Abstract: A multi-stage turbocharging assembly is described. The multi-stage turbocharging assembly includes a high-pressure stage including a high-pressure turbine coupled with a high-pressure compressor. Additionally, the multi-stage turbocharging assembly includes a low-pressure stage including a low-pressure turbine coupled with a low-pressure compressor: Further, the multi-stage turbocharging assembly includes a casing enclosing the high-pressure stage and the low-pressure stage, wherein the casing is a single unit.

Abstract: The system includes a methane reformer, a combined cycle power generator, and a switch. The reformer is configured to react methane with steam. The combined cycle power generator includes a steam turbine, a gas turbine, a power generator, and a water boiler. The steam turbine is configured to rotate in response to receiving steam. The gas turbine is configured to rotate in response to receiving a mixture of fuel and air. The power generator is configured to convert rotational energy from the steam turbine and the gas turbine into electricity. In a first position, the switch is configured to direct exhaust from the gas turbine to the reformer, thereby providing heat to the reformer. In a second position, the switch is configured to direct exhaust from the gas turbine to the water boiler, thereby providing heat to the water boiler to generate steam.

Abstract: An exhaust-gas treatment module for an exhaust system of an internal combustion engine has a plurality of elements which follow one another in an exhaust-gas flow direction. The elements include a first mixing path with a first reactant dispensing arrangement in an upstream end region of the first mixing path and with a first mixing channel which is elongate in the direction of a first mixing path longitudinal axis. A first exhaust-gas treatment arrangement follows and is elongate in the direction of a first exhaust-gas treatment arrangement longitudinal axis and has an upstream end region connected to a downstream end region of the first mixing path, a second mixing path with a second reactant dispensing arrangement in an upstream end region which is connected to a downstream end region of the first exhaust-gas treatment arrangement.

Abstract: An exhaust aftertreatment system for an internal combustion engine includes an outer casing defining an exhaust flow path for exhaust gases from the internal combustion engine, a selective catalytic reduction unit provided in the exhaust flow path for reducing nitrogen oxides, a urea dosing device for adding urea to the exhaust flow upstream of the selective catalytic reduction unit, and a rotatable mixer device for mixing the urea with exhaust gases upstream of the selective catalytic reduction unit. The exhaust aftertreatment system further comprises an air inlet valve provided upstream of the mixer device for introducing air into the exhaust flow path, and an electric motor arranged for rotating the mixer device to create a suction of air into the exhaust flow path via the air inlet valve.

Abstract: A method and a system for synthesizing thrust from a turbofan engine are provided. The turbofan engine comprising a compressor section, a combustor, and a turbine section in serial fluid flow communication. The engine is operated and, during the operating of the turbofan engine, a pressure of fluid at an exit of the compressor section and a temperature of fluid at a location upstream of the exit of the compressor section are determined. A synthesized value of thrust from the turbofan engine is determined based on a product of at least a first factor and a second factor, the first factor being a function of the pressure and the second factor being a function of the temperature. The synthesized value of thrust from the turbofan engine is output.

Abstract: This application provides a temperature gradient control system for a double wall casing of a compressor. The double wall casing may include an inner casing and an outer casing such that a flow of air is pulled through the double wall casing. The temperature gradient control system may include upper discharge piping with an upper modulation valve and a lower discharge piping with a lower modulation valve. The upper modulation valve and/or the lower modulation valve modulate the flow air pulled through the double wall casing to reduce a temperature gradient across the outer casing.

Abstract: Aircraft propulsion systems include a fan shaft connected to a fan, the fan shaft defining a centerline axis of the aircraft propulsion system, one or more offset cores arranged at an angle to the centerline axis, the one or more offset cores each comprising a hydrogen burning combustor, a centerline cavity defined along the centerline axis, and a heat exchanger arranged within the centerline cavity. In operation, a portion of air is directed from the fan into the centerline cavity to provide a first working fluid to the heat exchanger within the centerline cavity.

