Abstract: A bladeless fan assembly for creating an air current includes a nozzle mounted on a base. The nozzle comprises an interior passage and a mouth for receiving the air flow from the interior passage and through which the air flow is emitted from the fan assembly. The nozzle defines an opening through which air from outside the fan assembly is drawn by the air flow emitted from the mouth. The nozzle is detachable from the base, which is preferably sized to be accommodated within the opening of the nozzle for transportation.

Abstract: A centrifugal blower including a hollow housing and an impeller having a plurality of blades disposed in the hollow housing, wherein the impeller causes a fluid received in a fluid inlet of the hollow housing to flow in a radially outward direction to a fluid outlet of the hollow housing. A guide device for directing the flow of the fluid in the blower is disposed in the fluid inlet of the hollow housing, the guide device including a shroud configured to militate against turbulence, noise, a recirculation of flow of the fluid at the fluid inlet, and interference between the guide device and balance weights of the blower during an assembly of the blower.

Abstract: A turbine blade for a gas turbine engine with an airfoil portion defined by a perimeter wall surrounding at least one enclosure, the perimeter wall having a plurality of cooling holes defined therethrough and providing fluid communication between the at least one enclosure and a gaspath of the gas turbine engine. The plurality of cooling holes includes at least one row of holes selected from the group consisting of a first row, a second row, a third row and a fourth row, with the first, second, third and fourth rows of holes respectively including the holes numbered PA-1 to PA-10, PB-1 to PB-3, HA-1 to HA-9, and SA-1 to SA-8 located such that a central axis thereof extends through the respective point 1 and point 2 having a nominal location in accordance with the X, Y, Z Cartesian coordinate values set forth in Table 3.

Abstract: A mill that reacts to fluid flow to create energy includes a vertically oriented hub and an arm attaching to and rotating with the hub in a horizontal plane. A plate is attached to the arm, and a vane cooperates with the plate. The vane includes a curved suction side, a planar pressure side, a leading edge, and a trailing edge. Within any 90 degree rotation of the arm, the vane rotates relative to the arm no more than 45 degrees.

Abstract: A ram air fan inner housing for a ram air fan assembly comprises a center body housing, an end cup attached to the center body housing, and a perforated cone. The perforated cone is attached to the center body housing and the end cup such that the perforated cone extends away from the center body housing and radially inward toward an axis of the inner housing.

Abstract: The present invention relates to a cooled turbine blade for a gas-turbine engine having at least one cooling duct (14) extending radially, relative to a rotary axis of the gas-turbine engine, inside the airfoil and air-supply ducts (12) issuing into said cooling duct, characterized in that the cooling duct (14) extends into the blade root (6) in order to generate close to the wall a cooling airflow moved at high circumferential velocity and radially in helical form and that in the area of the blade root (6) at least one nozzle-shaped air-supply duct (12) issues into the cooling duct (14) tangentially or with a tangential velocity component.

Abstract: A rotary blood pump includes a casing defining a pumping chamber. The pumping chamber has a blood inlet and a tangential blood outlet. One or more motor stators are provided outside of the pumping chamber. A rotatable impeller is within the pumping chamber and is adapted to cause blood entering the pumping chamber to move to the blood outlet. The impeller has one or more magnetic regions. The impeller is radially constrained in rotation by magnetic coupling to one or more motor stators and is axially constrained in rotation by one or more hydrodynamic thrust bearing surfaces on the impeller.

Abstract: Embodiments of a gas turbine engine are provided, as are embodiments of an annular bearing support damper and embodiments of a method for manufacturing an annular bearing support damper. In one embodiment, the gas turbine engine includes engine housing and a rotor assembly disposed within the engine housing. A rotor bearing supports the rotor assembly within the engine housing, and an annular bearing support damper is positioned between the rotor bearing and the engine housing. The support damper includes an annular housing assembly having a damping fluid annulus. An array of circumferentially-spaced damper pistons is movably coupled to the annular housing assembly and fluidly communicates with the damping fluid annulus. The damper pistons are fixedly coupled to the rotor bearing and moves in conjunction therewith to force the flow of damping fluid around the annulus during engine operation to reduce the transmissions of vibrations to the engine housing.

Abstract: Provided is a propeller fan including a hub having an oval shape in an axial direction, a plurality of wings that extend from the hub, and at least one reinforcement rib that extends from the hub and is formed closer to a leading edge of each of the plurality of wings. Through this configuration, the propeller fan has blowing efficiency and stiffness, and the weight and material cost of the propeller fan can be reduced.

Abstract: A rotor blade arrangement (20), especially for a gas turbine, which can be fastened on a blade carrier (19) and includes in each case a blade aerofoil element (10) and a platform element (14), wherein the platform elements (14) of a blade row form a continuous inner shroud. With such a blade arrangement, a mechanical decoupling, which extends the service life, is achieved by the blade aerofoil element (10) and the platform element (14) being formed as separate elements and by being able to be fastened in each case separately on the blade carrier (19).

