Abstract: A system and method for repairing a hollow fan blade. In one aspect the blade includes a hollow portion having a plug disposed therein, wherein the plug is smaller than the opening. During processing the blade is located under a vacuum box and the gap is sealed between the plug and the opening using a fiber laser.

Abstract: Gas turbine blades which simplify the formation of cooling channels provided inside the turbine blades while simultaneously avoiding loss of turbine blade strength and rigidity due to forming of the cooling channels. Cooling channels provided in the interior of a gas turbine blade include a plurality of straight channel-like base-side elongated holes extending in a longitudinal direction at a base side of the turbine blade, a plurality of straight channel-like tip-side elongated holes extending in a longitudinal direction at a tip side of the turbine blade, and a plurality of communicating hollow portions interposed at connection portions between the two types of elongated holes to allow the two types of elongated holes to communicate with each other, and have larger cross-sectional areas than the channel cross-sectional areas of both elongated holes. The communicating hollow portions are formed to match the position of a platform portion of the turbine blade.

Abstract: A blade for a wind turbine comprising a blade root portion for attachment to a mounting flange of the wind turbine, the blade root comprising a plurality of first holes provided with an internal bushing wherein the bushings comprise a first end at or near a mounting surface of the blade root and an opposite second end embedded in their corresponding first holes, and wherein one or more internal bushing being guiding bushings, the guiding bushings comprising a first end that is adapted to guide the blade root with respect to a mounting flange.

Abstract: A method of balancing a gas turbine engine rotor comprises the step of obtaining a rotor disc with a circumferential array of balance tabs projecting from a peripheral rim of the disc. Stress shielding scallops are defined in the rotor disc between the tabs. The balancing is achieved by removing material from at least one of the tabs.

Abstract: A blade for a wind turbine comprising a blade root portion, the blade root portion defining an annular mounting surface for coupling to a hub or extender of the wind turbine and comprising a plurality of first holes provided with an internal bushing, wherein at least one first internal bushing comprises at least one first securing member, and at least one second internal bushing comprises at least one second securing member, the first and second bushings being located in or near substantially opposite positions of the annular mounting surface, and wherein said first and second securing members are adapted to receive connecting means for connecting the first securing member with the second securing member.

Abstract: A process for manufacturing a single-piece blisk, including: using an abrasive water jet to cut a block of material, so as to create blade preforms extending radially outwards from a disk, while keeping material to form a connecting mechanism between directly consecutive blade preforms, the cutting being done such that the connecting mechanism approximately forms a ring at a radial spacing from the disk, connecting the blade preforms together at a radially inwards distance from their tips, and then removing the connecting mechanism.

Abstract: A turbine blade growth pocket provides a feature to measure blade growth due to engine operation while maintaining dynamic characteristics of the turbine blade within acceptable limits by providing a variable radius fillet between the pocket and a side rail of the pocket.

Abstract: A turbine component for a turbine of an engine is provided. The turbine component includes a blade portion of a first material; and an attachment portion coupled to the blade portion, the attachment portion being a second material.

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

Abstract: A method of manufacturing an aerofoil structure capable of being diffusion bonded and superplastically formed to create a substantially hollow cavity within the aerofoil structure, the method comprising: providing a metallic plate for forming the aerofoil structure; joining mounting elements to opposing end surfaces of said metallic plate; dividing said plate along a plane extending substantially in a span-wise direction so as to produce two metallic panels each with one of said mounting elements joined thereto; assembling the two metallic panels so that the surfaces of the panels opposite to the surfaces which have been divided are facing each other; and joining the two metallic panels to one another to form the aerofoil structure; wherein the mounting elements are joined to one another to form the root of the aerofoil.

Abstract: The present invention relates to a blade rim segment for a turbomachine with at least one shroud band which extends along a segment of a circle and is connected in single-piece fashion with at least three blades, which extend radially from the shroud band and are configured to be hollow with at least one channel, wherein the blade rim segment is manufactured in a single piece by casting and directional solidification, and wherein at the outlet openings of the channels of the blades, the shroud band exhibits first reinforcement ribs that surround the opening and run axially, as well as at least one second reinforcement rib between at least the first reinforcement ribs, as well as a corresponding method for manufacturing a blade rim segment.