Abstract: An air turbine starter that includes a housing. The housing can circumscribe a turbine coupled that is coupled to a gear train in a gear box via a drive shaft. The gear train can couple to an output shaft via at least a carrier. The air turbine starter can include at least a first bearing assembly and a second bearing assembly to rotatably support one or more of the drive shaft, the carrier, or the output shaft.

Abstract: An airfoil for a fan section of a turbine engine may include a fan blade or an outlet guide vane, and an edge guard attached thereto. The edge guard may include a heating conduit disposed within at least a portion of the edge guard. An anti-icing system for a plurality of fan blades or outlet guide vanes may include a fluid supply pathway configured to supply heating fluid to respective ones of a plurality of heating conduits within the edge guards attached to respective ones of a plurality of fan blades and/or to a plurality of outlet guide vanes. The heating fluid may include bleed air from a core air flowpath. A method of inhibiting icing on an airfoil may include flowing a heating fluid into a heating conduit disposed within an edge guard attached to the airfoil and heating the edge guard with the heating fluid.

Abstract: A turbomachine includes a housing and a rotating group that is supported for rotation about an axis of rotation within the housing. The turbomachine also includes a turbomachine stage including a wheel of the rotating group supported within a turbomachine housing of the housing. The turbomachine further includes an e-machine section including an e-machine that is housed within an e-machine housing of the housing. The e-machine is operably coupled to the rotating group and configured to operate as at least one of a motor and a generator. Moreover, the turbomachine includes an integrated controller that extends in a circumferential direction about the axis of rotation. The integrated controller is configured for controlling the e-machine. Additionally, the turbomachine includes a thermally decoupled fastener arrangement that attaches the integrated controller to the e-machine housing. The fastener arrangement thermally decouples the integrated controller from the turbomachine stage.

Abstract: A gas turbine engine includes a compressor section, a turbine section and an intermediate combustor. The compressor section has a plurality of rotating compressor blades rotating about an axis of rotation, and static stator vanes positioned axially intermediate the rotating compressor blades. There are a plurality of bleed holes extending through a compressor outer housing positioned radially outwardly of the rotating compressor blades, and allowing air compressed by the compressor blades to move into a bleed chamber. There is a bleed chamber outer housing positioned radially outwardly of the compressor outer housing, and defining the bleed chamber in part in combination with the compressor outer housing. A flow discourager is positioned radially intermediate the bleed holes and the bleed outer housing, such that air leaving the bleed hole impacts upon the flow discourager before reaching the bleed chamber outer housing.

Abstract: The invention relates to a bleed air extraction device for a turbomachine, which has: an axial compressor, formed in a flow path and having at least one compressor stage, which comprises a rotor and a stator, and a bleed air duct, which is provided and designed to guide a bleed air flow branched off from the flow path of the axial compressor. In this case, the bleed air duct comprises an inlet opening, which is formed downstream of a stator of the axial compressor in the radially outer flow path boundary, an axially forward wall adjoining the inlet opening, and an axially rearward wall adjoining the inlet opening. Guide means are provided, which are provided and designed for the purpose of guiding at least a portion of the bleed air flow branched off from the flow path in the direction of the axially forward wall of the bleed air duct.

Abstract: In a turbocharged internal combustion engine system including an eCompressor as a secondary air pump (SAP) for injecting air into an exhaust system of the ICE, controllable valves enable the turbocharger compressor and the SAP to provide two-stage compressed air to the intake of the ICE in certain operating conditions, or to feed the air via a secondary air injection line (SAI line) into the exhaust system in other conditions. A conduit is tapped off the discharge of the SAP and connects with discharge ducting from the turbocharger compressor, and an on/off valve configured for defined leakage in the “off” position controls flow through the conduit. When the air from the SAP is needed only for injection air, the leakage through the leaky valve into the intake system suppresses surge of the SAP.

