Abstract: According to the present invention, the impeller inlet of a turbocharger compressor receives intake air from an inner channel and an outer channel. The outer channel is pressurized with an electrically powered secondary compressor. The pressurized air in the outer channel flows into the impeller near the outer wall of the impeller inlet. The pressurized air next to the outer wall of the impeller inlet prevents backflow of air out of the impeller and thereby prevents surge and enables the compressor to produce high boost pressures under small mass flow settings. Only a portion of the intake air is pressurized with the electrically powered secondary compressor, and the boost pressure of the electrical compressor is only a fraction of the turbocharger compressor's overall pressure ratio.

Abstract: A nacelle cover (100) for a wind turbine includes an elongate housing (105) and the front end (107) of the housing (105) is mounted on a bed plate frame (420) which is affixed to the tower (122), the bed plate frame (420) supporting at least one part of a drive train (124) of the wind turbine. At least one machinery component (125) is mounted on the housing (105) at a position laterally spaced from the bed plate frame (420) in a longitudinal direction along the housing (105). The housing (105) includes a structural tube (128) which functions as a vertically displaceable cantilever beam carrying the load of the at least one machinery component (125) mounted thereon.

Abstract: A stator configuration for a gas turbine engine including: a splitter segment, the splitter segment extending from a forward end to a rearward end, the splitter segment being configured to split an incoming fluid flow into a first, radially outer stream and a second, radially inner stream; a forward most first stator extending radially outwardly from the splitter segment, the forward most first stator being completely located downstream from the forward end of the splitter segment; a forward most second stator extending radially inwardly from the splitter segment, the splitter segment, the forward most first stator and the forward most second stator being formed as a single, integrally formed structure, the forward most first stator positioned closer to the forward end relative to a distance between the forward most second stator and the forward end and the forward most second stator positioned closer to the rearward end relative to a distance between the forward most first stator and the rearward end, wherei

Abstract: A rotary assembly is provided that may be operably connected to an engine. The rotary assembly may include a rotary device comprising a turbine wheel, a shaft connected to the turbine wheel, and a case that houses the shaft and the turbine wheel. The turbine wheel may receive exhaust gas from the engine which causes rotation of the turbine wheel and the shaft. The case may include an interior surface that defines a hollow volume in which the turbine wheel and the shaft are located. The case has a radial thickness extending from the interior surface to an exterior surface of the case. The case may include a lattice structure integrated within the radial thickness of the case. The lattice structure may include a repeating three-dimensional array of frame segments connected to one another at junctions and defining interstitial spaces between the frame segments.

Abstract: A self-priming jet pump includes a pump body provided with a water inlet and a water outlet. A jet tube and an impeller are arranged in the pump body. The jet tube is communicated with the water inlet and an inlet of an impeller. A first channel is arranged on the outer periphery of the jet tube. The first channel is communicated with the water inlet and the impeller. A cross-section of the first channel is a closed or open annular structure, and the first channel is around the outer periphery of the jet tube. The first channel is provided with a valve core. When a pressure at the water inlet is greater than a predetermined pressure at the impeller, the valve core moves to switch on the first channel. A cavitation problem is relieved by arranging the flow-increasing channel.

Abstract: A supersonic air intake of an aircraft propulsion assembly comprises: •? pipe with a longitudinal axis configured to guide the flow of air into the turbine engine, •? a speed reducer fixedly mounted inside the pipe along the longitudinal axis, •? at least one support arm linking the speed reducer to the pipe and having an upstream outer wall and a downstream outer wall together defining a cavity, and •? at least one de-icing device having an inner wall mounted in the cavity opposite the upstream outer wall in order to together define a calibrated de-icing space, as well as a member for supplying and a member for discharging a de-icing air flow in the de-icing space.

Abstract: Disclosed is a supersonic speed attenuator for an air inlet of an aircraft power plant, having a conical external wall with a tapered end upstream and an internal dividing wall that delimits, with the conical external wall, a cavity; the supersonic speed attenuator further having a de-icing device having: an internal wall mounted in the cavity opposite the conical external wall so that, together, the two walls delimit a calibrated de-icing volume; at least one member for supplying a de-icing air flow, opening into the de-icing volume; and at least one member for discharging the de-icing air flow from the de-icing space.

Abstract: A turbine stator vane includes: a stator vane body extending in a radial direction intersecting a flow direction of steam; a recovery portion that is defined on a surface of the stator vane body, and configured to recover a liquid film flowing along the surface of the stator vane body; and a center region, which is defined on the surface of the stator vane body and includes grooves extending from an upstream side toward the recovery portion in the flow direction. Intervals between adjacent grooves decrease from the upstream side toward the recovery portion.

Abstract: The present invention discloses a helicopter hoisting platform for a wind turbine nacelle cover, the helicopter hoisting platform comprising a composite layer and a plurality of metal plates arranged on the outer surface of the composite layer, wherein the plurality of metal plates forms a conductive network electrically connected to a ground connection.

Abstract: A wind turbine blade comprising a plurality of spar components extending along the longitudinal axis and providing the main bending stiffness of the wind turbine blade a major principal axis defining a structural pitch angle of at least 1° with respect to a chord line, and including: one or more suction-side spar caps each having a centre line; one or more pressure-side spar caps each having a centre line; and one or more shear webs distributed around a central shear web line and at least one of which being connected to first spar caps, wherein at least one suction-side spar cap centre lines is arranged with a first chordwise distance to the central shear web line, and at least one pressure-side spar cap centre lines is arranged with a second, different, chordwise distance to the central shear web line.

