Abstract: The description relates to a drive assembly with an internal combustion engine, a turbocharger designed to supercharge said internal combustion engine and a catalysing system; the drive assembly comprises: a first wastegate duct interposed between the turbine and the catalysing system and a first wastegate valve movable between a first and a second position; the drive assembly comprises a second duct interposed between said exhaust duct and said catalysing system; and a second bypass valve movable between a third position, in which it fluidly connects said exhaust duct and the catalysing system so as to covey said mixture along the second duct bypassing the entire turbine, thus heating said catalysing system, and a fourth position, in which it fluidly isolates said second duct from said exhaust duct.

Abstract: Provided is a rotary compressor excellent in energy saving performance and reliability that can suppress over-compression of a compressed refrigerant compressed in a compression chamber. A rotary compressor includes a discharge port provided on an end plate and partially located outside a cylinder inner wall and a discharge groove provided on the cylinder inner wall and communicating with a compression chamber and the discharge port, the compression chamber compressing a refrigerant by contracting as an annular piston revolves, in which the discharge port faces an end portion of a vane groove on the cylinder inner wall on the compression chamber side.

Abstract: A rotor support configured to rotatably mount a rotor shaft in a vacuum pump is disclosed. The rotor support comprises: a rolling bearing for rotatably supporting the shaft; an insert and at least one resilient damping member, the insert and the at least one resilient damping member surrounding the rolling bearing. The insert comprises inner and outer annular portions connected by a plurality of flexible members, the plurality of flexible members being configured to flex in a radial plane and resist movement in an axial plane, thereby absorbing radial movement of the shaft. The at least one resilient damping member is formed of an elastomeric material configured to flex in both a radial and axial direction.

Abstract: An aircraft gas turbine engine includes a heat exchanger module, and a core engine. The core engine includes an intermediate-pressure compressor, high-pressure compressor, and high and low-pressure turbines. The high-pressure compressor rotationally connects to the high-pressure turbine by a first shaft, and the intermediate-pressure compressor rotationally connects to the low-pressure turbine by a second shaft. The heat exchanger module fluidly communicates with the core engine by an inlet duct. The heat exchanger module includes a central hub and multiple heat transfer elements extending radially from the hub and spaced in a circumferential array, for heat energy transfer from a first fluid within the elements to an inlet airflow passing over a surface of the elements prior to airflow entry into an inlet to the core engine. The gas turbine engine further includes a first electric machine rotationally connected to the first shaft, and positioned downstream of the heat exchanger module.

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 at least partway around an axis of the gas turbine engine. The plurality of flow path components includes a flow path segment and a turbine vane. The mounting system couples the flow path segment to the case to support the flow path segment radially relative to the axis of the gas turbine engine.

Abstract: An electric compressor includes a housing, refrigerant inlet port, a refrigerant outlet port, an inverter section, a motor section, a compression device and a front cover. The housing defines an intake volume and a discharge volume. The refrigerant inlet port is coupled to the housing and is configured to introduce the refrigerant to the intake volume. The compression device is a scroll-type compression device configured to compress the refrigerant. The refrigerant outlet port is coupled to the housing and is configured to allow compressed refrigerant to exit the scroll-type electric compressor from the discharge volume.

Abstract: A control method is performed to control a traction device of a motor vehicle having an internal combustion engine that includes a plurality of cylinders. Each of cylinders has at least one air intake valve, at least one exhaust valve for the combustion gases generated by the internal combustion engine, and a fuel injector. A treatment device is provided for the combustion gases that is active from an actuation temperature. The treatment device is placed downstream of the exhaust valve. The traction device includes an electrical heater for heating the combustion gas treatment device. The traction method further compares a temperature of the combustion gas treatment device with an actuating threshold temperature and actuates the electrical heater and stopping a fuel supply being supplied to one or more of the cylinders as long as the temperature of the combustion gas treatment device is below the actuating threshold temperature.

Abstract: A vehicle includes a filter, a negative-pressure mechanism, and a first opening and closing mechanism. The filter is disposed in an exhaust passage coupled to an engine. The negative-pressure mechanism is configured to pressurize a portion of the exhaust passage upstream of the filter to a negative pressure less than an atmospheric pressure. The first opening and closing mechanism includes an opening disposed in the exhaust passage, and a valve configured to selectively open and close the opening. The valve is configured to, when the exhaust passage becomes negatively pressurized by the negative-pressure mechanism, open the opening.

Abstract: A method for preconditioning at least a part of an engine system of a vehicle. The engine system includes an engine and an exhaust aftertreatment system, EATS. The method providing predicted vehicle operational information comprising a vehicle operational initialization time and predicted engine operation, determining whether or not cold-start emissions of the predicted engine operation achieves a threshold criterium, in response to achieving the threshold criterium, preconditioning at least a part of the engine system such that at least said part of the engine system is preconditioned at a time of the vehicle operational initialization time.

Abstract: A system includes an exhaust collector tunnel (32) configured to mount inside an exhaust collector (30) of a gas turbine (12). The exhaust collector tunnel (32) has a tunnel wall (33) configured to extend around a turbine shaft (17, 19) of the gas turbine (12). The tunnel wall (33) has a variable diameter (98) along at least a portion of a length of the exhaust collector tunnel (32).

