Abstract: Provided is a drivetrain assembly including a rotor shaft; a bearing unit mounted about the rotor shaft; and a further drivetrain component connected to an end of the rotor shaft, wherein an annular face of the further drivetrain component is arranged opposite an annular face of the bearing unit with a distance between the annular faces. The drivetrain assembly is characterized by an annular arrangement of tapped holes formed in a first of the two opposing annular faces; a plurality of bolts, wherein each bolt includes a bolt shaft threaded into a tapped hole, a lock nut threaded onto the bolt shaft and tightened against the first annular face; and a bolt head arranged to make contact with the second of the two opposing annular faces. Also provided is a wind turbine including a such a drivetrain assembly; and a method of assembling such a drivetrain.

Abstract: A vibration dampening system includes a vibration dampening element for a turbine nozzle or blade. A body opening extends through the turbine nozzle or blade, e.g., through the airfoil among potentially other parts of the nozzle or blade. A vibration dampening element includes a plurality of stacked damper pins within the body opening. The damper pins include an outer body having an inner opening, a first end surface and an opposing second end surface; and an inner body nested and movable within the inner opening of the outer body. The end surfaces frictionally engage to dampen vibration. The inner body has a first central opening including a first portion configured to engage an elongated body therein and an outer surface configured to frictionally engage a portion of the inner opening of the outer body to dampen vibration.

Abstract: An acoustic panel includes a front skin comprising a plurality of apertures, a back skin, and a core positioned between the front skin and the back skin. The core includes at least one primary core portion including a honeycomb structure defining a plurality of cavities extending from the front skin to the back skin. The core further includes a secondary core portion external to the at least one primary core portion and including a foam structure extending from the front skin to the back skin.

Abstract: A gas turbine engine including: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order; a fan defining a fan axis and comprising a plurality of fan blades rotatable about the fan axis; and a pitch change mechanism operable with the plurality of fan blades, the pitch change mechanism including a plurality of linkages, the plurality of linkages including a first linkage coupled to a first fan blade of the plurality of fan blades and a second linkage coupled to a second fan blade of the plurality of fan blades; and a non-uniform blade actuator system operable with one or more of the plurality of linkages to control a pitch of the first fan blade relative to a pitch of the second fan blade.

Abstract: A guide vane ring which is divided into an upper and into a lower guide vane ring half, with an inner ring which is split at least in two, has a substantially U-shaped cross section, and forms a radially outwardly open flow duct which extends in the circumferential direction and is delimited by way of an inner ring bottom wall and two inner ring side walls, and with a multiplicity of vane platforms which receive guide vanes, are arranged along the outer circumference of the inner ring, and have holding webs which in each case project radially inwards, are spaced apart from one another in the axial direction, and engage around the inner ring side walls from the outside, wherein wear elements are inserted into gaps which are present between holding webs and directly adjacently arranged inner ring side walls.

Abstract: Provided is a wind turbine, including a tower and a damper module, especially a slosh damper module arranged in the tower, which damper module includes a frame with at least two elongated first frame ends at one side of the frame and at least two elongated second frame ends at the opposite side of the frame, which first and second frame ends are fixed to first and second fixation elements arranged at an inner wall of the tower, wherein the first frame ends are immovably fixed to the fixation elements while the second frame ends are fixed sliding relative to the fixation elements, wherein the first and second fixation elements are first and second plates fixed to the and extending horizontal from the inner wall, on which the first and second frame ends comprising flat support areas rest.

Abstract: A fluid cooler for installation in a bypass duct of a turbofan gas turbine engine and associated methods are provided. The fluid cooler includes an inlet duct, a heat exchanger and an outlet duct. The inlet duct includes an inlet protruding into the bypass duct to receive a portion of the bypass air into the inlet duct. The heat exchanger is in fluid communication with the inlet duct. The heat exchanger facilitates heat transfer between a fluid and the portion of bypass air received into the inlet duct. The heat exchanger defines a general flow direction for the portion of bypass air that is different from the main flow direction of bypass air inside the bypass duct. The outlet duct conveys the portion of bypass air from the heat exchanger back to the bypass duct.

Abstract: A vibration mitigating device for engagement with a wind turbine blade includes an air flow modifying element that is configurable between a retracted configuration and an extended configuration. A frame is attachable to and has a fixed length in a span-wise direction of the wind turbine blade. The air flow modifying element is movable along the frame between the retracted configuration and the extended configuration. In the retracted configuration, the modifying element extends between the blade tip and the blade root with a first spanwise length, and in the extended configuration the modifying element extends between the blade tip and the blade root with a second, greater spanwise length.

Abstract: A method of assembling a resolver rotor to a hub of a transmission assembly is provided. The method includes: forming a generally axially extending groove in an outer surface of the hub, the groove extending at an assembly angle greater than 0 degrees relative to an axial direction from a hub end toward a hub base, the assembly angle being positive in a direction that is opposite to a rotation direction of the hub in use; forming a projection on an inner surface of the resolver rotor, the projection being configured to have an interference fit with the groove upon assembly; and assembling the resolver rotor onto the hub with the at least one projection traveling along and interfering with a portion of the at least one groove as the resolver rotor moves to a seated position toward the hub base. A transmission assembly is also provided.

