Abstract: A guide vane arrangement for a turbomachine, wherein the guide vane arrangement has a plurality of adjustable guide vanes that are rotatably mounted around an adjustment axis, at least one inner ring segment that is formed separately from the guide vanes, and a seal carrier that is formed separately from the at least one inner ring segment, wherein the at least one inner ring segment is fastened to one guide vane or to a plurality of guide vanes, and wherein the seal carrier is mounted in a spoke-centered manner with respect to the at least one inner ring segment, so that the seal carrier is movably mounted with respect to the at least one inner ring segment in the direction of at least one adjustment axis of at least one guide vane.

Abstract: An airfoil vane assembly includes a vane piece defining a first vane platform, a second vane platform, and a hollow airfoil section joining the first vane platform and the second vane platform. The first vane platform defines a collar projection therefrom. A spar piece defines a spar platform and a spar extends from the spar platform into the hollow airfoil section. The spar platform includes a radial opening defined by first and second axial faces. The radial opening is configured to receive the collar projection, and a groove in the first axial face. A seal is situated in the groove. The seal seals against the collar projection and a biasing member is configured to bias the seal towards the collar projection. A method of assembling a vane is also disclosed.

Abstract: A coated article includes a substrate and an MCrAlY coating supported on the substrate. The M includes at least one of nickel, cobalt, and iron, Cr is chromium, Al is aluminum, and Y is yttrium. The composition of the MCrAlY coating varies in an amount of at least one of Cr, Al, and Y by location on the substrate with respect to localized property requirements. In one example, the coated article is an article of a gas turbine engine.

Abstract: In a fan case having an annular outer wall with a plurality of fan case bolt holes there through, bushings are inserted into the fan case bolt hole and are dimensioned to define an annular gap between the bolt hole inner surface and the bushing outer surface. An adhesive material disposed within each annular gap between the bushing and the corresponding fan case bolt hole, with the adhesive material forming a liquid shim separating the bushing outer surface from the bolt hole inner surface.

Abstract: A passive cooling system includes a fan configured to generate an air flow path for a radiator, the air flow path extending from the fan to the radiator and a cooling pipe extended between a turbocharger and an intake manifold, the cooling path positioned in the air flow path between the fan and the radiator.

Abstract: Methods and systems for operating an engine that includes adjustable poppet valve timing and an exhaust gas recirculation valve are described. In one example, the exhaust gas recirculation valve is opened and the timing of the poppet valves is retarded so that an amount of fresh air that is pumped by the engine to an after treatment device may be reduced.

Abstract: A tip rail cooling insert for attaching into a tip rail pocket in a tip rail of a turbine blade is disclosed. The insert includes a first inner layer defining at least one first insert cooling channel therein, the first inner layer including a pair of spaced legs defining a first coolant collection plenum with at least the tip rail pocket for directing coolant from at least one internal cooling cavity in the turbine blade to the at least one first insert cooling channel. Each of the pair of spaced legs has an angled outer end configured to accommodate rounded inner corners of the tip rail pocket. A first outer layer is on a first side of the first inner layer, and a second outer layer is on a second side of the first inner layer.

Abstract: A fan assembly for use in a gas turbine engine of an aircraft includes a fan disk having a number of fan blades and a windage shield coupled to the fan disk to move therewith. The fan assembly supplies air for use in the engine. The windage shield rotates with the fan disk during operation of the gas turbine engine and directs air supplied by the fan blade.

Abstract: A control system for an engine including a turbocharger disposed downstream of a plurality of cylinders. The control system includes an engine sensor configured to generate a signal indicative of an operational characteristic of the engine. The control system includes a first valve configured to control exhaust flow through a first set of cylinders from the plurality of cylinders. The control system includes a second valve configured to control exhaust flow through a second set of cylinders from the plurality of cylinders. The control system includes a controller communicably coupled to the engine sensor, the first valve, and the second valve. The controller is configured to receive the signal generated by the engine sensor. The controller is configured to actuate the first valve and the second valve based on the received signal. The first valve and the second valve are actuated to adjust exhaust flow received by the turbocharger.

Abstract: A spar cap for a wind turbine blade of a wind turbine, the spar cap including at least one elongated beam is provided. The spar cap includes at least one electrically isolating material cover and at least one electrically conductive material cover, wherein an entire circumference of the beam is enclosed by at least one electrically isolating material cover and the entire circumference of the at least one electrically isolating material cover is enclosed by at least one electrically conductive material cover, whereby the electrically conductive material cover has at least one electrical interface for electrically connecting it to a down conductor of the wind turbine blade.

