Abstract: An air cooled integrally bladed rotor with bore entry cooling holes for a small gas turbine engine cast using a ceramic core having an axial bore forming piece with a plurality of radial extending spokes that end in an annular ring to form cooling air supply passages for air cooled turbine blades. Bulbous chambers are formed in a circumferential cooling air supply channel formed below each blade, where cooling air holes are drilled from a tip of each blade and into the bulbous chambers. The radial spokes have an elliptical cross sectional shape with a major axis perpendicular to a rotational axis of the central bore of the IBR. A spacing of the inlet openings in the bore are minimized to reduce stress.

Abstract: A stationary blade includes a main unit having a hollow blade structure formed from a metal plate by plastic forming. The stationary blade includes a blade tail section. In a blade tail upper portion, the metal plate has a concave-shaped recess and a rib formed on an inner surface side thereof and the metal plate further has slits formed by slitting on a blade pressure side thereof, so that droplets affixed on a blade surface can be guided into an inside of the hollow blade when the blade tail section is joined to the hollow blade main unit. The recess in the metal plate is covered so as to be lidded by a suction-side protrusion of a suction-side metal plate from a blade suction side to thereby form a hollow blade tail section. The metal plates are welded together to the main unit.

Abstract: A method for manufacturing a bearing includes the following steps: a) providing of an outer part with a concave running surface which forms a receiving area for receiving an inner part, b), providing an inner part that is arranged inside the outer part, which inner part is shaped annularly, c) arranging the inner part within the outer part in a machining position in which at least a part of an outer surface of the inner part is exposed for machining, and d), generating of a convex running surface of the inner part, which running surface engages with the receiving area of the outer part whereby the inner part is held captively in the outer part. Subsequently, the inner part may be tilted from the machining position into a running position in which the inner part is concentric with the outer part.

Abstract: A turbocharger, with a turbine for expanding a first medium that includes a turbine rotor and a turbine housing, a compressor for compressing a second medium that includes a compressor rotor coupled to the turbine rotor via a shaft and a compressor housing, a bearing housing in which the shaft is mounted, a bearing housing cap delimiting the bearing housing facing the turbine, and a turbine cover delimiting the turbine on a side facing the bearing housing and has a section projecting into a recess of the bearing housing cap. On a section of the bearing housing cap delimiting the recess of the bearing housing cap on the outside, which on the outside follows the section of the turbine cover projecting into the recess of the bearing housing cap, an oil trapping lip is formed on a side of the bearing housing cap facing the turbine rotor.

Abstract: Turbomachines having one or more flow guiding features designed to increase the performance of the turbomachine (3400, 3700, 4000, 4800). In some examples, flow guiding features are designed and configured to bias a circumferential pressure distribution at a diffuser inlet (2210, 2310, 3410, 4204, 4810, 5208, 808) toward circumferential uniformity, otherwise account for such low-frequency spatial pressure variations, increase the controllability of spatial flow field variations, or modifying flow field variations, etc.

Abstract: A kinetic fluid energy conversion system comprises one or more hubs which rotate about a central hub carrier, each including one or more independently controlled articulating energy conversion plates (“ECP”). An articulation control system rotates each ECP independently of all others to control its orientation with respect to the fluid flow direction between an orientation of 90° perpendicular to the fluid flow, while traveling in the direction of the flow and 0° minimal drag parallel position to the flow, while traveling in the direction against the flow or blocked from it. Each hub can be operably coupled to another hub to form one or more counter-rotating hub and ECP assemblies whereby the mechanical energy is transferred through the hubs, to one or more clutch/gearbox/generator/pump assemblies thereby permitting such assemblies to be land-based when the system is air-powered, and above or near the surface, when the system is water-powered.

Abstract: A centrifugal compressor includes an electric motor coupled to a low-speed shaft, an impeller, and a speed increaser. The speed increaser includes a ring member, a high-speed shaft, rollers, a speed increaser housing member, a discharge passage, and a partition. The ring member includes a circumferential wall and is rotated when the low-speed shaft rotates. The high-speed shaft is coupled to the impeller. The rollers are located between the circumferential wall and the high-speed shaft. The speed increaser housing member stores oil. The discharge passage discharges oil out of the ring member. The partition is located between the speed increaser housing member and the circumferential wall in the radial direction. Power is transmitted from the low-speed shaft to the high-speed shaft by the ring member and the rollers.

Abstract: A method for making a railcar having a span bolster is disclosed. The method involves fabricating and joining the components of the span bolster in a manner such that a camber is built into span bolster. A camber is cut into longitudinal supports that span the length of the bolster. A jig is used to shape top and bottom plates prior to attaching the plates to the longitudinal supports, thus forming the bolster. Truck assemblies are attached to the bolster and a railcar body mounted to the combined unit.

