Abstract: The invention relates to a fan rotor for a turbomachine, including a fan disk, fan blades with a leading edge and a trailing edge, platforms inserted between the blades and fixed to the periphery of the disk, each including an aerodynamic surface extending from the leading edges to the trailing edges of the blades. The aerodynamic surface includes an upstream longitudinal portion on the side of the leading edges and a downstream longitudinal portion on the side of the trailing edges, the upstream longitudinal portion being supported by a first member of the platform fixed to the disk in a pivotable manner, and the downstream longitudinal portion being independent of the upstream longitudinal portion and supported by a second member of the platform which is independent of the first member and fixed to the disk in a pivotable manner.

Abstract: A method of forming a composite component comprising a layer which consists at least partly of polyethylene, a layer which consists at least partly of a polyurethane and/or an elastomer, at least one layer which consists at least partly of a plastic reinforced by fibers, or which consists at least partly of an adhesive, wherein the layer is disposed directly between the layer and the layer, wherein the layers have been joined in a first operation to form a laminate composite and the layer have been joined in a second operation onto the laminate composite comprising the layers.

Abstract: A cooling device for a rotor assembly of a gas turbine engine includes an airflow nozzle configured to be installed at a cooling location of the rotor assembly. The airflow nozzle extends entirely around a circumference of the rotor assembly and includes a plurality of airflow inlets and a nozzle outlet to direct an airflow toward the cooling location. An airflow source is operably connected to the plurality of airflow inlets.

Abstract: The present invention relates to a method for installing an offshore wind turbine at a target location at sea with an installation vessel, the vessel comprising: —a nacelle support structure for temporarily supporting a nacelle comprising a hub having a plurality of root end connectors to which the root ends of the blades are to be connected, the nacelle support structure comprising: ?a support tower extending upwardly from a deck of the installation vessel, ?a support platform configured to temporarily support the nacelle, —one or more lifting devices configured for: ?lifting the nacelle onto the support platform, ?lifting a nacelle assembly including the blades onto a wind turbine mast located adjacent the vessel, wherein the method comprises: a) lifting the nacelle onto the support platform, and securing the nacelle to the support platform, b) orienting a root end connector of the hub of the nacelle in a direction facing a guide path of the blade moving system, c) connecting the root end of the first blade

Abstract: An ear disimpactor for disimpacting material impacted in an ear canal and against a tympanic membrane, is disclosed. The impacted material comprises cerumen, insects, and other debris. The ear disimpactor comprises a housing, a warm water irrigation unit, and a suction unit. The housing comprises an ear speculum attached to an outer surface of the housing, a motorized auger comprising a drill bit extending from the motorized auger to a tip of the ear speculum, a warm water line extending from the tip of the ear speculum and across a length of the housing, and a suspension suction tube extending from the tip of the speculum and across the length of the housing. The warm water irrigation unit provides warm water to the ear canal through the warm water line and the suction unit sucks out suspension from the ear canal.

Abstract: A blade for a turbomachine fan, the blade being made from a composite material containing a plurality of longitudinal conductive fibres embedded in an electrically non-conductive matrix, the blade having at least one fastening region to which an identification medium for identifying the blade is fastened, the fastening region containing longitudinal fibres oriented along a preferred fibre axis, the identification medium contains an item of identification data for identifying the blade and at least one radio antenna having at least one communication lobe configured so as to receive a read request and transmit the item of identification data in return, the communication lobe being oriented along a radio axis that is angularly offset from the preferred fibre axis by less than 45°, preferably by less than 22.5°.

Abstract: A rotor for a turbomachine and a method of manufacturing the same. The method includes providing a lug with a lug body and an interface material disposed on the lug body. The method also includes friction welding the lug to a hub member via the interface material to define a projected structure for an outer radial area of a disc assembly of the rotor. The projected structure is configured to support a first side of a rotor blade of the rotor in cooperation with a second projected structure of the disc assembly supporting a second side of the rotor blade. The lug body and the hub member are made from different materials.

