Abstract: A fluid power-generating system operatively disposed between a first support and a second support, the system characterized by an absence of a centrally disposed rotor member, and including a machine capable of acting as a motor and as a generator, the machine coupled to the first support; a flexible wing(s) having an arcuate shape, a distal end coupled to the machine and a proximal end coupled to the second support, for catching and passing a flowing fluid; a tensioned balancing system coupled to the supports for stabilizing operation of the power-generating system; and a rigid strut(s) disposed between each flexible wing and the balancing system for supporting each flexible wing.

Abstract: A system can include a shaft and turbine wheel assembly that includes a seal portion; a bearing assembly that includes an outer race and rolling elements that rotatably support the shaft and turbine wheel assembly; a sleeve that includes an outer diameter and a through bore that includes a first inner diameter that accommodates an outer diameter of the outer race of the bearing assembly and a second, smaller inner diameter that accommodates an outer diameter of the seal portion of the shaft and turbine wheel assembly; and a center housing that includes a compressor side, a turbine side and a bore that includes a turbine side bore diameter that accommodates the outer diameter of the sleeve.

Abstract: An exhaust gas turbocharger shaft has an impeller connected to the exhaust gas turbocharger shaft in a form-locking manner and is connected to a shaft nut provided on an outer shell surface of the exhaust gas turbocharger shaft. The shaft nut is inserted into a central bore of the impeller in such a way that the impeller forms a form-locking connection with the shaft nut in the radial direction and the circumferential direction.

Abstract: A turbocharger for a powered machine including a turbine is disclosed. The turbocharger may include a turbine wheel including a disk section, the disk section including a disk body, the disk body including a length extending between a longitudinal axis and a blade platform. The disk section may further include a shoulder section positioned radially outward the longitudinal axis, a neck section positioned radially outward the shoulder section and a throat section positioned radially outward the neck section, an upstream axial plane coextensive with an upstream side of the blade platform, a downstream axial plane coextensive with a downstream side of the blade platform. Further, the turbine burst shield section may have a geometry that peaks in depth in the burst plane which prevents ejection of secondary mass in the event of a turbine burst.

Abstract: A one-way clutch includes: a plurality of engaging elements which restrict relative rotation toward the other side of a circumferential direction by engagement with an inner ring outer circumferential surface and an outer ring inner circumferential surface and which allows the relative rotation along the other side of the circumferential direction by releasing the engagement; and a ring-shaped cage which holds the engaging elements. In a clutch unit, a positioning member which is capable of contact a side surface of the cage in an axial direction and which positions the cage along the axial direction is provided between the one-way clutch and a rolling bearing.

Abstract: The invention refers to a method for producing a near-surface cooling passage in a thermally highly stressed component, which includes: a) providing a component which has a surface on a hot side in a region which is to be cooled; b) letting a channel into the surface; c) inserting a cooling tube into the channel; d) filling the channel, with the cooling tube inserted, with a temperature-resistant filling material in such a way that the inserted cooling tube is embedded into the filling material, leaving free an inlet and an outlet; and e) covering the channel, with the cooling tube embedded, with an anti-oxidation, temperature-stable cover layer. The method is inexpensive and can be used in a flexible manner in the most diverse situations in order to save cooling medium or to reduce the thermal load.

Abstract: An assembly can include a first radial compressor wheel that has a rotational axis and that includes a hub surface that includes an annular ridge disposed at a radius measured from the rotational axis; a second radial compressor wheel that includes a hub surface; and an annular baffle disposed at least in part between the hub surfaces where the annular baffle includes an outer surface and an inner edge that defines an opening having a central axis where the outer surface includes a surface portion to one side of the inner edge that faces the hub surface of the first radial compressor wheel, where the surface portion includes an annular channel over a radial width measured from the central axis and where the radial width spans the radius of the annular ridge.

Abstract: A power transmission system for a turbine engine is provided. The power transmission system includes a transmission shaft that is connected to a drive shaft by bevel gears, and that drives equipment or accessories. The transmission shaft is designed to operate under supercritical conditions and includes a damper system for damping vibration at its resonant speed.

Abstract: A propeller blade assembly includes a spar extending along a propeller blade axis and an outer sleeve surrounding the spar portion at a root end of the rotor blade assembly. The spar is adhesively bonded to the outer sleeve at an interface portion. A spar maximum diameter along the interface portion is larger than an outer sleeve minimum diameter along the interface portion. A method of assembling a propeller blade includes installing an outer sleeve over a spar at a root end of the spar, the spar a not fully cured composite component, and urging the spar into compressive conformance with the outer sleeve at an interface portion of the propeller blade assembly. A spar maximum diameter along the interface portion is larger than an outer sleeve minimum diameter along the interface portion. The spar is cured thereby adhesively bonding the spar to the outer sleeve at the interface portion.

Abstract: A nickel-base superalloy is disclosed. The superally includes aluminum, cobalt, chromium, molybdenum, tantalum, titanium and tungsten, in addition to nickel, as alloy constituents, wherein rhenium can additionally be contained and the rhenium content is less than or equal to 2 wt. % and wherein the titanium content is greater than or equal to 1.5 wt. %. Further disclosed is a component made of the nickel-base superalloy.

