Abstract: A vehicle including an engine; a turbocharger, an intake air flow path of the vehicle defined from air entering the vehicle, passing through the compressor, and flowing into the engine air inlet; a coolant container assembly; a temperature sensor configured for determining a temperature in the intake air flow path; and a controller configured to selectively cause cooling liquid to flow from the coolant container into the intake air flow path. A method for managing engine air intake temperature or piston temperature of a turbocharged vehicle including: sensing a temperature of fluid within the air intake flow path, determining an estimated piston temperature; and in response to the estimated piston temperature and/or the temperature of the fluid being above threshold temperatures, causing an amount of cooling liquid to flow from a coolant container to the air intake flow path.

Abstract: A compressor device of a supercharging device for an internal combustion engine (1), having an inlet channel (21) with a side wall (23), an exhaust-gas inlet (25) in the side wall (23), at which exhaust-gas inlet an exhaust-gas recirculation channel (27) opens into the inlet channel (21), and a flow barrier (29) in the inlet channel (21), which flow barrier at least partially spans the exhaust-gas inlet (25), is spaced apart from the exhaust-gas inlet (25) and is suitable for diverting exhaust gas which flows from the exhaust-gas inlet (25) into the inlet channel (21) at an angle with respect to an axial direction of the inlet channel (21) or with respect to the axis of a compressor (3).

Abstract: The invention relates to an assembly for a gas turbine engine which has a rotor disc, rotor blades and an annular blade retention plate, which adjoins the axially front side or the axially rear side of the rotor disc. The blade retention plate includes a radially outer region, which fixes the rotor blades axially, and a radially inner region, which is fixed axially by means of a securing ring in a recess on the axially front side or on the axially rear side of the rotor disc. Provision is made for the radially inner region of the blade retention plate to bear on the securing ring under axial preload. The invention relates further to a method for fastening a blade retention plate to a rotor disc of a gas turbine engine.

Abstract: A V-type engine includes an engine body including a crankcase configured to rotatably support a crankshaft, and a first and second cylinder banks extending from the crankcase, an exhaust collecting pipe connected to the first and second cylinder banks, a catalyst accommodated in the exhaust collecting pipe, and a muffler detachably connected to the exhaust collecting pipe, wherein the catalyst extends in a height direction of the engine body from a base end side of the first cylinder bank to a distal end side of the first cylinder bank.

Abstract: A unitized build assembly for a gas turbine engine includes an exhaust duct, a hot section with a locking structure and including a combustor and turbine section. The hot section at least partially circumferentially surrounds the exhaust duct. The build assembly includes a compressor section with an interface structure and is proximal to the hot section. The hot section at least partially circumferentially surrounds at least part of the compressor section and the locking structure is configured to engage the interface structure to limit movement of the hot section relative to the compressor section.

Abstract: This scroll compressor comprises: a shaft that is capable of rotating about an axis; a motor that rotatably drives the shaft; a compressor body that is driven by the rotation of the shaft; a housing that covers the motor and the compressor body and that has a bottom surface facing the motor from the axial direction; an intake port that guides a refrigerant into the housing; and heat-dissipating fins that are formed on the bottom surface, that extend in the direction in which the refrigerant flows, and that are divided in the flow direction.

Abstract: A variable speed pumping system, for an aircraft, comprising: a first electrical machine, the first electrical machine comprising an electrical machine rotor shaft mechanically connected to an engine of the aircraft and electrical machine stator coils; an electric pump motor-generator, the electric pump motor-generator comprising an electric pump rotor shaft mechanically connected to the electrical machine rotor shaft via a one way drive arrangement and electric pump stator coils; wherein the electric pump rotor shaft is mechanically connected to a fluid pumping system.

Abstract: Composite airfoils and methods for forming composite airfoils are provided. For example, a composite airfoil of a gas turbine engine comprises opposite pressure and suction sides extending radially along a span from a root to a tip, which define opposite radial extremities of the airfoil. The composite airfoil further comprises a body section and a tip section, which includes the tip, that each extend radially along the span. The composite airfoil is formed from a composite material comprising fibers disposed in a matrix material. The tip section has a tip fiber volume, and the body section has a body fiber volume that is greater than the tip fiber volume. Another composite airfoil comprises a tip cap applied over the tip that tapers from a first end to a second end such that each of the pressure and suction side walls of the tip cap narrows from a first thickness to a second thickness.

Abstract: An electric machine includes a rotor extending along an axis and a stator lamination stack radially spaced from the rotor. The stator lamination stack has circumferentially spaced teeth defining gaps therebetween. The electric machine also includes a coil winding disposed in the gaps between the circumferentially spaced teeth and a guard plate disposed at one of the first and second stator ends. The guard plate extends radially away from the axis and includes a plurality of teeth guards extending radially, with each of the teeth guards aligned with one of the teeth of the stator lamination stack to electrically insulate the coil winding from the teeth of the stator lamination stack. The plurality of teeth of the stator lamination stack extend radially inward toward the axis and the teeth guards of the guard plate extend radially inward toward the axis.