Abstract: The present disclosure relates to cable guiding assemblies for wind turbine power cables. A cable guiding assembly comprises an outer part and a central part. Each part has a top surface, a bottom surface, a laterally inner surface and a laterally outer surface. The laterally inner surface has a plurality of recesses suitable for receiving power cables. An outer portion of the central part is configured to be attached to an inner portion of the outer part.

Abstract: An airfoil for use in a gas turbine engine is formed to define cavities formed in the airfoil and a passage that extends between and fluidly interconnects the cavities. The airfoil further includes damping fluid located in the cavities and the damping fluid is adapted to flow between the cavities via the passage.

Abstract: A method for mounting a blade root of a blade on a blade flange of a wind turbine rotor, the method comprising: attaching a control line between a hold structure at the blade flange and the blade root; lifting the blade with a blade lifting crane while the blade root is guided towards the blade flange by use of said control line, and connecting said blade root to said blade flange.

Abstract: A coating occlusion resistant effusion cooling hole to form a film of a cooling fluid on a surface of a wall. The cooling hole extends along a longitudinal axis. The cooling hole includes an inlet section defined so as to be spaced apart from the surface. The inlet section is to receive the cooling fluid. The cooling hole includes a metering section fluidly coupled downstream of the inlet section. The cooling hole includes an outlet section fluidly coupled downstream of the metering section. The outlet section includes an overhang portion, a recessed portion, a first sidewall and a second sidewall. The first sidewall and the second sidewall interconnect the overhang portion with the recessed portion along a portion of the outlet section, and the first sidewall and the second sidewall converge and diverge in a plane transverse to the longitudinal axis.

Abstract: Disclosed is a support element for a lightning protection system of a wind turbine blade comprising: a first surface configured to face towards the suction side or the pressure side of the wind turbine blade; a second surface opposite the first surface; a root side surface configured to face towards the root of the wind turbine blade; and a tip side surface configured to face towards the tip of the wind turbine blade; wherein the first surface comprises a first receptor base recess configured to receive a first receptor base for coupling with a first receptor of the lightning protection system.

Abstract: A lock for preventing rotation of a rotor of a wind turbine has a rotatable lock pin, a pin support supportable in a nacelle of the wind turbine and a mechanism for rotating the lock pin. The pin support has a hub-facing face proximate a rotor hub. The rotatable lock pin is rotatably mounted on the pin support. The lock pin has a cammed portion extending away from the hub-facing face toward the hub. The lock pin inserted into a complementary rotor lock aperture on the rotor hub when the pin support is supported in the nacelle. Rotation of the lock pin causes engagement of an exterior surface of the cammed portion with an interior surface of the rotor lock aperture to immobilize the lock pin against the interior surface to prevent relative motion between the lock pin and the aperture to prevent rotation of the rotor.

Abstract: A lock for preventing rotation of a rotor of a wind turbine has a rotatable lock pin, a pin support supportable in a nacelle of the wind turbine and a mechanism for rotating the lock pin. The pin support has a hub-facing face proximate a rotor hub. The rotatable lock pin is rotatably mounted on the pin support. The lock pin has a cammed portion extending away from the hub-facing face toward the hub. The lock pin inserted into a complementary rotor lock aperture on the rotor hub when the pin support is supported in the nacelle. Rotation of the lock pin causes engagement of an exterior surface of the cammed portion with an interior surface of the rotor lock aperture to immobilize the lock pin against the interior surface to prevent relative motion between the lock pin and the aperture to prevent rotation of the rotor.

Abstract: A compressor rotor for a gas turbine engine is described which includes sets of blades having different airfoil thickness distributions, each including a frequency modifier forming a thickness differential relative to a baseline blade thickness. The frequency modifiers provide different natural vibration frequencies for each of the blades, and facilitate modifying natural vibration frequency separation between adjacent blades of the compressor rotor.

