Abstract: According to an embodiment of the present disclosure, a ceiling fan includes a shaft coupled to a ceiling or a wall surface, a housing cover provided at a central axis thereof with a shaft and receiving a motor assembly and an electronic unit, and a blade coupled to the housing cover. The electronic unit is provided in a multi-stage.

Abstract: The present disclosure provides a rotating propeller design that maintains a high efficiency and reduces noise. The design provides an unloaded tip zone of positive lift starting prior to an end of the tip with negligible, if any, positive lift that is counterintuitive to the purpose of a propeller. The unloaded tip zone decreases the strength of a tip vortex and reduces induced drag. The result is a significant reduction in noise while maintaining substantially high mechanical efficiency, even with an optional increase in RPM to compensate for the reduced lift without requiring a longer propeller. At least one propeller design can break the beta angle from the propeller hub with a different beta angle at a first location from the hub and then also break the beta angle at a second location further from the hub into the unloaded tip zone to form a double break propeller.

Abstract: A turbofan engine has a primary duct, in which there flows a primary flow at a primary pressure and a secondary duct, which radially surrounds the primary duct and in which there flows a secondary flow at a secondary pressure. The primary duct includes at least one compressor configured to compress the primary flow, a turbine driving the compressor in rotation and a combustion chamber designed to receive, at an inlet, the primary air flow compressed by the compressor. The turbomachine further includes a cooling circuit extending between the compressor and the turbine. The cooling circuit has an air flow rate regulating device arranged upstream of the turbine and having at least one valve that is configured to move between an open position and a closed position, located between the compressor and the combustion chamber in the primary duct and the pressure (PS) in the secondary duct.

Abstract: An energy conversion unit for converting wind energy into electrical energy includes at least one rotor with a substantially horizontal axis of rotation, having a plurality of rotor blades extending radially to the axis of rotation, wherein the rotor has a flow direction which corresponds to the axis of rotation, a wall to be arranged next to a traffic route for vehicles which can move on the traffic route in a direction of travel and the movement of which causes an air flow, wherein the wall has a receptacle in which the rotor is arranged, wherein the receptacle has an opening on a side surface of the wall to be directed towards the traffic route, and wherein the axis of rotation of the at least one rotor is oriented substantially perpendicular to the direction of travel.

Abstract: A hoist for lifting at least a portion of a gas engine assembly includes a support member including an upper portion, a lower portion, and a connecting portion extending therebetween. The hoist also includes an elongate member coupled to the lower portion of the support member and extending substantially orthogonally to the lower portion, and at least one bracket slidably engaged with the elongate member and axially translatable along a length of the elongate member. In addition, the hoist includes a plurality of linkage members coupled to the at least one bracket, where each linkage member of the plurality of linkage members is configured to attach to at least a portion of the gas engine assembly.

Abstract: A vortex-induced vibration (VIV) suppression system comprising: a vortex-induced vibration (VIV) suppression device dimensioned to be coupled to a tower of a wind turbine and operable to rotate about a tower of the wind turbine to suppress a vortex-induced vibration; and a drive member coupled to the vortex-induced vibration suppression device and operable to align the vortex-induced vibration suppression device with a nacelle of the wind turbine.

Abstract: A turbine blade includes: a platform; an airfoil portion extending from the platform in a blade height direction and having a pressure surface and a suction surface extending between a leading edge and a trailing edge; a blade root portion disposed on opposite side of the airfoil portion across the platform in the blade height direction and having a bearing surface; and a shank disposed between the platform and the blade root portion. The shank has: a first lateral surface having a first recess portion and disposed on a pressure surface side and along an extension direction of the blade root portion; and a second lateral surface having a second recess portion and disposed on a suction surface side and along the extension direction of the blade root portion.

Abstract: A turbine blade is provided with an airfoil portion having a leading edge, a trailing edge, and a pressure surface and a suction surface which extend between the leading edge and the trailing edge, the airfoil portion internally forming a cooling passage. The cooling passage includes: a first cooling passage located closer to the pressure surface than the suction surface; and a second cooling passage located closer to the suction surface than the pressure surface. The first cooling passage and the second cooling passage are separated by a partition member disposed in the airfoil portion. At least one communication space connecting the first cooling passage and the second cooling passage is formed in the partition member.

Abstract: A rotor blade for a wind power installation, which extends in a longitudinal direction with a profile course from a blade connector to a blade tip, wherein the profile course contains at least one profile, comprising: a suction side and a pressure side, a relative profile thickness of greater than 25%, a profile chord, which extends between a leading edge and a trailing edge of the profile and has a length which defines the profile depth, a mean line which extends at least partially below the profile chord, a convex region which extends on the suction side from the trailing edge, and a convex region which extends on the pressure side from the trailing edge, wherein the convex region on the pressure side defines a rounded transition region of the pressure side to the trailing edge.

Abstract: Accelerators, methods of manufacturing accelerators, and gas turbine engines are provided. For example, an accelerator for a gas turbine engine defines a radial direction and an axial direction and comprises an annular outer wall, an annular inner wall, an annular channel defined between the outer and inner walls, and a plurality of vanes disposed within the channel. The channel has an inlet for ingress of a cooling fluid and an outlet for egress of the cooling fluid. Each vane extends from the outer wall to the inner wall adjacent the outlet, which is angled such that an exit angle of the cooling fluid is nonzero with respect to both the radial and axial directions. The accelerator may be manufactured using an additive manufacturing method. The accelerator outlet may be disposed immediately upstream of a first turbine rotor blade stage of a gas turbine engine to direct the cooling fluid thereto.

