Abstract: A portable storage silo comprising a tank has a peripheral wall, a top wall and a bottom wall. There is provided a filling opening at or adjacent a top of the tank and a discharge opening at or adjacent a bottom of the tank. A support assembly for holding the tank with the bottom wall raised from the ground such that the discharge opening is raised for discharge into a receptacle at the ground. The support assembly includes a base for resting on the ground. The base including a plurality of arms connected to the base and located at spaced positions around the base. The discharge opening has an electrically actuated gate arrangement. The filling opening has an electrically actuated lid. The actuators at the discharge opening and the filling opening are solar powered.

Abstract: A groove inclined path for diagonally downwardly delivering hydrogenated petroleum resin pellets loaded through a loading port is provided in a storage hopper for storing the hydrogenated petroleum resin pellets. The groove inclined path is defined by a plurality of groove-inclined-path members each having an inclined plate and side plates to define a groove structure, the groove-inclined-path members being vertically disposed so that flow directions of the hydrogenated petroleum resin pellets become opposite. The vertically adjacent ones of the groove-inclined-path members are disposed so that the hydrogenated petroleum resin pellets dropped from upper one of the groove-inclined-path members are brought into contact with the plate member of immediately lower one of the groove-inclined-path members to reverse a flow direction thereof, thereby reducing a flow speed of the hydrogenated petroleum resin pellets.

Abstract: An overhead material handling system and methods for its use are provided, where the system comprises: (a) a compactor and (b) a leveler in communication with the compactor, where the leveler comprises (i) a cover, (ii) a trough, and (iii) a trigger, where the trough has a first end and a second end and the trough is rotatably-mounted between a first end of the cover and a second end of the cover.

Abstract: The present invention relates to a trailer loading ramp with a trailer ramp platform and a ramp platform that may include hydraulic cylinders to move between loading and hauling positions. The trailer ramp platform and ramp platform may allow for ease of loading by providing access from the ground surface when the trailer loading ramp is in the loading position and may retract to avoid the ground when in the hauling position.

Abstract: A vehicle loading apparatus with stanchions mounted on the first forward corners of a truck bed by means of saddles straddling the front rail of the truck bed and force stops in the forward stake wells of the truck bed. The (adjustably positioned) force stops are each mounted on a respective torque arm which is attached to a respective saddle. Resilient padding protects painted truck bed surfaces in contact with the stanchions as well as reduces noise and vibration. The vehicle loading apparatus can be installed as is needed, and removed as desired, simply, without tools, and without alterations to most common pickup truck beds.

Abstract: A pill counting tray for counting pills. The pill counting tray includes a digital counter with a sensor that can digitally count the pills as they are being moved by a wand on the tray. The pill counting tray also includes a number of small evenly spaced terrain domes on one part of the tray to prevent the pills from clumping or clustering. The pill counting tray also includes a hinged return funnel that inclines upward when the pill counting tray is placed on a counter during counting, such that the hinged funnel creates a backstop to prevent pills from rolling off of the tray. The hinged funnel will rotate downward when the pill counting tray is lifted to ease the return of excess pills to the stock bottle. A portion of the surface of the hinged funnel also includes a number of spaced terrain domes.

Abstract: A travel control section 60b is configured to control the revolution velocities of transversely opposite travel motors 51 and 52 such that when turning amount command signals are inputted from a turning amount operation dial 48, transversely opposite crawler travel devices 12a and 12b are caused to realize a turn according to the turning amount command signals by decelerating the traveling velocities of the transversely opposite crawler travel devices 12a and 12b from a target straight traveling velocity set by a travel operation lever 47 by equal values of velocity which are predetermined according to the turning amount command signals inputted from the turning amount operation dial 48 and further decelerating the traveling velocity of the crawler travel device 12a or 12b which is positioned inwardly relative to the other in the turning direction.

Abstract: A covering system for removably covering a vehicle, such as a boat, that includes a plurality of rotatively anchored swing arms rotatable between a covered position and an uncovered position. Each swing arm includes a mount and a pretensioner formed of one or more stays adjustably attached to part of a shaft of the arm to adjust an applied preload and transfer forces encountered during operation to part of the shaft rotatively anchored by the mount to a grounded structure such as a piling or post of a dock. The swing arms are pivotally connected to an elongate transversely extending carriage from which a cover is suspended with a boom of each arm connected to the carriage by a pivot assembly that also facilitates carriage and cover position adjustment. A pivot limiter can be included that limits or even stops pivoting of the carriage relative to the swing arm boom.