Abstract: A counterweight system for mounting a rotor blade on a balanced rotatable hub of a wind turbine is disclosed. The rotatable hub can have at least one blade root region configured to receive a blade root of the rotor blade, and also have a pitch system configured to rotate the rotor blade around a pitch axis. The counterweight system can have at least one support structure having a proximal end spaced apart from a distal end with the proximal end mountable to at least one blade root region of the rotatable hub. The at least one counterweight mass can be at least partially filled with fluid and coupled to the distal end of the at least one support structure. The at least one support structure can be arranged substantially parallel to the pitch axis such that the pitch system rotates the counterweight mass about the pitch axis.

Abstract: An air foil includes a body and a filler. The body may include a chamber formed therein and includes a first metallic material. The filler may at least partially occupy the chamber of the body and may include a second metallic material. The second metallic material may have a comparatively more negative electrode potential than the first metallic material.

Abstract: A rotor for a gas turbine is disclosed which includes alternating first and second set of rotor blades, the first set of rotor blades having a baseline profile and the second set of rotor blades having a profile with a cutback relative to the baseline profile, the cutback removing a portion of the baseline profile surrounding a maximum deflection point of a natural vibration mode. The cutback may be a leading edge cutback at a span position located a distance away from the hub between 50% and 90% of the total span length. The natural vibration mode may be a natural vibration mode higher than the 1st natural vibration mode, more specifically may be the 4th natural vibration mode.

Abstract: A rotor for a gas turbine is disclosed which includes alternating first and second set of rotor blades, the first set of rotor blades having a baseline profile and the second set of rotor blades having a profile with a cutback relative to the baseline profile, the cutback removing a portion of the baseline profile surrounding a maximum deflection point of a selected natural vibration mode. The cutback may be a leading edge cutback at a span position located a distance away from the hub between 50% and 90% of the total span length. The selected natural vibration mode may be a natural vibration mode higher than the 1st natural vibration mode, more specifically may be the 4th natural vibration mode.

Abstract: The present disclosure includes a system for balancing a turbine disk stack, including a high pressure turbine disk stack. A flange is grooved to accommodate and orient a slip ring. Balancing weights are attached to the slip ring to balance the turbine disk stack during rotation of a gas turbine engine.

Abstract: A rotor component for a rotor assembly of a fluid energy machine, particularly of a gas turbine, a steam turbine, a compressor or the like, wherein the rotor component is at least partly made of a material susceptible to corrosion and/or oxidation and can be arranged concentrically to a rotation axis of the rotor assembly. The rotor component includes a circular surface for checking concentricity of the rotor component with respect to the rotation axis. The rotor component includes at least one additional circular surface for checking concentricity of the rotor component with respect to the rotation axis, wherein the additional circular surface is coated with a corrosion and/or oxidation protection coating.

Abstract: The invention relates to a device for assembling a structure constructed from components, in particular a wind turbine. The device includes a lift placed on a surface for the purpose of placing a component on an available support structure, wherein a boom of the lift is provided with a main hoisting cable with a hoisting tackle for releasable attachment of the component for lifting to the boom. The boom further includes a guide device for the hoisting tackle, the guide device is connected to the boom for displacement along a longitudinal axis of the boom using a displacing device, and the guide device is configured to limit movement of the hoisting tackle in at least one direction. The invention likewise relates to a method which makes use of the invented device.

Abstract: A composite fiber component for a rotor blade of a wind power plant including a first sandwich core and a second sandwich core arranged next to each other, each having an inside facing a rotor blade interior and an outside facing a rotor blade exterior. A first fiber-containing laminate layer is arranged on the inside of the first sandwich core and on the outside of the second sandwich core. A second fiber-containing laminate layer is arranged on the outside of the first sandwich core and on the outside of the second sandwich core. And, a third fiber-containing laminate layer is arranged on the inside of the first sandwich core and on the inside of the second sandwich core. Also disclosed is a rotor blade for a wind power plant having a composite fiber component as disclosed.

