Abstract: A method of manufacturing a fan blade includes providing a metallic fan blade body, and applying at least a 200 volt potential to the fan blade body in a solution to produce a crystalline oxidation layer. A fan blade for a gas turbine engine includes a metallic fan blade body having a tip with a crystalline oxidation layer. A fan blade for a gas turbine engine includes a metallic fan blade body having a tip with a titanium dioxide layer.

Abstract: A method and manufacturing unit for producing a rotor blade (5) of a wind turbine (1) from at least a first rotor blade element (11, 11?, 12, 12?) and a second rotor blade element (11, 11?, 12, 12?). The first rotor blade element (11, 11?, 12, 12?) and the second rotor blade element (11, 11?, 12, 12?) are positioned in the desired relative arrangement with respect to each other such that a joint gap (13) remains between the first rotor blade element (11, 11?, 12, 12?) and the second rotor blade element (11, 11?, 12, 12?). Adhesive is introduced into the joint gap (13) for joining the first rotor blade element (11, 11?, 12, 12?) and the second rotor blade element (11, 11?, 12, 12?).

Abstract: A method of repairing a rotor blade, for example on an integrally bladed rotor, includes preparing a surface on a damaged area of the blade. The blade has first and second airfoil surfaces adjoining the prepared surface that are spaced apart a distance. An edge of a patch abuts the prepared surface to provide a weld interface defining a welding plane. First and second cover sheets respectively overlap the first and second airfoil surfaces. The first and second cover sheets adjoin the edge and the first and second airfoil surfaces. The blade, patch and first and second cover sheets are welded along the welding plane providing a welded joint at the weld interface. The first and second cover sheets are substantially unsecured to the first and second airfoil surfaces subsequent to the welding operation.

Abstract: A method of manufacturing a metal blading sector for low-pressure guide vanes of a turbomachine of which at least one blade includes an internal cavity configured to accept or communicate with a gas detection probe and at least one hole formed in the wall constituting a passage for gas from a low-pressure zone of the turbomachine toward the cavity and the probe through the fitting, into a casting mold, of a core corresponding to the cavity and the casting of a molten metal in the cavity of the casting mold. The core includes, for each hole for communication with the cavity, a protrusion penetrating the internal surface of the mold and constituting the only element holding the core in position in the casting mold.

Abstract: A sheet metal blank is formed into a helical turbine blade by stretching an outer portion of the blank by creating indents and detents thereon. Then the stretched side is flattened and the stretched structure is formed into a helical shape.

Abstract: A wind turbine blade (10) for a rotor of a wind turbine (2) having a substantially horizontal rotor shaft is disclosed. The rotor comprises a hub (8), from which the blade (10) extends substantially in a radial direction when mounted to the hub (8), the blade having a longitudinal direction (r) with a tip end (16) and a root end (14) and a transverse direction. The wind turbine blade comprises a blade shell defining a profiled contour of the blade and having an inner shell wall, wherein the blade is provided with a bulkhead mounted to the inner shell wall at the root end of the blade via an attachment part, the bulkhead comprising a first side and a second side. The attachment part is integrally formed with or connected to the bulkhead, and the attachment part comprises an elastomeric material.

Abstract: A method for producing, on the surface of a wall capable of being swept by a fluid, raised elements forming disruptions of the boundary layer is disclosed. The method includes applying laser shocks to the surface so as to create peaks on the edge of the impact zones such that the peaks form the disruptive raised elements.

Abstract: A rotor assembly includes a first rotor having first tabs and a second rotor that is arranged coaxial with the first rotor and that includes second tabs that are interlocked with the first tabs. A retainer locks the first tabs and the second tabs together.

Abstract: A method for producing a metal component such as a metal turbomachine blade reinforcement, includes positioning a plurality of metal staples in a forming tool having a die and a punch; and hot isostatic pressing the plurality of metal staples causing the agglomeration of the metal staples so as to obtain a solid component.

Abstract: A device and method for locally heat treating at least one airfoil in an integrally bladed rotor device. A pair of IR heat sources are positioned to direct IR heat rays in the direction where local heat treatment is required. A pair of parabolic mirrors are positioned to direct the IR heat rays on to the metal component. The heat treating is useful after welding the airfoil on to the rotor device.

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

Abstract: A method for producing, on the surface of a wall capable of being swept by a fluid, raised elements forming disruptions of the boundary layer is disclosed. The method includes applying laser shocks to the surface so as to create peaks on the edge of the impact zones such that the peaks form the disruptive raised elements.