Abstract: A neck fan, configured to be worn around a neck of a user, includes: an inner shell, disposed near the neck; an outer shell, connected to the inner shell and disposed opposite to the inner shell and away from the neck, wherein the outer shell and the inner shell cooperatively define a receiving space; a plurality of fan assemblies. Each fan assembly is received in the receiving space and connected to the inner shell and the outer shell. Each of the inner shell and the outer shell defines a plurality of air inlets, each fan assembly corresponds to both the air inlets in the inner shell and the air inlets in the outer shell, each of the plurality of fan assemblies is configured to intake air from an outside of the neck fan into the receiving space through the corresponding plurality of air inlets.

Abstract: A nozzle includes an endwall connected to an airfoil at one of a tip and root of the airfoil. The endwall includes a first and second side slash faces at respective circumferential edges thereof. The endwall also includes an inner surface extending between the first and second side slash faces. The inner surface includes a first planar surface portion adjacent to the first side slash face, a second planar surface portion adjacent to the second side slash face, and an arcuate surface portion extending between the first and second planar surface portions. The planar surface portions reduce a chute height by reducing hot gas path curvature locally along the side slash faces, which reduces working fluid ingestion between endwalls of the adjacent nozzles. The planar surface portions can be applied to an inner and/or an outer endwall of a nozzle.

Abstract: A fan includes a motor, a rotatable hub coupled to the motor, and at least one fan blade. The at least one fan blade includes a first end coupled to the rotatable hub, a second end, a leading edge, a trailing edge, a passage extending from the first end to the second end, and a winglet attached to the second end. At least one flexible strap extends through the passage of the at least one fan blade. The flexible strap is coupled at a first end to the rotatable hub and coupled at a second end to the winglet, such as to an inner portion thereof within the passage.

Abstract: A variable pitch fan assembly includes a plurality of rotating trunnion assemblies, a plurality of counterweight assemblies, a first unison ring gear engaged with the trunnion assemblies, and a second unison ring member that restricts out of synch movement of the counterweights relative to each other.

Abstract: Disclosed herein is a seal comprising an annular ring comprising: an outer diameter surface having an outer diameter, an inner diameter surface, a first height measured from the outer diameter surface to the inner diameter surface, wherein a first ratio of the outer diameter to the first height is greater than 10:1; and a cross-sectional shape comprising: a central beam extending from an inner end to an outer end, the central beam including a central axis that defines an angle with a neutral axis of the cross-sectional shape, the angle being between 5 degrees and 25 degrees; a first flange extending axially from the inner end of the central beam in a first axial direction; and a second flange extending axially from the outer end of the central beam in a second axial direction, the second axial direction being opposite the first axial direction.

Abstract: A method for cooling a high-temperature radial gas turbine engine increases turbine thermal efficiency and/or extends turbine operational lifetime. A bleed flow path enables cooling air to flow from a compressor outlet and along surfaces of the gas turbine rotors. The amount of cooling increases in proportion to a bleed fraction, which is defined as the ratio of mass flow in the bleed flow path to total mass flow in the compressor outlet. The heated air in the bleed flow path is mixed with the main mass flow into the turbine engine, so as to restore mass flow into the turbine, while maintaining a high turbine operating temperature and thermal efficiency. The thermal efficiency of a recuperator also increases in proportion to the bleed fraction.

Abstract: A vane for a gas turbine engine, the vane including: an inner diameter platform and an outer diameter platform and an airfoil that extends between the inner diameter platform and the outer diameter platform, the airfoil having a leading edge, a trailing edge, a pressure side and a suction side, the inner diameter platform has a suction side mate face and a pressure side mate face, wherein the suction side mate face and the pressure side mate face of the inner diameter platform have an axial feather seal slot and a radial seal slot, the axial feather seal slot includes a leading edge portion that extends from the radial seal slot towards a leading edge of the inner diameter platform and a trailing edge portion that extends from the radial seal slot towards a trailing edge of the inner diameter platform, and a chamfer extends between the radial seal slot and the trailing edge portion of the axial feather seal slot.

Abstract: A turbine shroud assembly includes a carrier assembly, a blade track segment, a retainer, and a clip shim. The carrier assembly is arranged circumferentially at least partway around an axis. The blade track segment is supported by the carrier assembly to locate the blade track segment radially outward of the axis and define a portion of a gas path of the turbine shroud assembly. The retainer extends into the carrier assembly and the blade track segment. The clip shim is located between the carrier assembly and the blade track and configured to urge the blade track segment axially toward the carrier assembly.

Abstract: A gas turbine engine for an aircraft configured with an engine core that has a turbine, a compressor, and a core shaft connecting the turbine to the compressor. A fan located upstream of the engine core, that has a plurality of fan blades. A gearbox arranged to receive an input from the core shaft and to output to the fan so as to drive the fan at a lower rotational speed than the core shaft. The gearbox being an epicyclic gearbox having a sun gear, a plurality of planet gears, a ring gear, and a planet carrier on which the planet gears are mounted. The gearbox having an overall gear mesh stiffness, and wherein the overall gear mesh stiffness of the gearbox is greater than or equal to 1.05×109 N/m and less than or equal to 8.0×109 N/m.

Abstract: A method for manufacturing a structural component of a blade segment for a rotor blade includes providing a mold of the structural component having an outer wall that defines an outer surface of the structural component. The method also includes laying up one or more fiber layers in the mold so as to at least partially cover the outer wall. As such, the fiber layer(s) form the outer surface of the structural component. Further, the method includes providing one or more metal mesh layers having one or more ends. Moreover, the method includes providing a cover material to the end(s) of the metal mesh layer(s). In addition, the method includes placing the metal mesh layer(s) with the covered end(s) atop the fiber layer(s). Thus, the method includes infusing the fiber layer(s) and the metal mesh layer(s) together via a resin material so as to form the structural component.