Abstract: A turbine bucket assembly and turbine system are disclosed. The turbine bucket assembly includes a single-lobe joint having an integral platform, the joint having a first axial length; a segmented airfoil having a root segment extending radially outward from the platform and a tip segment coupled to the root segment, the tip segment having a second axial length, which is less than the first axial length; and a turbine wheel defining a receptacle with a geometry corresponding to the single-lobe joint and being coupled to the single-lobe joint. The tip segment includes a tip segment material, the root segment includes a root segment material, and the turbine wheel includes a turbine wheel material, the root segment material and the turbine wheel material having a lower heat resistance and a higher thermal expansion than the tip segment material.

Abstract: A central shaft is oriented in a position that is normal to the surface of the ground and normal to a direction of fluid flow. The central shaft has a plurality of blades emanating from the central shaft, wherein each one of the plurality of blades has an outside edge and an inside edge, the inside edge being attached directly to an outside surface of the central shaft. The outside edge of the blade extends upward curving around the central shaft and the inside edge of the blade extends upward curving around the central shaft. The turn rate of the inside edge of the blades about the central shaft is less than the turn rate of the outside edge of the blades about the central shaft.

Abstract: A blade module and a fan using the same are provided. The blade module includes a rotating shaft and a plurality of blades. Each blade is connected to the rotating shaft and includes a blade body and an airflow guiding portion. The airflow guiding portion is connected to the blade body and has an opening.

Abstract: A flywheel is attached to a shaft of a turbine. As the shaft rotates, the flywheel swings outwards away from the shaft and regulates the angular velocity of the rotating shaft. In an embodiment, there are multiple flywheels attached to the shaft. In another embodiment there is a first flywheel that controls a second flywheel. In another embodiment, the flywheel has adjustable or centrifugal displacement of counterbalanced masses for effective rotational diameter with effective rotational balance. In another embodiment, a small pilot centrifugal displacement flywheel may control a clutch by rotational velocity and may include a hysteresis control. An example of a clutch may limit that degree to which the arms of the flywheel may be extended and/or retracted. In another embodiment, a small pilot centrifugal displacement flywheel controls the hysteresis of a centrifugal flywheel displacement.

Abstract: A number of variations may include a product including a rotor comprising a shaft having a rotation axis, a bearing at least partially surrounding the shaft allowing for rotation of the shaft within the bearing about the rotation axis, and a bearing housing comprising at least one fluid outlet passage constructed and arranged to flow fluid upward from the bearing to a top side of the bearing housing.

Abstract: A power plant includes a structure and a vehicle having at least one wing including a first wing part and a second wing part. The vehicle is arranged to be secured to the structure by at least one tether. The vehicle is arranged to move in a predetermined trajectory by a fluid stream passing the wing. The vehicle includes at least one turbine connected to a nacelle having a generator. At least the first wing part is arranged at a first angle relative to a horizontal center line of the wing. The nacelle is arranged to be attached to a surface of the wing facing the direction in which the first wing part is angled.

Abstract: A first stage turbine nozzle includes a first stage hub portion extending axially along a central axis, a first stage disk portion attached to the first stage hub portion and centered on the central axis, and a plurality of first stage vanes positioned radially around and attached to the first stage disk portion. Each vane extends a vane height H away from the first stage disk portion and each vane has a first end positioned at a diameter D away from the central axis. The first stage turbine nozzle also includes a plurality of first stage throats defined between radially adjacent first stage vanes. Each first stage throat has a throat width W between radially adjacent first stage vanes. The first stage turbine nozzle also includes a coating on a sidewall of each first stage vane.

Abstract: An airfoil assembly for use in a gas turbine engine is disclosed. The airfoil assembly includes a root, a tip shroud, and an airfoil located between the root and tip shroud. The airfoil includes a spar and a heat shield arranged around the spar.

Abstract: A blade assembly including a rotor; a body portion connected to the rotor and having a space therein; and at least one vibration reduction member provided in the space.

Abstract: An axial flow fan improves air capacity and static pressure characteristics, and can ease stress at a leading edge portion of a blade base, even when a shape for noise reduction is adopted. An axial flow fan includes a boss portion and rotor blades. A rotor blade is segmented into a first area extending from the boss portion toward the outer peripheral side, and a second area connected to the first area and extending from the first area to the outermost periphery of the rotor blade. The distribution of a forward sweep angle varies quadratically in the first area, and the maximum forward sweep angle in the first area is not larger than the forward sweep angle in the second area. The distribution of chord-pitch ratio varies in a curved manner from the base as the minimum value in the first area, and is linear in the second area.

