Volvo Lastvagnar Ab

Volvo Truck Corporation

Magnus Ising

Per Andersson

Kent Giselmo

Lars Sundin

Sebastian Krausche

Arne Andersson

Fredrik Rahm

Tove Audhav

Daniel Grunditz

Ulrich Gobert

Peter Tennevall

Nader Najjar

An air cooled resistor arrangement comprising a first elongated tube member forming a first air flow channel and a second elongated tube member forming a second air flow channel, wherein the first elongated tube member is at least partly housed inside the second elongated tube member. The air-cooled resistor arrangement further comprises an air dilution portion comprising at least one opening at which the first air flow channel is arranged in fluid communication with the second air flow channel.

Air-cooled resistor arrangement

An air cooled resistor arrangement comprising a first elongated tube member which is housed inside a second elongated tube member. The first and second elongated tube members are spaced apart from each other by an air gap for allowing a flow of air to flow through the first elongated tube member and the air gap.

Air cooled resistor

A turbocharger unit for an internal combustion engine having at least one exhaust line 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 is provided. The turbocharger unit includes a turbine which interacts with a compressor in order to extract energy from the exhaust-gas flow of the engine and pressurize the inlet air of the engine. The compressor is of the radial type and is provided with an impeller having backswept blades in which the blade angle 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 connecting the center axis of the impeller to the outer tip of the blade is at least about 40 degrees. The ratio between the inlet diameter of the impeller and its outlet diameter lies within the range 0.50-0.62. The compressor diffuser is provided with blades, the length of which has a ratio to the distance between them, along the periphery in the blade inlet, within the range 0.7-1.5.

Compressor

A gas flow unit includes a gas flow inlet, a gas flow outlet and a gas flow chamber configured to convey a gas flow from the inlet to the outlet, wherein the gas flow inlet is configured to convey the gas flow in a first direction into the gas flow chamber and wherein the gas flow outlet is configured to convey the gas flow in a second direction from the gas flow chamber, wherein the second direction is angular in relation to the first direction, and wherein the gas flow inlet is an inlet into the gas flow chamber and the gas flow outlet is an outlet from the gas flow chamber. In the first gas flow direction, the gas flow chamber extends beyond a projection of an outer periphery of the gas flow outlet and defines a prolongation configured for conveying a first part of the gas flow such that it enters the gas flow outlet from a different direction than a second part of the gas flow entering the gas flow outlet without passing through the prolongation.

Gas flow unit, a gas treatment device and a combustion engine provided therewith

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.

Growing community of inventors

Lund, Sweden

Magnus Ising