Abstract: An apparatus for mitigating vortex-shedding vibrations or stall-induced vibrations on one or more rotor blades of a wind turbine during standstill includes at least one positioning element located between a blade tip section and a blade root section thereof. The positioning element is adapted for wrapping around at least a portion of the rotor blade. The apparatus also includes at least one airflow modifying element coupled to the positioning element and defining a height relative to a surface of the rotor blade. Additionally, the apparatus includes at least one securing element operably coupled to the positioning element for temporarily securing the airflow modifying element to the rotor blade.

Abstract: A method and an apparatus for dynamically determining a yaw control precision. The method comprises: during a predetermined time period, collecting a plurality of wind speed data and a plurality of wind direction data, and processing the collected plurality of wind speed data and plurality of wind direction data; on the basis of the processed wind speed data and wind direction data, establishing a model of the corresponding relationship between wind speed, wind direction angle change, yaw control precision, yaw fatigue, and power loss; and, on the basis of the current wind speed data, wind direction data, predetermined yaw fatigue range, and predetermined power loss range, by means of the corresponding relationship model, determining the yaw control precision corresponding to the current wind speed and current wind direction angle change.

Abstract: A rotating airfoil assembly including a rotation axis and a plurality of rotating airfoils configured to rotate about the rotation axis. Each rotating airfoil of the rotating airfoils includes a leading edge, a trailing edge, a suction surface between the leading edge and the trailing edge, and a pressure surface between the leading edge and the trailing edge. The suction surface and the pressure surface are positioned on opposite sides of the rotating airfoil such that, when airflows over the suction surface and the pressure surface of the rotating airfoil as the rotating airfoil rotates about the rotation axis, the rotating airfoil generates lift. At least one opening is located on one of the suction surface or the pressure surface. The at least one opening is configured to eject air or to draw air into the opening.

Abstract: A variable vane includes a first vane portion and a second vane portion adjacent the first vane portion. The second vane portion includes a trunnion projecting outward from a radial end of the second vane portion. The second vane portion is configured to rotate about a trunnion axis of the trunnion from a first rotational position to a second rotational position.

Abstract: Turbomachines having one or more flow guiding features designed to increase the performance of the turbomachine. In some examples, flow guiding features are designed and configured to bias a circumferential pressure distribution at a diffuser inlet toward circumferential uniformity, otherwise account for such low-frequency spatial pressure variations, increase the controllability of spatial flow field variations, or modifying flow field variations, etc. In some examples, a diffuser having a row of vanes that include a plurality of first vanes and at least one second vane having a different characteristic than the first vanes are disclosed. In some examples, diffusers have an aperiodic section including one or more biased passages for biasing a flow field. And in some examples, turbomachines have flowwise elongate recesses in one or both of a hub and shroud surface.

Abstract: A flow control system, such as a thruster, includes an annular rotor within an annular housing. The annular rotor rotates about a central axis relative to the annular housing. The flow control system includes rotor blades with respective bases that are coupled to the annular rotor, and with respective tips directed toward the central axis. The flow control system includes a first actuator that rotates the annular rotor about the central axis relative to the annular housing, thus also rotating the rotor blades about the central axis relative to the annular housing. The flow control system includes a second actuator that rotates the rotor blades relative to the annular rotor. Actuation of the second actuator rotates a rotor blade about a rotor blade axis that extends from a base of the rotor blade toward the central axis.

Abstract: A rotor bearing of a wind turbine, in particular a rotor bearing having an improved and simplified axial introduction of force into the inner ring. It is specified for this purpose that the inner ring of the rolling bearing has a greater axial length with respect to the axial length of the outer ring of the rolling bearing by a section of the inner ring that corresponds to the axial length of the outer ring and has the length being adjoined by additional sections, wherein the axial lengths of these sections differ in size.

Abstract: A fluid power generator can enhance power generation efficiency by efficiently using the drag force of wind without increasing the size of blades, and includes: an ascending air current-forming body provided at a rotary shaft; a plurality of spiral blades which are spirally formed along the outer circumferential surface of the ascending air current-forming body; and a generator which generates electricity by rotation of the ascending air current-forming body.

Abstract: A machine has: an outer member; an inner member mounted for rotation about an axis relative to the outer member; and a seal system. The seal system has: a seal housing mounted to the outer member; one or more seal rings held by the seal housing and having an inner diameter surface; and a seal runner mounted to the inner member and having a first outer diameter surface portion contacting or facing the inner diameter surface of the one or more seal rings. The seal runner has a circumferential array of mounting features. One or more weights are mounted to one or more of the mounting features.

Abstract: A vertical axis wind turbine blade that includes an elongated wing and at least one airflow blocker in the elongated wing. The elongated wing has a first surface and a second surface which meet at a leading edge and a trailing edge, where the leading edge includes a convex curve. The elongated wing also includes a leading edge slat between the first surface and the second surface; and at least one hollow channel extending from the leading edge slat to the first surface. The hollow channel is curved, and the airflow blocker is configured to block the hollow channel.