Abstract: Rotor structure for a turbomachine, such as a centrifugal compressor, is provided. Disclosed embodiments make use of structural and/or operational relationships (e.g., distinct axially-extending zones in the radially-inner contour of respective impeller bodies configured to balance mass distribution about a rotor axis) designed to control relative radial and/or axial growth between corresponding interface locations along the rotor axis at which corresponding faces of respective hirth couplings mesh with one another. The ability to control relative radial and/or axial growth between corresponding interface locations may be effective for reducing rotor vibration and/or to establish more reliable contact patterns and reduced levels of mechanical stresses and distortion (e.g., angular distortion) at the hirth coupling interfaces.

Abstract: A servicing tool for a turbine engine and a method for using thereof are provided. A method includes inserting the tool into an access opening of the turbine engine, contacting a blade of the turbine engine, and removing material from the blade. The tool may comprise a wiper mount and a wiper, including a wiper surface, configured to contact and remove material from the blades. The tool may further comprise a body, an actuator, and fluid flowpaths for deploying the wiper and providing fluid locally to the blades of the turbine engine.

Abstract: A turbocharger having a centrifugal compressor includes a vaned diffuser. The vaned diffuser is formed by a diffuser ring formed separately from the compressor housing and center housing. The diffuser ring is installed between the compressor and center housings such that a diffuser passage is defined between a surface of the compressor housing and a surface of the diffuser ring. Integral vanes on the diffuser ring extend only partially across the axial width of the diffuser passage. A rectangular-section seal ring is axially compressed between the compressor housing and the diffuser ring for sealing and axial locating of the diffuser ring. Radial locating of the diffuser ring is accomplished by an integral locating pin on the ring, which fits into a receptacle in the center housing.

Abstract: A bulkhead removal device is including a bulkhead cutting system for cutting a bulkhead in a wind turbine blade, a positioning system for positioning the bulkhead cutting system, and a deployment assembly for moving the bulkhead cutting system inside the wind turbine blade. A method for cutting a bulkhead inside a wind turbine blade is also provided which includes moving a bulkhead cutting system inside a wind turbine blade, positioning the bulkhead cutting system, and cutting a bulkhead with the bulkhead cutting system.

Abstract: A propeller (20) for a marine vessel (10), the propeller (20) comprising a plurality of propeller blades (24, 26). The propeller blades comprise a leading edge (30), a trailing edge (32) and an outer edge (34) located between the leading edge and the trailing edge. A transition from the leading edge to the outer edge occurs at a first transition point (36) and a transition from the outer edge to the trailing edge occurs at a second transition point (38). A straight line from the first transition point to the second transition point coincides with the outer edge (34) or is located at least partially outside the propeller blade. A smallest distance (D2) from the second transition point to the axis of rotation (A) is smaller than a smallest distance (D\) from the first transition point to the axis of rotation.

Abstract: A bearing system for supporting a shaft, comprising: a bearing including: an inner race about an axis, the inner race having an interior coupled to the shaft; rolling elements about the axis and around the inner race; and an outer race about the axis and around the rolling elements; a housing having a cavity defining an axial location relative to the axis, the bearing received by the cavity; a first axial loading structure in the cavity and operatively connected to the bearing; and a second axial loading structure in the cavity extending axially away from the axial location in a first axial direction, the second loading structure opposing movement of the bearing relative to the axial location in a second axial direction when the bearing loads the second axial loading structure in the second axial direction, the first and second axial loading structures operationally independent from one another.

Abstract: An impeller seat for a pump, the impeller seat comprising an inlet wall, an inlet radius, and a guide pin connected to and extending radially inwards from the inlet wall. The guide pin includes a tip radius. A 40%-circle is offset radially inwards from a circular intersection forty percent of the difference between the inlet radius and the tip radius. The guide pin comprises a leading edge configured for scraping off pollutants from an impeller of the pump, and, at least between the inlet wall and the 40%-circle, comprises a pre-leading edge located upstream the leading edge of the guide pin, seen in the direction of rotation of the pump and seen in an axial direction.

Abstract: An internal combustion engine, ICE, system, includes a turbocharger having a turbine and a compressor for compressing intake air and feeding the intake air to the ICE. A turbo turbine unit is disposed in an exhaust gas path downstream the turbocharger to receive exhaust gas from the turbocharger. The turbo turbine unit having a turbine wheel, a bearing housing defining an inside volume for containing lubrication oil, and a sealing arrangement positioned in the vicinity of the turbine wheel for preventing lubrication oil from escaping from the inside volume of the bearing housing to an exhaust duct of the turbo turbine unit. A buffer air conduit extends between a selected position at the compressor and a buffer air inlet of the turbo turbine unit.

Abstract: A turbine housing has a scroll part, an outlet pipe, and an inlet pipe. A bypass passage is formed on an inner peripheral side of a twisting form leading from the inlet pipe toward the scroll part so as to allow communication between an inlet passage and an outlet passage. Viewing the turbine housing in an axial direction, an opening center of an outlet opening of the bypass passage is located in a quadrant where a mounting flange is located among four quadrants defined by a first imaginary plane that passes through a rotational center and that is parallel to a surface of the mounting flange, and a second imaginary plane that passes through the rotational center and that is orthogonal to the first imaginary plane.

Abstract: A gas turbine engine includes a plurality of annular discs arranged in an axial stack and defining axial passage, with at least one of the annular discs having an annular engagement member. A tie rod extends through the axial passage and secures the axial discs in the axial stack. The tie rod includes an annular collar defining an annular groove therein. The annular engagement member is received in the annular groove of the tie rod.