Abstract: A centrifugal compressor having a casing that houses an impeller allowing rotation about a rotational axis C, a gas channel, a treatment hollow part provided inside the casing, a first channel open to the gas channel on the downstream side of the blade leading edge of the impeller, a second channel open to the gas channel at the upstream side of the blade leading edge, a guide vane that imparts a swirl component in an opposite rotational direction of the impeller to gas discharged from the second channel, a constricting part that constricts the gas channel, and a rectifying part that rectifies gas in a direction that minimizes the swirl component about the rotational axis C and also increases the component in the direction of the rotational axis C.

Abstract: An impeller pump has a pump casing including a pump chamber and an inlet and an outlet thereon and an impeller therein, and including a heating device for heating the conveyed medium, which heating device forms an external wall of the pump chamber. The pump chamber extends annularly around the impeller and away from the pump chamber floor, wherein the outlet leads off on a region of the pump chamber which, viewed in the axial direction of the impeller pump, is pointing away from the pump chamber floor. The cross-sectional area of the pump chamber decreases in the axial direction of the longitudinal center axis of the impeller pump away from the pump chamber floor toward the outlet by virtue of an obliquely inwardly inclined external wall.

Abstract: An airfoil includes a dovetail root having a base. A grooved slot is disposed in the base and a plurality of root lightening cavities is disposed in the grooved slot.

Abstract: The main aim of the invention is a propeller (32) for a turboengine (1) comprising a plurality of blades (48) and a blade support ring (47) provided with housings (50), each receiving a pivot (52) bearing the foot (58) of one of said blades (48), characterized in that at least one of the pivots (52) is equipped with at least one counterweight system (90, 91) provided with at least one inner channel (93, 96) for airflow ventilation discharge (F1, F3) for capturing and guiding said airflow directly in contact with the blade foot (58) borne by said at least one of the pivots (52).

Abstract: A wind turbine blade vortex generator unit and a method for installing it, where a wind turbine blade has at least one series of vortex generator units formed of fins extending substantially perpendicular to the surface of the airfoil and substantially in a direction from the leading edge towards the trailing edge of the wind turbine blade. The vortex generator units each comprises a fin connected to an outer side of the fin base, and where the fin is delta shaped tapering from a trailing edge towards a leading edge and where each of the vortex generator units has a layer of adhesive on an inner side of the base that extends to an outermost periphery of the base. The vortex generator unit has exactly one fin, and the base has an airfoil shaped periphery with a rounded leading edge and a trailing edge.

Abstract: A fan casing for fitment around an array of radially extending fan blades of a gas turbine engine. The fan casing includes an annular casing element; and an annular fan track liner positioned radially inward of the annular casing element. The fan track liner includes an abradable layer and an abrasive layer, the abrasive layer being positioned radially inward of the abradable layer and proximal, in use, to the fan blades.

Abstract: A gas turbine engine includes an intercooled twin centrifugal compressor. A pipe diffuser extends from the intercooled twin centrifugal compressor into an airflow path.

Abstract: An aspect includes a compressor diffuser and shroud for a motor driven compressor assembly. The motor driven compressor assembly includes a first stage compressor and a second stage compressor. The compressor diffuser and shroud of the first stage compressor includes a diffuser portion, a compressor inlet portion, and a shroud portion. The diffuser portion includes a diffuser portion outer lip having a first sealing lip outer diameter to provide a first sealing interface to a first stage compressor housing. The compressor inlet portion includes an inlet portion outer lip having a second sealing lip outer diameter to provide a second sealing interface. The shroud portion includes a curvature between the diffuser portion outer lip and the inlet portion outer lip to align with a first stage compressor rotor, where a ratio of the first sealing lip outer diameter to the second sealing lip outer diameter is between 1.622 and 1.628.

Abstract: An airfoil of a turbine engine may have internal passages to permit the travel of cooling air through the airfoil. Multiple airfoils may be formed together in a stator vane assembly, and cooling air may be directed through the stator vane assembly. The stator vane assembly may be mounted to an engine structure to carry structural loads experienced by the stator vane assembly. Buttresses may be formed in the stator vane assembly, such as beneath each airfoil of the stator vane assembly, and extending into a passage permitting the travel of cooling air through the airfoil. The buttresses may enhance the strength and stability of the stator vane assembly by facilitating the transmission of structural loads to an engine structure. A channel may be defined through one or more buttress to enable the passage of cooling air into the airfoils, and yet allow the buttresses to carry structural loads.

Abstract: A marine propeller has an outer hub having a central axis and a blade having a blade root attached to the outer hub and extending radially outward from the outer hub toward a blade tip. The blade has a leading edge and a trailing edge. The propeller has a diameter between about 15 inches and about 17 inches and a pitch between about 14 inches and about 24 inches. The blade has a progressive rake angle such that a first local rake angle at the blade root is less than a second local rake angle at the blade tip. A combination of the diameter, pitch, and progressive rake angle provides a marine vessel to which the marine propeller is coupled with minimum drag while the marine vessel is operating at less than a maximum vessel speed. A method of designing a propeller is also disclosed.

Abstract: A turbine rotor blade is provided with a blade root, platform adjoining it, and turbine blade on that side of the platform which faces away from the blade root, with at least one opening for feeding coolant into the turbine rotor blade interior on an underside of the blade root, which opening merges into a coolant duct. An axial rotor section for a rotor is provided, having an outer circumferential surface adjoining two end-side first side surfaces with rotor blade holding grooves distributed over the circumference and extending along an axial direction, wherein a turbine rotor blade is arranged in every holding groove, wherein a multiplicity of sealing elements are at the side of a side surface of the rotor section, and lie opposite the end sides of blade roots to form a gap. Multiple outlet holes for impingement cooling of the sealing elements are provided in the end surface.