Abstract: Methods are disclosed for handling cylindrical tubulars in a process that, in preferred embodiments, also performs cleaning, inspection and other operations on the tubular. The tubular is held stationary while it is rotated. During rotation of the tubular, internal and external cleaning systems, and data acquisition systems, pass up and down the length of the rotating tubular. In preferred embodiments, a first tubular is loaded onto the handling machine, whereupon it is indexed and then rotated. Cleaning, inspection and other operations may be performed during rotation. Once operations are complete, the handling system ejects the first tubular while queuing up a second tubular to be loaded.

Abstract: Enhanced methods are disclosed for handling cylindrical tubulars, advantageously in association with cleaning, inspection and other operations on the tubular. The tubular is held stationary while it is rotated. During rotation of the tubular, internal and external cleaning systems, and data acquisition systems, pass up and down the length of the rotating tubular. In preferred embodiments, a first tubular is loaded onto the handling machine, whereupon it is indexed and then rotated. Cleaning, inspection and other operations may be performed during rotation. Once operations are complete, the handling system ejects the first tubular while queuing up a second tubular to be loaded. The handling machine comprises a plurality of user-positional pods. Each pod includes scissor mechanisms, index machines and a roller machine to perform the handling methods. Sensors on drive rollers in the handling machine generate vibrational response data of the tubular while it rotates.

Abstract: Certain embodiments of the disclosure may include systems, methods and apparatus for operating and validating a compressor. According to an example embodiment of the disclosure, a method is provided for validating compressor operation. The method can include receiving compressor operating parameter data from a plurality of sensors; and adjusting a portion of a variable flow area downstream of a compressor discharge to achieve a desired compressor pressure ratio.

Abstract: A gas turbine engine comprises a compressor, a combustor, a turbine, and an electronic engine control system. The compressor, combustor, and turbine are arranged in flow series. The electronic engine control system is configured to generate a real-time estimate of compressor stall margin from an engine model, and command engine actuators to correct for the difference between the real time estimate of compressor stall margin and a required stall margin.

Abstract: A method of operating a turbine assembly is provided. The method includes receiving a flow of air at a filter house that includes a first heat exchanger. The temperature of the air is controlled with the first heat exchanger by one of selectively cooling the air and by selectively heating the air. The air is then channeled from the first heat exchanger to a second heat exchanger to facilitate cooling the air.

Abstract: An exhaust diffuser arrangement for a turbine system includes an inlet for receiving a flow proximate a last stage bucket of the turbine system, the flow flowing in a first flow direction. Also included is a flow redirecting component. The flow redirecting component includes a first wall having a first side of a concave surface geometry for redirecting the flow and a second side of a convex surface geometry. The flow redirecting component also includes a second wall spaced downstream of the first wall and having at least one flow exit for reducing a boundary layer along the second side of the first wall.

Abstract: The present application provides a seal for use between components facing a high pressure cooling air flow and a hot gas path in a gas turbine engine. The seal may include a first surface facing the high pressure cooling air flow, a second surface with a second surface air plenum facing the hot gas path, and a number of cooling pathways extending from the first surface to the second surface air plenum of the second surface for the high pressure cooling air flow to pass therethrough.

Abstract: A compressor (1) of an exhaust-gas turbocharger (ATL), having a compressor wheel (2) and a compressor housing (3) which has a housing longitudinal axis (A). The compressor wheel (2) is arranged in the housing. An inlet duct (5) runs from a compressor inlet (4) to the compressor wheel (2). A recirculation duct (6) has a compressor-wheel-side inflow opening (7) and a compressor-inlet-side return flow opening (8). The inflow opening (7) and the return flow opening (8) can be opened and closed.

Abstract: A vane includes a surface with an aperture having an extended indentation at least partially therearound.

Abstract: A lubrication system for a fan drive gear system includes a lubricant supply and a collection conduit for drawing lubricant from within the lubricant supply. The collection conduit includes a first opening and a second opening for withdrawing lubricant and supplying lubricant to a pump. During normal operation lubricant may be drawn through both first and second openings. During negative G operating conditions a fitting at the second opening blocks the second opening to prevent air from being drawn into the lubricant system and communicated to the pump.

