Abstract: A turbine rotor blade includes a blade body and a tip shroud on a tip of the blade body. The tip shroud has a contact block configured to face a tip shroud of an adjacent turbine rotor blade, and the contact block includes a base material, an oxidation resistant coating on the surface of the base material, and a hard wear resistant coating on the surface of the oxidation resistant coating.

Abstract: The crane is hoisted from the ground to the nacelle by operating a cable winch at ground whereby a cable extends from the crane to a roller at the nacelle and to the cable winch. A hoist block with the roller is arranged on a jib at a first hoist block position above a second hinge part of a crane base and extended in horizontal direction from the nacelle. When a first hinge part of the crane is positioned at a corresponding second hinge part of the crane base, the cable extends in a downward direction directly from the roller of the hoist block and through a central opening in a pedestal. After mutual connection of the first and second hinge parts, the hoist block is removed from its first hoist block position.

Abstract: For replacing in particular a used main bearing of a wind turbine, a bearing housing is first pulled axially off the main bearing along a rotor shaft, then the used main bearing is divided and disassembled. A new main bearing is assembled around the rotor shaft and the original bearing housing is pushed axially back onto the main bearing. During the replacement of the main bearing, the rotor shaft is supported on a machine carrier by means of a holding device, wherein the holding device is arranged at least partially in the region between a bearing seat and a hub-side end region of the rotor shaft.

Abstract: A nacelle includes in turn a nacelle frame, and a yaw bearing having likewise/in turn at least a geared ring for providing a rotatable connection between the nacelle and the tower around a yaw axis. A method includes the steps of: a) disengaging the rotatable connection between the nacelle and the tower; b) lifting the nacelle from the tower by using lifting means, allowing the rotation of the geared ring; and c) rotating the geared ring around the yaw axis until the geared ring reaches a predetermined position with respect to the component to which the geared ring is connectable, either to the nacelle or the tower.

Abstract: A rotor blade for a wind turbine has a rotor blade root defining a reference plane for attachment to a hub. Adjacent to the rotor blade root is a profile region extending to the rotor blade tip. In the profile region, the rotor blade has a blade profile defining a chord. The chord angle between the reference plane and the chord increases over the entire profile region, from the rotor blade root towards the rotor blade tip.

Abstract: The present application relates to an electric machine splitting or assembling method, an electric machine assembling method, and an electric machine splitting or assembling device including a sleeving device separating or coaxially sleeving first and second rotary bodies; the first disassembly device fixes the first rotary body and includes at least two first separable portions, and the first rotary body is split into petals in a circumferential direction by disassembling the first separable portions, or its respective petal segments are assembled in the circumferential direction by combining the first separable portions; and the second disassembly device is fixed to the second rotary body and includes at least two second separable portions, and the second rotary body is split into petals in the circumferential direction by disassembling the second separable portions, or its respective petal segments are assembled in the circumferential direction by combining the second separable portions.

Abstract: Systems and methods for repairing compressor blades using hybrid manufacturing techniques. A tool for repairing a compressor blade has a plurality of support bases, and a slot configured for securement of said compressor blade to said mounting tool. The tool has a pair of support bases, each of which is configured for the building of a sacrificial support thereon to stabilize the compressor blade during repair. The tool is coupled to a hybrid manufacturing machinery and the sacrificial supports stabilize the compressor blade during additive and subtractive manufacturing processes.

Abstract: A safety apparatus for containing an energy release from a rotor sub-assembly, the safety apparatus includes a plurality of containment members. The containment member has an elongate region defining a longitudinal axis; and at least two arms projecting away from the longitudinal axis of the elongate region; and at least one connecting member connected to at least two of the plurality of containment members. In use the at least one connecting member is configured to connect the safety apparatus to the sub-assembly and the plurality of containment members are configured to withstand an energy release from the sub-assembly.

Abstract: a tooling assembly for installation relative to a first and second turbomachine component is provided. The tooling assembly includes an axial mounting portion removably couplable to the first turbomachine component. The axial mounting portion includes a first plate, a second plate spaced apart from the first plate, and at least one turnbuckle assembly that extends between, and is coupled to, the first plate and the second plate. At least one of the first plate and the second plate include a radial compression portion. The radial compression portion includes a compression bar radially movable relative to the axial mounting portion and configured to contact the second turbomachine component.

