Abstract: A rotor has formed therein a groove with which a moving blade including a dovetail portion and a platform portion connecting the dovetail portion and a blade portion engages. The groove opens in a surface intersecting the axis of rotation of the rotor, and includes a contacting portion extending obliquely with respect to the axis of rotation and coming into contact with the dovetail portion, a bottom portion of an end portion on the radially inner side of the rotor, a joining portion between the contacting portion and the bottom portion, a platform facing portion facing the platform portion, and a chamfered portion formed on an end surface in the groove-extending direction. The chamfered dimension of the joining portion is greater on the side with an acute angle between the groove and the end surface than on the side with an obtuse angle between the groove and the end surface.

Abstract: Gas turbine engine (GTE) airfoils, such as rotor and turbofan blades, having multimodal thickness distributions include an airfoil tip, and an airfoil root opposite the airfoil tip in a spanwise direction. The GTE airfoil has a first, second and third locally-thickened region, with the first locally-thickened region defined at the airfoil root. A maximum thickness of each chord between the airfoil root and the airfoil tip transitions toward the leading edge between the first locally-thickened region and the second locally-thickened region, and the third locally-thickened region extends in the spanwise direction. A chord line that extends through the third locally-thickened region contains a first local thickness maxima and a second local thickness maxima interspersed with at least two local thickness minima, and the first local thickness maxima is defined by the third locally-thickened region and is greater than the second local thickness maxima.

Abstract: A fuel cell centrifugal compressor includes: an impeller including a hub and blades; and a shroud. A smaller one of angles formed by each blade and a meridian surface is a blade angle. An absolute value of the blade angle on a hub-side of the blade is local minimum between hub-side front and rear edges of the blade. An absolute value of the blade angle on a shroud-side of the blade is local minimum between shroud-side front and rear edges of the blade. The hub-side of the blade is constantly less than or equal to the shroud-side of the blade in absolute value of the blade angle between the hub-side front and rear edges. The shroud-side rear edge is less than the shroud-side front edge in absolute value of the blade angle. The hub-side rear edge is greater than the hub-side front edge in absolute value of the blade angle.

Abstract: The invention regards a structural assembly for a gas turbine engine which includes a bearing with a statically arranged outer ring and a rotatably arranged inner ring, the bearing outer ring including a radially outer surface. The assembly further includes a housing structure supporting the statically arranged outer ring. It is provided that the housing structure forms a housing ring against which the radially outer surface of the bearing outer ring lies and which supports the bearing outer ring radially outwards.

Abstract: A wind power plant comprising a first structural element, a second structural element, a bearing assembly by means of which the first structural element is rotatably mounted on the second structural element, a first flange connection between the first structural element and the bearing assembly, a second flange connection between the second structural element and the bearing assembly, and at least one drive, held by a support structure for rotating the first structural element relative to the second structural element. The support structure is formed as a plate and is arranged at one of the flange connections.

Abstract: Pumps and fluid-handling devices for modifying at least one property of a fluid and related method comprise a compensation assembly including at least one biasing element to enable a hydraulic insert to move within a housing.

Abstract: A first aspect of the invention provides a method of testing a yaw system (200) of a wind turbine, the wind turbine comprising a rotor; the yaw system (200) comprising a yaw gear (202) coupled to the rotor so that rotation of the yaw gear (202) causes yaw rotation of the rotor, and first and second sub-systems (204a, 204b), the first sub-system (204a) comprising a first pinion gear (206a) and a first drive motor (208a) coupled to the yaw gear (202) by the first pinion gear (206a), the second sub-system (204b) comprising a second pinion gear (206b) and a second drive motor (208b) coupled to the yaw gear (202) by the second pinion gear (206b).

Abstract: Lubricant pump systems and associated methods for aircraft engines are provided. The method includes receiving an input torque, dividing the input torque between a first load path receiving a first portion of the input torque, and a second load path receiving a second portion of the input torque. A first lubricant pump of the aircraft engine is driven via the first load path using the first portion of the input torque. A second lubricant pump of the aircraft engine is driven via the second load path using the second portion of the input torque. When a malfunction of the second lubricant pump occurs, the method includes ceasing to drive the first lubricant pump and the second lubricant pump using the input torque.

Abstract: The invention relates to a method and a wind turbine system reducing, preventing or mitigating vibrations due to wind induced vibrations. The wind turbine system includes a wind turbine tower 102, a sensor arrangement 304 for sensing vibrations of the wind turbine tower, a nacelle 104 mounted to the wind turbine tower via a yaw bearing 310 and a control system 306 for controlling yawing of the nacelle relative to the wind turbine tower. The system is adapted for sensing 402 a vibration of the wind turbine tower using the sensor arrangement, providing 404 an input for the control system in response to the vibration of the wind turbine tower as sensed by the sensor arrangement, and providing 406 an output by the control system based on the input, and yawing 408 the wind turbine nacelle based on the output from the control system, and hereby reducing wind induced vibrations of the tower and nacelle, particularly vortex induced vibrations and/or vibrations due to galloping.

Abstract: Provided is a water pump which may be easily manufactured and a manufacturing method thereof, the water pump including: a motor housing having a concave container shape; a lower casing including a first side wall protruding downward for a lower end of the first side wall to be in contact with an upper end of the motor housing; and an upper casing fitted to the outside of the lower casing, and including a second side wall protruding downward for a lower end of the second side wall to be in contact with the upper end of the motor housing, wherein the upper end of the motor housing, the lower end of the first side wall, and the lower end of the second side wall are simultaneously fusion-coupled with one another.