Abstract: Method and gas turbine system having a reduced footprint. The gas turbine system includes a gas turbine configured to produce energy and having a gas turbine shaft; an auxiliary equipment attached to the gas turbine; an overhung shaft of the auxiliary equipment being configured to be attached to the gas turbine shaft; a flexible joint configured to be provided between the shaft of the auxiliary equipment and the gas turbine shaft; and a bearing system having at least two bearing units provided at a first end of the shaft of the auxiliary equipment next to the flexible joint. A second end of the shaft of the auxiliary equipment is free of bearings.

Abstract: A connector between a first object having a first coefficient of thermal expansion and a second object having a second coefficient of thermal expansion has a slot attaching to the second object. The slot formed by an inner shell having a slot shape and a first portion that blends into an outer surface of the second object, the slot having an enclosed portion facing forward and an aft portion that is open.

Abstract: Systems and devices configured to reduce windage and mixing losses in a turbine by redirecting and/or aligning a direction of a leakage flow with the flowpath of the main flow of a turbine are disclosed. In one embodiment, a device includes: a base configured to connect to a diaphragm of a turbine; and a radial portion connected to the base and extending radially inboard from the base toward a rotor of the turbine, the radial portion oriented to adjust a direction of travel of a leakage flow of working fluid radially inboard at an angle complementary to a primary working fluid path of the turbine.

Abstract: A turbomachine has a seal which mates to a plurality of airfoils. The seal is formed from an abradable aluminum based material having a plurality of hard phase particles embedded therein and having a melting point higher than a melting point of the melting point of the abradable coating matrix alloy.

Abstract: An airfoil component for a gas turbine engine includes an airfoil extending from a platform. At least one of the airfoil and the platform includes a cooling passage defined by a surface. A chevron-shaped trip strip extends from the surface into the cooling passage at a trip strip height along a length. The trip strip height varies along the length. A turbine vane for a gas turbine engine includes inner and outer platforms. A cooling passage is provided in the inner platform. The cooling passage is provided by first and second radially extending legs spaced circumferentially apart from one another and joined to one another by a circumferential passage. A pair of airfoils extend radially from the same inner platform. A trip strip extends from the surface into the circumferential passage at a trip strip height along a length. The trip strip height varying along the length.

Abstract: An exemplary gas turbine engine component assembly includes, among other things, a case having a generally cylindrical outer surface. At least one synchronizing ring is received at least partially about the outer surface of the case. A plurality shims situated between an inner surface on the at least one synchronizing ring and the outer surface of the case at a plurality of shim locations are circumferentially spaced about the case outer surface. Each shim location includes at least one of the shims. A radial thickness of the shims at a first one of the shim locations is different than the radial thickness of the shims at a second one of the shim locations.

Abstract: An assembly includes a plurality of vanes, a forward liner segment, and an aft liner segment. The forward liner segment and the aft liner segment are mounted to the plurality of vanes and each segment comprises an arc of less than 360° in length.

Abstract: Implementations of the present disclosure are directed to turbine assemblies for turbocharger systems. In some implementations, turbine housings include a body that defines an inlet for fluid communication with a fluid source, and a wall, the wall dividing the inlet into an inner inlet and an outer inlet, and a fluid guide assembly disposed within the housing, the fluid guide assembly including a plurality of vanes that demarcate an inner volute and an outer volute within the housing, the inner volute being in fluid communication with the inner inlet and the outer volute being in fluid communication with the outer inlet, each vane of the plurality of vanes being fixed at a respective angle relative to a radial direction, the plurality of vanes guiding fluid flow from the outer volute to the inner volute.

Abstract: A process of fabricating a shield, a process of preparing a component, and an erosion shield are disclosed. The process of fabricating the shield includes forming a near-net shape shield. The near-net shape shield includes a nickel-based layer and an erosion-resistant alloy layer. The nickel-based layer is configured to facilitate secure attachment of the near-net shaped to a component. The process of preparing the component includes securing a near-net shape shield to a substrate of a component.

Abstract: A centrifugal fan includes an impeller, and a lower casing provided below the impeller. The impeller includes an upper shroud having an upper portion formed with an inlet, a lower shroud, and a plurality of blades arranged along a circumference direction between the upper shroud and the lower shroud. The blades extend from an inner side area to an outer side area in a radial direction, and are only connected to the lower shroud with the inner side area such that at least an outer circumferential side portion of each blade faces an upper surface of the lower casing. A surface of the lower casing, which faces the impeller, configures a portion of a wall surface which guides the fluid introduced from the inlet. A surface of each blade at a side of a leading edge portion is formed with a discontinuous portion having a step shape.