Abstract: A support ring for a row of vanes in an engine section of a gas turbine engine includes an annular main body portion to which a row of vanes is affixed for providing structural support for the vanes in the engine section, and an aft hook extending from an aft side of the main body portion with reference to a direction of air flow through the engine section. The aft hook is coupled to an outer engine casing for structurally supporting the support ring in the engine section. The support ring does not include a forward hook having a flange that extends axially from a forward or aft side of the forward hook with reference to the direction of air flow through the engine section.

Abstract: Wind turbine systems and methods are provided. The wind turbine system includes a plurality of coaxial, counter-rotating turbine assemblies. First and second shroud assemblies define a generally spherical volume containing the first and second turbine assemblies. The first and second shroud assemblies each include a shroud member that can selectively shield or expose portions of the respective turbine assemblies to the wind by changing the rotational position of the shroud members about the system axis. The turbine assemblies are interconnected to a generator for the production of electrical power.

Abstract: A coaxial dual-rotor model helicopter system includes a power control mechanism, a transmission mechanism, a control mechanism and a rotor mechanism. The rotor mechanism includes an upper rotor and a lower rotor coaxially installed on an upper side and a lower side of a main shaft and controlled by an inner shaft and an outer shaft for rotating. The control mechanism includes a Bell self-balance mechanism to control the upper rotor and a Bell-Hiller control structure to control the lower rotor. The power control mechanism controls the rotor mechanism through the transmission mechanism and the control mechanism. The present invention achieves balance effect through the upper rotor by employing the Bell self-balance mechanism that has a great stability to provide automatic control. The lower rotor aims to control direction and employs the Bell-Hiller control structure that has a high maneuverability to perform active control.

Abstract: A ram air fan bearing housing for a ram air fan assembly includes a bearing section, a disk section, and radial support ribs. The disk section is at one end of the bearing section for connecting the bearing section to the ram air fan assembly. The disk section includes an outer ring with a circumferential support rib; and a disk wall connecting the outer ring to the bearing section. The disk wall includes arcuate cooling slots defined by edges, including an arcuate edge having an arc center at an axis of the bearing housing and positioned adjacent to and radially inward from the circumferential support rib. The radial support ribs extend axially along most of the length of the bearing section and extend radially along the disk wall to the circumferential support rib. The radial support ribs and the cooling slots alternate about the axis of the bearing housing.

Abstract: A damper pin for a turbine bucket includes an elongated main body portion having a first substantially uniform cross-sectional shape and axially-aligned, leading and trailing end portions having a second relatively smaller cross-sectional shape at opposite ends of the main body portion. A seal element is provided on one or both of the opposite leading and trailing end portions projecting radially outwardly beyond the main body portion.

Abstract: A serpentine coolant flow path is formed by inner walls in a cavity between pressure and suction side walls of a turbine airfoil, the cavity partitioned by one or more transverse partitions into a plurality of continuous serpentine cooling flow streams each having a respective coolant inlet.

Abstract: A turbomachine includes a housing, and at least one turbine vane arranged within the housing. The at least one turbine vane includes a platform portion operatively connected to the airfoil portion. A cooling cavity is formed in the platform portion. The cooling cavity includes a first wall, a second wall arranged opposite the first wall, a third wall linking the first and second walls, and a fourth wall linking the first and second walls and positioned opposite the third wall. An impingement cooling plate extends into the cooling cavity and defines an inner cavity portion and an outer cavity portion. The impingement cooling plate including at least one impingement cooling passage that is configured and disposed to guide an impingement cooling flow onto at least one of the first, second, third and fourth walls of the cooling cavity.

Abstract: Fluid-powered devices are detailed. The devices may be utilized as motors or pumps, for example, and are capable to switching dynamically between these functions. They additionally may use surface-area, rather than solely pressure, differentials to produce rotary motion.

Abstract: An abnormal vibration detection unit which is capable of stopping a wind turbine generator when excessive vibration is detected. The vibration detection unit has first and second acceleration detectors, a calculation device, a filtering relay, and a safety system which performs an emergency stop of the wind turbine generator in accordance with an output terminal of the filtering relay. The filtering relay has a filter circuit to extract a frequency component from the second analog output signal. The calculation device generates a predicted value of the output signal of the filter circuit part, and detects a failure of the first and second acceleration detectors or the filter circuit part by comparing the predicted value of the output signal of the filter circuit part with a measured value of the output signal of the filter circuit part received from the filtering relay.

Abstract: The invention provides a method for preparing a pre-form comprising at least two layers of fiber tows, these layers being at least partly fixed by a resin. The method comprising steps of providing a work surface, and alternating distribution of layers of resin and layers of fiber tows.