Abstract: A process and tool for installing and removing various kinds of wear parts used with earth working equipment. The process and tool allows the operator to remove and install the wear parts at a safe distance so that the operator is physically remote from the potential risks of the removal and installation process. The tool may be manually operated via an operator or the tool may be a semi-automated or fully automated.

Abstract: Provided is an arrangement for removing and/or exchanging a hydraulic fluid accumulator installed within a hub of a wind turbine, the arrangement including: a first pair of mounting legs each having at an upper portion connector for connecting to a hub component; a second pair of mounting legs each having at an upper portion connector for connecting to a hub component; a first bar connecting the first pair of mounting legs at a lower portion; a second bar connecting the second pair of mounting legs at a lower portion; an elongate resting structure for carrying an accumulator, the resting structure being at one end slidably supported by the first bar and at another end slidably supported by the second bar and being movable in a parallel manner traverse, in particular perpendicular, to a longitudinal direction the resting structure.

Abstract: A method 14 for the controlled removal of a protective layer 3 from a surface of a component 10, wherein the component comprises: a base body 1; an intermediate layer 2, which at least partially covers the base body; and said protective layer 3, which comprises an amorphous solid, in particular an amorphous nonmetal, in particular amorphous ceramic, and at least partially covers the intermediate layer; wherein the method comprises the following steps: bringing 11 the protective layer 3 into contact with an etching or solvent medium 4; and removing 12 the protective layer 3 under the action of the etching or solvent medium 4 until the intermediate layer 2 is exposed; and wherein the etching or solvent medium causes a first etching or dissolving speed of the protective layer and a second etching or dissolving speed of the intermediate layer and wherein the first etching or dissolving speed is greater than the second etching or dissolving speed.

Abstract: A control device controls sectors for the assembly of turbine stators of a turbine. Each turbine stator is formed of an assembly of sectors juxtaposed to one another, and each sector has a reference. The control device includes an automated system for identifying the sector with means for reading the sector reference, a database of the references of the sectors that form the turbine stators of the turbine, and means for associating the read reference of the sector with a determined turbine stator of the turbine.

Abstract: The invention relates to a method for repairing a damaged blade tip of a turbine blade which is armor-plated and provided with a blade coating, of a thermal gas turbine. The method according to the invention comprises the steps of removing a blade tip armor plating of the turbine blade at least in the region of the damaged blade tip and producing a repair surface (12), removing only a part of the blade coating of the turbine blade in the region of the repair surface while preserving a part of the blade coating separated from the repair surface (14), restoring the blade tip reinforcement (20), and restoring the blade coating in the region of the repaired blade tip (22). The invention furthermore relates to a device for carrying out such a method.

Abstract: A system for a turbine blade tip to address wear during rubbing with a shroud, and also tip rail cooling, is provided. The turbine blade tip includes a tip rail and cooling passage(s) extending through a radially outer end surface thereof, providing direct cooling to the tip. The tip rail may include tip rail cooling inserts. The radial outer end surface of the tip rail includes a first portion radially inward of a second portion thereof. An abrasive layer extends along the first portion adjacent the cooling passage(s), and may include a matrix alloy having a plurality of cubic boron nitride (cBN) particles and a plurality of ceramic particles embedded therein. The abrasive layer extends radially outward of the second portion of the radial outer end surface. The system also may include a shroud including an abradable coating thereon.

Abstract: A variable pitch mechanism for a wind turbine and a wind turbine having the variable pitch mechanism. The variable pitch mechanism includes a variable pitch bearing and a driving gear, the variable pitch bearing includes an outer ring of the bearing fixed to the hub and an inner ring of the bearing connected to the blade, the variable pitch mechanism further includes a flange mounted on the hub, the driving gear is mounted on the flange and engages with the teeth on the inner ring of the bearing, and the mounting position of the flange on the hub is adjustable along a circumferential direction of the variable pitch bearing.