Abstract: A blade for a wind turbine comprising a blade root portion is described. The blade root portion defines an mounting surface for coupling to a hub or extender of the wind turbine and comprises a plurality of first holes provided with an insert, the blade root portion further comprises a mounting flange arranged in the periphery of the mounting surface and provided with second holes, wherein the inserts comprise a first end embedded in the blade root portion and a second end opposite to said first end, the second end protruding beyond the mounting surface of the blade root portion, and wherein the second ends are fitted in the second holes of the mounting flange and the mounting flange is attached to the blade by means of the inserts. Furthermore, a wind turbine rotor comprising such a blade is described. Methods of manufacturing half a wind turbine blade and a whole wind turbine blade are also described.

Abstract: A method and system is provided for assembling or disassembling a blade of a wind turbine. The wind turbine includes a tower resting on a base, a rotor including at least one rotor blade having a blade connection flange and a nacelle mounted atop the tower, a hub rotatably connected to the nacelle and including a hub connection flange adapted to be detachably connected to a blade connection flange of a rotor blade. Thy wind turbine further includes a first positioning element adapted to be attached to the nacelle or to the tower in a top area and a second positioning element adapted to be joined to the blade in a root blade area, where the first and second positioning elements are configured to cooperate to provide an accurate position of the blade connection flange prior to connection to the hub connection flange.

Abstract: A method of manufacturing a family of airfoils includes providing a plurality of airfoil blanks of identical geometry, selecting a first airfoil geometry from a family of airfoil geometries, selecting a second, different airfoil geometry from the family of airfoil geometries, machining a first one of the plurality of airfoil blanks to the first airfoil geometry to produce a first airfoil of the family of airfoil geometries, and machining a second, different one of the plurality of airfoil blanks to the second airfoil geometry to produce a second, different airfoil of the family of airfoil geometries

Abstract: The invention provides a manufacturing method of a component of a split blade of a wind turbine (such as an inboard shell or an inboard spar) having joining elements with its complementary component (i.e. an outboard shell or an outboard spar). The method comprises the following steps: a) manufacturing a joint laminate of a composite material having embedded into it the joining elements, said joint laminate being configured for becoming a part of the component; b) manufacturing the component using as a preform said joint laminate. The invention also refers to a split blade comprising components manufactured by said manufacturing method.

Abstract: A wind turbine rotor blade for a wind turbine having a length extending from a first end, a leading edge and a trailing edge, where a pressure side and a suction side extend between the leading edge and the trailing edge and thus define an airfoil shaped cross section. At least along a part of the length of the wind turbine rotor blade, the trailing edge comprises a trailing edge part having a first and a second installation flange, each of which has a width. The installation flanges are arranged in connection with a trailing edge extender, the first and second installation flanges both having an inner surface for installation on the pressure side and the suction side of the wind turbine blade. Also, method for fitting a wind turbine rotor blade with a trailing edge part is provided.

Abstract: A method of making a platform of a blade includes the steps of creating two platform sections by solidifying a material with a fabric in a mold and positioning a band of fabric around the two platform sections to retain an airfoil and define a blade. The method further includes the step of bonding the two platform sections together by solidifying the material to define a platform of a solid material. The platform is not bonded to the airfoil.

Abstract: A method of producing a pre-bent wind blade, includes: obtaining a pre-bent curve of a straight wind blade; and producing a bent wind blade according to the pre-bent curve, in such a manner that under a rating wind speed, the wind blade extends to be straight, so as to increase energy yield annually.

Abstract: A film cooling hole for a turbine airfoil having a diffusion section with a convergent wall and two divergent side walls, and with a thin exit slot that opens onto the airfoil surface. The divergent side walls have an expansion of 15 to 25 degrees and the convergent wall converges up to 15 degrees. The film hole is formed by an electrode than is pushed into the metal surface to form the divergent side walls and then pivoted to form the convergent wall.

Abstract: The invention relates to a device for the production or repair of a blade for a gas turbine, said device comprising: a holding device for holding a blade or an aerofoil of a blade; a lowering mechanism for lowering the blade or the aerofoil; a container for receiving power and/or for receiving the blade or the aerofoil; a heating device; and a radiation source, wherein the heating device is formed as an induction coil.

Abstract: Provided are a manufacturing method for a blade material and a manufacturing device for a blade material, by which a long blade material can be manufactured without using a large-sized press forging machine. A manufacturing method for a blade material, in which hot forging is sequentially performed by molds from the root side to a blade (vane) tip, wherein when a root-side portion is grasped and a material to be forged is restrained by a mold, twisting is performed on a region between the grasped portion and the restrained portion. A manufacturing method for a blade material, in which hot forging and twisting are repeated, is preferable, and a manufacturing method for a blade material, in which hot forging is performed while molds are sequentially changed, is more preferable.