Abstract: A rotor assembly for use in a gas turbine engine having an axis of rotation includes a plurality of rotor blades. Each rotor blade includes a platform extending between opposing side faces, a shank extending radially inward from the platform, and a slot at least partially defined in each of the opposing side faces. A sealing member is configured to be inserted into each slot of a first rotor blade of the plurality of rotor blades such that at least a portion of each sealing member extends beyond one of the opposing side faces. A second rotor blade of the plurality of rotor blades is coupled adjacent the first rotor blade such that at least a portion of one sealing member is inserted into a corresponding second slot on the second rotor blade.

Abstract: A system includes a turbomachine rotor having a shaft and turbomachine blades coupled to the shaft. The system also includes a turbomachine stator having a shroud surrounding the turbomachine blades of the turbomachine rotor. Further, the system includes a cooling channel having at least a first portion of the cooling channel extending upstream of a final stage of a compressor of the system, where the cooling channel is configured to receive cooled compressed air from the compressor and direct the cooled compressed air adjacent to the turbomachine rotor to reduce thermal expansion and/or axial displacement of the turbomachine rotor.

Abstract: A rotor disk is provided. The rotor disk may comprise a disk lug and a trench. The disk lug may be fixed to a distal surface of the rotor disk. The trench may be disposed on a surface of the disk lug. The trench may extend radially inwards from a distal surface of the disk lug. The trench may be configured to at least partially define a flow path by which cooling air may reach a distal surface of the disk lug in order to provide disk lug cooling.

Abstract: An exhaust gas turbocharger may include a turbine housing and a turbine wheel. The turbine wheel may include a first quantity of a plurality of moving blades. The turbine wheel may be rotatable relative to the turbine housing about a turbine wheel center of rotation and have a turbine wheel radius. A variable turbine geometry may include a blade bearing ring on which a second quantity of a plurality of guide blades are rotatably mounted in each case about a guide blade center of rotation. The plurality of guide blades may be adjustable between a closed position, in which a flow cross section between the guide blades for an exhaust gas to flow through is at a minimum, and an opened position, in which the flow cross section is at a maximum.

Abstract: A pump system for high pressure, high volume applications is presented. The pump system includes a turbo-shaft engine having a drive shaft and a high pressure, high RPM centrifugal pump coupled to the drive shaft. In certain embodiments the pump system further includes a second low pressure, high RPM centrifugal pump coupled to the drive shaft.

Abstract: A method of de-icing a wind turbine blade (5) comprises the steps of: generating heated air using heating means (10) provided in the root portion of the blade; and continuously circulating the heated air around the interior of the blade through at least a portion of two more longitudinal blade cavities (24, 26, 28) defined within the blade. The circulating step includes: channeling the heated air from an outlet (32a) of the heating means at least part way through a first longitudinal blade cavity (26), towards the tip end (18) of the blade; at a position along the length of the blade, diverting the heated air from the first longitudinal blade cavity (26) into a second longitudinal blade cavity (24); and channeling the diverted air at least part way through the second longitudinal blade cavity (24) back to an inlet (34) of the heating means (10). The heated air is circulated through at least a central cavity (24) and a leading edge cavity (26) defined between longitudinal webs (22) within the blade.

Abstract: A supporting structure for a gas turbine engine comprises an inner ring, an outer ring, and a plurality of circumferentially spaced, load carrying radial elements connecting the inner and outer rings, said radial elements being configured to transfer loads between the inner ring and the outer ring, wherein a gas channel for a primary axial gas flow is defined between the inner and outer rings, wherein the supporting structure has an inlet side for primary gas flow entrance and an outlet side for primary gas outflow, wherein the radial elements have an airfoil shape with a leading edge directed towards the inlet side, a trailing edge directed towards the outlet side, and two opposite sides connecting the leading edge and the trailing edge, and wherein at least a first of said radial elements is connected to an adjacent part of the supporting structure via a weld joint that extends across the leading edge and circumferentially at least partly around the first radial element.

Abstract: Provided is a seal device configured to prevent leakage of a fluid on an outer circumferential surface of a rotary shaft in a direction along an axis of the rotary shaft. The seal device includes an annular main body section disposed in a circumferential direction of the rotary shaft, and a plurality of at least two kinds of holes formed in an inner circumferential surface of the main body section opening and facing to the outer circumferential surface of the rotary shaft, and having different depths.

Abstract: The present invention relates to a gas turbine casing arrangement having a gas turbine casing element (10), a guide-vane ring with an outer ring (20), and a coated ring (30), which lies radially opposite a rotor grid (40) adjacent to the guide-vane ring, whereby an intermediate ring (50) by a downstream front face (51) engages behind an upstream stop (61; 61?) fixed in place on the casing element, and by an upstream front face (52) of a radial flange (53) of the intermediate ring engages behind a downstream stop (22) fixed in place on the outer ring, in order to secure the guide-vane ring axially at the gas turbine casing element in the direction of through-flow.

Abstract: An electric actuator for control of an engine includes an electric motor coupled to a drive shaft that extends to align a gear interface of the electric actuator with a variable geometry adjustment interface of the engine. A position feedback shaft extends coaxially with respect to the drive shaft. The position feedback shaft is coupled to an output shaft of the gear interface at a gear interface end of the position feedback shaft. A rotational position sensor is coupled to a motor end of the position feedback shaft proximate the electric motor. The drive shaft and the position feedback shaft are sized to position an output ring gear of the output shaft in contact with the variable geometry adjustment interface within a casing of the engine and to further position the electric motor and the rotational position sensor external to the casing of the engine.