Abstract: A method for repairing a discharge ring of a hydraulic turbine with a turbine runner in place includes: mounting adjustable fixtures to runner blades that are approximately evenly spaced around the turbine runner, where each adjustable fixture is mounted to a different runner blade at a different predetermined vertical position with respect to a surface of the discharge ring; attaching cutting equipment configured to remove material from the discharge ring to each adjustable fixture installed on the runner blades; installing a drive unit configured to rotate the turbine runner; controlling the drive unit to rotate the runner at a specified speed; and controlling the cutting equipment attached to each adjustable fixture to concurrently remove material from the discharge ring as the turbine runner rotates.

Abstract: A turbine blade repair method is provided. The turbine blade repair method includes quantizing a position and a shape of a damaged portion of a turbine blade into numerical values, calculating a momentum loss of the turbine blade due to removal of the damaged portion, modeling a shape of a repair portion to replace the damaged portion so that the repair portion has the same momentum as the damaged portion, removing the damaged portion, and forming the modeled repair portion by performing an additive manufacturing at a position of the removed damaged portion.

Abstract: The gas turbine compressor for an aircraft gas turbine engine includes a compressor rotor having a plurality of compressor blades circumferentially distributed around a hub. Each of the compressor blades has an airfoil extending radially outward from the hub to a blade tip. A circumferential row of the compressor blades includes two or more different blade types, at least one modified blade of the two or more different blade types having means for generating different shock patterns between adjacent ones of the two or more different blade types when the gas turbine compressor operates in supersonic flow regimes. The means for generating different shock patterns on the modified blade aerodynamically mistune the two or more different blade types.

Abstract: The present disclosure relates to turbine blades adapted for use in gas turbine engines. In particular, this disclosure is directed to turbine blades that include components made from ceramic matrix composite materials and that incorporate abradable materials.

Abstract: A system and method for cooling a turbine blade tip shroud is provided. The turbine blade comprises a blade attachment, a platform extending radially outward from the attachment, an airfoil extending radially outward from the platform, and a tip shroud extending radially outward from the airfoil. The tip shroud has one or more knife edges extending radially outward from an outer surface of the tip shroud. One or more cooling passages extend through the airfoil and to the tip shroud. The turbine blade also includes one or more tip plates secured at or near the outer surface of the tip shroud thereby forming a plenum between the outer surface and the one or more tip plates. The one or more tip plates also include a plurality of cooling holes for flowing cooling air through the plenum to cool the tip shroud.

Abstract: A turbomachinery component of a gas turbine engine is disclosed having a number of techniques of reducing the effects of a gap flow between an airfoil member of the gas turbine engine and a wall of the gas turbine engine. The airfoil member can be variable and in one form is a variable turbine vane. In one embodiment a brush seal is included between the vane and the wall. In another form a wear surface is disposed between the vane and the wall. In yet another form a moveable member capable of being actuated to change position can be disposed between the vane and the wall to alter the size of a gap between the two.

Abstract: The present embodiments set forth a blade including an airfoil including an outer tip having a floor, a leading edge and a trailing edge, a concave pressure sidewall and a convex suction sidewall extending axially between corresponding leading and trailing edges and radially between the floor and the tip cap. The airfoil further includes a tip cap extending from the floor of the outer tip and coextensive with the pressure sidewall and suction sidewall and around the leading edge and trailing edge. The tip cap includes a squealer tip configuration including a suction side tip cap portion and a pressure side tip cap portion. The suction side tip cap portion and pressure side tip cap portion extend unequal distances above the floor providing for cooling fluid flow out of the tip cap.

Abstract: A gearbox repair assembly is disclosed herein. The gearbox repair assembly includes a sleeve having an inner diameter configured to receive a bearing assembly and an outer diameter configured to fit within a bore of a gearbox housing. The gearbox housing can be part of a gearbox of a wind turbine. The gearbox repair assembly further includes a retaining plate configured to be attached to the gearbox housing for preventing an outer race of the bearing assembly from rotating in the bore relative to the gearbox housing. Also provided are methods to repair such a gearbox. The gearbox repair assembly and related methods reduce the time and cost needed to repair the gearboxes.

