Abstract: A feedback sensor system is provided. The feedback sensor system includes a first ring rotatable about an axial direction and a second ring also rotatable about the axial direction. The first ring includes one or more first ring features and the second ring includes one or more second ring features. The feedback sensor system also includes a sensor directed at the surface of the first ring for sensing a parameter influenced by the one or more first ring features and the one or more second ring features. The sensor may determine a position of the first ring relative to the second ring by sensing the parameter.

Abstract: A fan for generating an air current includes a body having an air inlet, and a nozzle connected to the body. The nozzle includes an interior passage and an air outlet from which the air flow is emitted from the fan. The interior passage extends about an opening or bore through which air from outside the nozzle is drawn by air emitted from the air outlet. The body includes a duct having a first end defining an air inlet of the duct and a second end located opposite to the first end and defining an air outlet of the duct, an impeller located within the duct for drawing the air flow through the duct, and a motor for driving the impeller. The second end of the duct protrudes from the body into the interior passage of the nozzle.

Abstract: A system includes a turbine casing assembly that includes an outer shell and an inner shell positioned substantially concentrically within the outer shell. The inner shell includes an inner surface facing away from the outer shell and an outer surface facing toward the outer shell, and the outer surface has one or more false flanges. At least one of the one or more false flanges includes a first surface protruding from the outer surface and facing the outer shell, and a flow diverting portion extending between the first surface and the outer surface of the inner shell. The flow diverting portion includes a first portion that diverges in a first circumferential direction between the first surface and the outer surface.

Abstract: An airfoil for a gas turbine engine includes pressure and suction walls spaced apart from one another and joined at leading and trailing edges to provide an airfoil that extends in a radial direction. The airfoil has a cooling passage arranged between the pressure and suction walls that extend toward a tip of the airfoil. The tip includes a pocket that separates the pressure and suction walls. Scarfed cooling holes fluidly connect the cooling passage to the pocket. The scarfed cooling holes include a portion that is recessed into a face of the suction wall and exposed to the pocket.

Abstract: The present disclosure includes a system for balancing a turbine disk stack, including a high pressure turbine disk stack. A flange is grooved to accommodate and orient a slip ring. Balancing weights are attached to the slip ring to balance the turbine disk stack during rotation of a gas turbine engine.

Abstract: An object is to is to reduce a leakage flow by reducing a clearance between an end surface of a nozzle vane, forming a variable nozzle mechanism of a variable geometry turbocharger, and a wall surface facing the end surface, and prevent the nozzle vane from being stuck due to contact of the end surface.

Abstract: A turbine exhaust case comprises a frame, a fairing, a heat shield and a mechanical linkage. The frame comprises an outer ring, an inner ring, and a plurality of struts joining the outer ring and the inner ring. The fairing comprising a ring-strut-ring structure disposed within the frame. The heat shield is disposed between the frame and the fairing. The mechanical linkage couples the heat shield to the fairing. In one embodiment, the heat shield comprises a multi-piece heat shield that inhibits heat transfer between the frame and the fairing. In various embodiments, the mechanical linkage comprises a slip joint or a fixed joint for coupling the heat shield to the fairing.

Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform that axially extends between a leading edge and a trailing edge and circumferentially extends between a first mate face and a second mate face and a trench disposed on at least one of the first mate face and the second mate face. A plurality of cooling holes are axially disposed within the trench.

Abstract: A press-fit thrust bearing system and apparatus. A press-fit thrust bearing for an electric submersible pump includes a protruding band extending around a midsection of a bushing, the protruding band extending inward towards a drive shaft, outward towards a diffuser, or both. When extending outwardly, the band is press-fit into the diffuser to prevent dislodgment of the bushing. A non-rotating guide sleeve extends around the bushing above the protruding band, the guide sleeve interlocking with the protruding band to prevent rotation of the bushing. The guide sleeve includes a projection, the protruding band has a channel and the projection mates with the channel to form the interlock. A pair of flanged, rotatable bearing sleeves extend inwards of the single bushing and are keyed to the drive shaft. The top and bottom faces of the bushing serve as thrust handling surfaces.

Abstract: A blade for a gas turbine engine includes a body that includes an airfoil that extends in a radial direction from a 0% span position near an airfoil base to a 100% span position at an airfoil tip. The airfoil includes a first portion near the airfoil base with a first density and includes a second portion near the airfoil tip with a second density. The second density is less than the first density. The second portion includes an increasing true chord length in the radial direction.

Abstract: An exhaust-gas turbocharger (1) having a compressor housing (2); a turbine housing (3); and a bearing housing (4) which has a compressor-side flange (5) and which has a turbine-housing-side flange (6). The turbine-housing-side flange (6) is produced from a material which corresponds in terms of its mechanical and thermal properties to the material of the turbine housing (2).

