Volvo Lastvagnar Ab

Volvo Aero Corporation

Volvo Truck Corporation

Schneider Electric Industries Sas

Lars Sundin

Sebastian Krausche

Kent Giselmo

Magnus Ising

Per Andersson

Bertil Jönsson

Ulrich Gobert

Daniel Grunditz

Per I Persson

Magnus Ekstrand

Håkan WÄNGSTRE

Magnus Brunberg

Staffan Eriksson

Sture Dahl

A device for controlling a gas flow through a passage includes a plurality of pivotable gas flow control vanes. The pivot axes of a first and a second adjacent vane are spaced so that a trailing edge of the first vane overlaps a leading edge of the second vane when the first and second adjacent vanes are positioned in a first mutual end state for substantially restricting the gas flow through the passage. The second vane includes a recess with such a shape that the trailing edge of the first vane is at least partly received in the recess when the first and second adjacent vanes are positioned in the first mutual end state.

Device for controlling a gas flow, an exhaust aftertreatment system and a system for propelling a vehicle

A power turbine unit includes a turbine housing, an exhaust duct, a turbine wheel with blades positioned in the exhaust duct, a shaft rigidly connected to the turbine wheel and rotatably supported in the housing, and an oil sealing system. The oil sealing system includes a sealing arrangement positioned in the vicinity of the turbine wheel for preventing oil from escaping from the turbine housing along the shaft to the exhaust duct. The oil sealing system further includes a buffer gas duct that is arranged to supply exhaust gas from the exhaust duct to the sealing arrangement for pressurizing the sealing arrangement.

Pressurized seal system for a power turbine unit

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

An internal combustion engine is provided with an exhaust gas pipe for taking exhaust gases from the engine's combustion chamber and an intake pipe for supplying air to the combustion chamber. The engine includes a turbo charging system with a high-pressure turbine that interacts with a high-pressure compressor and a low-pressure turbine that interacts with a low-pressure compressor, for recovery of energy from the engine's exhaust gas flow and pressurizing of the engine's intake air. The high-pressure turbine is connected to the low-pressure turbine via a duct. An exhaust gas pressure regulator is located in the duct between the high-pressure turbine and the low-pressure turbine.

Internal combustion engine with two-stage turbo charging system

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

Method and arrangement for providing and controlling a gas turbine () at least one turbine ('), at least one compressor () driven by the turbine and a combustion chamber () arranged between the compressor and the turbine in the airflow path. The gas turbine includes devices () for direct measurement of the air mass flow at a position upstream of the combustion chamber in the airflow path, with the aim of regulating the quantity of fuel that is delivered to the combustion chamber () on the basis of the measured air mass flow.

Gas turbine and a method for controlling a gas 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.

Turbo compressor system for internal combustion engine comprising two serially placed turbo units with their rotation axes essentially concentric

Method for manufacturing a vane () to a gas turbine component intended for guiding a gas flow. The vane () is produced by casting, and an internal hole () for coolant is then cut out of the cast vane (). The vane () is provided with a starter hole (), either during casting or once casting is completed, following which the internal hole () for coolant is cut out of the vane, proceeding from the starter hole. A method is also disclosed for manufacturing a gas turbine component including a plurality of vanes () for guiding a gas flow. The gas turbine component is cast in such a way that it includes the vanes and an internal hole () for coolant is then cut out of each of the vanes.

Method for manufacturing a vane to a gas turbine component and a method for manufacturing a gas turbine component

Method and arrangement for providing a gas turbine () having a first compressor (), a combustion chamber () and a first turbine (), the turbine being adapted to drive the compressor via a first shaft (). The gas turbine also has a bleed valve () arranged upstream of the first turbine for conducting part of a gas compressed by the compressor past it during engine braking. The invention also relates to a method for engine-braking a gas turbine.

Method and arrangement for providing a gas turbine, and engine-braking therefore

An internal combustion engine is disclosed including at least two cylinders, each including an inlet port, an air inlet manifold for providing air to the cylinders, at least two outlets for emitting exhaust gases from the cylinders, a recirculation conduit for reducing harmful emissions from the exhaust gases and extending from one of the outlet for recirculating the exhaust gases from an outlet to a connection point in the air inlet manifold thereby defining a first volume from the outlet to the connection point, the air inlet manifold being divided into at least two further volumes defined by the distance between the connection point to each of the inlet points, at least one turbine for recovering energy from the exhaust gases, and a compressor for compressing air supplied to the air inlet manifold, the first volume and the further volumes being dimensioned such that the recirculated exhaust gases are substantially equally distributed between each of the cylinders.

Growing community of inventors

Malmö, Sweden

Lars Sundin