Abstract: An airfoil includes an airfoil body made of a first metal with a leading edge, a trailing edge, pressure side and suction side; a sheath with first and second flanks made of a second metal; a first layer of non-conductive material adhesively bonded between a portion of the end of the first flank and the airfoil body and extending beyond the end of the first flank on the pressure side; and a second layer of non-conductive material adhesively between a portion of the end of the second flank and the airfoil body and extending beyond the end of the second flank on the suction side.

Abstract: An outer case employed in a gas turbine engine includes a plurality of support member bosses and a plurality of gusseted bosses. The plurality of support member bosses are disposed circumferentially around the outer case for receiving and securing support members that attach the outer case to an inner hub. The plurality of gusseted bosses are disposed circumferentially around the outer case and between the plurality of support member bosses.

Abstract: A turbine engine case includes a first panel, a second panel and a support hanger. The second panel defines an aperture. The support hanger includes a strut that is connected to the first panel, and a base that is pivotally connected to the strut. The base includes a pivot member that is pivotally engaged with the second panel. The base extends away from the strut and through the aperture to the pivot member.

Abstract: A wrenching mechanism includes a multiple of rectilinear fastener plates each with a nut-shaped opening, each of the multiple of rectilinear fastener plates located within one of the multiple of rectilinear openings. A fastener mounted at least partially through the nut-shaped opening of each of the multiple of rectilinear fastener plates.

Abstract: A heat shield for a mid-turbine frame has a conical body, including at least one axial retention feature, at least one circumferential retention feature, and at least one radial retention feature.

Abstract: A case assembly includes a plurality of segments, at least one braze joint, and one or more welds. The braze joint connects the plurality of segments together and the one or more welds extend across adjacent segments.

Abstract: A system and associated method for detecting lighting strikes on a wind turbine uses a plurality of lightning strike conductors that are connected to any combination of the wind turbine components. A common ground cable is connected to the conductors and to a wind turbine grounding system. A sensor is operatively configured on the common ground cable to detect current flowing through the cable from a lightning strike incident on any one of the receptors, with the sensor producing a signal proportional to the intensity of the lightning strike.

Abstract: A constraint assembly for an aircraft, having a first member; a second member mounted to translate along and rotate about its own axis; and connecting means for connecting the first and second member, to prevent rotation of the second member about the axis with respect to the first member; the connecting means having a retaining arm, which projects outwards from one of the first and second member, and extends at a distance of other than zero from the axis; and an antirotation bracket, which projects from the other of the first and second member, extends at a distance of other than zero from the axis, and defines a through opening engaged in sliding manner by the retaining arm.

Abstract: A system for minimizing non-integral vibrations in rotor blades located in a compressor section of a gas turbine engine includes a casing having a plurality of bleed slots, at least one of the bleed slots being located in close proximity to a row of rotor blades, a plurality of structural ligaments, at least one of the structural ligaments extending between two adjacent ones of the bleed slots; and a channel for reducing the height of at least one of the structural ligaments so as to minimize the non-integral vibrations in the rotor blades in the row.

Abstract: Impellers made of composite materials with flow path cavities covered by an erosion resistant coating are manufactured by covering removable molds having shapes corresponding to a negative geometry of the flow path cavities, with the erosion resistant coating using plating or thermal spraying. After shaping and curing a composite material around the molds covered with the erosion resistant coating, the molds are removed, while the erosion resistant coating remains on the composite impeller.

Abstract: A steam turbine, a rotor and a method for making an extruded rotor are disclosed as having a rotor bore formed of an extruded high temperature alloy. The method includes providing a high temperature alloy, melting the high temperature alloy, extruding the high temperature alloy to form a bore, and forming the bore into a rotor.

Abstract: A coating is described for an airfoil blade component. The coating comprises a cermet material and has, when applied to the rotor blade, a compressive residual stress greater than about 60 ksi. In another embodiment, the compressive residual stress of the coating is in the range of approximately 90-110 ksi.

Abstract: A gas turbine engine component is described which (100), comprises: a shell having an internal cavity for receiving a multi-part insert; a multi-part insert located within the cavity, wherein the multi-part insert comprises separate insert parts assembled in an abutting relation with one another within the cavity to provide the multi-part insert; an insertion aperture within a wall of the shell which is sized to receive each of the insert parts individually and wherein the multi-part insert cannot be withdrawn from the cavity through the insertion aperture when assembled.

