Abstract: A turbine exhaust case has an outer housing to be secured within a gas turbine engine and a central hub. Struts extend between the outer housing and the central hub. The struts are formed at least in part of a first material. The central hub is formed at least in part of a second material.

Abstract: The invention relates to a guide vane ring with at least one guide vane ring segment for a turbomachine, including a plurality of guide vanes arranged radially around an axis of rotation, an outer shroud arranged radially on the outer side of the guide vanes, and an inner shroud arranged radially on the inner side of the guide vanes, wherein the outer shroud or the inner shroud has at least one expansion joint, wherein the guide vane ring segment is formed in one piece with the guide vanes, the outer shroud, and the inner shroud and the at least one expansion joint is sealed in each case by at least one sealing device arranged in the respective expansion joint.

Abstract: A rotor hub for a wind turbine, comprising a first device for lifting and/or transporting being arranged in a first interior of the rotor hub is provided. Further a wind turbine comprising the rotor hub is suggested. The rotor hub is applicable for all kinds of wind turbines.

Abstract: A blade (10) for a rotor of a wind turbine (2) is disclosed. The blade is assembled from an inboard blade part (50) closest to the hub and an outboard blade part (110) farthest from the hub of the wind turbine. The inboard part (50) comprises a load carrying structure (60) with a first aerodynamic shell (70) fitted to the load carrying structure (60), and the outboard part (110) comprises a blade shell (141, 143) with a load carrying structure (142, 144) integrated in the blade shell (141, 143).

Abstract: A gas turbine engine includes a turbine section that has a disk rotatable about an axis. The disk has circumferentially-spaced blade mounting features and radially outer rim surfaces extending circumferentially between the blade mounting features. Turbine blades are mounted circumferentially around the disk in the blade mounting features. Seals are arranged radially outwards of the disk adjacent the radially outer rim surfaces such that there are respective passages between the seals and the radially outer rim surfaces. The radially outer rim surfaces include radially-extending protrusions that extend into the respective passages.

Abstract: A turbomachine fan blade preform (10) comprising a pair of mutually opposing panels (12), and a membrane (20) sandwiched between the pair of panels (12). The membrane (20) is of a non-uniform thickness. The thickness of at least a portion of the membrane tapers along its length and/or width, between a relative thicker first region and relatively thinner second region.

Abstract: An impeller for used in a fluid pump device includes a shaft controlled to revolve in a first direction; an impeller body coupled to the shaft and driven by the revolving shaft to rotate, the impeller body having a top surface, a bottom surface and a circumferential surface; a first set of fluid-guiding members disposed on the top surface of the impeller body for driving a fluid to flow along a centrifugal direction of the revolving shaft; and a second set of fluid-guiding members disposed on the circumferential surface of the impeller body. Each or at least one of the second set of fluid-guiding members has a titling structure for driving the fluid to flow from the top to the bottom of the impeller along a designated path on the circumferential surface.

Abstract: A drive mechanism is provided for driving at least two adjusting members used to adjust the orientation of the blades of a turbomachine rectifier vane associated therewith, where the drive mechanism simultaneously drives the displacement of at least two adjusting members in the turbomachine. A single threaded rod drives several levers, each lever being associated with an adjusting member. A first part of each lever engages with the threaded rod and one end of an arm of the lever is connected to the adjusting member associated therewith so that the rotation of the threaded rod causes a simultaneous rotation of the levers associated with the adjusting members.

Abstract: A rotor blade for a gas turbine configured for use within a row of samely configured rotor blades. The rotor blade may include an airfoil defined between pressure and suction faces and a midspan shroud. The midspan shroud may include pressure and suction wings. The pressure wing and suction wing of the midspan shroud may be configured so to cooperatively form an interface between neighboring ones of the rotor blades within the row of samely configured rotor blades. The interface may include: a pressure wing contact face disposed on the pressure wing that opposes across a gap a suction wing contact face disposed on the suction wing; and a predetermined offset between the pressure wing contact face and suction wing contact face. The predetermined offset may be configured for desirably aligning the contact faces when an expected operating condition closes of the gap.

Abstract: Systems and methods related to linear turbine systems are presented. Each embodiment described herein may be designed as a single-stage, linear, impulse turbine system. In an embodiment, a linear turbine includes a first shaft extending along a first axis; a second shaft extending along a second axis, the second axis being separated from and substantially parallel to the first axis; a first plurality of buckets to travel a first continuous path around the first shaft and the second shaft along a first plane, the first path including a first substantially linear path segment between the first axis and the second axis; and a nozzle configured to direct a first fluid jet to contact the first plurality of buckets in the first linear path segment.

Abstract: An actuator includes a pump including a first cavity and a diaphragm coupled in flow communication with the first cavity. The diaphragm is configured to pressurize a fluid contained in the first cavity. The pump further includes a first valve coupled in flow communication with the first cavity. The first valve is configured to release fluid from the first cavity when the first cavity is pressurized. The actuator also includes a piston assembly operatively coupled to the pump.

