Abstract: A portable air displacement system for introducing or removing air from a zone has a cylindrical fan housing with an exhaust aperture located on a housing side wall of a housing anterior end. The fan housing has a raised dome with a primary directional intake nozzle located on a raised dome posterior end. The raised dome has a plurality of secondary intake slots located around an arc on a dome anterior side, a dome first side and a dome second side. The system has a centrifugal fan located in the housing cavity connected to a power supply and a power switch. The system has a positioning platform with a first panel and a second panel pivotally attached to housing posterior end for clasping a planar object on either side.

Abstract: A system, in certain embodiments, includes a centrifugal compressor diffuser including a flow path having a first surface and a second surface defining opposite axial sides of the flow path. The centrifugal compressor diffuser also includes multiple vanes extending from the first surface to the second surface of the flow path. A first profile of each vane varies along an axial direction. The centrifugal compressor diffuser further includes multiple vanelets extending from the first surface toward the second surface in the axial direction. A first axial extent of each vanelet is less than a second axial extent of the flow path. In addition, a second profile of each vanelet varies along the axial direction and/or the vanelets form a non-periodic pattern around a circumference of the flow path.

Abstract: A fluidic torque transfer device is configured such that the attachment angle of a turbine blade at a fluid outlet of a turbine runner is smaller than the attachment angle of the turbine blade at a fluid inlet of the turbine runner. Furthermore, the turbine runner is structured so that a cross-sectional area St of a turbine flow path defined by the turbine shell, adjacent turbine blades, and the turbine core, which is perpendicular to a centerline of the turbine flow path, satisfies |St?Sref|/Sref?0.2, where a reference area Sref is an average of maximum and minimum values of a cross-sectional area of a pump flow path defined by the pump shell, adjacent pump blades, and the pump core of the pump impeller, which is perpendicular to a centerline of the pump flow path.

Abstract: A compressor is disclosed having a shaft seal assembly and system that allows a high-pressure compressor to settle-out at a lower pressure level during shutdown. The seal assembly may be disposed about a portion of the shaft and define a blow-down seal chamber, the seal assembly including one or more gas seals in fluid communication with the blow-down seal chamber. A blow-down line is communicably coupled to the blow-down seal chamber to reference the blow-down seal chamber to a low pressure reference, such as a separate centrifugal compressor, or the like. Referencing the blow-down seal chamber to the low pressure reference reduces the required sealing pressure of the one or more gas seals. A valve may be disposed in the blow-down line and configured to regulate a flow of process gas leakage through the blow-down line.

Abstract: A ring segment for a blade outer air seal which includes an array of separated floating wall surfaces each extending from a pedestal and having an inner side with a fibrous metal pad secured and a TBC secured over the pads. The pedestals are formed by diffusion chambers formed between an outer side and an inner side of the ring segment. Purge air holes connect the diffusion chambers to the impingement cavity formed above the ring segment. Thin slots form the separated floating wall surfaces and connect the diffusion chambers to discharge cooling air through the sides of the floating wall surfaces. Cooling air holes also pass through the pedestals to discharge cooling air onto the TBC surfaces.

Abstract: In a radial turbine scroll, an operating gas is led to flow in the radial direction from a spiral scroll formed in a turbine casing into turbine moving blades of a turbine rotor, which is positioned on the inner side of the scroll, so as to act on the turbine moving blades, and then led to flow outside in an axial direction, thereby rotatively driving the turbine rotor, wherein the scroll 4 has a partition plate 20 a length of a certain range on a line of a tongue portion formed on the inner periphery of a gas inlet portion or has a reduced height between scroll side walls at an outlet portion of a tongue portion 21 formed on the inner periphery of a gas inlet portion of the scroll.

Abstract: A steam turbine nozzle assembly having a flush aperture is disclosed. In one embodiment, the steam turbine nozzle assembly includes a diaphragm assembly comprising: an inner diaphragm ring segment; an outer diaphragm ring segment; a static nozzle blade positioned between the inner diaphragm ring segment and the outer diaphragm ring segment; and a first cavity between the static nozzle blade and one of the inner diaphragm ring segment or the outer diaphragm ring segment; wherein the one of the inner diaphragm ring segment or the outer diaphragm ring segment includes a first aperture fluidly connected with the first cavity.

Abstract: The thrust load of an outer shaft is received by a contra-rotating thrust bearing provided in a boss of a front propeller and transmitted to an inner shaft. The combined thrust load of the outer shaft and the inner shaft is received by an inner thrust bearing provided on the bow side of the power transmission unit and transmitted to a ship body. The rotational force of an outer output shaft is transmitted to the outer shaft via a flexible joint (gear coupling). Thus, the thrust load of the outer shaft is transmitted to the ship body only via the inner shaft without being directly transmitted to the ship body, and the axial displacement and angular displacement are allowed by the gear coupling, so that it is possible to eliminate the influence of the change of hull deformation on the shaft center of the outer shaft.

Abstract: A blade outer air seal with ring segments forming a mate face gap in which a riffle seal is placed to seal the axial gap. The riffle seal includes a horizontal plate and a vertical plate extending from a bottom surface of the horizontal plate and occupies the axial gap space. The bottom end of the vertical extending plate is angled in a direction of rotation of rotor blades and includes ribs that form open slots in the riffle seal. The ring segments include metering holes that discharge cooling air into the slots to discharge film cooling air onto the hot gas surface of the BOAS and cool the ring segments.

