Abstract: One aspect of the present application provides an apparatus comprising a shape operable as a gas turbine engine component, an internal cavity within the shape including a radius, a trench on an external surface of the shape including a rear face tangential to an arc centered on the radius of the internal cavity, and a cooling hole extending from the internal cavity and exiting to the trench through the rear face of the trench wherein a cooling fluid introduced to the internal cavity flows through the cooling hole and into the trench during operation of the gas turbine engine component.

Abstract: There is provided an impeller rotating about a rotary shaft, the impeller including: an inlet through which a fluid is introduced; an outlet through which the fluid is discharged; a supporter connected to the rotary shaft; a blade portion provided on the supporter; a shroud portion disposed to cover the blade portion; and a sealing portion including at least one sealing protrusion protruding in a direction that is in parallel with the rotary shaft, and disposed at a portion of the shroud portion, which configures the inlet.

Abstract: A turbocharger for an engine includes a compressor impeller, a turbine wheel, a turbine housing, a cover, and a flow passage switching valve. The impeller is for compression of intake air. The wheel drives the impeller. The housing includes first and second exhaust scrolls independently of each other, and a flow passage switching hole. The first and second exhaust scrolls swirl exhaust gas which is discharged from the engine and blow the swirled exhaust gas toward the wheel. The hole guides exhaust gas into the second exhaust scroll. The cover is provided separately from the housing. The valve opens or closes the hole, and includes a movable part having a rotatable shaft and a valving element. The movable part is attached to the cover. The cover is press-fitted to the housing, so that the valve is attached to the turbocharger.

Abstract: An assembly for a turbocharger can include a pinched nozzle cartridge that includes a base component, an insert component and vanes disposed at least in part between the base component and the insert component, where the insert component includes a shroud surface and an upper pinch profile, where the base component includes an annular surface that defines a turbine wheel opening and a lower profile and where the upper pinch profile and the lower profile form a pinched nozzle. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.

Abstract: The present invention relates to a wind direction adjustable blade type vertical axis wind turbine that is configured to allow blades to be automatically swung, thereby making more efficient use of wind power. The wind turbine includes: a rotating shaft adapted to be rotated by means of wind power; an upper plate adapted to be coupled to the upper portion of the rotating shaft; a lower plate adapted to be coupled to the lower portion of the rotating shaft; a plurality of blades disposed between the upper plate and the lower plate; and swing motion units disposed between the top end of each blade and the upper plate and between the underside end of each blade and the lower plate in such a manner as to form the center of rotation of each blade, while allowing each blade to be rotatable in accordance with the wind direction.

Abstract: Provided is a driving apparatus of a variable pitch propeller having blades, each of which has a pitch angle changed in a rotational direction of a propeller shaft, and a pitch adjuster for adjusting the pitch angle. The pitch adjuster includes blade actuating shafts that are connected to eccentric stubs coupled to lower ends of the blades and are disposed inside the propeller shaft so as to allow linear reciprocation and to push or pull the eccentric stubs, and a power converter that converts a rotating motion of the propeller shaft into a linearly reciprocating motion of the blade actuating shafts.

Abstract: A turbojet fan blade in which a leading edge presents a sweep angle greater than or equal to +28° in a portion of the blade that is situated at a radial height lying in a range of 60% to 90% of a total radial height of the blade measured from its root towards its tip, and the leading-edge sweep angle presents a difference of less than 10° between a minimum sweep angle measured at a radial height of minimum sweep angle situated in the portion of the blade lying in a range of 20% to 90% of the radial height of the blade, and a sweep angle measured at a radial height that is 10% greater than the radial height of minimum sweep angle.

Abstract: A vertical-axis wind turbine apparatus is disclosed. In at least one embodiment, the apparatus provides a substantially vertically-oriented main shaft. A blade assembly is coaxially aligned with and rotatably engaged about the main shaft. The blade assembly provides an at least one blade radially projecting therefrom. A housing is rotatably engaged with the main shaft and configured for selectively encompassing the blade assembly. A first screen is integral with the housing and configured for shielding a return portion of the blade assembly. A second screen is rotatably engaged with the housing and configured for selectively moving between a retracted position, wherein the second screen is positioned substantially adjacent to the first screen such that a catch portion of the blade assembly is exposed, and a deployed position, wherein the second screen is rotated away from the first screen for at least partially shielding the catch portion from the wind.

Abstract: A blade wheel for a rotary electric machine may include a hollow cylindrical main body having an outer surface extending around an axis of rotation in a circumferential direction of the main body; a first end region and a second end region of the main body, each peripherally extending around the main body in the circumferential direction, the first and second end regions lying opposite each other in the direction of the axis of rotation; a recess extending along the outer surface and between the first end region and the second end region of the main body in the circumferential direction; and at least one web-shaped vortexing element extending within the recess and between the first and second end regions. The at least one vortexing element is designed to generate a movement of air away from the outer surface when the blade wheel rotates about the axis of rotation.