Abstract: Rotor blade assemblies for wind turbines and methods for reducing rotor blade noise are disclosed. A rotor blade assembly includes a rotor blade having external surfaces defining a pressure side, a suction side, a leading edge, and a trailing edge extending between a tip and a root. The rotor blade further defines a span and a chord. The rotor blade assembly further includes a tab. The tab includes an inner surface, an outer surface, a forward end and an aft end. The inner surface is mounted to one of the pressure side or the suction side. The outer surface has a cross-sectional profile configured to modify an operational value of the rotor blade at the trailing edge. The forward end is disposed within the chord.

Abstract: A turbine component, a turbine blade, and a turbine component fabrication process are disclosed. The turbine component includes ceramic matrix composite plies and a feature configured for preventing interlaminar tension of the ceramic matrix composite plies. The feature is selected from the group consisting of ceramic matrix composite tows or precast insert tows extending through at least a portion of the ceramic matrix composite plies, a woven fabric having fiber tows or a precast insert preventing contact between a first set of the ceramic matrix composite plies and a second set of the ceramic matrix composite plies, and combinations thereof. The process includes laying up ceramic matrix composite plies in a preselected arrangement and securing a feature configured for interlaminar tension.

Abstract: Disclosed is a wind turbine rotor blade includes a root portion, an airfoil portion, a thickened zone extending outward from an inner hub end of the blade into the airfoil portion of the blade; and an airflow correction arrangement arranged on a pressure side of the blade over at least a portion of the thickened zone. The airflow correction arrangement includes a spoiler to increase blade lift and a vortex generator arranged between a leading edge and the trailing edge and realized to maintain an attached airflow between the vortex generator and the spoiler. A wind turbine with at least one such rotor blade is disclosed. An airflow correction arrangement for correcting the airflow over the pressure side of a wind turbine rotor blade for a region of the blade having a thickened zone is further disclosed.

Abstract: A wind turbine includes a rotor having a hub and at least one blade having a torsionally rigid root, an inboard section, and an outboard section. The inboard section has a forward sweep relative to an elastic axis of the blade and the outboard section has an aft sweep.

Abstract: A method of forming a complex shaped part includes the steps of forming a polymer core by an additive manufacturing process. A metal is plated about surfaces of the polymer core, and the polymer core is removed, leaving hollows within a plate core. Metal powder is deposited within the hollows. An integral blade rotor is also disclosed.

Abstract: A securing system for a fan assembly. The securing system includes a first member which attaches to a motor mount and a second member which attaches to the hub of the fan assembly. The first member is interposed between the hub and the second member such that should the shaft of the motor break, the first and second members engage with one another and inhibit the fan assembly from falling away from the motor mount.

Abstract: A cooled turbine blade having a base and an airfoil, the base including cooling air inlet and an internal cooling air passageway, and the airfoil including an internal heat exchange path beginning at the base and ending at a cooling air outlet at the trailing edge of the airfoil. The airfoil also includes a “skin” that encompasses a tip wall, an inner spar, a plurality of inner spar cooling fins extending from the inner spar to the skin, and a plurality of trailing edge cooling fins extending from the pressure side of the skin to the lift side of the skin aft of the inner spar.

Abstract: A method of manufacturing a cooled turbine blade for use in a gas turbine engine. The method includes forming an inner blade pattern, the inner blade pattern including an inner spar and a plurality of inner spar cooling fins. The method also includes forming an inner blade core, removing the inner blade pattern from the inner blade core, forming an outer blade pattern, forming a casting shell, removing the outer blade pattern from the casting shell, and casting the cooled turbine blade in the casting shell. The method also includes removing the casting shell from the cast cooled turbine blade, and removing the inner blade core from the cast cooled turbine blade.

Abstract: A cooled turbine blade having a base and an airfoil, the base including cooling air inlet and an internal cooling air passageway, and the airfoil including an internal heat exchange path beginning at the base and ending at a cooling air outlet at the trailing edge of the airfoil. The airfoil also includes a “skin” that encompasses a tip wall, an inner spar, a leading edge rib, and a leading edge air deflector. The leading edge rib is configured to form a leading edge chamber in conjunction with the leading edge of the skin. The leading edge air deflector is at least partially intersected by the inner spar.