Abstract: A system and method for nose cone edge delamination repair is provided. A nose cone may comprise an outer skirt having an aft edge, a flange, and a pin landing. The system and method may comprise trimming the aft edge of the nose cone to form a repaired edge. A first layer of fiberglass may be placed over repaired edge. A second layer of fiber glass may be placed over the first layer and the repaired edge. The first layer and second layer may be trimmed to create a spot face to allow for lower tolerances when installing the nose cone into a gas turbine engine.

Abstract: A rotary wing with a curved outer surface, inlet openings and an edge foil for use in helicopters to improve lift and efficiency, maximizing the gross weight lift and the horizontal flight speed capabilities and minimizing performance penalties and unstable, inefficient operation.

Abstract: A second stage turbine nozzle includes a second stage disk portion having a central axis, and a plurality of second stage vanes positioned radially around and attached to the second stage disk portion. Each second stage vane extends a vane height H away from the second stage disk portion and each second stage vane has a first end positioned at a diameter D away from the central axis. The second stage turbine nozzle also includes a plurality of second stage throats defined between radially adjacent second stage vanes. Each second stage throat has a throat width W between radially adjacent second stage vanes. The second stage turbine nozzle also includes a coating on a sidewall of each second stage vane, wherein a surface roughness of the sidewall is between 125 microinches Ra and 200 microinches Ra.

Abstract: According to an aspect of an exemplary embodiment, there is provided a rotation body of a rotary machine, the rotation body comprising: an impeller comprising a blade; and a shroud that is integrally formed with the impeller and has a cladding stack structure in which a plurality of laser cladding layers are stacked.

Abstract: A cooling fan includes a frame base including a frame wall, a bottom plate and a cover plate for enclosing and defining a containing space. The vane wheel is installed in the containing space and provided for producing a cooling forced airflow when the vane wheel is in a forward rotation status and forming a strong wind area, and producing a dust discharging forced airflow when the vane wheel is in a reverse rotation status. The moving baffle module is rotably installed in the strong wind area, and the frame base includes a dust discharging opening configured to be corresponsive to the periphery of the strong wind area, and the dust discharging forced airflow is affected by the moving baffle module to discharge dust from the dust discharging opening to the outside.

Abstract: A rotor of a vacuum pump has a circular member that is driven rotatably, a cylindrical member joined to an outer circumference of the circular member, and a thread groove pump flow path formed between the cylindrical member and a stator member surrounding an outer circumference of the cylindrical member. The cylindrical member is made of a material having at least a feature of lower thermal expansivity or lower creep rate than that of a material of the circular member. A gap of a second region provided between a non-joint portion of the cylindrical member and the stator member is set to be smaller than a gap of a first region provided between a joint portion of the cylindrical member and the stator member.

Abstract: A turbomachine including at least one blade-row group that is arranged in the main flow path and at least two rows of blades that are adjacent to each other in the main flow direction, each row having a plurality of blades (38, 40), whereby a narrow cross section and a degree of overlap between the blades of the upstream row of blades and the blades of the downstream row of blades vary starting at the center of the main flow path in the direction of at least one main flow limiter.

Abstract: The present invention relates to a vibration generator, an more particularly to a technology in which an actuating shaft protrudes from the opposite ends of a housing such that vibrations generated from the actuating shaft are alternately output in opposite directions of the housing so as to improve vibration efficiency and such that a single vibration generator simultaneously applies the vibrations to a plurality of external objects so as to additionally enhance an economic effect. Furthermore, the present invention relates to a technology in which an actuating shaft protrudes from the opposite ends of a housing, thereby enabling stable installation. In addition, the present invention relates to a technology in which a fluid supply tube is configured to be movable in the axial direction of an actuating shaft so as to prevent breakage of the connected portion of the fluid supply tube, which might otherwise occur during the operation of the vibration generator.

Abstract: A turbine wheel for use in a gas turbine engine having a plurality of blades attached to a rotor disk. Each blade is formed as a composite structure including a number of plies of ceramic-containing material. The blades each include a root to fit within dovetail slots of the rotor disk to couple the blades to the rotor disk.

Abstract: A positioning system, for a boom having right and left boom arms, comprises: a first actuator for moving the right boom arm relative to a support frame; a second actuator for moving the left boom arm relative to a support frame; a first hydraulic link between the first and second actuators; and a hydraulic control device for controlling movement of hydraulic fluid within the first hydraulic link, thereby controlling extension and/or retraction of the first and second actuators.