Abstract: A component for a gas turbine engine includes an airfoil having a plurality of channels with a main body extending between a leading edge and a trailing edge. The main body forms a portion of one side of the airfoil and the entirety of an opposing side of the airfoil. A cover is secured to the main body about a perimeter by a weld. The cover extends across a majority of the one side of the airfoil. A plurality of ribs extends from the cover in a direction toward the main body to define the channels. The ribs are secured to an inner surface of the main body by an adhesive. A gas turbine engine and a method are also disclosed.

Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a rotating structure, a stationary structure, a bearing and a gearbox. The rotating structure is configured to rotate about a rotational axis. The rotating structure includes a shaft and a bladed rotor connected to the shaft. The stationary structure circumscribes the rotating structure. The bearing rotatably mounts the shaft to the stationary structure. The gearbox is disposed radially inboard of the bearing.

Abstract: An internal combustion engine for a motor vehicle includes a drive shaft, an intake tract, an exhaust gas tract, an exhaust gas aftertreatment device disposed in the exhaust gas tract, a heating element disposed in the exhaust gas tract upstream of the exhaust gas aftertreatment device, an electrically assisted exhaust gas turbocharger, and a conduit element which is fluidically connected to the exhaust gas tract at a first connection point disposed downstream of the exhaust gas aftertreatment device and at a second connection point disposed upstream of the heating element.

Abstract: A hydrogen fueled power system of a vehicle includes a liquid hydrogen fuel source having a volume of liquid hydrogen fuel and a thermal engine configured to expand the liquid hydrogen fuel into gaseous form via interaction between a heated first portion of the hydrogen fuel and a second portion of the hydrogen fuel. A heat exchanger is positioned between the liquid hydrogen source and the thermal engine, and is configured to heat the first portion of the hydrogen fuel via thermal energy exchange with a relatively warm fluid. A turbine is located fluidly downstream of the heat exchanger and upstream of the thermal engine, and is driven by the heated first portion. A power generator is located fluidly downstream of the thermal engine. The power generator utilizes exhaust from the thermal engine to generate electrical or mechanical power. A compressor is operably connected to and driven by the turbine.

Abstract: A fan body includes a fixture, a first fan blade set, and a second fan blade set. The fixture is located at a middle of the fan body and configured to be connected to a power mechanism that drives the fan body to rotate. A first fan blade of the first fan blade set is connected to the fixture. A second fan blade of the second fan blade set is connected to neighboring first fan blades of the first fan blade set.

Abstract: A thrust bearing device is provided with: a rotational shaft; a collar member fitted to the rotational shaft and having a first thrust surface; and a thrust member having an insertion hole into which the rotational shaft is inserted and a second thrust surface which is disposed around the insertion hole and faces the first thrust surface of the collar member. The first thrust surface is configured to be inclined with respect to a plane perpendicular to an axis of the rotational shaft so that a distance between the first thrust surface and the second thrust surface periodically increases and decreases with rotation of the rotational shaft.

Abstract: Disclosed is an improved method and system of operating the semi-closed cycle, which both reduces parasitic loads for oxygen generation and for gas clean up, while also reducing, capital cost of the gas clean up plant (reduced drying requirement) and of the oxygen plant (enabling membranes vs. mole sieves). The invention is applicable to piston or turbine engines, and results in a near fully non-emissive power system via the Semi-Closed Cycle (SCC), in a manner which both captures carbon in the form of carbon dioxide, CO2, and in a manner which improves the efficiency and cost effectiveness of prior disclosures. The captured carbon is of a purity and pressure directly suitable for Enhanced Oil Recovery (EOR), sequestration, or industrial use.

Abstract: A variable turbine geometry assembly for controlling flow of exhaust gas to a turbine wheel of a turbocharger includes an adjustment ring extending about an axis and rotatable about the axis, at least one vane lever coupled to the adjustment ring, and at least one vane coupled to the at least one vane lever. The at least one vane is moveable with respect to the adjustment ring when the adjustment ring rotates about the axis. The variable turbine geometry assembly further includes a wave spring operably in contact with at least one of the at least one vane lever and the adjustment ring. The wave spring is configured to bias one of the at least one vane lever and the adjustment ring toward the other of the at least one vane lever and the adjustment ring.

Abstract: An aircraft engine includes a core gas path through which a core gas flow flows, an exhaust duct receiving the core gas flow, an air-cooled heat exchanger disposed in a heat exchanger duct having an air inlet providing cooling air to the air-cooled heat exchanger and an air outlet in fluid communication with the exhaust duct, and a cover disposed in the heat exchanger duct downstream of the air-cooled heat exchanger. The cover is movable between an open position, in which the cover allows the cooling air to flow through the air outlet into the exhaust duct, and a closed position, in which the cover substantially blocks the air outlet. The cover is operable to move from the open position to the closed position at a predetermined temperature of the cover.

Abstract: A powerplant is provided that includes an engine and a water recovery system. The engine includes an engine combustor, an engine turbine, a flowpath and a fluid delivery system. The flowpath extends out of the engine combustor and through the engine turbine. The fluid delivery system includes a hydrogen reservoir and an oxygen reservoir. The hydrogen reservoir is configured to store fluid hydrogen as liquid hydrogen. The oxygen reservoir is configured to store fluid oxygen as liquid oxygen. The fluid delivery system is configured to provide the fluid hydrogen and the fluid oxygen for combustion within the engine combustor to produce combustion products within the flowpath. The water recovery system is configured to extract water from the combustion products. The water recovery system is configured to provide the water to a component of the powerplant.