Abstract: A method of forming an internal structure in a hollow component that includes the steps of forming an assembly having first, second, and third plates the first and second plates each with a substantially planar surface and a surface that includes at least one protrusion and is on the exterior facing surfaces of the assembly. The third plate is sandwiched between the first and second plates. The method also includes the steps of selectively bonding portions of the third plate to sections of the first and second plates substantially opposite the at least one protrusions of the first and second plates; and forming the assembly against a die such that the at least one protrusions of the first and second plates are transferred from the exterior facing surfaces to the interior facing surfaces of the first and second plates.

Abstract: The invention provides a method for the generative manufacture of a component (1) with integrated damping for a turbomachine, in particular a gas turbine, having the following method steps: building up the component (1) in a generative manner, and introducing a damping material (2) into the component (1) during the method step of the generative building up of the component (1). The invention further provides a component (1) with integrated damping for a turbomachine, in particular a gas turbine, wherein the component (1) is built up in a generative manner, and the component (1) has a damping material (2) which is introduced into the component (1) during the generative building up of the component (1). The invention further provides a turbomachine, in particular a gas turbine, comprising such a component (1).

Abstract: A turbine engine airfoil includes an airfoil structure having an exterior surface that provides a leading edge. A first cooling passage includes radially spaced legs extending laterally from one side of the leading edge toward another side of the leading edge and interconnecting to form a loop with one another. A trench extends radially in the exterior surface along the leading edge. The trench intersects one of the first and second legs to provide at least one first cooling hole in the trench.

Abstract: A mold system for manufacturing wind turbine blades includes two mold halves shaped for molding respective mold halves. A first mold is supported by a hinge system which is capable of moving the mold from a first position wherein the mold faces upwards to a position wherein the first mold faces the second mold. A final linear displacement of the first mold is carried out by actuators which may be integrated with the first or the second mold. The actuators are engaged with the hinge system so that the first mold is displaceable or the hinge system holding the first mold is displaceable. In both alternatives the actuators merely transfer the load of the first mold to a support via the hinge system.

Abstract: An airfoil includes a body that includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface. A cooling passage is arranged interiorly of the exterior airfoil surface and provides an interior surface. The interior cooling surface includes micro-bumps that protrude from the interior cooling surface into the cooling passage. The micro-bumps are discrete from and noncontiguous relative to one another in multiple directions along the interior cooling surface. The micro-bumps may be provided while forming the airfoil or using correspondingly shaped micro-depressions on an airfoil core.

Abstract: A fan impeller structure and a manufacturing method thereof. The fan impeller structure includes a base seat, multiple blades and a ring member. Each blade has a main body made of plastic material and at least one fixing member made of metal material. The base seat and the ring member are made of metal material. The base seat and the ring member are respectively disposed on two sides of the blades. By means of the manufacturing method, the blades can be diversified and the universality of the blades is greatly increased to lower the manufacturing cost.

Abstract: A method of making a wind turbine component of composite construction with enhanced radar absorbing properties is described. The method comprises making the component and then modifying the component by applying circuit analogue elements to a surface of the component.

Abstract: An airfoil includes an airfoil body that defines a longitudinal axis. The airfoil body includes a leading edge and a trailing edge and a first side wall and a second side wall that is spaced apart from the first side wall to define a camber line there between. The first side wall and the second side wall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. Multiple ribs extend longitudinally in the cavity and are laterally spaced apart from each other relative to the longitudinal axis. In at least one plane that is perpendicular to the longitudinal axis, each of the ribs connects the first side wall and the second side wall along respective minimum distance directions that are perpendicular to the camber line. At least two of the respective minimum distance directions are non-parallel.

Abstract: A resinous blade-supporting rotator is prepared to rotate around a rotational axis. The blade-supporting rotator has rotator weld parts including rotator weld surfaces formed on one side surface in the axial direction. A plurality of resinous blades are disposed annularly around the axis. The plurality of resinous blades have hollow spaces formed in the blade interiors, and blade weld parts with blade weld surfaces. The blade weld surfaces and the rotator weld surfaces are inclined with respect to each other when facing each other in the axial direction. An axial pressure load is applied to opposite axial ends of the blade-supporting rotator so as to compress the blades in the axial direction such that the blade weld surfaces and the rotator weld surfaces are no longer inclined with respect to each other. The blade weld surfaces are fixed to the rotator weld surfaces by laser welding.