Abstract: The invention relates to a method for manufacturing a wind turbine blade, comprising the steps of pre-manufacturing a first blade member, positioning said pre-manufactured first blade member in a joining mold and bonding said first blade member with a second blade member using a vacuum assisted infusion process so as to form an integrated blade part.

Abstract: A method of fabricating a composite joint from a first cured composite component (13) and a second cured composite component (14), the first and second cured composite components (13, 14) comprising fibre elements embedded in a thermoset resin matrix; the method comprising the steps of providing an adhesive (15) on at least one of the first and/or second composite components (13, 14); forming a joint region between the first and second composite component by bringing the first and second composite component into contact with each other with the adhesive (15) therebetween; applying a force to the joint region (16, 17); and heating the first composite component in the joint region to a temperature above the glass transition temperature of the thermoset resin matrix of the first composite component.

Abstract: A method of manufacturing a metal component from metal powder comprises preparing (12) a metal powder, providing (14) gallium on at least part of the surface of at least some of the metal powder particles, encapsulating (16) the metal powder in a container, evacuating (18) the container to remove air and/or gas from the container, sealing (20) the container, hot isostatically pressing (22) the container to consolidate the metal powder particles to produce the metal component and removing (24) the container from the metal component. The process is used to produce gas turbine engine metal components, for example turbine discs with improved fatigue properties.

Abstract: A wind turbine blade includes a blade body whose chord length increases from a blade tip toward a blade root. The blade body includes a blade tip region located near the blade tip and whose chord length increases gradually toward the blade root, the blade tip region having a substantially constant first design lift coefficient, a maximum-chord-length position located near the blade root and having a maximum chord length, the maximum-chord-length position having a second design lift coefficient higher than the first design lift coefficient, and a transition region located between the blade tip region and the maximum-chord-length position. The transition region has a design lift coefficient increasing gradually from the first design lift coefficient to the second design lift coefficient in a direction from the blade tip toward the blade root.

Abstract: A stator subassembly includes an array of circumferentially arranged stator vanes. A damper spring is provided between the array and an outer case, which supports the array. The damper spring is configured to bias the array radially inwardly from the outer case.

Abstract: An equipment for coating an airfoil of a turbine blade of a turbine engine in a coating block, including a base on which a molding block is positioned for flow of the coating metal, the molding block including a cavity defining a reference plane on the block for positioning the block in space, wherein the base also includes a cradle supporting the blade via six bearing points defining an orientation plane representative of an angular position of the airfoil relative to a root of the blade. The cradle is rotatably movable relative to the base about an axis oriented so as to be substantially parallel to a direction of a leading edge of the blade, to enable a modification in an angle formed between the reference and orientation planes.

Abstract: A method for adjusting a predetermined contour of a turbine blade root including a main salient edge defined by a determined interior angle. The method includes: chamfering the main edge of the contour to obtain two auxiliary salient edges, associated interior angles of which are respectively greater than the interior angle of the main edge; and blunting the auxiliary edges obtained to fine-tune the contour of the blade root.

Abstract: A method for repairing turbine blades by replacing at least a part of the blade profile, the method having: a) manufacture of a replacement blade part; b) separation of the damaged area with a standardized cutting plane, leaving behind a remaining blade; c) matching of the replacement blade part to the actual geometry of the remaining blade; d) connecting or joining of the replacement blade part to the remaining blade by soldering of at least one web and welding of an outer contour.

Abstract: An airfoil and method of fabricating an airfoil including a first and a second side coupled together at a leading and a trailing edge and extending there between. The airfoil includes a plurality of first chord sections having a first chord length and extending outward from one of the first side or second side of the airfoil at the leading edge and a plurality of second chord sections having a second chord length and extending outward from the one of the first side or the second side of the airfoil at the leading edge. The leading edge including spaced-apart wave-shaped projections defining a waveform. The configuration defining a three-dimensional crenulated airfoil configured to facilitate desensitization of an airfoil unsteady pressure response to at least one impinging upstream generated wake or vortex by decorrelating spatially and temporally and reducing in amplitude an unsteady pressure caused by interaction of the airfoil with the upstream generated wake or vortex.