Abstract: A dome for a rotor of a rotorcraft, the dome comprising a cap extending radially from an axis of rotation in elevation towards a periphery and in azimuth over 360 degrees, the cap extending in thickness from a bottom face for facing a hub of the rotor towards a top face above the bottom face. At least one of the top and bottom faces is an undulating face that undulates at least in azimuth between the periphery and the axis of rotation in elevation, by including in azimuth along at least one internal circle a succession of bulges and of recesses.

Abstract: A de-oiler balance weight for a rotor disk stack susceptible to collecting oil is provided. The rotor disk stack is configured for use in a gas turbine engine. The de-oiler balance weight comprises a front wall having a first mounting aperture and a first outboard end. An aft wall has a second mounting aperture and a second outboard end. An inboard wall connects the front wall and the aft wall and defines a recess therebetween that is configured to receive a flange portion of a rotor disk in the rotor disk stack. A channel extends at least partially through the de-oiler balance weight for directing the oil away from the rotor disk stack.

Abstract: A torque converter, including: an axis of rotation; a cover arranged to receive torque; an impeller including a shell non-rotatably connected to the cover; a turbine in fluid communication with the impeller and including a turbine shell including a radially outermost segment including a radially outermost end of the turbine shell, at least one blade connected to the turbine shell and an entirety of which is located radially inward of the radially outermost segment; a vibration damper including at least one spring and at least one tab directly engaged with at least one circumferential end of the at least one spring and non-rotatably connected to the turbine shell; at least one rivet passing though the radially outermost segment and fixedly connected to the radially outermost segment; and a torque converter clutch arranged to transmit torque from the cover to the damper when the torque converter clutch is closed.

Abstract: A Ceramic Matrix Composite (CMC) airfoil segment for a gas turbine engine includes a box-shape fiber geometry which defines a rectilinear pressure side bond line and a rectilinear suction side bond line.

Abstract: A gas turbine engine airflow member including a blade core portion, a shroud tip portion extending from the blade core portion, and an airfoil portion formed exteriorly to the blade core portion, where the blade core portion and the shroud tip portion are constructed as a first unitary structure and the airfoil portion is constructed as a second structure. A method of forming a gas turbine engine component is also disclosed.

Abstract: A system and method for repairing a blade are provided. The system includes an induction heating coil configured for heating a platform and slash face of the blade. The induction heating coil extends under the platform and is adjacent to the slash face to provide substantially uniform localized heating to both the platform and slash face of the blade. The induction heating coil is configured so that the platform is visible during a repair or welding operation.

Abstract: Provided are a manufacturing system and a method for fabricating a component. The manufacturing system includes a wire delivery assembly arranged and disposed to deliver a wire feed to a fabrication assembly arrangement; the fabrication assembly arrangement includes a wire manipulation assembly, the wire manipulation assembly being arranged and disposed to convert the wire feed into a wire segment and position the wire segment on a workpiece positioner to form a workpiece stack; an energy beam source assembly arranged and disposed to direct one or more energy beams toward one or more aligned surfaces of adjacent wire segments within the workpiece stack, to weld the wire segments together. The method includes delivering a wire feed to a fabrication assembly; cutting and positioning a wire segment; and directing an energy beam toward one or more aligned surfaces of adjacent wire segments to weld the wire segments together.

Abstract: A structural assembly for a fluid-flow machine includes a main flow path boundary, a row of relatively rotating blades with a gap existing between the blade ends and the main flow path boundary. A secondary flow duct is connected to the main flow path via the two openings spaced apart in the flow direction. A structural assembly has at least one support component and at least one replaceable plug connected directly or indirectly to the support component. The replaceable plug includes a part-section of a secondary flow duct, where the part-section complements at least one further part-section of the secondary flow duct extending outside the plug in the structural assembly to form a secondary flow duct which is continuous between its openings.