Abstract: A submersible pump assembly includes a centrifugal pump driven by a motor. The pump has a number of stages, each of the stages having a diffuser and an impeller. An upthrust washer is located between a diffuser upthrust surface and an impeller upthrust surface. Balance holes extend from an inlet on an upper side of the impeller to an outlet within one of the impeller passages. The upthrust washer overlies the inlets while the impeller is in the upthrust position. Slots are located at an interface between the upthrust washer and the impeller upthrust surface. Each of the slots registers with the inlet of one of the balance holes to allow fluid flow into the inlets of the balance holes while the impeller is in the upthrust position.

Abstract: A steam turbine stationary blade is configured to be a stationary blade structure having a hollow structure. The steam turbine stationary blade is provided with a slit disposed on a stationary blade surface. The pressure of a stationary blade hollow is reduced to suction a liquid film through the slit for removing the liquid film formed on the stationary blade surface. An opening portion of the slit is covered with a sheet in a meshed pattern formed of a fine mesh thereby reducing an accompanied steam amount so as to effectively remove the liquid film.

Abstract: A drive pod of a watercraft such as a boat may be designed to break off the hull of the boat in the event of an underwater collision involving the drive pod. A shaft assembly that transmits power from the engine in the hull to blades or a jet in the drive pod is designed to break at a precise point so that seals in the hull and seals in the drive pod are protected from damage. The shaft assembly may include an axial blind hole with an undercut at a bottom of the blind hole. A pin may be inserted to reinforce the shaft above the undercut.

Abstract: A gas turbine engine includes a liner disposed around a flowpath. The liner has a forward end, a radially outer surface, and a radially inner surface. A hole extends axially into the forward end of the liner between the radially outer surface and the radially inner surface, and an engagement member is partially disposed in the hole and extends axially forward from the forward end of the liner.

Abstract: A centrifugal fan includes a fan frame and a fan impeller received in the fan frame. The fan frame has at least one air inlet and at least one air outlet respectively formed on two sides of the fan frame. The fan impeller has a hub, an extension section outward extending from the hub and multiple blades disposed on the extension section. Each blade has a front end and a rear end. The rear ends of the blades are annularly arranged to together define a virtual geometrical configuration. A flow guide space is defined between the virtual geometrical configuration and the hub. A chord length is defined between the front and rear ends of the blade. The flow guide space has a width larger than or equal to the chord length so as to thin the centrifugal fan and enhance the performance thereof.

Abstract: An electric fan includes a fan body having a fan shaft coupled to a fan motor. A fan motor bracket is connected to a fixing portion of the fan motor. A swivel shaft is coupled to the fan motor bracket. A sleeve is mounted around the swivel shaft and is coupled to an output shaft of a swivel motor. The sleeve includes an inner periphery having grooves. The swivel shaft receives an elastic element extending in a radial direction of the swivel shaft. A ball is mounted to an end of the elastic element. The ball is biased by the elastic element to be partially received in one of the grooves. If the fan body is impeded during the swiveling movement, the ball moves inward and compress the elastic element, disengaging the swivel shaft from the sleeve to reduce damage to the sleeve and the output shaft of the motor.

Abstract: A turbomachine aerofoil blade has an aerofoil body portion and a dovetail root fixing at the base of the aerofoil body portion which slides, in use, into a correspondingly shaped slot of a rotor of the turbomachine. The dovetail root fixing has a neck portion, and support flanks engage with matching angled surfaces of the slot under centrifugal loading of the aerofoil blade to support the aerofoil blade on the rotor. The neck portion is shaped such that a rotational adjustment of the aerofoil blade relative to its angular position when supported under centrifugal loading is needed to provide adequate clearance at the neck portion to allow the dovetail root fixing to slide into the slot. On centrifugal loading the engagement of the support flanks with the matching angled surfaces of the slot forces a reversal of the rotational adjustment and reduces the clearance at the neck portion.

Abstract: An apparatus may include a cage that rotates around a cage axis and a turbine located at an end of the cage and rotating around a turbine axis. A turbine blade may have an adaptable shape. A frame of the turbine blade may have a first frame portion that pivots relative to the second frame portion. The curvature of the turbine blade may be controlled by shortening a connection while concurrently lengthening another connection. Controllers may control the rotation of the cage(s) and/or turbine(s) based on a speed, a direction, a velocity, an acceleration of wind, and/or a load carried by the apparatus. The apparatus may be a Savonius machine. Rotation of the cage(s) and/or turbine(s) may induce a Magnus effect. A seat and user controls near the seat may be included. The user controls may control the rotation of the cage(s) and/or turbine(s).

Abstract: Systems and methods for monitoring wind turbine loading are provided. In one embodiment, a system includes a main shaft, a bedplate, and a gearbox coupled to the main shaft and mounted to the bedplate. The gearbox includes an outer casing and a torque arm extending from the outer casing. The system further includes an isolation mount coupled to the torque arm, and a sensor configured to measure displacement of the torque arm. In another embodiment, a method includes operating the wind turbine, and detecting displacement of a torque arm of a gearbox of the wind turbine. The method further includes calculating a moment for a main shaft of the wind turbine based on the displacement of the torque arm.