Abstract: A bulkhead (22) of a wind turbine (10) to be arranged on a rotor blade connection of a rotor blade (14), especially on a rotor hub (9). The bulkhead (22) has a core body (30). A layer (31, 32) of fiberglass-reinforced plastic (31, 32) is arranged on the core body (30) on both sides respectively and a metal layer body (33) is arranged on one side of the layer of fiberglass-reinforced plastic (31). A method for producing a bulkhead (22) of a wind turbine (9), which is arranged on a rotor blade connection of a rotor blade (14) and a use of a bulkhead (22) of a wind turbine (10).

Abstract: A blade with an aerodynamic blade body having a leading edge and a trailing edge is provided. The blade includes at least one flexible adaptor component having a first side coupled to the trailing edge. Further, the blade includes at least one rigid acoustic segment attached to an opposing second side of the at least one flexible adapter component for mitigating noise during fluid flow over the blade.

Abstract: An airfoil, a fan assembly and an unducted contra-rotating fan engine include fabricating at least one airfoil including a suction and a pressure side coupled together at a leading and a trailing edge and extending therebetween. The airfoil includes a plurality of chord sections having a chord length. The airfoil including a tip profile defining a reducing slope extending from the leading edge at the tip portion along at least a portion of the chord length. The tip profile is configured to reduce the high unsteady pressure near the tip portion of the airfoil.

Abstract: A process for manufacturing a single-piece bladed disk, including: using an abrasive water jet to cut a block of material, so as to create blade preforms extending radially outwards from a disk, while keeping material forming a connecting mechanism between at least two directly consecutive blade preforms, the connecting mechanism being at a radial spacing from the disk; then removing the connecting mechanism; then milling the blade preforms.

Abstract: A turbine engine component has an airfoil portion with a tip portion and the tip portion has at least one chamfered edge on one side. If desired, the tip portion may have a first chamfered edge on a first side and a second chamfered edge on a second side opposed to the first side. A flattened tip portion may extend between the first and second chamfered edges. A tip treatment may be applied to the flattened tip portion.

Abstract: Composite aerofoils for gas turbine engines are commonly provided with a metal protection strip along the leading edge, to prevent erosion of the leading edge in use and to protect against impacts from foreign bodies. A problem with such strips is that they can cause serious damage to other parts of the engine if they become detached from the aerofoil. The invention provides an aerofoil having such a protection strip, characterized in that the protection strip includes one or more weakening features to reduce the ability of the protection member to withstand a compressive force applied along its length. The weakening features encourage the protection member to break up under impact, or if it becomes detached from the aerofoil, so that damage to other parts of the engine is minimized.

Abstract: An airfoil for a gas turbine engine includes an aft trailing edge support between a pressure side and a suction side.

Abstract: A blading for a turbomachine, particularly for a gas turbine, wherein thickened areas and depressions formed and disposed on a lateral wall having a plurality of blades such that at least one depression is disposed on a blade pressure side and at least one thickened area is disposed on a blade suction side for each blade of the plurality of blades.

Abstract: A blading for a turbomachine, particularly for a gas turbine, wherein thickened areas and depressions are formed and disposed on a lateral wall having a plurality of blades such that at least one depression or thickened area is disposed at a blade pressure side and at least one thickened area or depression is disposed at a blade suction side for each blade of the plurality of blades.

Abstract: A turbine is described for deriving energy from a fluid flow. The turbine has a plurality of generally arcuate blades that are rotatable about a rotational axis transverse to the direction of fluid flow. Each blade comprises a plurality of separately formed straight sections that are straight when unstressed, and that are joined to form a blade in which at least some adjacent sections are inclined at an angle to one another.

Abstract: Aerogenerator blade and method of manufacturing thereof, the aerogenerator blade comprising an intrados shell, an extrados shell and a structural beam, the structural beam comprising a root spar, a transitional spar and a box spar, wherein the root spar has a substantially circular cross section configured to support the connection of the blade to the aerogenerator hub; the transitional spar tapers from the root spar towards the box spar; and the box spar tapers towards the blade tip; and wherein the aerogenerator blade is characterized by comprising: a first section of the structural beam including at least a root spar portion, a transitional spar portion and a box spar portion, the portions forming a first integral structural beam section; a second section including at least the counterparts of the root spar portion, the transitional spar portion and the box spar portion, said counterpart portions forming a second integral structural beam section; and wherein the first section of the structural beam is join