Abstract: A rotor assembly for a gas turbine engine including a circumferential array of regularly spaced apart features provided on the disk which are each configured for receiving a balancing weight. The circumferential array of features has an angular orientation relative to the circumferential array of blades such that the features are each located at an at least substantially same offset angle from a stacking line of a respective adjacent blade.

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: The present invention provides a metal forming system, comprising a platform and a gantry means, in which the platform is provided with a plurality of lower mold bases bearing sheet metals, while the gantry means is provided with at least one upper mold base and a toggle unit. The gantry means is performing lateral displacement on the platform, so as to be displaced to a location above the lower mold base which is predetermined to operate. The toggle unit is for adjusting the longitudinal position of the upper mold base so as to change the distance between the upper mold base and the lower mold base, resulting in determining whether a mold-closing state or a mold-opening state. A metal forming operation is performed on the sheet metal between the upper mold base and the lower mold base so as to manufacture a metal formed part when the mold-closing state.

Abstract: The invention relates to a tool holder comprising a tool receptacle in the form of a sleeve part, which comprises a tool receptacle opening comprising a mating surface which is concentric with the axis of rotation of the tool holder and on which the shaft of a tool inserted in accordance with the intended purpose thereof into the tool receptacle opening of the sleeve part can be fixed in a press fit, wherein the sleeve part comprises a number of circumferential recesses from the side of the mating surface, wherein the recesses divide the mating surface into several mating surface segments which are comparable to each other and which are substantially inherently rigid in the axial direction, wherein the radial depth of the recesses is selected such that the press fit releases substantially uniformly on all mating surface segments under the influence of heat applied over the outer circumference of the sleeve part.

Abstract: A method for fabricating a turbomachine blade or vane of composite material including fiber reinforcement densified by a matrix is disclosed. The method includes: making a one-piece fiber blank by three-dimensional weaving; shaping the fiber blank to obtain a one-piece fiber preform having a first portion forming a blade airfoil and root preform and at least one second portion forming a blade platform preform; and densifying the preform with a matrix to obtain a composite material blade or vane having fiber reinforcement constituted by the preform and densified by the matrix, forming a single part with at least one incorporated platform.

Abstract: A system and method for uptower machining of a wind turbine to accommodate a load control system, such as an Advanced Load Controls (ALC) system is disclosed. The load control system includes a plurality of load control components, such as one or more proximity sensors. The method includes designating a first machining location on a rotor lock plate of the wind turbine; mounting a machining device within the wind turbine proximate to the first machining location; machining the first machining location on the rotor lock plate via the machining device; and, installing the load control system within the wind turbine such that at least one of the load control components is installed proximate to the first machining location.

Abstract: A rigid template for aligning surface features on a rotor blade is disclosed. The rigid template is shaped to correspond to the surface of the rotor blade. Further, the rigid template includes a base end and a tail end opposite the base end. The base end is configured to connect to an alignment structure, the alignment structure being fixed relative to the rotor blade. The tail end includes at least one marker configured to locate at least one surface feature on the surface of the rotor blade.

Abstract: Provided is an impeller in which a through hole is provided in a center of a base member of the impeller and a plurality of recessed parts are formed on a bottom surface of the base member. Meanwhile, a jig using in a cutting work of the impeller includes a seating part having a seating surface, a shaft part is erected from a central part of the seating part and is engageable with the through hole of the impeller, and protruded parts are formed on the seating surface and are engageable with the recessed parts provided on the base-member bottom surface of the impeller.

Abstract: A rotor turning system includes a fixture plate configured for attachment to a gearbox, a locking mechanism configured for attachment to the fixture plate, and a reaction fixture configured for attachment to the locking mechanism. The rotor turning system is configured to permit rotation of the rotor only when rotational torque is applied to the locking mechanism, and this rotation is in only one rotational direction.

