Volvo Lastvagnar Ab

Per Andersson

Magnus Ising

Kent Giselmo

Lars Sundin

Sebastian Krausche

Daniel Grunditz

Ulrich Gobert

Martin Bauer

A method of controlling turbine efficiency in a turbo unit provided on an internal combustion engine includes providing a flow of gas in an area upstream a turbine at a direction different to the flow of exhaust gases in the same area, regulating the flow by a valve, and controlling the valve from a control unit having at least boost pressure and/or EGR flow as input parameters.

Method and apparatus for controlling turbine efficiency

A turbocharger unit () for an internal combustion engine () with at least one exhaust line () for conducting exhaust gases away from the combustion chamber () of the engine and at least one inlet line () for supplying air to the combustion chamber. The turbocharger unit includes a turbine () which interacts with a compressor () for extracting energy from the exhaust gas flow of the engine and pressurizing the inlet air of the engine. The compressor () is of radial type and provided with an impeller with backswept blades () where the blade angle (&#x3b2;) between an imaginary extension of the center line of the blade between root section and tip section in the direction of the outlet tangent and a line () which connects the center axis of the impeller to the outer tip of the blade is at least roughly 45&#xb0;. The turbine () which drives the compressor () is of radial type.

Turbo compressor system for an internal combustion engine comprising a compressor of radial type and provided with an impeller with backswept blades

A turbocharger system for an internal combustion engine having at least one exhaust line for evacuating exhaust gases from the combustion chamber of the engine and at least on inlet line for supplying air to the combustion chamber. A high-pressure turbine interacts with a high-pressure compressor and a low-pressure turbine interacts with a low-pressure compressor to extract energy from the exhaust flow of the engine and pressurize the inlet air of the engine. Both compressor stages are of the radial type and are provided with compressor wheels having backswept blades, in which a blade angle between an imaginary extension of the blade along the centerline between root section and tip section in the direction of the outlet tangent and a line connecting the center axis of the compressor wheel to the outer point of the blade, is at least about 40 degrees.

Turbochanger system for internal combustion engine comprising two compressor stages of the radial type provided with compressor wheels having backswept blades

A turbocharger unit for a multicylinder internal combustion engine has at least two exhaust lines for the evacuation of exhaust gases from the combustion chamber of the engine and at least one inlet line for the supply of air to the combustion chamber. The turbocharger unit includes at least one turbine which cooperates with at least one compressor to extract energy from the exhaust flow of the engine and pressurize the inlet air of the engine. The turbine is provided with a worm-shaped housing having at least two flow paths which are defined by guide tongues in the housing and which conduct mutually separate exhaust flows via stator blades to at least one turbine wheel. In order to maintain the kinetic energy in the separate exhaust flows, each respective guide tongue meets a stator blade extending toward the tongue.

Turbo charger unit comprising double entry turbine

A turbocharger system for an internal combustion engine having at least one exhaust line for evacuating exhaust gases from the combustion chamber of the engine and at least one inlet line for supplying air to the combustion chamber. A high-pressure turbine interacts with a high-pressure compressor forming a high-pressure turbo unit with a common rotation axis. A low-pressure turbine interacts with a low-pressure compressor forming a low-pressure turbo unit with a common rotation axis. The high-pressure turbo unit and the low-pressure turbo unit are serially placed with the rotation axes essentially concentric and with the high-pressure turbine and the low-pressure turbine placed adjacent to each other and coupled together by an intermediate piece configured as a flow duct. The low-pressure turbo unit () is attached to one part of the internal combustion engine, while the high-pressure turbo unit is attached to another part of the engine.

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Malmö, Sweden

Per Andersson