Abstract: In a moving blade system for a turbomachine, in particular a gas turbine, having at least one moving blade (1), the moving blade system having at least one cavity (3) in which at least one tuning mass (2) is movably situated, the tuning mass and/or the cavity is/are adapted in such a way that the tuning mass rests against an inner wall (3.1) of the cavity in a predefined first operating state of the turbomachine and at least temporarily moves away from the inner wall in a second predefined operating state of the turbomachine.

Abstract: A method for welding superalloy components at ambient temperature conditions while reducing the propensity of the superalloy material to crack as a result of the weld. A root pass region of the weld is formed using a filler material that exhibits ductility that is higher than that of the base superalloy material. The ductile material mitigates stress in the root region, thereby preventing the formation of cracks. A remaining portion of the weld is formed using a filler material that essentially matches the base superalloy material. The method may utilize a pre-weld heat treatment to grow a gamma prime precipitate phase in the superalloy material, a chill fixture to remove heat during welding, a relief cut to reduce stress in the root region, and a conventional post-weld heat treatment.

Abstract: A turbine rotor blade formed from three pieces with a pressure wall side piece and a suction wall side piece bonded to an intermediate piece so that a pressure side cooling circuit can be formed as a separate cooling circuit from a suction side cooling circuit. The intermediate piece has film cooling holes and blade tip cooling holes and trailing edge exit slots formed in it that are enclosed when the outer two pieces are boded to it.

Abstract: In a method and a device for machining an elongate workpiece that is not rotationally symmetrical in the form of turbine blades, the workpiece is supported by a steady rest that has clamping elements for clamping the workpiece on the cross-section thereof that is not rotationally symmetrical. After clamping the workpiece, the steady rest moves with its open clamping elements along the longitudinal axis of the workpiece into a supporting position. During movement of the steady rest into the supporting position and/or while the supporting position of the steady rest is being changed, a collision between the open clamping elements of the steady rest and the workpiece is prevented by a program-controlled rotation of a rotary part of the steady rest.

Abstract: When a distance from a front edge along a blade chord line is represented by X and a distance from the blade chord line to a blade back side is represented by Y, a blade back shape of a wind turbine blade includes a first region extending from the maximum blade thickness position toward the rear edge with dY/dX as a primary derivative amount of Y to X decreasing by a first amount of change, a second region on a side of the rear edge of the first region and extending toward the rear edge with dY/dX having a second amount of change smaller than the first amount of change, and a third region on the side of the rear edge of the second region and connected to the rear edge with dY/dX decreasing by a third amount of change larger than the second amount of change.

Abstract: A method of manufacturing a blade comprising: applying a stop-off material in a first predetermined pattern between a first layer and a membrane so as to prevent a diffusion bond from forming between the first layer and the membrane across said first predetermined pattern; and applying the stop-off material in a second predetermined pattern between a second layer and the membrane; wherein the first and second predetermined patterns are arranged to allow a diffusion bond to be formed along the blade tip edge, the diffusion bond along the blade tip edge extending across the blade in a chord-wise direction; applying the first and second predetermined patterns so that over at least a first portion of the blade chord at the blade tip, a greater portion of the first layer at the tip edge, extending in a span-wise direction, is diffusion bonded to the membrane than the opposing second layer.

Abstract: An enhanced performance rotorcraft rotor blade system and methods are presented. A rotor blade comprises an inboard blade portion, and at least one controllable surface coupled to the inboard blade portion. The at least one controllable surface is operable to improve a lift of the inboard blade portion by altering an angle of attack of the inboard blade portion independent of the rotor blade.

Abstract: An airfoil with a tip cover surface treatment for reducing leakage flows, minimizing tip vortex size and penetration into main flow that will improve turbine efficiency. The surface treatment for the airfoil tip covers includes a series of concave shapes, such as grooves or holes. These grooves and holes will cause the leakage flow into separate flow paths within the cavities and generate more resistance to leakage flows through the airfoil tip clearance, thereby reducing the leakage mass flow and weakening tip vortex and its interaction with turbine main flows. The material removed from the tip cover provides the additional benefit of reducing the weight of the tip cover, thereby enhancing blade reliability.

Abstract: A method for manufacturing a stator for a progressive cavity motor or pump comprises (a) forming an elastomeric stator insert. In addition, the method comprises (b) exposing the elastomeric stator insert to ionizing radiation. Further, the method comprises (c) positioning the elastomeric stator insert in a stator housing to form a stator.

