A turbocharger and a method are disclosed. The turbocharger includes a casing having an inlet end and an outlet end. A flow passage within the casing may have a substantially continuous inner surface and may be configured to pass inlet air from the inlet end to the outlet end. A compressor wheel may be located in the casing and may have at least one main blade and may be configured to rotate within the casing to compress the inlet air. A flow disrupting feature on the casing may be configured to disrupt the continuity of the inner surface and may be located at a leading edge of the at least one main blade. The flow disrupting feature may be closed to upstream communication with the flow passage except via the flow passage.

A turbocharger and a method are disclosed. The turbocharger includes a casing having an inlet end and an outlet end. A flow passage within the casing may have a substantially continuous inner surface and may be configured to pass inlet air from the inlet end to the outlet end. A compressor wheel may be located in the casing and may have at least one main blade and may be configured to rotate within the casing to compress the inlet air. A flow disrupting feature on the casing may be configured to disrupt the continuity of the inner surface and may be located at a leading edge of the at least one main blade. The flow disrupting feature may be closed to upstream communication with the flow passage except via the flow passage.

The present disclosure relates to an engine assembly for a vehicle. The engine assembly comprises an engine including an extended crankshaft with additional main bearings, an alternator or a generator, a drive chain assembly, and a starter motor assembly. The engine may be used in different models of the vehicle having different characteristics, which enables to interchange or replace an internal generator with an external alternator, and vice versa in addition enable to use a common starter motor assembly, crankshaft, crankcase, and drive chain assembly for both engine configuration without modifying a basic design of the engine. Further, placement of the starter motor assembly provides a compact arrangement. In addition, the extended crankshaft with the additional main bearings enables low noise level operation, avoids additional shafts and roller bearings to be attached, and cost effective. Similarly, the drive chain assembly produces less vibration and noise.

The present disclosure relates to an engine assembly for a vehicle. The engine assembly comprises an engine including an extended crankshaft with additional main bearings, an alternator or a generator, a drive chain assembly, and a starter motor assembly. The engine may be used in different models of the vehicle having different characteristics, which enables to interchange or replace an internal generator with an external alternator, and vice versa in addition enable to use a common starter motor assembly, crankshaft, crankcase, and drive chain assembly for both engine configuration without modifying a basic design of the engine. Further, placement of the starter motor assembly provides a compact arrangement. In addition, the extended crankshaft with the additional main bearings enables low noise level operation, avoids additional shafts and roller bearings to be attached, and cost effective. Similarly, the drive chain assembly produces less vibration and noise.

Disclosed is an air supply system for supplying air to an outside of a hull of a vessel, the vessel holding a combustion engine. The air supply system comprises one or more air discharge units (ADUs) for releasing compressed air to an outside of the hull below a waterline of the vessel. The air supply system comprises a plurality of turbocharger(s) for supplying a compressed air flow to the combustion engine of the vessel via a first flow path. The plurality of turbochargers each comprises a turbine configured to be driven by an exhaust gas flow of the combustion engine and a compressor connected to the turbine and comprising an inlet for receiving air and an outlet for providing the compressed air flow to the first flow path. The plurality of turbochargers comprises a first turbocharger and a second turbocharger arranged in series with the compressor of the second turbocharger being downstream of the compressor of the first turbocharger in the first flow path. The air supply system comprises a first sub-path and a second sub-path branching off the first flow path and supplying the sub-flow of air to the ADUs. The first sub-path branches off from the first flow path downstream of the first turbocharger and upstream of the second turbocharger and wherein the second sub-path branches off from the first flow path downstream of both the first turbocharger and the second turbocharger.

Disclosed is an air supply system for supplying air to an outside of a hull of a vessel, the vessel holding a combustion engine. The air supply system comprises one or more air discharge units (ADUs) for releasing compressed air to an outside of the hull below a waterline of the vessel. The air supply system comprises a plurality of turbocharger(s) for supplying a compressed air flow to the combustion engine of the vessel via a first flow path. The plurality of turbochargers each comprises a turbine configured to be driven by an exhaust gas flow of the combustion engine and a compressor connected to the turbine and comprising an inlet for receiving air and an outlet for providing the compressed air flow to the first flow path. The plurality of turbochargers comprises a first turbocharger and a second turbocharger arranged in series with the compressor of the second turbocharger being downstream of the compressor of the first turbocharger in the first flow path. The air supply system comprises a first sub-path and a second sub-path branching off the first flow path and supplying the sub-flow of air to the ADUs. The first sub-path branches off from the first flow path downstream of the first turbocharger and upstream of the second turbocharger and wherein the second sub-path branches off from the first flow path downstream of both the first turbocharger and the second turbocharger.

A turbocharger includes a turbine housing that defines a flow passage for a fluid. The turbine housing includes a turbine shroud member. The turbocharger also includes a turbine wheel supported for rotation within the turbine housing relative to the turbine shroud member. The turbine wheel is configured to rotate as the fluid flows through the flow passage. Moreover, the turbocharger includes a port extending through the turbine shroud member. The port is configured to receive a portion of the fluid flowing through the flow passage.

A turbocharger includes a turbine housing that defines a flow passage for a fluid. The turbine housing includes a turbine shroud member. The turbocharger also includes a turbine wheel supported for rotation within the turbine housing relative to the turbine shroud member. The turbine wheel is configured to rotate as the fluid flows through the flow passage. Moreover, the turbocharger includes a port extending through the turbine shroud member. The port is configured to receive a portion of the fluid flowing through the flow passage.

A compound engine assembly having an engine core including at least one internal combustion engine in driving engagement with an engine shaft, a compressor having an outlet in fluid communication with an inlet of the engine core and including at least one rotor rotatable about an axis coaxial with the engine shaft, the engine shaft in driving engagement with the compressor rotor, and a turbine section having an inlet in fluid communication with an outlet of the engine core and including at least one rotor engaged on a rotatable turbine shaft, the turbine shaft configured to compound power with the engine shaft. The turbine and engine shafts are parallel to and radially offset from one another, and the turbine shaft and the axis of the compressor rotor are parallel to and radially offset from one another. A method of driving a rotatable load of an aircraft is also discussed.

A compound engine assembly having an engine core including at least one internal combustion engine in driving engagement with an engine shaft, a compressor having an outlet in fluid communication with an inlet of the engine core and including at least one rotor rotatable about an axis coaxial with the engine shaft, the engine shaft in driving engagement with the compressor rotor, and a turbine section having an inlet in fluid communication with an outlet of the engine core and including at least one rotor engaged on a rotatable turbine shaft, the turbine shaft configured to compound power with the engine shaft. The turbine and engine shafts are parallel to and radially offset from one another, and the turbine shaft and the axis of the compressor rotor are parallel to and radially offset from one another. A method of driving a rotatable load of an aircraft is also discussed.