Abstract: A centrifugal pump comprises a pump assembly, through which a fluid can be impelled. The pump assembly includes a fluid inlet and a fluid outlet, a fluid casing, and an impellor positioned within the fluid casing, the impellor being driven by a power source and being operable to generate fluid flow within the fluid casing from the fluid inlet to the fluid outlet. The pump assembly also includes a volute area formed on a periphery of the fluid casing, the volute area being operable to receive fluid pressurized by flow induced by the impellor. A pitot tube is positioned within the volute area, the pitot tube being operable to receive pressurized fluid from the volute area and pass the fluid through an outlet having an expanding geometry that increases the flow rate of the fluid as it passes through the outlet.

Abstract: A rotor wheel assembly has a rotor wheel including a plurality of dovetail slots. The rotor wheel assembly includes a bucket closure assembly having a leading auxiliary bucket with a dovetail coupled to a dovetail slot and an integral cover having a back side edge oriented at a first angle relative to the rotor wheel rotation axis. The bucket closure assembly includes a closure bucket having a dovetail coupled to a dovetail slot and an integral cover having a front side and a back side edge, where the back side edge is oriented to a second angle and the front side edge is parallel to the back side edge of the leading auxiliary bucket. The bucket closure assembly includes a trailing auxiliary bucket having a dovetail coupled to a dovetail slot and an integral cover having a front side edge parallel to the back side edge of the closure bucket.

Abstract: An adjustable lift regulating device (30, 32, 40, 50, 52, 56, 60, 68, 72, 76) on an inboard portion of a wind turbine blade (28). The lift regulating device is activated to reduce lift on the inboard portion of the blade by causing flow separation (41) on the suction side (22) of the blade. To compensate for the lost lift, the blade pitch is increased to a running pitch that facilitates stalling on the outer portion of the blade in gusts. This provides passive reduction of fatigue and extreme loads from gusts while allowing full power production under non-gust conditions.

Abstract: A turbocharger has a casing system which houses a centrifugal impeller connected to a turbine by a shaft. The casing system includes an insert casing which forms a duct for feeding air to and through the impeller, and a volute casing which forms a volute for receiving compressed air from the impeller, the insert casing inserting into the volute casing. The casing system further includes a main casing which forms a housing for the shaft and for the shaft-side end of the impeller. The impeller includes a hub which has a radially outer annular rim, and has front and rear faces which converge towards the rim from respectively the inlet side and the shaft side of the hub. The impeller further includes a plurality of circumferentially arranged vanes on the front face of the hub. The impeller further includes a seal formation formed on the rear face at the rim.

Abstract: A reinforcing part of ?-shaped section made out of composite material, and a method of making the part, the method including: making a first set of layers of interlinked yarns by three-dimensional weaving to form a first fiber blank portion to form a base preform; making a second set of layers of interlinked yarns by three-dimensional weaving to form a second fiber blank portion to form a stiffener preform, yarns of the second set being interlinked with yarns of the first set by weaving over a central interlinked strip that flares towards side edges of the first fiber blank portion in a zone corresponding to the step of the base; shaping the two fiber blank portions to obtain a single-piece fiber preform having a portion forming a base preform and a portion forming a stiffener preform; and depositing a resin in the fiber preform to form a matrix.

Abstract: An aircraft gas turbine having a core engine casing for a core engine, said core engine casing including at least a compressor area, a combustion chamber area and a turbine area, wherein the core engine casing is provided on its outer wall with several cooling-air tubes which are designed in one piece with said outer wall and extend in the axial direction relative to an engine axis.

Abstract: Methods and apparatus to adjust bleed ports on an aircraft engine are disclosed. An example apparatus for bleeding air from a multi-stage compressor of an aircraft engine includes a compressor case having a plurality of bleed ports. A first bleed port is associated with a first stage of a compressor, and a second bleed port is associated with a second stage of the compressor. The apparatus includes a plenum connected to the compressor case to define a plenum cavity. The plenum fluidly coupling the first and second bleed ports to a fluid conduit for providing bleed air to one or more systems of an aircraft. The apparatus also includes a bleed port selection mechanism located within the plenum cavity. The bleed port selection mechanism including a first portion proximate the first bleed port and operable to prevent fluid flow through the first bleed port.

Abstract: A component in a gas turbine engine includes an airfoil extending radially outwardly from a platform associated with the airfoil. The airfoil includes opposed pressure and suction sidewalls, which converge at a first location defined at a leading edge of the airfoil and at a second location defined at a trailing edge of the airfoil opposed from the leading edge. The component includes a built-up surface adjacent to the leading edge at an intersection between the pressure sidewall and the platform, and at least one cooling passage at least partially within the built-up surface at the intersection between the pressure sidewall and the platform. The at least one cooling passage is in fluid communication with a main cooling channel within the airfoil and has an outlet at the platform for providing cooling fluid directly from the main cooling channel to the platform.

Abstract: A rotor structure for a centrifugal flow machine includes working vanes attached to the hub of the rotor without any support disc or shroud. Additionally, the vane has a device for efficiently flushing the sealing chamber behind the rotor.

Abstract: A rotor wheel assembly includes a rotor wheel having a plurality of dovetail slots spaced circumferentially about a peripheral surface of the rotor wheel. The rotor wheel also has a plurality of notches formed in the peripheral surface. The rotor wheel assembly includes at least one bucket having an integral cover, an airfoil, a dovetail, and a platform having a first surface and an opposite second surface. The first surface of the platform includes a keyway. The keyway has an opposing tapered surface oriented at a first angle relative to the first surface of the platform. Furthermore, the rotor wheel assembly includes a wedge key having first face that is oriented substantially parallel to the first surface of the platform and an opposite second face that is oriented at the first angle relative to the first face, such that the second face is substantially parallel to the taper surface.

