An apparatus and methods are provided for a turbocharger intake system for an off-road vehicle. The turbocharger intake system comprises a turbocharger disposed at a rear of an engine of the vehicle, such that heat radiated from the turbocharger is directed rearward of the engine during operation of the vehicle. The turbocharger is coupled with an exhaust manifold for conducting exhaust gases from the engine to the turbocharger. An air intake duct is routed from an intake air filter canister to the turbocharger for conveying filtered air to the turbocharger. A suitable air filter is housed within the intake air filter canister so as to remove airborne particulate matter from the air entering the engine. The turbocharger drives charged intake air through an intercooler for lowering the temperature of charged intake air. The charged intake air is directed to combustion chambers of the engine by way of an intake manifold.

A turbocharger includes a shaft, a compressor wheel, a turbine wheel, and a bearing assembly including an inner race, a first outer race spaced from the inner race, a second outer race spaced from the inner race, a first rolling element disposed between the first outer race and the inner race, and a second rolling element disposed between the second outer race and the inner race. The bearing assembly includes a first biasing member configured to bias the first outer race toward the second outer race and against the first rolling element, and preload the first rolling element with a preloading force, and a second biasing member configured to bias the second outer race toward the first outer race and against the second rolling element, and preload the second rolling element with a second preloading force. The first preloading force is different than the second preloading force.

A turbocharger includes a shaft, a compressor wheel, a turbine wheel, and a bearing assembly including an inner race, a first outer race spaced from the inner race, a second outer race spaced from the inner race, a first rolling element disposed between the first outer race and the inner race, and a second rolling element disposed between the second outer race and the inner race. The bearing assembly includes a first biasing member configured to bias the first outer race toward the second outer race and against the first rolling element, and preload the first rolling element with a preloading force, and a second biasing member configured to bias the second outer race toward the first outer race and against the second rolling element, and preload the second rolling element with a second preloading force. The first preloading force is different than the second preloading force.

A system for introducing a gaseous fuel to an internal combustion engine includes a fuel storage device, a compressor, and an air and fuel conduit in fluid communication with the fuel storage device and with the compressor. The air and fuel conduit includes a first passage and a second passage that includes a first portion and a second portion, the second portion being a venturi portion, the second passage being fluidly connected to the compressor in parallel with the first passage.

A bearing device includes a rotary part which is configured to be rotatable about a rotational axis and has a rotary surface intersecting the rotational axis, and a stationary part which has a stationary surface facing the rotary surface. One of the rotary surface or the stationary surface includes a bearing surface part for forming a bearing oil film. The rotary surface includes a first inner circumferential region, and a first outer circumferential region facing the stationary surface on a radially outer side of the bearing surface part and having higher oleophobicity than the first inner circumferential region.

A dual turbocharger system for an engine is provided. In one example, the dual turbocharger system may include two variable geometry turbines (VGTs), with each turbine being of the same size and operating in parallel, and with each compressor of the turbocharger operating in series, the first compressor of the first turbocharger being larger than the second compressor of the second turbocharger.

An internal combustion engine with at least one combustion chamber, at least one fuel delivery line for the delivery of fuel to at least one combustion chamber, and at least one differential pressure control valve for controlling the pressure in the at least one fuel delivery line. The at least one differential pressure control valve is configured to perform a valve opening or valve closing movement based on a pressure difference between the at least one fuel delivery line and a reference volume having a reference pressure. The internal combustion engine further includes at least one pressure relief valve, separate from the at least one differential pressure control valve, and configured to open to cause a pressure relief in the reference volume and a decrease in the reference pressure if a drop occurs in the power to be performed by the internal combustion engine.

A power system includes an engine; an exhaust gas recirculation (EGR) system supplying a first portion of the engine exhaust gas from the exhaust manifold to the intake manifold; a turbine generator in communication with the exhaust manifold and configured to be driven by a second portion of the engine exhaust gas from the exhaust manifold to generate electrical power; a power network including at least one battery to store the electrical power generated by the turbine generator; and an electric compressor in fluid communication with the intake manifold and configured to be powered by the electrical power from the at least one battery of the power network and to compress at least a portion of the intake air for the engine.

Aircraft power plants including combustion engines, and associated methods for recuperating waste heat from such aircraft power plants are described. A method includes transferring the heat rejected by the internal combustion engine to supercritical CO.sub.2 (sCO.sub.2) used as a working fluid in a heat engine. The heat engine converts at least some the heat transferred to the sCO.sub.2 to mechanical energy to perform useful work onboard the aircraft.

Aircraft power plants including combustion engines, and associated methods for recuperating waste heat from such aircraft power plants are described. A method includes transferring the heat rejected by the internal combustion engine to supercritical CO.sub.2 (sCO.sub.2) used as a working fluid in a heat engine. The heat engine converts at least some the heat transferred to the sCO.sub.2 to mechanical energy to perform useful work onboard the aircraft.