Abstract: An assembly for a gas turbine engine includes a first casing, a fairing, and a multi-piece heat shield assembly. The fairing is disposed adjacent the first casing. The multi-piece heat shield assembly includes a first shield mounted to the first casing and extending between the first casing and the fairing, and a second shield mounted to the fairing and extending between the fairing and the first casing.

Abstract: Various aspects include an alignment key for a turbomachine, along with a turbomachine including the alignment key and a related storage medium. In some cases, the alignment key includes: a body having primary axis and sized to engage a diaphragm slot in the turbomachine, the body having sidewalls extending along the primary axis; a chamfered tip section continuous with the body, the chamfered tip section sized to engage a casing slot in the turbomachine; and a slot extending through the body and the chamfered tip section, the slot having a first opening proximate an end of the body and a second opening proximate the chamfered tip section, wherein the sidewalls of the body taper from the end of the body toward the chamfered tip section.

Abstract: A turbine blade assembly for a gas turbine engine is provided. The turbine rotor blade assembly includes a turbine rotor blade and an attachment pin, and the turbine rotor blade and attachment pin have features for providing a surface interface between the blade and pin. In particular, the attachment pin has a triangular cross-sectional shape, and the blade defines a pin hole for receipt of the attachment pin. An attachment pin for attaching a turbine rotor blade to a turbine rotor disk of a gas turbine engine also is provided. The attachment pin includes a body defining at least one planar surface, and the planar surface provides a surface contact interface between the attachment pin and the turbine rotor blade.

Abstract: A rotary machine includes a guide section formed in an annular flow path in communication with a suction volute at an inner circumferential side of the suction volute, at which a plurality of vanes are installed in a circumferential direction, and configured to guide a fluid introduced from the suction volute, and an impeller connected to the guide section in the axial direction and into which the fluid guided by the guide section is introduced, wherein the suction volute has an annular opening section in communication with the guide section at the inner circumferential side, and an inner wall surface extending from the opening section toward the axial direction impeller in the axial direction to increase a width dimension in the axial direction and connected to a partition section at an opposite side of the suction nozzle.

Abstract: An oil drain (8) in a turbocharger bearing housing (1) is provided in which the oil flows out along the outer edge of the oil drain (8) leaving the center of the drain (8) open. Air can flow between the bearing housing (1) and the oil sump allowing for an equalization of air pressure therebetween.

Abstract: A wind turbine system is presented. The wind turbine system includes a wind turbine tower, a plurality of blades, a rotor supported by the wind turbine tower and rotatably coupled to the plurality of blades, a torque control device coupled to the rotor, and a control system programmed to predict an over-speeding time T of an occurrence of an over-speed rotor event based at least in part upon a current rotor acceleration and a current rotor speed, that cannot be compensated by an available counter-torque margin of the torque control device, and, in response, to generate pitch commands for the pitch angles of the plurality of blades to avoid the over-speed rotor event.

Abstract: A rotor blade main body includes multiple first composite sheet groups and multiple second composite sheet groups which are provided in a blade thickness direction. Each first composite sheet group includes multiple composite sheets which are stacked one on another from a blade thickness center side toward a dorsal surface. Each second composite sheet group includes multiple composite sheets which are stacked one on another from the blade thickness center side toward a ventral surface. A composite direction of orientation directions of fibers in the multiple composite sheets in each of the sheet groups inclines by 20 degrees to 45 degrees from a span direction.

Abstract: A radial turbine comprises a plurality of nozzle vanes disposed along a circumferential direction inside a spiral scroll and configured to regulate a flow of a working gas from the scroll to a rotor blade, wherein each of the nozzle vane includes a leading edge bulging portion on both end portions in a width direction of an inlet leading edge portion, the leading edge bulging portion being bulged toward a pressure face side of the nozzle vane relative to a central portion, so that a vane angle is configured to correspond with an inflow angle of the working gas to be flown into the nozzle vane, and wherein each of the nozzle vane includes a trailing edge bulging portion on both end portions in a width direction of an outlet trailing edge portion, the trailing edge bulging portion being bulged toward the pressure face side relative to a central portion, so that an outflow angle of the working gas from the outlet trailing edge of the nozzle vane becomes uniform.

Abstract: A bearing housing (1) of an exhaust-gas turbocharger (2) having a turbine-side flange (3), having a compressor-side flange (4) and having a center part (5) which is arranged between the turbine-side flange (3) and the compressor-side flange (4). The turbine-side flange (3), the compressor-side flange (4) and the center part (5) are separate components which are connected to one another in the fully assembled state by a connection device (6) or thermally or by adhesive bonding.