Abstract: A fluid and wind turbine system suitable for horizontal or vertical axis applications comprising (i) blades radially spaced around a rotational axis attached to a shaft by mounting formations so that the length axis of the mounting formations are substantially parallel to the width axis of the blades which mounting formations suspend the blades from the rotational axis creating a passageway allowing the air flow to pass through the turbine and impart a unidirectional rotational force to the shaft at all times the blades are exposed to the air flow on both the windward and leeward sides of the rotational axis (ii) an air flow director which shields the rotating blades from the air flow for a portion of their 360-degree rotation.

Abstract: A composite piston machine has two moving assemblies of a rotor and a composite piston placed 180° out of phase with each other and linked to a shaft eccentrically placed inside the inner cavity of a main body that has ports for the inlet and outlet of fluids from it. This inner cavity is covered by two lids and divided in two working chambers by a separator. The composite pistons move following the rotation of the rotors while oscillating with respect of them and following the path of skid guides carved in separator and lids, dividing each working chamber in inlet and outlet chambers of variable volume, and intermittently obstructing the inlet and outlet of fluids from the inner cavity through the ports. The machine is designed for compressing gases or pumping liquids and can also operate as an engine driven by compressed gases or with pressurized liquids.

Abstract: A wall of a hot gas part, having a first surface subjectable to a cooling fluid, a second surface located opposite of the first surface and subjectable to a hot gas and, at least one film cooling hole extending from an inlet area located within the first surface to an outlet area located within the second surface for leading the cooling fluid from the first surface to the second surface. The respective film cooling hole has a diffusor section located upstream of the outlet area, the diffusor section is bordered at least by a diffusor bottom and two opposing diffusor side walls, wherein the diffusor section has a delta wedge element for dividing the cooling fluid flow into two sub-flows and subsequent formation of a pair of delta vortices. The respective delta wedge element protrudes in a step-wise manner from the diffusor bottom and is, in a top view, triangular-shaped.

Abstract: A control device for an engine is provided, which includes variable intake and exhaust valve operating mechanisms, a supercharger provided to an intake passage and configured to boost intake air introduced into a cylinder, and a controller. The controller drives the supercharger when the engine operates in a boosted range. The controller controls the variable intake and exhaust valve operating mechanisms so that a valve overlap period during which intake and exhaust valves open simultaneously is formed, when the engine operates in a low-speed boosted range of the boosted range where the engine speed is less than a reference speed. The controller controls the variable exhaust valve operating mechanism so that the open timing of the exhaust valve is more advanced when the engine operates in a high-speed boosted range of the boosted range where the engine speed is greater than or equal to the reference speed.

Abstract: A compact inlet design including a single bulkhead and/or an acoustic panel extending into nacelle lip region for noise reduction. The compact inlet is used with a low power fluid ice protection system capable of preventing ice build-up on the acoustic panel in the nacelle lip region.

Abstract: A device is disclosed including a wear ring formed as a hollow cylinder with an inside diameter and an outside diameter. The hollow cylinder may have multiple holes through at least a portion of the wear ring from the inside diameter towards the outside diameter. The multiple holes may be passages between the inside diameter and the outside diameter that allow fluid under pressure to pass between the inside diameter and the outside diameter through the multiple holes.

Abstract: An aircraft rotor blade assembly includes a rotor blade rotatable about an axis of rotation and a weighted assembly mounted to the aircraft rotor blade. The weighted assembly includes an actuator which moves a mass to adjust a moment of the rotor blade assembly when the rotor blade is rotated about the axis of rotation.

Abstract: Disclosed is a turbine vane having a turbine vane airfoil extending from a platform to an end wall and having an airfoil-shaped cross section having a leading edge, a trailing edge, and a pressure side and a suction side that extend from the leading edge to the trailing edge, wherein a plurality of cavities defined by a plurality of ribs extending from the pressure side to the suction side is formed in the turbine vane airfoil, at least one of the cavities is provided with a plurality of insert supports protruding inward from an inner surface of the turbine vane airfoil, and the insert supports are arranged in a circumferential direction of the cavity and arranged in a plurality of rows arranged in a radial direction.

Abstract: A compressor for use in a gas turbine engine including: an airfoil configured to rotate about an engine central longitudinal axis of the gas turbine engine; a casing, the casing including a radially inward surface; and a groove located within the casing opposite the airfoil, the groove is recessed in a radially outward direction from the radially inward surface of the casing, wherein the groove is defined by a forward groove wall, an aft groove wall opposite the forward groove wall, and a base groove interposed between the forward groove wall and the aft groove wall, and wherein the forward groove wall is operably shaped to generate an aft directed jet.

Abstract: An impeller includes a disk section having a tube section with a grip section which is fixed by thermal deformation to a rotary shaft that is configured to rotate around an axis line, and a main disk body, which is on another end in an axial direction from the grip section and which extends outward in a radial direction of the rotary shaft; and blade sections that protrude from the main disk body in the axial direction. The disk section has a hoop stress-limiting section with a tube section which extends further towards the other end in the axial direction than the main disk body.