Abstract: A reconfigurable maintenance apparatus includes a body configured to operate within a cavity. The body has a first shape in a first configuration and a second shape in a second configuration. The first configuration facilitates the body entering the cavity. The reconfigurable apparatus also includes at least one maintenance device operably coupled to the body. The second configuration facilitates the at least one maintenance device of the reconfigurable apparatus performing a maintenance operation.

Abstract: Embodiments of an integrated laser hot wire deposition head are disclosed. In one embodiment, the deposition head includes a structural frame, a laser process sub-system, a wire feeding device, and a contact tube. The laser process sub-system is mounted within the structural frame to deliver a single beam path laser beam in a longitudinally-oriented direction toward a substrate or a part to be additively manufactured. The wire feeding device and contact tube are mounted within the frame to feed a consumable filler wire toward the substrate or part at an angle with respect to the longitudinally-oriented direction. The deposition head can be moved omni-directionally with respect to the substrate or the part, under the guidance of a motion control system, to additively manufacture the part without having to angularly change an orientation of the single beam path laser beam from the longitudinally-oriented direction or rotate the deposition head.

Abstract: A system includes a controller, a pretreating machine, and an additive manufacturing machine. The pretreating machine is coupled to the controller. The pretreating machine includes a pretreater structured to form an interface layer on a component. The additive manufacturing machine is coupled to the controller. The additive manufacturing machine includes a material feed and a forming beam. The material feed is configured to selectively provide a first amount of material on the interface layer. The forming beam is configured to substantially melt the first amount of material, thereby forming a first layer of a first material deposit on the interface layer.

Abstract: Methods of manufacturing or repairing a turbine blade or vane are described. The airfoil portions of these turbine components are typically manufactured by casting in a ceramic mold, and a surface made up of the cast airfoil and at the least the ceramic core serves as a build surface for a subsequent process of additively manufacturing the tip portions. The build surface is created by removing a top portion of the airfoil and the core, or by placing an ultra-thin shim on top of the airfoil and the core. The overhang projected by the shim is subsequently removed. These methods are not limited to turbine engine applications, but can be applied to any metallic object that can benefit from casting and additive manufacturing processes. The present disclosure also relates to finished and intermediate products prepared by these methods.

Abstract: A method of repairing erosion on a wind turbine blade while on a wind turbine includes placing a scanning device on an erosion zone. The device scans the erosion zone to gather an image and/or digital data. A printing system deposits a material according to the image and/or digital data. The repair system may include a frame such that scanning and/or depositing are with respect to the frame. A processing system interprets the image and/or digital data and produces an instruction file. Depositing the material may include depositing the material according to the instruction file. An unmanned aerial vehicle may be operated to position at least one of the scanning device and the printing system on the wind turbine blade. Alternatively, a rope/wire system may be operated to lower at least one of the scanning device and the printing system along the wind turbine blade.

Abstract: A reinforcement object is reinforced without being carried out from a wind turbine power generation facility. A method of remodeling a wind turbine power generation facility includes: a carry-in step of carrying a reinforcement member into a hub through an opening portion which has a smaller dimension than a reinforcement object inside the wind turbine power generation facility and which brings into communication inside of the hub and outside of a front side of the wind turbine power generation facility, the reinforcement member having a smaller dimension than the opening portion; and a reinforcement step of processing the reinforcement object inside the hub, and reinforcing the reinforcement object by using the reinforcement member carried into the hub.

Abstract: In a first aspect, a yaw system for rotating a nacelle with respect to a tower is provided. The yaw system comprises a gliding yaw bearing, an annular gear and a plurality of yaw drives, a braking disk and one or more braking disk for braking the rotation of the nacelle. In a further aspect, a tower adapter for a wind turbine is provided. The tower adapter comprises a first bearing component of a gliding yaw bearing and braking disk to brake the rotation of the nacelle with respect to the tower adapter. In yet a further aspect, a wind turbine comprising such a yaw system and/or such a tower adapter is provided.

Abstract: A method of fabricating an airfoil includes imaging a second end of the body portion to obtain image data, casting the tip portion utilizing the image data of the second end of the body portion and coupling a first end of the tip portion to the second end of the body portion. One or more features of the tip portion align with one or more features of the body portion. The method also includes additively manufacturing a core of the tip portion utilizing the image data and forming a casting mold about the core. The tip portion is cast in the casting mold. The coupling of the tip portion to the body portion including depositing a bonding material on a first end of the tip portion. An airfoil formed by the method is also disclosed.