Abstract: An apparatus (60) is provided for forming a trailing edge (52) of a wind turbine blade having first and second shells (40, 42). The first and second shells define a gap therebetween, and the apparatus has a first mold component (62) that is adapted to form the first or second shell, and an engaging element (77). The engaging element is configured to securely support a trailing edge component to be coupled to the first and second shells. The engaging element is coupled to the first mold component. The apparatus may additionally include a second mold component (64) that is adapted to form the other of the first or second shells and which is coupled to the first mold component. In this embodiment, the first and second mold components have a closed position in which the first and second shells are closed over one another so as to define a generally closed profile of the wind turbine blade.

Abstract: A method of manufacturing a component is provided. The method includes forming one or more grooves in an outer surface of a substrate. Each groove extends at least partially along the surface of the substrate and has a base, a top and at least one discharge point. The method further includes forming a run-out region adjacent to the discharge point for each groove and disposing a coating over at least a portion of the surface of the substrate. The groove(s) and the coating define one or more channels for cooling the component. Components with cooling channels are also provided.

Abstract: An airfoil includes a blade having a pocket recess therein and one or more features disposed within the pocket recess. The one or more features are configured to disrupt pressure oscillations within the pocket recess. In another embodiment, a blade is disclosed having a first wall and a second wall. The first wall is disposed on a suction side of the blade and the second wall is disposed on a pressure side of the blade. The second wall is connected to the first wall at a leading edge of the blade. Together the first wall and the second wall form a portion of a pocket recess and the pocket recess is disposed asymmetrically with respect to a camber line of the blade.

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

Abstract: A vertical axis turbine and method of making same is disclosed. The device and method comprise a plurality of blades rotatably disposed around an axis of rotation at a plurality of blade locations, each blade being twisted at a first angle about its longitudinal axis, each blade having its distal ends located a predetermined distance from the axis of rotation, each blade being bent at one or more central locations along the longitudinal axis so the one or more central locations are the same predetermined distance from the axis of rotation as the distal ends, each blade having a foil cross section perpendicular to the axis of rotation for maintaining unidirectional rotation of that blade about the axis of rotation in a fluid flow, and each blade having its longitudinal axis tilted at a second angle with respect to the axis of rotation.

Abstract: A method for producing a metal reinforcement for the leading edge or trailing edge of a turbomachine blade, the method including cutting a plurality of metal foils from a flexible metal sheet, corresponding substantially to the developed length of the leading or trailing edge metal reinforcement; producing a plurality of metal pockets, each pocket being produced from two of the metal foils obtained during the cutting; stacking the metal pockets one inside the other, such as to form a preform of the leading or trailing edge metal reinforcement; and hot isostatic pressing the preform, causing the metal pockets to bond to one another, so as to produce the leading or trailing edge metal reinforcement.

Abstract: A pump assembly 1, 33, 200 adapted for continuous flow pumping of blood. In a particular from the pump 1, 200 is a centrifugal pump wherein the impeller 100, 204 is entirely sealed within the pump housing 2, 201 and is exclusively hydrodynamically suspended therein as the impeller rotates within the fluid 105 urged by electromagnetic means external to the pump cavity 106, 203. Hydrodynamic suspension is assisted by the impeller 100, 204 having deformities therein such as blades 8 with surfaces tapered from the leading edges 102, 223 to the trailing edges 103, 224 of bottom and top edges 221, 222 thereof.

Abstract: A method for bonding airfoil sections includes aligning upper and stub airfoil sections having upper airfoil pressure and suction sides and stub airfoil pressure and suction sides respectively, pressing together upper and stub airfoil cross sections at upper and stub airfoil distal ends of the upper and stub airfoil sections respectively, and then resistance welding, preferably solid state resistance welding, the upper and stub airfoil sections together along the upper and stub airfoil cross sections by passing electrical current across the upper and stub airfoil cross sections. The upper and stub airfoil sections may be clamped between pressure and suction side upper airfoil electrodes and between the stub airfoil pressure and suction sides respectively. The method may be performed while the stub airfoil section is attached to an airfoil carrier such as a rotor disk rim, a gas turbine engine drum, or a gas turbine engine blade platform.

Abstract: A method of fixturing a plurality of dissimilar blade assemblies, wherein each assembly undergoes one or more manufacturing steps to bring it to a finished form, the method comprising the step of providing on each of the articles a datum feature, wherein each datum feature is of identical form and dimension, in turn a) locating the datum feature of a first one of the articles in a complimentary fixture to secure the dissimilar article, b) performing at least one manufacturing step on the secured dissimilar article, c) removing the dissimilar article from the fixture, d) locating the datum feature of another of the articles in the complimentary fixture to secure the dissimilar article, e) performing at least one manufacturing step on the secured dissimilar article, f) removing the dissimilar article from the fixture.

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