with at least one rib (60) forming a protrusion extending from the first panel partially across the space between the first and second panels.

Abstract: According to the method, a turbine aerofoil is made starting from a reference aerofoil, locally reducing the metallic exit angle at the trailing edge in two areas which substantially correspond, in use, to the position of the peaks of the secondary flows in the boundary layer.

Abstract: With a method for finish-machining the blade tips of rotor wheels made in BLISK design, the rotor wheel or multi-stage compressor rotor (1), is machined—blade by blade and stage by stage—at the blade tips (2) by a conical cutter (5) whose cutting edge (6) is oriented tangentially to the outside surface of the rotor wheel/compressor rotor and routed on the blade tip essentially along the centerline thereof, with the cutting force being introduced perpendicular to the tool axis and in the stiffest direction of the blade (3), i.e. the centerline (11) of the blade cross-section and the perpendicular axis extending from the centerline. The cutting action and the force introduction of the conical cutter at the blade tip allow production of blade tips with a geometrically precisely defined edge without setting the respective blades into vibration.

Abstract: A guide vane for a turbomachine axially pivotably coupled to a radially outwardly disposed flow-limiting wall and to a radially inwardly disposed inner ring of the turbomachine; and a trailing edge gap being formed between an upper trailing edge of the guide vane and the flow-limiting wall and/or between a lower trailing edge of the guide vane and the inner ring; the upper trailing edge and/or the lower trailing edge of the guide vane having at least one air outlet opening for an air outflow for forming an air curtain for at least partially sealing the trailing edge gap in the area of the upper trailing edge and/or the lower trailing edge in the area of the lower trailing edge. Also, a guide vane cascade, as well as a method for manufacturing a guide vane or a guide vane cascade.

Abstract: A method of flank and/or point milling an integrally bladed rotor is conducted with an automatic tool path generator which generates a new created tool path including smooth transitions merging between an actual finished surface and a nominal surface of the integrally bladed rotor. The actual finished surface is presented in a mathematical transformation matrix which may be obtained in a 3-D scanning process.

Abstract: A method of producing an airfoil is provided. The method includes forming a steel airfoil preform with a pocket on at least one of the pressure and suction surfaces, forming a cover plate for the pocket and welding the cover plate over the pocket.

Abstract: A rotor blade assembly for a gas turbine engine includes two aerofoil members joined together at their roots by a blade assembly attachment web. The rotor blade assembly is made from a composite material, for example an organic fibre composite material. The blade assembly attachment web is used to attach a plurality of rotor blade assemblies to the rest of the gas turbine engine in order to form a rotor stage. The rotor stage may, for example, be the fan stage of a turbofan gas turbine engine.

Abstract: A rotor blade for use in a turbine of a turbine engine is described. The rotor blade may include an airfoil that extends from a connection with a root. The airfoil may include a pressure sidewall and a suction sidewall that define an outer periphery and an outboard tip. The rotor blade may further include a tip shroud assembly disposed at the outboard tip of the airfoil. The tip shroud assembly includes a non-integral tip shroud.

Abstract: An aerodynamic fan nosecone for a gas turbine engine is provided and includes a fan nosecone that may be made of composite material. To improve airflow transition to the blade members, aerodynamic fairings are provided and are secured to an exterior surface of the nosecone which enhances fuel economy. The fairings may be secured to the nosecone by various methods, including providing for the fairings to be changed out and replaced with other fairings on the same nosecone assembly.

Abstract: A method for making a rib for an aerofoil structure, the aerofoil structure including a skin component, the method including the steps of scanning the inner surface of the skin component to determine the surface profile thereof, providing a rib having a rib body and a rib foot protruding from the body, machining a foot surface profile into the rib foot, the foot surface profile being arranged to complement the skin inner surface profile where the rib foot is intended to abut the skin component.

Abstract: A blade or vane of different roughness and a process for producing such a blade or vane are presented. The performance of the blade or vane of a compressor or of a turbine can be improved because of the different configuration of the roughness of the surfaces on the suction side and the pressure side of the blade or vane.

Abstract: A system for attaching a rotating blade in a turbine includes a bush having an axial slot and a radial slot that intersects with the axial slot. A radial retention member fits within the radial slot, and an axial retention member fits within the axial slot and engages with the radial retention member. A method for attaching a rotating blade in a turbine includes inserting a bush into an axial passage in a rotor wheel and inserting a radial retention member into a radial passage in the rotor wheel and through at least a portion of the bush. The method further includes inserting the rotating blade in a slot in the rotor wheel, inserting the radial retention member into a retention slot in the rotating blade, and inserting an axial retention member into the bush.

Abstract: A blade assembly for a groove of a wheel of rotating machinery is described. The blade assembly includes, a blade root having two longitudinal sides, a base, and a roof, wherein the profile of the longitudinal sides includes a rounded surface, a blade connected to the roof of the blade root, and one or more keys juxtaposed along each longitudinal side of the blade root, each key having an inboard side and an outboard side, wherein the profile of the inboard side of each key is configured to mate with the profile of the blade root. The blade assembly allows replacement of a compressor blade without the need for unstacking the rotor to gain access to the damaged blade.