Abstract: A fan section comprises a fan rotor having a plurality of blades and a spinner positioned forwardly of the fan rotor. The fan rotor is driven through a gear reduction. The spinner includes a spinner body having an outer surface with a forward end and a rearward end. A conical line extends between the forward end to the rear end. A first radius is measured from a centerline of the spinner at substantially 0.25 of a length of the spinner to the conical line. A second radius is also measured at substantially 0.25 of the length and extends outwardly to the outer surface of the spinner. A ratio of the second radius to the first radius is less than or equal to about 2.0. A gas turbine engine is also disclosed.

Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a rotating component, a turbine engine component and a lubrication system. The lubrication system is adapted to lubricate the turbine engine component where the rotating component rotates a first direction about an axis. The lubrication system is also adapted to lubricate the turbine engine component where the rotating component rotates a second direction about the axis.

Abstract: A centralizing assembly for an engine having a plurality or rotatable vanes is provided including an engine casing and at least one unison ring disposed concentrically there about. A spacing gap is formed between the unison ring and the engine casing and is variable between a maximum spacing gap and a minimum spacing gap in response to thermal expansion of the engine casing. A centralizer element includes a plunger element movably mounted to unison ring and spanning the spacing gap. At least one conical spring washer is mounted to the plunger element and exerts a centralizing force through the plunger element onto the engine casing. The at least one conical spring washer maintains the centralizing force between the maximum spacing gap and the minimum spacing gap.

Abstract: The high performance mini-pump for liquids includes a motor assembly including a motor to supply power to the pump, and a housing assembly including a housing. The housing has a first housing portion and a second housing portion removably connected to the first housing portion defining an inner chamber therein. The housing assembly also includes an impeller provided in the inner chamber of the housing, and at least one fastening member to removably connect the first housing portion and the second housing portion. The pump further comprises a shaft assembly removably connected to the impeller and operatively connected to the motor, such that when the high performance pump is activated, the motor rotates the impeller, forcing fluid to flow through the housing.

Abstract: A compressor device for a turbocharger. The compressor device includes a compressor housing and a separate snorkel member which are provided separately and then connected together. The compressor housing has two air passages separated by a partition wall, while the snorkel member similarly has two separate air ducts separated in part by a partition wall. The two components have mating fittings to connect them together.

Abstract: In a seal member, a turbine, and a gas turbine, a plurality of vanes includes a vane main body extending in a radial direction of an axis, an outer shroud, an inner shroud and forming a main flow path of a combustion gas between the outer shrouds and the inner shroud, and a retainer protruding from an inner surface in the radial direction of the inner shroud to the inside in the radial direction. The retainers in the vanes, which are adjacent to each other in the circumferential direction, are adjacent to each other in the circumferential direction via a third gap, and relative to one end of the seal member, the other end is positioned downstream in a direction along the axis in the combustion gas to close the third gap.

Abstract: Systems and methods related to linear turbine systems are presented. Each embodiment described herein may be designed as a single-stage, linear, impulse turbine system. In an embodiment, a linear turbine includes a first shaft extending along a first axis; a second shaft extending along a second axis, the second axis being separated from and substantially parallel to the first axis; a first plurality of buckets to travel a first continuous path around the first shaft and the second shaft along a first plane, the first path including a first substantially linear path segment between the first axis and the second axis; and a nozzle configured to direct a first fluid jet to contact the first plurality of buckets in the first linear path segment.

Abstract: An inlet for a turbofan engine, including an inlet wall surrounding an inlet flow path. The inlet wall extends axially from an upstream end to a downstream end adjacent the fan. The inlet wall has a shape defining a plurality of teeth circumferentially spaced around the inlet. The teeth extend axially and project radially inwardly toward the central longitudinal axis. A central portion of the inlet flow path has a cross-sectional dimension measured diametrically between opposed teeth, the cross-sectional dimension varying along the axial direction. The central portion defines a geometric throat at a minimum value of the cross-sectional dimension. The inlet wall is shaped so that the geometric throat is axially spaced from the upstream end and the downstream end. A gas turbine engine and a method of shielding tips of fan blades from impact by an object having a predetermined minimum dimension are also discussed.

Abstract: A molten metal rotor receives and retains an end of a molten metal rotor shaft. The rotor shaft has one or more projections at the end received in the rotor. The rotor has an inner cavity, a top surface with an opening leading to the inner cavity, and at least one abutment. The opening includes one or more portions for allowing each projection to pass through the opening and into the inner cavity. The rotor and/or shaft are then rotated so at least one of the outwardly-extending projections is under the top surface of the rotor and is against an abutment. A molten metal pump, rotary degasser scrap melter or other device used in molten metal may utilize a rotor/shaft combination as disclosed herein.