Abstract: A method for making a gas turbine engine ceramic matrix composite airfoil is disclosed. The method includes fabricating an airfoil preform that has a slotted forward end and a continuous trailing end. The slotted forward end of the airfoil preform is coupled to an airfoil core insert. A ceramic matrix composite covering is applied to cover the slots of the airfoil perform. The continuous trailing end of the airfoil preform is removed to expose the slots. A gas turbine engine airfoil is also disclosed.

Abstract: An exhaust-gas turbocharger (1) having a compressor (2), which has a compressor housing (3); a turbine (4), which has a turbine housing (5): and a bearing housing (6), which is arranged between the compressor housing (3) and the turbine housing (5) and is connected to the compressor housing (3) by way of a compressor-side connecting device and to the turbine housing (5) by way of a turbine-side connecting device (7). The turbine housing-side and/or compressor-side connecting device (7) is in the form of a taper key bolted joint having bolts (8, 9, 10) which are arranged at least substantially perpendicularly to an exhaust-gas turbocharger longitudinal axis (L).

Abstract: A method of positioning an inlet guide vane assembly before start-up of a chiller system including a compressor, a condenser, and a cooler is provided including receiving a first input form sensors located in the cooler and the condenser. A saturation temperature is calculated based on the input from the sensors. A second input indicative of a minimum speed of a motor coupled to the compressor at start-up is received. Using the calculated saturation temperature and the second input, an allowable position of the inlet guide vane assembly is determined. The inlet guide vane assembly is then moved to the determined allowable position.

Abstract: A metallic seal assembly, a turbine component, and a method of regulating flow in turbo-machinery are disclosed. The metallic seal assembly includes a sealing structure having thermally-responsive features. The thermally-responsive features deploy from or retract toward a surface of the sealing structure in response to a predetermined temperature change. The turbine component includes the metallic seal assembly. The method of regulating flow in turbo-machinery includes providing the metallic seal assembly and raising or retracting the thermally-responsive features in response to the predetermined temperature change.

Abstract: In a turbine for an exhaust gas turbocharger with a turbine casing having a receiving chamber for accommodating a turbine wheel and at least one volute through which the exhaust gas is guided via a feed passage into the receiving chamber and wherein at least one guide element is provided in the turbine casing so as to project into the feed passage in a guide region for guiding the exhaust gas onto the turbine wheel, the guide element comprises a first length region in the axial direction of the turbine, in which the guide element is designed with respect to its aerodynamic properties differently from its aerodynamic design in a second length region adjoining the first length region.

Abstract: A magnet case for a rotor includes a hollow cylindrical supporting body for accommodating two magnetic bands, an annular flange extending outwardly from a top end of the supporting body, and a positioning plate extending inwardly from a bottom end of the supporting body. The annular flange of the magnet case has two spaced notches defined in an outer periphery thereof, and the two spaced notches are configured to reduce vibration of a cooling fan associated with the rotor during operation of the cooling fan. A rotor incorporating the magnet case is also provided.

Abstract: One embodiment of the present invention is a unique gas turbine engine. Another embodiment is a unique machine. A further embodiment is a unique self-aligning foil bearing system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for machines and self-aligning foil bearing systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Abstract: An airfoil includes an airfoil body having a first section and a second section that differ by coefficient of thermal expansion. The second section is arranged in thermomechanical juxtaposition with the first section such that the first section and the second section cooperatively thermomechanically control a profile of the airfoil body responsive to varying thermal conditions.

Abstract: A turbine engine blade, including an airfoil which extends radially between a blade root and an airfoil tip, axially between a leading edge and a trailing edge, and tangentially between a pressure side and a suction side, the profile of the blade having a series of basic profiles, in a form of a vane section, stacked on one another along a stacking line connecting the center of gravity of all the vane sections. The projection of the stacking line of the airfoil on at least one plane extending radially from the blade root includes a double tangential inversion of the direction of the curvature thereof, located in the last thirty percent of the height of the airfoil, the projection plane being positioned substantially perpendicular to the chord of the blade.

Abstract: A section of a gas turbine engine includes a case structure and a liner. The liner is attached to the case structure by a compliant adhesive. The adhesive covers at least a portion of the liner surface area, and can have interruptions used to tune the compliance of the adhesive layer.

Abstract: A vertical axis wind turbine including a turbine rotor having an axis of rotation and at least one blade spaced from and mounted for rotation about the rotation axis of the turbine. The blade has at least one longitudinal surface substantially parallel to the rotation axis and for engagement, in use, with wind incident on the turbine rotor. The blade is a two part blade with a first leading blade portion pivotably connected to a second trailing blade portion. The turbine includes pitch control means and camber control means for controlling the pitch and camber of the blade.