Abstract: A method of manufacturing a root section of a rotor blade of a wind turbine is disclosed. The method includes assembling a plurality of supporting rods with an interface section to a hub interface of the wind turbine in an essentially circular shape such that there are gaps between the supporting rods; arranging first fibres in the gaps which first fibres are physically and/or chemically compatible with an injection material; placing a first molding tool along an outer surface of the circular shape and a second molding tool along an inner surface of the circular shape, treating the injection material so that it bonds with the first fibres. The invention also concerns a supporting rod holding arrangement for such purpose and a root section of a rotor blade manufactured by such method.

Abstract: An article is disclosed that comprises a thermal material having a first surface and a second surface. The thermal material defines a film hole between the first surface and the second surface, and the film hole includes a metering portion adjacent the first surface and a diffuser portion adjacent the second surface. The metering portion defines a metering hole axis, and the diffuser portion defines a trench. The trench extends substantially parallel to a metering hole axis.

Abstract: A process for forming a turbine blade comprises the step of forming an as-cast turbine blade having an airfoil portion and a tip shroud, wherein the forming step comprises forming at least one as-cast cooling circuit within the tip shroud.

Abstract: A method to manufacture an integrally bladed rotor, including: cutting a block of material by an abrasive waterjet, undertaken so as to reveal blade preforms extending radially from a disk, while retaining the material forming a linking mechanism between at least two preforms of directly consecutive blades, wherein the linking mechanism is spaced radially from the disk; followed by removal of the linking mechanism.

Abstract: A process for heat treating selected portions of an integrally bladed rotor (IBR) having a plurality of blades, the process using an IBR on a fixture having a rotor engaging portion that moves the IBR into an environmental chamber. An IR heater is placed on one of the IBR blades and heat treated after air has been removed from the chamber and an inert gas is added. The IR heater is lifted from the blade and indexed to position another blade on the IBR. The process is repeated until all the IBR blades are heat treated.

Abstract: A turbine bucket includes a radially inner mounting portion; a shank radially outward of the mounting portion; at least one radially outer airfoil having a leading edge and a trailing edge; a substantially planar platform radially between the shank and the at least one radially outer airfoil; at least one axially-extending angel wing seal flange on a leading end of the shank thus forming a circumferentially extending trench cavity along the leading end of the shank, radially between an underside of the platform leading edge and a radially outer side of the angel wing seal flange; and slash faces along opposite, circumferentially-spaced side edges of the platform. At least one of the slash faces is formed with a dog-leg shape, a leading end of the at least one of slash face terminating at a location circumferentially offset from the leading edge of the at least one radially outer airfoil.

Abstract: A turbine rotor disk includes a row of buckets secured about a radially outer periphery of the rotor disk, each bucket having an airfoil, a platform, a shank and a mounting portion, the mounting portion received in a radial slot formed in the rotor disk such that adjacent buckets in adjacent radial slots are separated by a rotor disk post located between adjacent mounting portions and a shank cavity between adjacent shanks, radially outward of the rotor disk post and radially inward of adjacent platforms. The shank cavity is substantially filled with at least one discrete thermal plug.

Abstract: A process for manufacturing a single-piece blisk, including: using an abrasive water jet to cut a block of material, so as to create blade preforms extending radially outwards from a disk, while keeping material forming a connecting mechanism between at least two directly consecutive blade preforms; then milling on the blade preforms so as to obtain profiled blade blanks; then a finishing by milling of the blade blanks, so as to obtain blades with a final profile; then removing the connecting mechanism.

Abstract: There is disclosed a method of manufacturing a rotor for a dynamoelectric machine. The rotor includes a rotating shaft, a rotor core fixed on the rotating shaft, and a cooling fan fixed to an axial end face of the rotor core. The method includes the step of fixing the cooling fan to the axial end face of the rotor core by resistance welding. The method is characterized in that in the resistance welding, both a positive electrode and a negative electrode are first brought into contact with the cooling fan to have the cooling fan held between the axial end face of the rotor core and both the positive and negative electrodes, and then weld current is supplied to flow from the positive electrode to the negative electrode.

