Abstract: A method of making an aluminum airfoil includes brazing a first airfoil piece and a second airfoil piece together using a braze material that includes an element selected from magnesium and zinc, to form a braze joint between the first airfoil piece and the second airfoil piece. At least one of the first airfoil piece or the second airfoil piece has an aluminum alloy composition that includes greater than 0.8% by weight of zinc.

Abstract: A wind-powered machine system includes a base station including a machine for performing work and a crankshaft operatively coupled to the machine. The rotation of the crankshaft drives the machine to perform work. The system further includes a first and a second airfoil operatively coupled to the crankshaft. In a first stage, a wind-driven movement of the first airfoil in a first direction away from the base station causes the crankshaft to rotate. The rotation of the crankshaft causes a movement of the second airfoil in a second direction generally opposite to the first direction and toward the base station. In a second stage, a wind-driven movement of the second airfoil in the first direction away from the base station causes the crankshaft to rotate. The rotation of the crankshaft causes a movement of the first airfoil in the second direction toward the base station.

Abstract: A rotary pump has a pump housing enclosing a flow space and provided with an intake opening and a discharge opening, wherein the intake opening and the discharge opening are connected to each other by the flow space. An impeller wheel is disposed in the flow space and is driven in rotation. An expansion body is provided that is fluidically connected to the flow space. A spiral casing surrounds, in a mounted position in the pump housing, an outer circumference of the impeller wheel, wherein the spiral casing is a single-part or multi-part shaped component and is embodied separate from the pump housing.

Abstract: A gas turbine engine has a plurality of compressor rotors, as well as a plurality of turbine rotors. A tie shaft of the engine is constrained to rotate with the compressor and turbine rotors during normal operating conditions. Further, an upstream hub is in threaded engagement with the tie shaft. The threads of the upstream hub are handed in a first manner when viewed from an upstream location. A downstream abutment member is positioned downstream of the turbine rotors and is also in threaded engagement with the tie shaft. Threads of the downstream abutment member are handed in the first manner when viewed from a downstream location. Accordingly, the compressor and turbine sections of the engine are reliably held together, and the tie shaft is substantially prevented from unwinding.

Abstract: A stationary ground tube for use in an aircraft rotor fairing includes a first cylindrical portion including a first bore aligned along a longitudinal axis, the cylindrical body portion having a tubular body from a first end to a second end; and a second cylindrical portion coupled to the first cylindrical portion, the second cylindrical portion including a second bore aligned along the longitudinal axis. The second cylindrical portion is coupled to the aircraft rotor fairing via at least one attachment device.

Abstract: There is provided a centrifugal fan including an upper casing which has an air suction opening, a lower casing, and an impeller which is disposed between the upper casing and the lower casing. The impeller includes an upper shroud which is provided on an upper casing side, and a plurality of blades which are arranged along a circumference direction below the upper shroud, and is rotatable around a rotary shaft. The upper casing and the lower casing configure an open-type casing. A surface of the upper shroud facing the upper casing includes a first portion which becomes closer to the lower casing as separating further from the rotary shaft. A surface of the upper casing facing the upper shroud includes a second portion which faces the first portion of the upper shroud and becomes closer to the lower casing as separating further from the rotary shaft.

Abstract: The present disclosure relates to a seal assembly for a turbomachine that includes at least one arcuate plate, a biasing member, and a packing ring. In addition, the seal assembly includes a plurality of arcuate teeth disposed intermediate to the packing ring and the rotor. The plurality of arcuate teeth includes at least one subset of arcuate teeth. The clearance of at least one of the arcuate teeth is different from the clearances of the rest of the arcuate teeth. The clearances of the arcuate teeth of the at least one subset do not progressively increase going from an upstream to a downstream side of the turbomachinery.

Abstract: A method of manufacturing a shell construction part of a wind turbine blade, the shell construction part being made of a fibre reinforced polymer material including a polymer matrix and fibre reinforcement material embedded in the polymer matrix. The method comprises the steps of a) providing a forming structure comprising a mould cavity and having a longitudinal direction, b) placing the fibre reinforcement material in mould cavity, c) providing a resin in the mould cavity simultaneously with and/or subsequently to step b), and d) curing the resin in order to form the composite structure, wherein at least 20% by volume of the fibre reinforcement material consists of metallic wires.

Abstract: A ceiling fan blade includes a lower blade and an upper blade combined together. The lower blade is provided with a recess and secured thereon with a plurality of engage fasteners, and the upper blade is formed with a recess and embedded therein with a plurality of engage posts respectively corresponding with the engage fasteners. The engage post is engaged with the engage fastener to form a one-way engagement for reinforcing combination of the upper blade with the lower blade. The ceiling fan blade of this invention can not only conform to environmental protection but also avoid being broken apart when used to insure safety in use. In addition, the ceiling fan blade of this invention is hollow in structure, able to lighten the blade, and no locking member is provided on the surface of the blade, able to keep beautiful external features of the ceiling fan.

Abstract: The present application provides a steam turbine side support system for use with a steam turbine having a rotor. The steam turbine side support system may include a shell for the steam turbine, a number of side support arms extending from the shell in a perpendicular configuration with respect to the rotor, and a foundation in communication with the side support arms.

