Abstract: Components are fastened with inserts that are placed into a hole in the component and bonded with an adhesive. A decoupling element is provided on the front face of the insert. This diverts the forces around the highly stressed front face of the inserts. The insert may be of a material with a lower stiffness compared with the adhesive. This arrangement may reduce stress peaks and increase the load capacity of the connection. A tool may be provided that reduces air inclusion between the insert and the component during fitting. The connection arrangement can be used when components of different stiffnesses have to be securely connected to one another. This applies to, among other things, fastening of fibre composite components or mineral components to metal components.

Abstract: A dual-motor system includes a first motor rotationally coupled to a first drive shaft. The first drive shaft is coupled to a common shaft couplable to a rotationally driveable member. The dual-motor system also includes a second motor rotationally coupled to a second drive shaft. The second drive shaft is coupled to the common shaft. The first motor and the second motor are coaxially aligned with the first drive shaft passing through the second drive shaft.

Abstract: A planetary gear box (and method of assembly), where the gear box includes a sun gear, a plurality of planet gears, a ring gear, a plurality of planet pins, an axially forward carrier plate and an axially rearward carrier plate. Each planet pin is fixed respectively at its axially forward end on the axially forward carrier plate and at its axially rearward end on the axially rearward carrier plate of the planetary gear box. The planet pin is of two-part design and forms a radially outer pin part and a radially inner pin part, which are connected to one another in a manner precluding relative rotation therebetween, wherein the radially outer pin part forms a bearing with the planet gear, and only the radially inner pin part is fixed at its axial ends to the forward and rearward carrier plates.

Abstract: The present invention relates to an impeller comprising: a shroud having a plurality of spiral upper slot units formed therein; a hub located to face the shroud; and a plurality of blades connected to the hub and inserted into the upper slot units to be coupled to the shroud, wherein the blade includes a body portion formed to be inclined to one side and an upper end portion, which is bent upward from the body portion and has a second concave surface formed in one side and a second convex surface formed on the other side thereof, and the upper slot unit includes an upper slot bottom for forming a space in which the upper end portion is inserted; an upper slot wall divided into a first upper slot wall located at the second concave surface side and a second upper slot wall located at the second convex surface side; and a second inclined surface formed to be inclined from the first upper slot wall so as to face the second concave surface.

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor section including a propulsor that delivers flow to a core flowpath and a compressor section including first and second compressors. The core flowpath passes through the first compressor. The core flowpath in the first compressor has an outer diameter relative to the engine longitudinal axis. The outer diameter has a slope angle relative to the axis.

Abstract: A gas turbine engine includes a propulsor section including a propulsor, a compressor section including a first compressor and a second compressor, a geared architecture, a turbine section including a first turbine and a drive turbine, and a power density of greater than or equal to 4.75 and less than or equal to 5.5 lbf/in3, wherein the power density is a ratio of a thrust provided by the engine to a volume of the turbine section.

Abstract: A scupper suitable for a bearing compartment of a gas turbine engine includes a windage blocker in a gutter section upstream of a drain hole, the windage blocker extends from a wall of the gutter section. A method for capturing wept oil in a bearing compartment of a gas turbine engine includes positioning a windage blocker adjacent to a drain hole forming a passage space and increasing a pressure upstream of the windage blocker to generate a vortex downstream of the windage blocker creating an oil re-circulation zone promoting oil drainage into the drain hole.

Abstract: A gearbox assembly includes a plurality of planet gears. At least one planet gear of the plurality of planet gears includes a layshaft that supports a first stage planet gear and a second stage planet gear. The at least one planet gear is characterized by a Radial Stage Distance greater than or equal to 30 millimeters and less than or equal to 100 millimeters. The Radial Stage Distance is Rrm1?Rrt2. Rrm1 is a first stage rim inner radius of the first stage planet gear and Rrt2 is a second stage root radius of the second stage planet gear.

Abstract: A compressor system includes a compressor housing including an inlet opening and a diffuser outlet, the compressor housing includes a first recirculation passage extending from the diffuser outlet to a mounting face of the compressor housing. The compressor housing defines a cavity that receives a compressor wheel. An inlet adapter is mounted to the mounting face of the compressor housing and the inlet adapter includes a second recirculation passage in communication with the first recirculation passage in the compressor housing and with a compressor air inlet passage of the inlet adapter. A recirculation valve is mounted to the inlet adapter and is disposed in communication with the second recirculation passage for providing a selective connection of the first recirculation passage to the compressor air inlet passage.

Abstract: A fan apparatus has a housing with an enlarged portion defining at least one air intake and an outlet portion defining an outlet port. The outlet port has a greater width and a lesser height. A blower wheel having a plurality of fan blades is supported in the enlarged portion of the housing for rotation about an axis. A driver is connected to the blower wheel to cause rotation of the blower wheel. A flow straightener assembly is located in the outlet portion of the housing. The flow straightener assembly has first and second fins spaced apart from one another and oriented substantially orthogonal to the axis of the blower wheel. Third and fourth fins are located outside of a respective one of the first and second fins, the third and fourth fins being oriented substantially parallel to the axis of the blower wheel.

Abstract: An acoustic monitoring system and method for the health status of an offshore wind turbine and an ocean wave are provided. The acoustic monitoring system includes a first laser transmitter, a second laser transmitter, a telephoto camera provided at a hub, a vibration detection sensor provided on a tower of a wind turbine, and four acoustic detection sensors arranged at an interval of 90° along the circumference of the tower. The first and second laser transmitters are arranged at the bottom of a nacelle of the wind turbine and emit laser lights vertically downward. The first laser transmitter, the second laser transmitter, the telephoto camera, the vibration detection sensor, and the acoustic detection sensors are connected to a data acquisition and conversion module through a transmission module. The acoustic monitoring system combines laser light detection with acoustic signal feature detection to improve stability and safety of the offshore wind turbine.

