Patent ID: 7806110

Claim:
A marine propulsion system comprising an engine comprising a plurality of cylinders and a plurality of pistons operatively attached to a crankshaft, each of said plurality of pistons being disposed within an associated one of said plurality of cylinders, said crankshaft being supported for rotation about a generally vertically axis, a turbocharger comprising a turbine portion and a compressor portion, said turbocharger being disposed above a generally horizontal plane that extends through a vertical center of said plurality of cylinders, said turbine portion comprising a turbine rotor supported for rotation about a turbine axis, said compressor portion comprising a compressor rotor supported for rotation about a compressor axis, said plurality of cylinders being distributed vertically in a configuration which is generally perpendicular to said generally horizontal plane, said turbine axis and said compressor axis being coaxial and disposed colinearly with a turbocharger axis, said turbocharger axis being generally parallel with said generally horizontal plane, a turbine inlet configured to conduct exhaust gas from said engine into said turbocharger, a turbine outlet configured to conduct exhaust gas from said turbocharger to an exhaust passage of said marine propulsion system, a compressor inlet configured to direct air into said turbocharger, a compressor outlet configured to direct air from said turbocharger to said plurality of cylinders, said plurality of cylinders being vertically aligned along a vertical alignment plane, said turbine portion and said compressor portion being connected together by a turbocharger shaft extending axially therebetween, said turbine portion, said turbocharger shaft and at least a section of said compressor portion being on one axial side of said vertical alignment plane, wherein said compressor inlet is on another axial side of said vertical alignment plane distally opposite said one side, wherein said turbine inlet, said turbine outlet and said compressor outlet are all on said one axial side of said vertical alignment plane, wherein said compressor portion straddles said vertical alignment plane such that one section of said compressor portion is on said one axial side of said vertical alignment plane, and another section of said compressor portion is on said other axial side of said vertical alignment plane, wherein said vertical alignment plane extends vertically through the centerline diameters of said plurality of cylinders.