Abstract: A centrifugal pump has a gas accumulation reduction system to reduce the risk of gas locking caused by the accumulation of gas at the inlet of the impeller. The gas accumulation reduction system includes: (i) one or more diffuser ports extending through the hub of a diffuser; and (ii) one or more recirculation passages extending through the hub of an impeller. The recirculation passages are in fluid communication with the one or more diffuser ports to permit the recirculation of a portion of pumped fluid through the stage. Additionally, a centrifugal pump that includes at least one turbomachinery stage. The stage includes a rotatable impeller that has an impeller hub with a centrally disposed eye and a plurality of impeller vanes. The impeller is variously configured to encourage mixing of two-phase fluids at the eye of the impeller hub.

Abstract: A light weight fan blade for a gas turbine engine is disclosed. The disclosed fan blade has an increased chord length at a transition section between the inner edge or single tooth attachment portion of the fan blade that connects to the rotor disk and the airfoil. Increasing the chord length at the transition section substantially reduces the stress concentration when the fan blade is operated under normal operating conditions. Reducing the stress concentration enables engineers to design lighter fan blades and larger fan blades for larger gas turbine engines. By increasing the size of gas turbine engines, additional thrust can be provided without adding additional engines to the aircraft.

Abstract: A wind turbine rotor blade has a longitudinal axis, a blade root, a blade tip, a pressure side, a suction side and an aerodynamic profile which, in a longitudinal section of the rotor blade, has a profile chord and a thick trailing edge. The rotor blade includes a multiplicity of flow deflection elements which are arranged on the thick trailing edge and have respective inflow surfaces which are shaped and arranged such that a radial flow running in the direction from the blade root toward the blade tip is diverted by the inflow surface in the direction of the profile chord.

Abstract: A ceiling fan has a plurality of blades with upper and lower surfaces. Each blade has side edges and arcuate convex interior and exterior edges forming a blade periphery. A plurality of similarly configured pads have upper and lower surfaces. Each pad has side and interior and exterior edges forming a pad periphery. The pads are fabricated of a synthetic microfiber material. Each peel strip of a plurality of peel strips has a size and shape of an associated pad. An adhesive is in contact with the lower surface of each pad removably coupling the lower surface of each pad to a peel strip. The peel strips are adapted to be removed from the pads and the pads removably coupled to the upper surfaces of the blades.

Abstract: An abutment mechanism for limiting the flapping of the blades of a rotor (1). High abutment members (6) can be moved into an engagement position by return means (13) exerting an intrinsic return force (R), and into a disengagement position by a flyweight (10) exerting a centrifugal force (C) under the effect of the rotor (1) rotating. At least one magnetic type bistable latch (15) is in selective engagement with the high abutment members (6). When the rotor (1) is stationary and while it is starting to rotate, an engagement latch (15) engages with the high abutment member (6) to prevent it passing from the engagement position towards the disengagement position. At a predetermined centrifugal force threshold, the engagement of the engagement latch (15) with the high abutment member (6) is broken, and the high abutment member (6) quickly passes into the disengagement position.

Abstract: An integrated strut and turbine vane nozzle (ISV) arrangement according to an embodiment, includes a single-piece interturbine duct (ITD) and a plurality of vane nozzle segments removably attached to the ITD. Vane airfoils of the vane nozzle segments in combination with trailing edge portions of the struts, form a vane nozzle integrated with the ITD.

Abstract: A lock link for locking variable stage stator vanes in a compressor includes a substantially planar body portion having a slot formed on one edge and a narrow neck portion extending away from an opposite edge, the narrow neck portion adapted to seat in a corresponding slot in an adjacent lock link attached to an adjacent vane; and a profiled opening in the substantially planar body portion adapted to receive a key provided on a vane stem to prevent relative rotation between the vane and the lock link.

Abstract: A windmill blade assembly that is rotated in response to the wind. Each of a first and a second blade member has first and opposite ends and a hub mounting hole located between the ends. The first blade member is located above the second blade member such that the hub mounting holes thereof are axially aligned to receive a hub therethrough. The first and second blade members are turned along the hub or bent so as to provide a pitch that is aerodynamically configured to cause the rotatable blade assembly to spin. The windmill blade assembly is connected by a correspondingly rotatable shaft which extends from the hub thereof to an electrical power generator.

Abstract: A multi-stage axial compressor incorporating a counter-rotational movement is provided with a series of rotors mounted along and driven by a driveshaft, and a geared counter-rotating outer casing. A planetary gear system is assembled along a static casing, which can be assembled as a forward or aft casing for the compressor. The bearings of the planetary gear system typically will be aligned concentrically with a center rotor drum assembly mounted along the single driveshaft. The counter-rotating drum assembly will be assembled over the rotor drum assembly and will be engaged by the forward and aft casings so as to provide for counter-rotation of selected ones of the rotors driven by the driveshaft of the compressor.

Abstract: A cooling device for use with an engine is provided. The cooling device includes a flow control portion that includes a base and an opening defined therein. The flow control portion also includes a plurality of blades that extend from at least a portion of the base. The cooling device also includes a grid portion having an opening defined therein, said grid portion opening is substantially concentrically aligned with the base opening. An attachment portion is configured to couple the cooling device to at least one rotatable component of the engine. Each of the flow control portion, the grid portion, and the attachment portion are formed integrally together such that the cooling device is a single component.