Abstract: A fan cooling system has individual fan modules which are connected together in an end-to-end configuration, where one of the fan modules is connected to a mechanism which rotates the linear array of fan modules. The fan modules are substantially identical, which allows prefabrication of the fan modules prior to on-site installation of the system. Each fan module may contain water injection piping and nozzles, which allows the fan cooling system to dispense fog. The linear array of fan modules may be rotated along a longitudinal axis, such that the axial flow direction of the fans may be changed with respect to a vertical plane. A suggested use of the fan cooling system is for the cooling of livestock in large livestock structures.

Abstract: A rotor for a helicopter, having: a hub rotating about an axis and in turn having a number of blades; and an at least partly hollow drive shaft connectable to a drive of the helicopter and connected functionally to the hub to rotate the hub about the axis; the rotor also having vibration damping means in turn having a mass, and an elastically deformable member connected to the mass and supported by the shaft; the member extending at least partly inside the shaft, and being elongated parallel to the axis; and the mass vibrating, in use, at such a frequency as to oppose transmission to the shaft of the vibration produced by rotation of the hub and blades.

Abstract: A fluidic torque transfer device configured with a pump impeller that includes a pump shell, a pump blade attached to the pump shell, and a pump core attached to the pump blade; a turbine runner that includes a turbine shell, a turbine blade attached to the turbine shell, and a turbine core attached to the turbine blade; and a stator that includes a stator blade, and rectifies a flow of a hydraulic fluid from the turbine runner to the pump impeller. The outer contour line of the turbine blade extends outward in an extending direction of a rotation center axis of the pump impeller and the turbine runner on the fluid outlet side of the turbine runner more than an outer contour line of the pump blade on the pump shell side.

Abstract: A gas turbine engine includes a fan section. A turbine section is coupled to the fan section via a geared architecture. The geared architecture includes a torque frame and a flex support spaced apart from one another at a location. A gear train is supported by the torque frame. A damper is provided between the torque frame and the flex support at the location.

Abstract: A wind turbine includes a nacelle support structure rotationally mounted to a tower through a yaw bearing for rotation about a yaw axis. A hollow shaft is rotationally mounted to the nacelle support structure through a rotor bearing for rotation about a rotor axis of rotation and a blade support body is mounted to the hollow shaft, the blade support body supports either of a two-bladed rotor system and a three-bladed rotor system, the two-bladed rotor system and the three-bladed rotor system have essentially equal solidity.

Abstract: Provided is a propeller fan that can prevent deformation of the propeller fan while maintaining the basic performance thereof, such as the air blowing performance, efficiency, and noise performance. In a plastic propeller fan including a hub and a plurality of blades integrally molded in a radial pattern on the outer circumference of the hub, assuming that the radial size of each blade from the base to the outer peripheral edge is 100, a ring member that joins the plurality of blades together is provided at a dimension position of 5 to 45 from the outer peripheral edge.

Abstract: An inducer for vertical flow, cryogenic liquid centrifugal pumps comprising a stationary outer housing portion having an inlet and an outlet, the inlet located at a lower end and the outlet located at an upper end, the housing further having an inner wall portion with one or more spiral grooves formed in the inner wall portion, the grooves defining a hollow opening in the inner wall portion that spiral in a first direction, and an inner rotating impeller mounted on a rotating center shaft, the impeller having at least one curved blade which defines a curved, helicoid plane surface in which the slope of the plane increases as the distance from the center axis increases, the impeller rotating in a second direction which is in counter rotation to the first direction.

Abstract: Systems for protecting a wind turbine in high wind conditions are disclosed. A shrouded turbine may have an ejector shroud disposed adjacent and downstream of a turbine shroud. In one version, the ejector shroud can move to surround the turbine shroud. In another version, the turbine can be pivoted on a support tower to cover the intake end of the turbine and rotate the turbine about an axis at a right angle to the tower axis. In another version, the turbine is supported by a telescoping tower which may be retracted to lower the turbine in high winds. In another version, the tower sections may be connected by a pivotable connection and supported by guy wire(s) which may be lengthened to lower the upper tower section pivotally.

Abstract: A compressor stator vane and rotor blade tip clearance control assembly in which a plurality of stator vane segments each with vanes extending inward are connected to an annular sync ring through eccentric cranks so that circumferential movement of the sync ring will produce radial displacement of the vane segments and control the clearance between the blade tips. An actuator piston is rigidly fixed to the sync ring and forms an actuator chamber with stationary actuator housing. Bleed off pressure from one of the compressor stages is used to move the actuator piston, which moves the sync ring to radially displace the vane segments.

Abstract: A gas turbine engine includes a fan section. A turbine section is coupled to the fan section via a geared architecture. The geared architecture includes a torque frame and a flex support spaced apart from one another at a location. A gear train is supported by the torque frame. A damper is provided between the torque frame and the flex support at the location.

Abstract: An inducer for a casing of a gas turbine system is disclosed. The inducer includes a plurality of orifices defined in the casing, the plurality of orifices disposed in an annular array about the casing, and a plurality of cartridges, each of the plurality of cartridges configured to mate with one of the plurality of orifices. Each of the plurality of cartridges includes an inlet and an outlet for flowing a cooling medium therethrough. The inducer further includes at least one flow modifier disposed in each of the plurality of cartridges for modifying the flow of the cooling medium through each of the plurality of cartridges. Each of the plurality of cartridges is independently removable from each of the plurality of orifices.