Abstract: The main rotor control system includes a rise/fall swashplate assembly that is coupled to three triplex actuators. The swashplate assembly is configured to provide full collective and cyclic pitch controls. Each triplex actuator includes three piston/cylinder assemblies in parallel. Selective actuation of each triplex actuator is controlled by a fly-by-wire system in conjunction with three flight control computers and three hydraulic power packs. Integrated three function valves can be associated with an individual manifold for each piston/cylinder assembly of each triplex actuator, the integrated three function valve be configured to insure safe operation of the triplex actuator during a failure of a certain piston/cylinder assembly.

Abstract: A structural joint includes a first flange, a second flange and a fastener with a head and a shaft. The first flange extends out from a first component to a distal first flange end. The second flange extends out from a segmented second component to a distal second flange end. The second flange includes a first lateral flange segment that extends laterally to a first flange sidewall, and a second lateral flange segment that extends laterally to a second flange sidewall, which is engaged with the first flange sidewall. The head is encased in the second flange and extends laterally into the first flange sidewall and the second flange sidewall. The shaft extends longitudinally out from the second flange and through the first flange.

Abstract: Wind turbine rotor blades with a reduced radar cross sections include a shell having a leading edge opposite a trailing edge, a structural support member that supports the shell and is disposed internal the wind turbine rotor blade between the leading edge and the trailing edge and extends for at least a portion of a rotor blade span length, wherein the structural support member comprises carbon fiber, one or more cavities internal the wind turbine rotor blade, and a lightweight broadband radar absorbing filler material disposed in at least one of the one or more cavities to provide the reduced radar cross section.

Abstract: A turbine blade for a gas turbine engine includes an airfoil that includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending from a platform in a radial direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate scaled by a local axial chord. A circumferential coordinate is scaled by a local axial chord, and a span location. The local axial chord corresponds to a width of the airfoil between the leading and trailing edges at the span location.

Abstract: Apparatus is provided featuring a bearing cartridge in combination with a pedestal. The bearing cartridge may be configured to be coupled to a pumping assembly combination and having a predetermined centerline. The pedestal may be configured with an axial channel to receive and support the bearing cartridge and allow the bearing cartridge to slide therein. The bearing cartridge and the pedestal are configured to couple together substantially at or above the centerline of the bearing cartridge in order to reduce center height requirements of the apparatus, where the center height is defined as the distance between the centerline of the bearing cartridge and the bottom surface of the pedestal supporting the bearing cartridge. The apparatus takes the form of a pump or pumping assembly, arrangement or combination, including a slurry-type pump or a centrifugal pump.

Abstract: A cooled turbine blade comprises a root for fixing the blade to rotor, an airfoil extending along a radial axis from the root, and a tip shroud disposed at a radially outward end of the airfoil. The tip shroud extends in a circumferential direction from the airfoil and defines, within itself, a core plenum and a peripheral plenum. The airfoil defines an aft airfoil cooling passage that extends radially through the airfoil proximate a trailing edge portion of the airfoil. The airfoil also defines an aft cooling inlet for providing an aft stream of cooling fluid to the aft airfoil cooling passage. The airfoil also defines at least one aft cooling exit for discharging the aft stream of cooling fluid from the aft airflow cooling passage to the peripheral plenum. The tip shroud defines at least one peripheral plenum vent for discharging the aft stream of cooling fluid.

Abstract: A turbine section of a turbine engine includes rotatable structure, an outer casing disposed about the rotatable structure, and an inner casing disposed about the rotatable structure and suspended radially inwardly from the outer casing. Rotation of the rotatable structure during operation drives at least one of a compressor and a generator. The inner casing defines a hot gas flow path through which hot combustion gases pass during operation. The inner casing comprises a plurality of wall sections. Each wall section includes a panel having an inner portion and an outer portion opposed from and affixed to the inner portion. The inner portion at least partially defines the hot gas flow path and the inner portion is radially spaced from the outer portion such that a substantially fluid tight chamber is formed therebetween. The fluid tight chamber reduces thermal energy transfer from the inner portion to the outer portion.

Abstract: An example turbomachine assembly includes, among other things, a nose cone of a turbomachine, and a pump that is selectively driven by a motor or a shaft to communicate air to an interior of the nose cone. The pump shaft is driven by a dedicated geared architecture.

Abstract: A rotor assembly includes a first rotor having first tabs and a second rotor that is arranged coaxial with the first rotor and that includes second tabs that are interlocked with the first tabs. A retainer locks the first tabs and the second tabs together.

Abstract: A gas turbine engine system is disclosed which includes a core passage and a bypass passage which can be configured as a fan bypass duct or a third stream bypass duct. The core passage and bypass passage are routed to flow through a nozzle before exiting overboard an aircraft. The nozzle includes moveable members capable of changing a configuration of the nozzle. In one form the moveable members are capable of changing throat areas for portions of the nozzle that receive working fluid from the core passage and the bypass passage. The bypass passage can include a branch. In one form the branch can include a heat exchanger. The bypass passage can also provide cooling to one or more portions of the nozzle, such as cooling to a deck of the nozzle.