Abstract: A turbocharger includes a turbine housing including an interior surface defining a turbine housing interior. The interior surface extends between a turbine housing inlet and a turbine housing outlet. The turbine housing also includes a wastegate duct disposed downstream of the turbine housing inlet and defining a wastegate channel. The turbocharger also includes a valve seat disposed about the wastegate channel, with the valve seat having a valve seat plane extending along the valve seat. The turbocharger further includes a wastegate assembly including a valve element engageable with the valve seat. The wastegate channel extends along a channel axis, and the channel axis is obliquely oriented with respect to the valve seat plane such that the wastegate channel and the valve element are configured to direct exhaust gas to a catalytic converter.

Abstract: A stator vane is provided. The stator vane including an airfoil that has a nominal suction-side profile substantially in accordance with suction-side Cartesian coordinate values of X, Y, and Z set forth in Table I. The Cartesian coordinate values of X, Y, and Z are defined relative to a point data origin at a base of the airfoil. The Cartesian coordinate values of X, Y, and Z are non-dimensional values that are convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y, and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values are connected by smooth continuing arcs to define suction-side profile sections at each Z value. The suction-side profile sections at the Z values are joined smoothly with one another to form a complete airfoil suction-side shape.

Abstract: A system converts mechanical wave energy into electrical energy. The system includes a wave energy converter (WEC), which includes a surface float, a reaction structure, a plurality of flexible tethers, and a plurality of drivetrains. Each flexible tether connects the surface float to the reaction structure. Each drivetrain is connected to a corresponding flexible tether. Each flexible tether has a length established to treat the system as an inverse pendulum to utilize a horizontal surge motion of the surface float to present tension at the corresponding drivetrain for production of electrical energy from the horizontal surge motion.

Abstract: A gas turbine system includes a compressor section, a turbine section, a combustor section. The combustor section is in fluid communication with a fuel supply via a fuel supply line. The water circuit includes a first water line extending between a first feed water supply line and a return water line. The gas turbine system further includes an extraction-air line that extends between an inlet port on the compressor section and an outlet port on the turbine section. A first heat exchanger thermally couples the first water line to the extraction-air line for transferring heat from a flow of extraction-air within the extraction-air line to a flow of water within the water circuit. A second heat exchanger thermally couples the first water line to the fuel supply line for transferring heat from the flow of water within the water circuit to a flow of fuel within the fuel supply line.

Abstract: In a rotary electric machine housing, a first bearing and a second bearing are provided for supporting a rotating shaft. A lubricating oil is supplied to the first bearing and the second bearing. Further, a gas is supplied to the first bearing and the second bearing. The lubricating oil and the gas are recovered by a single recovery device.

Abstract: A system for feeding operating gas to a drive (1) of a motor vehicle, including an atmosphere-side suction inlet (2a) for air under atmospheric pressure, and a feed line (2) for the operating gas to the drive (1) under an operating pressure, the operating gas which is conducted to the drive comprising at least part of the air which is sucked in, at least part of the operating gas being conducted through a turbomachine (3) upstream of the drive (1) in a first operating type, the turbomachine (3) comprising an electric generator (4), and the turbomachine (3) being operated in a second operating type as a compressor for the operating gas, an actuable valve arrangement (5) being provided, at least part of the air which is sucked in being conducted in a turbine direction (T) through the turbomachine (3) in a first position of the valve arrangement (5), and at least part of the air which is sucked in being conducted in a reversed compressor direction (V) through the turbomachine (3) in a second position of the valv

Abstract: A radially flexible connection joint for a gas turbine engine includes an exhaust manifold flange operatively coupling an exhaust cylinder to an exhaust manifold of the gas turbine engine. The exhaust cylinder includes a cylindrical flange that extends radially outwardly from a rotation axis of the gas turbine. The cylindrical flange defines a downstream axial face. The exhaust manifold is positioned downstream from the exhaust cylinder. The exhaust manifold includes an upstream edge. The exhaust cylinder and the exhaust manifold are substantially coaxial with the rotation axis of the gas turbine. The exhaust manifold flange has a bellows portion that extends radially between the cylindrical flange of the exhaust cylinder and the upstream edge of the exhaust manifold. The bellows portion permits relative radial motion of the exhaust cylinder and the exhaust manifold.