Abstract: An impulse turbine of a turbine device includes a cylindrical body having an axial hole, and a blade unit arranged to surround the periphery of the body. The blade unit includes a cylindrical base arranged to surround the periphery of the body, and a plurality of unit blades radially arranged in a line along the periphery of the base. Each of the unit blades includes an outlet that discharges fluid, injected onto the unit blade, in a direction different from the fluid spray direction, but does not discharge the fluid toward the other unit blades.

Abstract: A pump head includes a casing including a blood inlet configured to receive a flow of a blood and a blood outlet configured to allow the blood to flow out of the casing. The pump head also includes a shaft disposed in the casing. The pump head also includes a magnetic structure mounted onto the shaft. The pump head further includes an impeller having an open structure and mounted to an exterior surface of the magnetic structure through an opening provided at the open structure.

Abstract: A turbine rotor wheel for an aircraft turbomachine includes a rotor disk, an annular shroud extending around the disk, and blades arranged between the disk and the shroud. The root of each of the blades has two tabs configured for attachment to the disk. The tabs are arranged upstream and downstream, respectively, of a wall of the disk, relative to the axis. The tab arranged upstream is engaged in a first recess of the disk and configured to cooperate by abutment with a peripheral edge of the first recess. The tab arranged downstream is engaged in a second recess of the disk and is configured to cooperate by abutment with a peripheral edge of the second recess.

Abstract: A gas turbine engine assembly includes, among other things, a fan section including a fan, the fan including a plurality of fan blades, a diameter of the fan having a dimension D that is based on a dimension of the fan blades, a turbine section including a high pressure turbine and a low pressure turbine, the low pressure turbine driving the fan, a nacelle including an inlet portion forward of the fan, a length of the inlet portion having a dimension L, and a dimensional relationship of L/D between 0.30 and 0.40.

Abstract: A gas turbine engine assembly may include, among other things, a fan section including a fan, the fan including a plurality of fan blades, a diameter of the fan having a dimension D, each fan blade having a leading edge, and a forward most portion on the leading edges of the fan blades in a first reference plane, a geared architecture, a turbine section including a high pressure turbine and a low pressure turbine, the low pressure turbine driving the fan through the geared architecture, a nacelle surrounding the fan, the nacelle including an inlet portion forward of the fan, a forward edge on the inlet portion in a second reference plane, and a length of the inlet portion having a dimension L between the first reference plane and the second reference plane. A dimensional relationship of L/D may be between 0.30 and 0.40.

Abstract: Platform for an aircraft turbo machine fan rotor, the platform being configured to be secured to a fan disc between two adjacent fan blades. The platform further including a longitudinal wall defining an aerodynamic external face. The wall includes a honeycomb structure interposed between two skins which are respectively an internal skin and an external skin, with the external skin defining the aerodynamic external face.

Abstract: An adjusting drive for adjusting the rotational position of a large rolling bearing that comprises two bearing rings that can be rotated relative to each other, having an actuator for rotating the two bearing rings relative to each other. According to the invention, the actuating drive has a ring channel cylinder, which is formed in or on one of the bearing rings of the large rolling bearing, and at least one piston, which is received in the ring channel cylinder in a movable manner and is drivingly connected to the other bearing ring of the two bearing rings.

Abstract: A rotor assembly for a gas turbine engine includes a rotatable hub that has a main body and an array of annular flanges that extend about an outer periphery of the main body to define an array of annular channels. An array of airfoils are circumferentially distributed about the outer periphery. Each one of the airfoils includes an airfoil section extending from a root section received in the annular channels. Retention pins extend through the root section of a respective one of the airfoils and through the array of annular flanges to mechanically attach each root section to the hub.

Abstract: A nozzle ring for a radial turbine includes a disc-shaped main body having a central opening for passing a shaft therethrough. Additionally, the nozzle ring includes guide vanes disposed circumferentially in a radially outer portion on a first surface of the main body. Two or more bores are provided in a radially inner portion of the main body. Further, a groove is provided in the first surface of the main body, the groove connecting at least two of the two or more bores.

Abstract: A turbine operable to convey a flow of exhaust gas along a central axis includes a strut having a flow portion positioned within the flow of exhaust gas and a strut cover having a length and positioned to surround the flow portion of the strut, the strut cover including a leading-edge portion, a mid-chord portion, and a trailing-edge portion. The mid-chord portion has a uniform cross-section, and the trailing-edge portion has a trailing-edge center positioned such that the mid-chord portion and the trailing-edge portion define a master chord plane. The leading-edge portion defines a leading-edge nose, and the leading-edge portion is twisted with respect to the master chord plane and the leading-edge nose along the length defines a curve that is not coincident with the master chord plane.