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: It is intended to provide a wind turbine blade with superior aerodynamic characteristics and rigidity, a wind turbine generator equipped with the wind turbine blade, and a method of designing the wind turbine blade. The wind turbine blade 1 is provided with a blade tip part 2, a blade root part 4 connected to a hub 112, and an airfoil part 6 disposed between the blade tip part 2 and the blade root part 4. The airfoil part 6 includes a flatback airfoil 10 with a blunt trailing edge 8 at least in an area in a longitudinal direction of the wind turbine blade 1 where a blade thickness ratio X is 40% to 50%. X indicates a ratio of a maximum thickness tMAX to a chord length LC. In the area where the blade thickness ratio X is 40% to 50%, the flatback airfoil has a trailing edge thickness ratio Y which is 5% to YH%, Y indicating a ratio of a trailing edge thickness tTE to the maximum thickness tMAX and YH has a relationship of YH=1.5X?30 with the blade thickness ratio X.

Abstract: A method for producing a solid component which in succession includes deforming a metal bar by forging using two dies in order to obtain an intermediate component including two fins one on each side of a solid part capable of forming the base of the metal reinforcement, the two fins being at a divergent angle ?; deforming the two fins of the intermediate component, altering the divergent angle ?, so as to obtain the final shape of the turbomachine blade leading edge or trailing edge metal reinforcement.

Abstract: Blades are connected to the surface of a disk and slots are formed in the surface of a shroud, which is opposite from the other surface of the shroud where the blades are to be welded. The blades are arranged on the opposite surface from the slots and a laser beam is applied from the surface in which the slots are formed, to weld the shroud and the blades. Components are installed on the surfaces of the slots on the opposite side from the blades after the blades and the shroud in which the slots are formed are welded. Alternatively, the slots are filled with a material different from that of the shroud, such as a resin. With this configuration, distortion caused by welding heat can be reduced without degrading the fluid performance.

Abstract: The invention relates to an electrical machine having a fan wheel which comprises an injection-moulded blade carrier ring with fan blades as well as an annular insertion part which is integrated into the blade carrier ring and which comprises passage openings via which the blade carrier ring is connected to the fan blades.

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

Abstract: A method is provided which manufactures a vane used for an oil-sealed rotary vacuum pump and having at least a part formed of a resin material, the method including: an oil impregnating process of immersing the vane into oil used for the oil-sealed rotary vacuum pump under a depressurized condition, the oil impregnating process being carried out before a finishing process of finishing the vane into a final shape.

Abstract: A plunge milling method includes: a) the area of material that is to be removed is enclosed by a plurality of milling paths, each milling path defining end positions of a milling head during the formation of plunge milling bores; b) to each milling path there is allocated a guide curve for the tool axis, each guide curve defining initial positions of the milling head during the formation of plunge milling bores; c) during the formation of plunge milling bores, the tool axis is oriented, as a function of a milling path and the respective guide curve, so that there is no danger of collision of the milling tool with a contour formed by plunge milling; d) for each milling path, bore axes for plunge milling bores are determined as a function of the respective guide curve, corresponding to a prespecified overlap of milling bores formed along the milling paths.

Abstract: Blade insert connected in the lamination of a blade determining a double shear joint between insert and lamination. The insert is made up of two defined parts, head (2), designed to screw the insert to another structure (2?), and the body (3) that determines a cylindrical or conical shape with an internal conical cavity. In an embodiment, the insert is designed to be joined to the lamination (1) of the blade with adhesive means (4). In another embodiment, the insert is embedded in the blade lamination with an inner part (5) stuck to the body (3) of the insert.

Abstract: The invention concerns a tool (1), a method and use of such a tool (1) for mounting stud bolts (12). The tool (1) is intended for use in connection with a drive, preferably a hand held drive, and is provided with a threaded part (4) that interacts with the threaded end (14) of the stud bolt during mounting of the stud bolt (12). The threaded part (4) is the part forming mechanical connection to a stud bolt (12) and which during mounting of the stud bolt (12) serves as operating measure. In a preferred variant of a tool (1) according to the invention, the threaded part (4) is made conical. By making a conical screw thread there is achieved the advantage that the engagement between stud bolt (12) and tool (1) is imparted low frictional resistance.