Abstract: In some examples, an apparatus may include a gas turbine engine component comprising a blade, a platform forming an airflow surface from which the blade extends on one side, and a motion weld receiving surface disposed on a non-airflow side of the platform, and a disk having a motion weld disk portion to receive the motion weld receiving surface of the gas turbine engine component and form a motion weld coupling when the disk and gas turbine engine component are coupled, wherein, prior to coupling, the gas turbine engine component further includes a blade stalk disposed on the non-airflow side of the platform and in which is formed the motion weld receiving surface.

Abstract: A fluid turbine blade and method of fabrication are provided. The fluid turbine blade includes a centrally disposed longitudinal spar having a substantially circumferential cross section. The fluid turbine blade also includes at least one chord stiffener coupled to the longitudinal spar. The fluid turbine blade further includes a torsionally compliant segmented skin coupled to the at least one chord stiffener. The centrally disposed longitudinal spar and the torsionally compliant segmented skin are functionally decoupled to relieve the torsionally compliant segmented skin of one or more of a flapwise load condition, an edgewise load condition and a torsional load condition.

Abstract: In a gas turbine blade where a part of the ?? phase precipitation strengthened type Ni-based alloy base material is composed of a weld metal, the weld metal is a Ni-based alloy containing Ta from 4.8 to 5.3 wt. %, Cr from 18 to 23 wt. %, Co from 12 to 17 wt. %, W from 14 to 18 wt. %, C from 0.03 to 0.1 wt. %, Mo from 1 to 2 wt. %, and Al of 1 wt. % or less, in which the oxygen content is 0 to 30 ppm, the Ti content from 0 to 0.1 wt. %, and the Re content from 0 to 0.5 wt. %. A blade base metal is manufactured by the step of stripping, the step of solution heat treatment where the ?? phase is dissolved again, the step of welding in an inert gas chamber by a TIG method using a welding wire where the weld metal can be obtained, the step of HIP treatment at 1100° C. to 1150° C., and the step of an aging treatment at 835° C. to 855° C.

Abstract: A production method enables use of ultrasonic forming but does not leave a bonding face in a final product. One cuts into a plate member having a first side face and a second side face from the first side face toward the second side face to form a slit that does not reach the second side face; seals lips of the slit to leave an opening; causes superplastic forming of the plate member by pressurizing the plate member in a mold with gas through the opening; and cuts out a portion including the sealed lips.

Abstract: In at least one implementation, a method of making a turbine blade may include providing a preform having a hollow cross-section, hydroforming the preform to form a turbine blade body comprising a shell that includes a continuous hollow portion along its interior, and providing a mounting portion attached to the body to mount the turbine blade to a hub. In one or more implementations of the method, the mounting portion may be provided during the step of hydroforming the preform and the mounting portion may be formed from the same preform as the turbine blade body.

Abstract: An apparatus to reduce wear and friction between CMC-to-metal attachment and interface, including a metal layer configured for insertion between a surface interface between a CMC component and a metal component. The surface interface of the metal layer is compliant relative to asperities of the surface interface of the CMC component. A coefficient of friction between the surface interface of the CMC component and the metal component is about 1.0 or less at an operating temperature between about 300° C. to about 325° C. and a limiting temperature of the metal component.

Abstract: A method of making a root end joint for a wind turbine. A plurality of root segments (10) are formed of a composite material. Each has an arcuate end face (11) which subtends an angle of 90° or less and has a plurality of connection holes (12). The segments are joined together side-by-side to build up the circular profile of the root end. The segments include a proportion of uni-axial to multiaxial fiber which decreases from the arcuate end face towards the opposite end.

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

Abstract: The present invention relates to a production facility (100, 200, 300, 400, 500) for forming elongated products, in particular wind turbine blades, wherein elongated mould assemblies (110a, 110b, 210a, 210b, 310a, 310b, 410a, 410b, 510a, 510b) may be accessed on the basis of an appropriate transport system (150, 250, 350, 450, 550) comprising at least one support member (251a-h, 151, 251, 351, 451, 551) laterally positioned between the elongated mould assemblies. The support member (251a-h, 151, 251, 351, 451, 551) is positioned so as to enable a rotational movement of an arm (121a, 121b, 221a) or is configured to change position or comprises a rotatable carrier element (259). For example, an elongated support member (151, 251, 351, 451, 551) may be positioned in a non-interference position, in which one or both mould assemblies can be moved into a position so as to form a composite mould assembly.

Abstract: A sheath for a fan airfoil having a leading edge and a trailing edge in a chordwise direction, a tip and a root in a spanwise direction, a suction side and a pressure side includes a solid portion to wrap around the airfoil leading edge; a first wing attached to the suction side of the airfoil; and a second wing attached to the pressure side of the airfoil. At least one of the first wing and the second wing extends at least about 35% of the chord of the airfoil.

Abstract: The present invention provides a method for manufacturing a closed impeller that has a simple configuration and enables fusion in a very accurate position. The method includes: forming a frustum-shaped front plate and a disk-shaped base plate formed therebelow, upper surfaces of a plurality of unit impeller blade plates made from a synthetic resin extending in radial directions which are formed as impeller blade tip surfaces, with sharp-pointed ridge-like protrusions having an acute upper end and a width less than a width of the impeller blade tip surface being integrally formed on the impeller blade tip surfaces. In the method, an inner surface of the front plate and the plurality of impeller blade tip surfaces are formed as parts of conical surfaces and formed so that the cone apex angles of the two conical surfaces are equal to each other.