Abstract: Provided is a wind turbine including a tower and a nacelle rotatable relative to the tower by means of a yaw bearing arrangement having a yaw ring fixed relative to the tower, several upper sliding pads arranged between the upper side of the yaw ring and a sliding structure of the nacelle and several lower sliding pads arranged between the lower side of the yaw ring and the sliding structure, wherein the sliding pads are fixed to the yaw ring and that at least one radial opening is provided in the sliding structure allowing access to the upper or lower sliding pads.

Abstract: A method for repairing a component is disclosed. The method includes removing a portion originally including a plurality of cooling holes, of the component to form a cavity, forming by additive manufacturing a replacement portion including a plurality of cooling holes, and varying a surface roughness and a diameter of at least one cooling hole of the plurality of cooling holes during the forming by additive manufacturing the replacement portion. The replacement portion replaces the portion of the component.

Abstract: A method of remanufacturing a turbine blade having a platform includes placing a puck against a surface of the platform. The method may include electrical discharge machining an interface between the puck and the platform and brazing the puck to the platform. A total radial thickness of a finally remanufactured platform of the remanufactured turbine blade is greater than an initial radial thickness of the platform before remanufacturing the turbine blade.

Abstract: Methods for repairing a trailing edge of an airfoil are provided. The method can include removing a portion of the trailing edge of the airfoil to form an intermediate component, and then applying using additive manufacturing a replacement portion on the intermediate component to form a repaired airfoil. The replacement portion defines at least one trailing edge ejection slot.

Abstract: An airfoil according to an example includes, among other things, a suction sidewall and a pressure sidewall. A tip wall extends from a leading edge to a trailing edge and joins respective outer ends of the suction and pressure sidewalls. A tip rib extends along a pressure side of the tip wall. A tip leakage control channel is provided at the tip wall and has a floor that extends between a first control channel vane sidewall and a second control channel vane sidewall established by a corresponding tip leakage control vane. Each of the tip leakage control vanes is contiguous with and extending from a suction side surface of the tip rib. The tip leakage channel extends toward the trailing edge while extending toward the suction sidewall. One or more of an internal cavity, a channel cooling aperture, and a sidewall microcircuit may be provided.

Abstract: A helicopter has a mast axis and a rotorcraft blade assembly. The rotorcraft blade assembly has a main body and a blade tip movable relative to the main body. The rotorcraft blade assembly is selectively rotatable about the mast axis.

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil having a tip wall that joins outer spanwise ends of a suction sidewall and a pressure sidewall and including a tip rib extending chordwise along a pressure side of said tip wall. The tip wall includes a tip shelf disposed at a junction between said pressure sidewall and said tip rib. A tip leakage control channel at an outer surface of said tip wall, wherein said tip leakage control channel is between first and second tip leakage control vanes contiguous with a suction side surface of said tip rib, said tip leakage control channel extending toward said trailing edge while extending toward said suction sidewall. An air seal is radially outward of said tip wall and positioned to minimize leakage at said tip wall.

Abstract: A nose cone assembly is provided comprising a nose cone, a support ring on which the nose cone is mounted, and an insulating layer disposed between the nose cone and the support ring, the insulating layer at least partially comprising glass fibres. A composite nose cone is also provided comprising an attachment region A, in which composite fibres are oriented substantially perpendicular to an axis of rotation of the nose cone, and an impact region I, in which composite fibres are oriented substantially parallel to the axis of rotation of the nose cone. Also provided is a support ring for a nose cone assembly, the support ring comprising an annular main body and an annular projecting attachment flange, the attachment flange terminating in a plurality of circumferentially spaced attachment tabs, wherein the attachment flange forms with the main body a cross section having at least two C curves.

Abstract: A process for cladding a metal part of an aircraft turbojet, including a plurality of metal portions, using a nozzle for emitting a laser beam, the process including positioning the metal part to be cladded on a turntable; positioning a cover on the turntable; positioning the nozzle in an aperture present in the cover; introducing an inert gas under the cover; and cladding a first portion of the metal part by carrying out operations of: spraying metal powders; emitting the laser beam; and moving the nozzle relative to the first metal portion.

