Abstract: An aerofoil component (32) defining an in use leading edge (38) and a trailing edge (40). At least one of the leading edge and the trailing edge (38, 40) comprises a plurality of first and second recesses (52, 56) projecting in a direction corresponding with an in use flow direction, the first and second recesses being spaced apart normal to the in use flow direction and having a different chordal extent.

Abstract: An exhaust gas variable geometry turbine assembly can include a number of pivotable vanes that define throats within an exhaust gas nozzle where each of the pivotable vanes includes a corresponding post, where each of the pivotable vanes is made of a first alloy that includes a first amount of nickel by mass, where each of the corresponding posts is made of a second alloy that includes a second amount of nickel by mass and where the second amount of nickel by mass exceeds the first amount of nickel by mass.

Abstract: Dual alloy Gas Turbine Engine (GTE) rotors and method for producing GTE rotors are provided. In one embodiment, the method include includes arranging bladed pieces in an annular grouping or ring formation such that shank-to-shank junctions are formed between circumferentially-adjacent bladed pieces. A first or bonding alloy is deposited along the shank-to-shank junctions utilizing a localized fusion deposition process to produce a plurality of alloy-filled joints, which join the bladed pieces in a bonded blade ring. The bonding alloy is preferably selected to have a ductility higher than and a melt point lower than the alloy from which the bladed pieces are produced. After deposition of the first alloy and formation of the alloy-filled joints, a hub disk is inserted into the central opening of the bonded blade ring. The hub disk and blade ring are then bonded utilizing, for example, a Hot Isostatic Pressing process.

Abstract: The present invention relates to an adjustable guide vane for a turbomachine, having a vane element and a turning disk, which has a first impact chamber, in which an impulse element is arranged with play of movement.

Abstract: A platform is disclosed. The platform may include an airfoil section with a cooling cavity and a platform. The platform may have various cooling features, such as a platform cooling apparatus. The platform cooling apparatus may have a cooling chamber forming a channel disposed at least partially through the platform and the platform cooling apparatus may have an inflow channel in fluidic communication with the chamber and the cooling cavity so that cooling air may travel from the cooling cavity of the blade airfoil section and into the platform cooling apparatus. Moreover, the platform cooling apparatus may have a cooling cover apparatus at least partially fluidically sealing the platform cooling apparatus.

Abstract: Articles of manufacture, preferably pump component parts, and a method for making the articles, include providing a plurality of layers of reinforcing fibers in a stack of consecutive layers in a matrix of synthetic polymeric material. The reinforcing fibers of different layers are of corresponding different materials, and the layers are arranged such that the material of the reinforcing fibers in each layer is different from the material of the reinforcing fibers in the next consecutive layer. The layers are stitched together with further reinforcing fibers extending within the stack essentially perpendicular to the layers and interspersed throughout the stack. The stack is compressed and cured to establish a block having a plurality of layers of reinforcing fibers and further reinforcing fibers in a matrix of synthetic polymeric material. The block is machined to establish a prescribed configuration of a desired article.

Abstract: A fan impeller structure of cooling fan includes a blade assembly and a hub. The blade assembly has multiple blades and an annular cover body. The annular cover body is integrally formed on the rear ends of the blades by injection molding to enclose and connect with the rear ends of the blades. Alternatively, the annular cover body is fused and integrally connected with the rear ends of the blades by means of laser welding. The blade assembly and the hub are integrally connected with each other to form the fan impeller structure.

Abstract: A method and apparatus for operating an air cycle machine is disclosed. The apparatus includes a detector for measuring a rotational speed of a component of the air cycle machine. A processor estimates a rate of change of rotational speed of the component from the measured rotational speed and shuts down the air cycle machine when the estimated rate of change of the rotational speed of the component is greater than a selected rate threshold.

Abstract: A central shaft is oriented in a position that is normal to the surface of the ground and normal to a direction of fluid flow. The central shaft has a plurality of blades emanating from the central shaft, wherein each one of the plurality of blades has an outside edge and an inside edge, the inside edge being attached directly to an outside surface of the central shaft. The outside edge of the blade extends upward curving around the central shaft and the inside edge of the blade extends upward curving around the central shaft. The turn rate of the inside edge of the blades about the central shaft is less than the turn rate of the outside edge of the blades about the central shaft.

Abstract: A mid-turbine frame (MTF”) for a jet engine is disclosed and comprises a duct that extends between a high pressure turbine (“HPT”) and a low pressure turbine (“LPT”), the duct comprising a plurality of segments that together form an outer annular structure and an inner annular structure, the inner annular structure situated radially inward of the outer annular structure, and/or a plurality of vanes that extend radially outward from the inner annular structure toward the outer annular structure, each vane comprising a channel. Each segment may be coupled to an adjacent segment by a seal.