Abstract: A method for mounting a wind turbine blade to a wind turbine hub by use of a crane boom is provided. The orientation of the blade is kept substantially horizontal when the blade is lifted off the ground and mounted to the rotor hub. Control wires which connect the blade via the crane boom to a winch arrangement are used for keeping the blade orientation substantially horizontal in addition to at least one bearing wire for bearing the blade weight.

Abstract: A securing device for securing a rotor of a turbomachine against tilting is provided, the rotor being arranged perpendicular in relation to a horizontal plane. The securing device includes a support surface enabling the rotor to be laterally supported in relation to the securing device. The rotor or the tie rod, arranged in an essentially vertical manner, are oriented vertically such that during an alignment, the support surface on which the rotor or the tie rod support, are displaced such that rotor is perpendicular in relation to the horizontal plane.

Abstract: A turbine engine assembly is provided. The turbine engine assembly includes a stator assembly and a rotor assembly having a rotor disk coupled to a plurality of rotor blades, the plurality of rotor blades extending radially outward from the rotor disk. The assembly also includes a casing that at least partially circumscribes the plurality of rotor blades. The assembly also includes a dynamic sealing device coupled to the stator assembly. The at least one dynamic sealing device is configured to insert a seal between the casing and the plurality of rotor blades to facilitate reducing a clearance gap defined between the plurality of rotor blades and the casing while the rotor assembly is operating.

Abstract: A gas turbine engine includes a gas turbine engine internal compartment structure having an integral passageway. Wiring is routed through the integral passageway of the gas turbine engine internal compartment structure.

Abstract: A method of manufacturing a carbon composite duct assembly includes providing a first carbon composite fabric layer having a first section. The first section is formed into a first portion and a second portion. The first portion is separately moveable relative to the second portion. The first portion overlaps the second portion to define a first corner of the first carbon composite fabric layer. The first carbon composite fabric layer is formed into at least a portion of a duct extending along an axis.

Abstract: A method of masking a component includes installing a flexible gasket over a portion of a component masking area leaving an unmasked area exposed. A backer is installed over the flexible gasket to compress the flexible gasket between the backer and the portion. The flexible gasket and the backer are secured to the component to provide an assembly. The assembly is deposited into a slurry with an abrasive media to polish the unmasked area, in one example. The flexible gasket and backer prevent abrasive media from reaching the masked area. The flexible gasket and backer can be removed from the component and reused on other similarly shaped components.

Abstract: A method for mounting a wind turbine blade to a wind turbine hub by use of a crane boom is provided. An orientation of the blade is kept substantially horizontal when the blade is lifted off the ground and mounted to the rotor hub. Control wires, which connect the blade via the crane boom to a winch arrangement, are used for keeping the blade orientation substantially horizontal in addition to at least one bearing wire for bearing the blade weight.

Abstract: A rotor blade of a turbine engine comprising a body made of composite material consisting of a fiber-reinforced thermosetting resin and a connecting yoke designed to be attached to a fastener of a rotor disc of the said turbine engine, the said blade characterized in that the connecting yoke comprises a metal reinforcement and a casing made of composite material encasing the said reinforcement.

Abstract: In one embodiment, a gas turbine engine component includes a foam based core and a composite skin member. Both the foam based core and the composite skin member can be used to structurally support the gas turbine engine component. The composite skin member can be a CMC material and is used to partially encapsulate the foam core. The gas turbine engine component can take the form of an airfoil member such as a blade or a vane, a combustor liner, etc. A first portion of the composite skin member includes a first surface extending past an edge of the component creating a step approximate an edge section. In another embodiment, composite skin members can be used to form a continuous shape for the edge section such that the foam core forms part of a gas path surface.

Abstract: A method of extending the life of an extruder screw by affixing tiles of wear-resistant material along the crest of the extruder screw flighting threads, and optionally grinding the hardened material to remove any sharp edges. In another configuration of the present invention, plates of wear-resistant material are secured to the leading edges of the extruder screw threads to further prolong the life of the extruder screw.