Abstract: A tip structure for a turbine blade comprises a tip surface of an airfoil that extends from a leading edge to a trailing edge and from a pressure side to a suction side of the airfoil. A suction side rail protrudes from the tip surface and comprises: a trailing portion extending flush with the suction side of the airfoil from an origination location at or near the trailing edge to an intermediate location on the suction side; and a leading portion extending from the intermediate location across the tip surface so as to create a suction side shelf region between the leading portion of the suction side rail and the suction side of the airfoil.

Abstract: According to an embodiment, a method is provided for preparing a reconditioning of a damaged portion of a component, particularly of an aircraft, by adding an insert, which fills and/or bridges the damaged portion. The method involves: producing a 3D CAD repair model of the damaged portion by scanning; analyzing the repair model and thus evaluating complexity of the damage and/or its reconditioning; as a function of the complexity, deciding between at least two alternative means to perform at least a following step, which is analyzing the repair model and thus dimensioning the reconditioning including the insert. Further, an insert is provided for filling and/or bridging a damaged portion for reconditioning of the damaged portion of a component, particularly of an aircraft, produced according to the method.

Abstract: The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil and a tip shroud coupled to the airfoil. The tip shroud defines a core. The tip shroud includes a rib positioned within the core and a radially outer wall. The rib separates a first portion of the core and a second portion of the core. The airfoil, the rib, and the radially outer wall partially define a first cooling passage fluidly isolated from the core.

Abstract: A turbine blade includes cooling passages formed inside the blade and extending in a blade height direction, blade surfaces on a suction side and a pressure side being covered with thermal barrier coating, a design point on a suction side being set on the blade surface on the suction side of each blade section perpendicular to the blade height direction within a range from a position on a back side of and including a throat position, and to a position in front of and not including a tailing end of a final cooling passage. Thickness distribution of the thermal barrier coating on the suction side of each blade section is configured such that a thickness of the thermal barrier coating is uniform from a blade leading edge to the design point and gradually reduces from the design point toward the back side up to the blade trailing edge.

Abstract: A method of repairing a diaphragm of a rotary machine includes removing an initial steam path from the diaphragm. The initial steam path includes a plurality of initial partitions. Each initial partition is associated with an original trailing edge profile and an original axial length. The method also includes coupling a replacement steam path to the diaphragm. The replacement steam path includes a plurality of replacement partitions. Each replacement partition has a replacement axial length that is greater than the original axial length.

Abstract: A turbomachine rotor blade, which includes a body radially extending and an insert covering the body tip, the insert being made of a first portion radially covering the blade tip and of a second portion partly covering the intrados face of the blade. The cross-section of the insert along a radial plane with respect to an axis of a rotor is corner-shaped and the first portion of the insert extends tangentially with respect to the main axis of the rotor and the second portion extends globally radially with respect to the main axis of the rotor.

Abstract: Described herein a bucket for use in the last stage of a steam turbine engine. The bucket includes a titanium-based alloy having a leading edge wherein the leading edge includes titania having a plurality of pores and a top sealing layer filling the plurality of pores, the sealing layer selected from the group consisting of: chromium, cobalt, nickel, polyimide, polytetrafluoroethylene and polyester.

Abstract: An exhaust-side journal bearing for supporting a gas turbine rotor is disposed inside a bearing box. The bearing box is supported by a strut which extends inward from an exhaust casing, and a seal ring having an annular inner peripheral end is disposed on the bearing box. Executed during a maintenance work are: a bearing adjustment step of displacing a bearing surface of the journal bearing relative to the bearing box in a perpendicular direction perpendicular to the axial direction; and a seal ring adjustment step of displacing the inner peripheral end of the seal ring relative to the bearing box in accordance with the direction of displacement and the amount of displacement of the bearing surface.

Abstract: A ceramic matrix composite blade may include an airfoil and a root. A protective metallic layer may be coupled to the root. The protective metallic layer may be plasma sprayed on the root. A portion of the protective metallic layer may be removed.