Abstract: A centrifugal fan is disclosed and includes a housing, a fan wheel, a first throat portion and a second throat portion. The housing includes a lower cover connected to an upper cover through a peripheral wall to form an accommodation space and an outlet. The upper cover includes an inlet communicated with the outlet. The fan wheel is disposed on the lower cover and accommodated in the accommodation space. The fan wheel is rotated along a rotation direction. The first throat portion is disposed adjacent to a lateral end of the outlet and protrudes from the peripheral wall toward the accommodation space. The second throat portion is disposed adjacent to another lateral end of the outlet, and protrudes from the peripheral wall toward the accommodation space. When the fan wheel is rotated along the rotational direction, an airflow is guided from the first throat portion to the second throat portion.

Abstract: A variable pitch bladed disc including a plurality of blades, each being of variable pitch about a blade axis of rotation and having a root, the plurality of blades including at least one first blade and at least one second blade, a plurality of rotor connecting shafts, each shaft having a root and a tip, the root of each blade being mounted on the tip of a corresponding rotor connecting shaft via a pivot so as to allow each blade to be rotated about the blade axis of rotation, the first blade having a first rotation axis inclination such that the rotation axis thereof is inclined in a fixed manner with respect to a radial axis passing through the root of the corresponding shaft, and the second blade has a second rotation axis inclination different from the first rotation axis inclination.

Abstract: A root assembly of a wind turbine blade for a wind turbine is provided. Also provided is a wind turbine blade including the root assembly and a wind turbine including the wind turbine blade.

Abstract: An exemplary rotorcraft lockout system includes a main rotor lockout comprising a base operable to be attached to a bottom surface of a fuselage and a first and a second tension arm operable to be connected to the base and a main rotor hub, and a tail rotor lockout including a clamp operable to connect to a horizontal stabilizer, a rotor arm connector operable to connect to a tail rotor hub, and a tail rotor tension arm operable to interconnect the clamp and the rotor arm connector in tension.

Abstract: A fan module comprises a frame, a wire-stopping structure, an impeller and a circuit board. The frame includes a frame wall, a base, a plurality of static blades and a connector. A wire groove formed on an outside of the frame wall to accommodate a wire. The static blades are radially connected to the base and the frame wall. The connector is formed on the outside of the frame wall and extended from one end of the wire groove to the base along one of the static blades. The connector includes a plurality of pins. The wire-stopping board is fixed to the frame wall to cover the wire groove. The impeller is disposed in the frame. The circuit board is disposed in the frame and located on the base. The circuit board includes a plurality of pin holes, and the pin holes are electrically connected to the pins.

Abstract: A fan and an electronic device are provided. The fan includes a hub, an outer frame surrounding the hub, and a plurality of blades connected between the hub and the outer frame. The outer frame includes a first side facing an air inlet of the fan, a second side facing an air outlet of the fan, and an inner wall between the first side and the second side. Each of the plurality of blades includes a first end connected to the hub and a second end connected to the outer frame. The second end includes a first region and a second region, the second region is connected to the inner wall. The first region extends from the second region and is disposed above the first side. A first notch is defined among the first regions of two adjacent blades and the first side.

Abstract: Apparatuses and systems are provided herein for unducted propulsion systems. The system includes a forward housing for high efficiency for high subsonic sustained flight. A plurality of blades are affixed to the forward housing, wherein the forward housing defines a flowpath curve extending from the forward-most end of the forward housing through the axial extent of a forward blade root. The flowpath curve is described by an axial direction parallel to an axis of rotation and a radius from the axis of rotation. The flowpath curve includes a first point having a first radius where the radius reaches a maximum forward of the forward blade root and a second point aft of the first point having a second radius where the radius stops decreasing. The ratio of the first radius to the second radius is greater than or equal to 1.029.

Abstract: A convertible ducted fan engine having a shroud, a drive shaft connected to a mechanical fan, and a rotational drive motor configured to rotate the mechanical fan. An embodiment includes a linear drive motor configured to translate the drive shaft and mechanical fan in a direction parallel to a longitudinal axis of the shroud. The convertible ducted fan engine includes a fluid-propulsion configuration in which the mechanical fan rotates freely with respect to the shroud to produce thrust through fluid flow, and a drive-wheel configuration in which the shroud rotates about the rotational axis.

Abstract: A wind turbine includes a nacelle which houses components including a generator connected to a rotor. The nacelle includes a cover and a skeleton, the skeleton including a plurality of connected elongated skeleton members. The skeleton members include a first skeleton member, a second skeleton member non-parallel to the first skeleton member, and a bolt extending in parallel with the second skeleton member for connecting the second skeleton member and the first skeleton member. Also, a method is presented for removing a component housed in a nacelle of a wind turbine, including disconnecting a second skeleton member from first skeleton members, removing the second skeleton member from a path of removal of the component, and removing the component along the path.

Abstract: A rotor bearing for bearing a rotor hub on a nacelle housing of a nacelle for a wind turbine has at least one inner ring element and at least one outer ring element, wherein at least one sliding bearing element is arranged between the inner ring element and the outer ring element, which sliding bearing element is fastened to the inner ring element or to the outer ring element. On the sliding bearing element, a sliding surface is formed, which cooperates with a counterface, which is coupled with that ring element, to which the sliding bearing element is not fastened. The counterface is designed to be resilient.