Abstract: An aerofoil module for use in a blade of a propeller or turbine comprising: a body comprising a suction surface and a pressure surface; an air passage traversing the body, the air passage having an entrance opening on the pressure surface and an exit opening on the suction surface; a cover for covering a variable portion of a cross-section of the air passage; and a mechanism for varying the portion of the cross-section of the air passage covered by the cover, wherein the mechanism reacts passively to the oncoming air speed of oncoming air in the axial direction of the propeller/turbine; wherein the mechanism varies the portion of the cross-section covered by the cover such that the cover covers a smaller portion of the cross-section in response to a higher oncoming air speed, and covers a larger portion of the cross-section in response to a lower oncoming air speed.

Abstract: An assembly for an aircraft turbomachine, comprising an intermediate casing hub, an equipment support having an upstream face located downstream of the intermediate casing hub, and a transfer gear box driving a power transmission shaft configured to transmit mechanical power, taken off an engine shaft of the turbomachine, to at least one upstream equipment item mounted on the upstream face of the equipment support, the upstream equipment item comprising a structural element attaching the equipment support to the intermediate casing hub.

Abstract: A turbine section of a gas turbine engine includes a case, a plurality of flow path components, and a mounting system. The case extends circumferentially around a central axis of the gas turbine engine. The plurality of flow path components includes a turbine vane, a turbine blade, and a flow path ring. The mounting system is configured to couple the flow path ring to the case.

Abstract: Disclosed are a fixed scroll and a scroll compressor. The fixed scroll comprises a fixed scroll end plate, a fixed scroll wrap, and a peripheral wall, wherein an air inlet is provided in the peripheral wall, the fixed scroll wrap comprises a starting end connected to the peripheral wall, an engagement position to be engaged with an orbiting scroll wrap, and a scroll section extending from the starting end to the engagement position; the fixed scroll further comprises a flow-guiding passage in fluid communication with the air inlet; the flow-guiding passage extends from the starting end and extends along at least part of the scroll section; the scroll section comprises a first side wall comprising a first section having a first center of curvature and a second section having a second center of curvature, which are respectively located on radially opposite sides of the first side wall.

Abstract: An inlet cone for an aircraft turbomachine, having at least one first portion made of a first material, referred to as rigid material, and at least one second portion made of a second material which has a hardness less than that of said first material and which is referred to as flexible material, these second portions being configured to deform elastically in the radial direction with respect to the axis when the cone is being driven to rotate.

Abstract: Some embodiments of the present disclosure provides a head shaking device and a fan. The head shaking device includes a fixing assembly; and a rotating assembly, which rotates relative to the fixing assembly in a reciprocating manner, wherein one of the fixing assembly and the rotating assembly includes at least one first connecting structure, the other includes at least one second connecting structure, and the first connecting structure is rotatably clamped with the second connecting structure.

Abstract: An aircraft turbomachine module having two tubular casings equipped with first and second annular flanges assembled by studs received in the first flange and receiving nuts on the back of the second flange, each stud having an intermediate stretch of hexagonal shape cooperating with a locking plate. The locking plate can have a first orifice received on the intermediate stretch by at least two opposite walls, and a transverse body which is immobilized to prevent the rotation of the plate and that of the stud. Each plate can be fitted on two immediately adjacent studs and the body can have, for this purpose, a second orifice opposite the first orifice and which is received on an intermediate stretch of an immediately adjacent stud and cooperates with the intermediate stretch of hexagonal shape of the stud.

Abstract: An ATS includes an SCR device and is connected to an internal combustion engine so as to receive an exhaust gas flow from at least one cylinder of the internal combustion engine when fuel is injected and combusted in such cylinder; an NH3 storage is increased in such SCR device after an engine shut off command has been detected, such that an increased NH3 storage is ready for a subsequent cold start of the internal combustion engine; the increase of NH3 storage is carried out by injecting a reducing agent in the ATS and by supplying an air flow towards the SCR device; such air flow flows through the cylinder after the fuel injection has been shut off.

Abstract: An assembly for an aircraft turbine engine, includes a fan, a speed reduction gear and an intermediate casing including an internal annular structure that houses an epicyclic gear train equipped with a planet carrier. The assembly includes a secondary retention device for the ring gear of the planet carrier, the device including: first projections that project radially inwards from the internal annular structure, each first projection having a recess that is open radially inwards, axially downwards and circumferentially in a first direction; and second projections that project radially outwards from the ring gear of the planet carrier and cooperate with the first projections in such a way that each second projection is partially accommodated in the recess of the first projection with which it is associated and downstream therefrom.

Abstract: A vortex generator for wind turbine blade is a vortex generator for wind turbine blade, the vortex generator being made of a resin, including: a platform; and at least one fin disposed projecting from an upper surface of the platform. The vortex generator includes a cavity that opens to a bottom surface of the platform and extends to an inside of the fin.

Abstract: A multi-stage compressor assembly is disclosed. Each of the stages of the compressor assembly has rows of blades arranged to rotate in counter-opposite directions, and this is effective to produce relatively high specific work, and high flow-capacity in a compact footprint at moderate blade tip speeds. In one non-limiting application, the compressor assembly can be utilized to compress a gas having a low-molecular weight and density, such as hydrogen.