Abstract: Blade root receptacle for receiving a blade root of a rotor blade of a turbomachine. The blade root receptacle, for radially bearing in a form-fitting manner on the blade root, has a supporting flank which, in terms of a rotation axis, at least in proportions faces radially inward, wherein the supporting flank is provided with a convexity which, when viewed in an axially perpendicular section, at least in portions has a convex shape and, also when viewed in an axially parallel section, at least in portions has a convex shape.

Abstract: A rotor blade is a rotor blade to be attached to a rotor shaft rotatable about an axis, and includes a blade body extending in a radial direction with respect to the axis and having a blade-shaped cross-section orthogonal to the radial direction; a fillet portion provided on a radial outer side of the blade body and having a hollow portion formed therein; a shroud provided on a radial outer side of the fillet portion and extending in a circumferential direction; and a seal fin projecting from the shroud to an outer circumferential side and extending in a direction intersecting the blade body when viewed from the radial direction. A wall thickness on a suction side of the fillet portion is greater than a wall thickness on a pressure side of the fillet portion on a leading edge side of the blade body as demarcated by an intersection portion between the blade body and the seal fin serving as a boundary.

Abstract: A variable guide vane assembly is provided for a turbine defining a core air flowpath. The variable guide vane assembly includes an airfoil band defining a flowpath surface and a cavity. The variable guide vane assembly further includes an airfoil including a first end extending at least partially into the cavity of the airfoil band and an opposite second end, the airfoil extending generally along an axis between the first end and the second end and being moveable generally about the axis relative to the airfoil band. The variable guide vane assembly further includes a sealing element operable to form a seal between the first end of the airfoil and the airfoil band.

Abstract: A fan with an impeller having, in an embodiment, backward-curved blades and having a scroll housing, the flow channel of which is formed by an inner spiral contour of the housing, the flow channel guiding the air conveyed by the impeller towards an outlet wherein the spiral contour with its local pitch angles is adapted to the outlet angle from the impeller.

Abstract: A wind turbine is provided, including a hub, rotor blades, wherein each rotor blade is rotatably supported at or in the hub by a pitch bearing, a pitch control device for changing a pitch angle of the rotor blades, and a measurement system for capturing a sensor signal in or at the pitch bearing and for changing the pitch angle by the pitch control device as a function of the sensor signal to prevent failure of the pitch bearing due to a lack of lubrication, wherein the sensor signal represents a change in vibration, noise and/or temperature in or at the pitch bearing. Due to the fact that the pitch angle can be changed as a function of the sensor signal, lubrication of the pitch bearing is ensured throughout the lifetime of the pitch bearing. Unnecessary pitch movements can be prevented.

Abstract: A method changes a sliding bearing element of a rotor bearing of a wind turbine. The rotor bearing includes inner and outer ring elements, between which the sliding bearing element is arranged. The inner ring element and the outer ring element are rotatable relative to each other. A rotor hub is fastened to the inner ring element or to the outer ring element. The sliding bearing element includes multiple individual sliding bearing pads, each of which are releasably fastened to the inner ring element or outer ring element of the rotor bearing by at least one fastener. When changing the sliding bearing element, the individual sliding bearing pads are removed one after the other and replaced by new sliding bearing pads, wherein during the changing of the individual sliding bearing pads of the sliding bearing element, the inner ring element and the outer ring element are not disassembled.

Abstract: An aircraft engine, has: an upstream stator having upstream stator vanes circumferentially distributed about a central axis; and a downstream stator having downstream stator vanes circumferentially distributed about the central axis, the downstream stator located downstream of the upstream stator relative to an airflow flowing within a core gaspath of the aircraft engine, a number of the upstream stator vanes being different than a number of the downstream stator vanes, the downstream stator vanes including: a first vane made of a first material, a major portion of a leading edge of the first vane circumferentially overlapped by one of the upstream stator vanes, and a second vane made of a second material having a greater stiffness, strength, and/or ductility than that of the first material, a major portion of a leading edge of the second vane exposed via a spacing defined between two of the upstream stator vanes.

Abstract: The present disclosure relates to pitch assemblies and methods for determining one or more pitch references for a pitch control system of a wind turbine. The assembly comprises a wind turbine hub; a pitch bearing including a hub bearing ring configured to be attached to a hub flange and a blade bearing ring configured to be attached to a wind turbine blade; a target configured to be attached to one of the blade bearing ring and the hub; and a sensor configured to be connected to the other of the wind turbine hub and the blade bearing ring, and configured to sense the target such that a position of the target with respect to the sensor can be determined.

Abstract: The present invention is directed to a molten metal pump comprising an elongated pumping chamber tube with a base end and an open top end. A shaft extends into the tube and rotates an impeller therein, the impeller rotates proximate the base end. The tube has a diameter at least 1.1 times the diameter of the impeller. The pumping chamber tube preferably has a length at least three times the height of the impeller. The base end includes an inlet and the top end includes a tangential outlet. Rotation of the impeller draws molten metal into the pumping chamber and creates a rotating equilibrium vortex that rises up the walls of the pumping chamber. The rotating vortex adjacent the top end exists the device via the tangential outlet.