Abstract: An information generating device includes a control unit for causing a motor to rotate a pinion gear meshing with a ring gear while a predetermined braking force is applied to brake rotation of a turnable part of a wind turbine, thereby causing a fastening part to deform, where the fastening part is provided to fixedly attach the motor to a target part, a deformation amount obtaining unit for obtaining an amount of deformation experienced by the fastening part, and an information generating unit for generating correlation information indicating a correspondence between a driving torque of the motor and the amount of deformation experienced when the driving torque is used to rotate the motor.

Abstract: A method for rotating a hub of a wind turbine in an inching operation to rotate the hub includes reconfiguring the generator from normal operation by coupling a first string of a first electrical phase of the stator in series with a second string of a second electrical phase of the stator, the first and second strings comprising one or more coils coupled in series. Current is provided from a power converter to the first and second strings o rotate the hub. The generator includes a first and a second winding system, each including a plurality of electrical phases in the normal operation. The first string of the first electrical phase is part of the first winding system in normal operation, and the second string of the second electrical phase is part of the second winding system in the normal operation.

Abstract: An axial turbomachine comprising a compression device with a variable-orientation vane rectifier stage; a combustion chamber downstream of the compression device; a turbine device downstream of the combustion chamber; and a leak passage of air compressed by the compression device, between the compression device and the turbine device for cooling the turbine device; and where the rectifier stage is configured to modulate the section of the leak passage according to the orientation of the vanes of the stage.

Abstract: Systems and methods for protecting an aerodynamic structure, e.g., a wind turbine blade, rotor blade, aerodynamic aerostructure, etc., are provided. Long fiber reinforced composites having a helicoidal architecture with material aligned with a graded hardness and stiffness are used to develop an efficient and highly tailorable leading edge protection (LEP) solution with longer durability than conventional solutions while yielding lighter, and optionally, more environmentally sustainable solutions. At least a portion of the plurality of plies are helicoidally arranged relative to one another to tailor stress wave propagation speed of the aerodynamic blade and to provide load carrying strength for the aerodynamic blade.

Abstract: A fan module for an aircraft turbomachine includes a fan with a disc carrying fan blades and a rotor of an electric machine. The rotor has an annular shape and is mounted coaxially downstream of the fan. The module further includes an annular support for the rotor with a downstream end fixed to the rotor and with an upstream end fixed to the fan disc. The support is fixed to the disc by shear bolts configured to break when a torque transmitted by the disc to the support exceeds a predetermined threshold.

Abstract: A damping device that includes features for damping bending vibration of a shaft rotating about its axis of rotation and methods for damping bending vibration utilizing the damping device are provided. In one exemplary aspect, the damping device includes a damping disc operatively coupled with a shaft, e.g., of a turbine engine or shaft system. The damping disc is at least partially received within a chamber defined by a housing. The chamber of the housing is configured to receive a damping fluid. When the shaft is rotated about its axis of rotation, the damping disc is movable within the chamber to move the damping fluid such that the damping fluid absorbs bending vibration emitted by the shaft. The damping fluid moved by the damping disc dampens bending vibration emitted by the shaft.

Abstract: A heat shield includes a first wall defined between a first end and a second end; a second wall defined between the first end and the second end, the second wall connected to the first wall at the first and second ends; a space defined between the first wall and the second wall; and thermal insulation disposed in the space. A gas turbine engine and a method of installing a heat shield in a gas turbine engine are also disclosed.

Abstract: Embodiments of the invention are directed to a rotor for use in molten metal and devices including the rotor. The rotor has a rotor body and blades, wherein each blade includes a tip that is at least twice as hard as the rotor body.

Abstract: A coupling for a turbomachine, including a first and a second disc attached along an axis, and extending in majority respectively from a first and from a second side of a median plane normal to the axis, the first and the second discs being provided respectively with first and second teeth mutually engaging through the median plane to form a curvic connection. Several first teeth each include a first protuberance jutting out towards the axis while extending from the second side; several second teeth each include a second protuberance jutting out towards the axis of rotation while extending from the first side; the first protuberances are spaced apart from the second protuberances along the axis; at least one blocking member is brought to be supported against the first and second protuberances to block axially the first element relatively to the second element.

Abstract: A system may include an insulation mount assembly configured to mount insulation within a component of an exhaust diffuser of a combustion system. The insulation mount assembly includes an insulation cover plate configured to cover the insulation over a wall of the component, and a plurality of mounting clips configured to extend partially over the insulation plate and couple to the wall of the component. Each clip of the plurality of mounting clips is configured to enable movement of the insulation cover plate in a first direction along a surface of the wall and block movement of the insulation cover plate in a second direction crosswise to the surface of the wall.

Abstract: A method of operating a multi-engine system of a rotorcraft includes, during a cruise flight segment of the rotorcraft, controlling a first engine to provide sufficient power and/or rotor speed demands of the cruise flight segment; and controlling a second engine to by providing a fuel flow to the second engine that is between 70% and 99.5% less than a fuel flow provided to the first engine. A turboshaft engine for a multi-engine system configured to drive a common load is also described.