Abstract: A turbine vane assembly adapted for use in a gas turbine engine includes a support strut and a turbine vane arranged around the support strut. The support strut is made of metallic materials. The turbine vane is made of ceramic matrix composite materials to insulate the metallic materials of the support strut.

Abstract: A flexible damper (24) for turbine blades (10) includes a plurality of segments (32) positioned together in a substantially linear pattern, each segment (32) having a first side (46), a second side (48), a top side (50), a bottom side (52), a length (56), a width (54), and a thickness (58).

Abstract: A gas turbine and a method for replacing a bearing thereof to easily adjust a clearance of a bearing housing and a bearing covering a tie rod, such that the bearing can be easily replaced is disclosed.

Abstract: A compressor includes a compressor screen mounted on the outer circumferential surface of a compressor disk or the inner wall of a compressor casing. The compressor screen is positioned between a row of compressor blades and a row of compressor vanes to stabilize airflow by regulating the amount of air flowing in the compressor. The compressor screen is formed of annular plate having openings through which the compressed air flows, arranged in a pattern to smoothly regulate the flow of air. The compressor screen may be variously configured, for example, to facilitate installation or to guide the flow of air using a tapered surface or a directionality of the openings or a flow guide. A gas turbine includes a combustor, a turbine, and a compressor employing the compressor screen.

Abstract: A method including providing a mold cavity to produce an outer contour of an acoustic resonator and providing a mold core to produce an inner contour of the resonator. The inner contour corresponds to a plenum, and a connecting channel in fluid communication with the plenum. An insert fitting adjacent to the mold core defines a length of the connecting channel during injection molding of the resonator.

Abstract: A multi-shaft assembly includes an inner shaft and an outer shaft coaxially aligned with the inner shaft to establish a shared axis of rotation. The multi-shaft assembly also includes an ablatable shaft feature with a lubricant surface coating on an interior surface of the outer shaft and an ablatable metallic alloy layer overlaying a portion of the lubricant surface coating with a radial air gap formed between the ablatable metallic alloy layer and an exterior surface of the inner shaft.

Abstract: A variable diffuser for a centrifugal compressor comprises a passage between opposing disc faces and a plurality of vanes extending therethrough with a fixed angle relative to the engine centerline. Axial displacement between the opposing disc faces is variable. The vanes extend through one of the opposing disc faces as that disc face is axially translated.

Abstract: A blade/vane cascade segment of a blade/vane cascade for a turbomachine is disclosed, which comprises a stage with a stage surface as well as a first blade/vane element and a second blade/vane element. The stage surface comprises a first elevation reaching as far as the pressure side of the first blade/vane element and a second elevation reaching as far as the suction side of the second blade/vane element. A furthest downstream point of a boundary of the second elevation has an axial position which differs from the axial position of at least one highest point of the first elevation by a maximum of 10% of an axial cascade span. Furthermore, a blade/vane cascade, a blade/vane channel, a stage, a turbomachine and an aircraft engine are disclosed.

Abstract: Aspects of the disclosure are directed to an inlet cap, comprising: a first lug slot located proximate a perimeter of the inlet cap, and a second lug slot located proximate the perimeter of the inlet cap and located peripherally adjacent to the first lug slot, where the first lug slot includes a first ply, the second lug slot includes a second ply that is different from the first ply, and at least a third ply is common to the first lug slot and the second lug slot.

Abstract: A method for producing a turbine rotor includes forming a rotor base material having a maximum outer diameter of 1000 mm or less from low-alloy steel including carbon, silicon, manganese, nickel, chromium, molybdenum, and vanadium; heating the rotor base material, by a quenching process, to a temperature range of 940° C. to 960° C.; performing oil quenching on the rotor base material, after the quenching process, in a temperature range of 250° C. to 500° C., at a cooling rate of at least 2.0° C./min; and tempering the rotor base material, after the quenching process, at a temperature of at least 630° C., and under a condition that a tempering parameter P is in the range of 19700 to 19900, wherein P is defined by the formula P=T (C+log(t)).

Abstract: A gas turbine engine has a compressor section with a low pressure compressor and a high pressure compressor having a downstream end. A cooling air system includes a tap from a location upstream of the downstream most location. The tap passes air to a boost compressor, and the boost compressor passes the air back to a location to be cooled. The boost compressor is driven by a shaft in the engine through an epicyclic gear system. A speed control changes the relative speed between an input and an output to the epicyclic gear system.

Abstract: Bed foundation beams are sandwiched by a compression bar extending parallel to the first and second rails and moved towards the first and second rails while being conveyed. Further, the first and second rails and the spacers are sandwiched against spaced fixtures on an endless chain. While being compressed and sandwiched, staple guns fasten the rails and spacers together. The fixtures include front and back stops, with the back stop pivotable about a fixture axis to be movable by a cam moving in a cam track from a pushing position extending perpendicular to the endless chain and abutting with a trailing edge of one of the spacers and a non-intervening position after the staple gun and before the sprocket of the endless chain to reduce the apparatus footprint.