A centrifugal compressor for a turbocharger includes an inlet-adjustment mechanism in an air inlet for the compressor, operable to move between an open position and a closed position in the air inlet. The inlet-adjustment mechanism includes a plurality of vanes formed as ring segments and disposed about the air inlet and each movable circumferentially and radially inwardly through a slot in the air inlet wall so as to form an orifice of reduced diameter relative to a nominal diameter of the inlet. Movement of the inlet-adjustment mechanism from the open position to the closed position is effective to shift the compressor's surge line to lower flow rates.

A hydraulic driving device for a steam valve includes a plurality of hydraulic actuators to generate driving force to be transmitted to the valve body through a valve shaft of the steam valve. The hydraulic actuators each include a cylinder, a piston that is capable of reciprocating in the cylinder, and a rod having respective ends connected to the piston and valve shaft. The hydraulic actuators include a main actuator including a throttle portion for regulating a flow of pressure oil in a hydraulic chamber defined by the cylinder and piston so that a damping force is applied to the valve body during its closing operation. The one or more hydraulic actuators other than the main actuator include at least one sub actuator not having the throttle portion. The hydraulic chamber of the sub actuator communicates with the hydraulic chamber of the main actuator.

An aeroengine includes an inlet duct having a section including opposed and substantially flat first and second peripheral walls, a first deformable wall providing a portion of the first peripheral wall and a second deformable wall providing a portion of the second peripheral wall. The deformable walls are deformable between undeployed and deployed positions, and each include panels pivotally connected one to another to allow pivotal movement of the panels relative to respective adjacent panels about respective parallel axes oriented transverse to a direction of the air flow. The deformable walls in the undeployed position each being substantially flat to substantially avoid interfering with the air flow, and in the deployed position each projecting into the inlet duct from the respective peripheral wall to reduce an effective cross-sectional area of the inlet duct to reduce line-of-sight noise propagation.

An assembly for a two-stage turbocharger can include a first turbocharger stage and a second turbocharger stage where one of the stages includes a boss that includes a bore; an exhaust bypass valve that includes an arm pivotable to orient the exhaust bypass valve in an open state and a closed state; a valve shaft disposed at least in part in the bore and operatively coupled to the exhaust bypass valve where the valve shaft includes an inner end, an outer end and an axial stop disposed between the inner end and the outer end; an outer bushing disposed at least in part in the bore and located axially along the valve shaft; and an inner bushing disposed at least in part in the bore and located axially along the valve shaft between the axial stop and a portion of the arm of the exhaust bypass valve.

An adjusting mechanism, adaptive to a main body of a centrifugal compressor, comprises a diffuser channel width adjusting assembly and a gas bypass assembly. The diffuser channel width adjusting assembly comprises a width adjusting annular plate and a first valve stem. The width adjusting annular plate is movably disposed in a diffuser channel of the main body. The first valve stem is connected to the width adjusting annular plate, and configured for driving the width adjusting annular plate to move to adjust the width of the diffuser channel. The gas bypass assembly comprises a gas bypass valve and a second valve stem. The gas bypass valve is movably disposed in a gas bypass passage of the main body. The second valve stem is connected to the gas bypass valve, and configured for driving the gas bypass valve to move to adjust the opening of the gas bypass port.

An aeroengine has an inlet system which includes at least one deformable wall disposed adjacent a peripheral wall of an inlet duct and a plurality of acoustic cells attached to a back side in fluid communication through respective holes in the at least one deformable wall with an inlet duct air flow. The at least one deformable wall selectively forms part of the peripheral wall of the inlet duct when in an undeployed position and selectively forms a curved profile projecting into the inlet duct to reduce line-of-sight noise propagation through the inlet duct.

An aeroderivative gas turbine including an air intake plenum; a compressor with a compressor air intake in fluid communication with the air intake plenum; a combustor; a high pressure turbine; a power turbine. A forced air-stream generator is arranged in fluid communication with the air intake plenum. A shutter arrangement is provided in a combustion-air flow path, arranged and controlled to close the combustion-air flow path for pressurizing said air intake plenum by means of the forced air-stream generator to a pressure sufficient to cause pressurized air to flow through the aeroderivative air turbine.

A method for extending thermodynamic turbine mapping of a turbocharger, the turbocharger including a turbine and a compressor, the method including the steps of providing a steady-state turbocharger gas test stand configured to flow continuous gas to the turbocharger, the test stand including a throttle device disposed upstream of an inlet of the compressor of the turbocharger, and varying an area of the inlet with the throttle device to change density of the continuously flowing gas at the inlet of the compressor and establish a choked-flow condition for extending the thermodynamic turbine mapping of the turbocharger.

A variable displacement supercharger includes a turbine having: a turbine housing that forms a scroll flow passage disposed around a turbine impeller; a variable nozzle unit that includes a second nozzle ring that faces the scroll flow passage and forms a part of an inner wall of the scroll flow passage; and an annular seal member that seals the gap between the turbine housing and the second nozzle ring. The seal member has a disc spring structure that is inserted into the gap and biases the turbine housing and the second nozzle ring in an axial direction of rotation, and is arranged further inside than the scroll flow passage in the radial direction of the turbine impeller.

A twin scroll turbocharger device for an internal combustion engine includes a turbine and a compressor, wherein the turbine comprises a first turbine scroll and a second turbine scroll, and wherein at least the first turbine scroll is provided with a turbine scroll inlet valve such that the exhaust gas flow through the first turbine scroll is controllable. The twin scroll turbocharger device is further characterized in that a bypass conduit is provided between a compressor and at least the first turbine scroll. The bypass conduit is provided with a bypass conduit valve such that a flow through the bypass conduit is controllable.