Abstract: A flywheel is attached to a shaft of a turbine. As the shaft rotates, the flywheel swings outwards away from the shaft and regulates the angular velocity of the rotating shaft. In an embodiment, there are multiple flywheels attached to the shaft. In another embodiment there is a first flywheel that controls a second flywheel. In another embodiment, the flywheel has adjustable or centrifugal displacement of counterbalanced masses for effective rotational diameter with effective rotational balance. In another embodiment, a small pilot centrifugal displacement flywheel may control a clutch by rotational velocity and may include a hysteresis control. An example of a clutch may limit that degree to which the arms of the flywheel may be extended and/or retracted. In another embodiment, a small pilot centrifugal displacement flywheel controls the hysteresis of a centrifugal flywheel displacement.

Abstract: A noise reduction structure includes a compressor discharge-side pipe portion, a first porous plate having a plurality of through holes and extending circumferentially along an inner circumferential surface of the compressor discharge-side pipe portion so that an air layer is formed between the first porous plate and the inner circumferential surface, a partition dividing an interior of the compressor discharge-side pipe portion in a radial direction in a circumferential direction of the compressor discharge-side pipe portion so as to form a plurality of flow paths in the compressor discharge-side pipe portion, and a second porous plate having a plurality of through holes. The second porous plate is provided in each of the plurality of flow paths and extends along the partition so that an air layer is formed between the second porous plate and the partition.

Abstract: A power plant includes a structure and a vehicle having at least one wing including a first wing part and a second wing part. The vehicle is arranged to be secured to the structure by at least one tether. The vehicle is arranged to move in a predetermined trajectory by a fluid stream passing the wing. The vehicle includes at least one turbine connected to a nacelle having a generator. At least the first wing part is arranged at a first angle relative to a horizontal center line of the wing. The nacelle is arranged to be attached to a surface of the wing facing the direction in which the first wing part is angled.

Abstract: A number of variations may include a product including a rotor comprising a shaft having a rotation axis, a bearing at least partially surrounding the shaft allowing for rotation of the shaft within the bearing about the rotation axis, and a bearing housing comprising at least one fluid outlet passage constructed and arranged to flow fluid upward from the bearing to a top side of the bearing housing.

Abstract: A blade assembly including a rotor; a body portion connected to the rotor and having a space therein; and at least one vibration reduction member provided in the space.

Abstract: A first stage turbine nozzle includes a first stage hub portion extending axially along a central axis, a first stage disk portion attached to the first stage hub portion and centered on the central axis, and a plurality of first stage vanes positioned radially around and attached to the first stage disk portion. Each vane extends a vane height H away from the first stage disk portion and each vane has a first end positioned at a diameter D away from the central axis. The first stage turbine nozzle also includes a plurality of first stage throats defined between radially adjacent first stage vanes. Each first stage throat has a throat width W between radially adjacent first stage vanes. The first stage turbine nozzle also includes a coating on a sidewall of each first stage vane.

Abstract: A system and method for nose cone edge delamination repair is provided. A nose cone may comprise an outer skirt having an aft edge, a flange, and a pin landing. The system and method may comprise trimming the aft edge of the nose cone to form a repaired edge. A first layer of fiberglass may be placed over repaired edge. A second layer of fiber glass may be placed over the first layer and the repaired edge. The first layer and second layer may be trimmed to create a spot face to allow for lower tolerances when installing the nose cone into a gas turbine engine.

Abstract: An axial flow fan improves air capacity and static pressure characteristics, and can ease stress at a leading edge portion of a blade base, even when a shape for noise reduction is adopted. An axial flow fan includes a boss portion and rotor blades. A rotor blade is segmented into a first area extending from the boss portion toward the outer peripheral side, and a second area connected to the first area and extending from the first area to the outermost periphery of the rotor blade. The distribution of a forward sweep angle varies quadratically in the first area, and the maximum forward sweep angle in the first area is not larger than the forward sweep angle in the second area. The distribution of chord-pitch ratio varies in a curved manner from the base as the minimum value in the first area, and is linear in the second area.

Abstract: A second stage turbine nozzle includes a second stage disk portion having a central axis, and a plurality of second stage vanes positioned radially around and attached to the second stage disk portion. Each second stage vane extends a vane height H away from the second stage disk portion and each second stage vane has a first end positioned at a diameter D away from the central axis. The second stage turbine nozzle also includes a plurality of second stage throats defined between radially adjacent second stage vanes. Each second stage throat has a throat width W between radially adjacent second stage vanes. The second stage turbine nozzle also includes a coating on a sidewall of each second stage vane, wherein a surface roughness of the sidewall is between 125 microinches Ra and 200 microinches Ra.

Abstract: A turbine wheel for use in a gas turbine engine having a plurality of blades attached to a rotor disk. Each blade is formed as a composite structure including a number of plies of ceramic-containing material. The blades each include a root to fit within dovetail slots of the rotor disk to couple the blades to the rotor disk.