Loading patent…
AssigneeVolvo Lastvagnar AB
InventorsUlrich Gobert, Lars Sundin, Magnus Ising, Daniel Grunditz, Per Andersson, Kent Giselmo, Sebastian Krausche
Estimating the term…
A turbocharger system for an internal combustion engine having at least one exhaust line (15, 16) 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 (17) interacts with a high-pressure compressor (19) and a low-pressure turbine (21) interacts with a low-pressure compressor (23) in order 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. The high-pressure turbine (17) is of the radial type and is connected to the low-pressure turbine by a short intermediate duct (20). The low-pressure turbine (21 ) is provided with inlet guide rails (34).
A turbocharger system for an internal combustion engine (10) having at least one exhaust line (15, 16) for evacuating exhaust gases from the combustion chamber (11) of the engine and at least one inlet line (12) for supplying air to said combustion chamber, the turbocharger system includes a high-pressure turbine (17) interacting with a high-pressure compressor (19) and a low-pressure turbine (21) interacting with a low-pressure compressor (23) for extracting energy from the exhaust flow of the engine and pressurizing the inlet air of the engine, both compressor stages are of the radial type and are provided with compressor wheels having backswept blades (35) in which the blade angle (βb2), between an imaginary extension of the centerline of the blade between root section and tip section in the direction of the outlet tangent and a line (36) connecting the center axis of the compressor wheel to the outer point of the blade, is at least about 40 degrees, the high-pressure turbine (17) is of the radial type and is connected to the low-pressure turbine by a short intermediate duct (20) and the low-pressure turbine (21) is provided with inlet guide rails (34).
A turbocharger system in an internal combustion engine (10) having at least one exhaust line (15, 16) for evacuating exhaust gases from the combustion chamber (11) of the engine and at least one inlet line (12) for supplying air to said combustion chamber, the turbocharger system includes a high-pressure turbine (17) interacting with a high-pressure compressor (19) and a low-pressure turbine (21) interacting with a low-pressure compressor (23) for extracting energy from the exhaust flow of the engine and pressurizing the inlet air of the engine, both compressor stages are of the radial type and are provided with compressor wheels having backswept blades (35) in which the blade angle (βb2), between an imaginary extension of the centerline of the blade between root section and tip section in the direction of the outlet tangent and a line (36) connecting the center axis of the compressor wheel to the outer point of the blade, is at least about 40 degrees, the high-pressure turbine (17) is of the radial type and is connected to the low-pressure turbine by a short intermediate duct (20) and the low-pressure turbine (21) is provided with inlet guide rails (34) and the internal combustion engine (10) further has an early or late shutting of the inlet valve relative to the lower dead center piston-position.
A turbocharger system in an internal combustion engine (10) having at least one exhaust line (15, 16) for evacuating exhaust gases from the combustion chamber (11) of the engine and at least one inlet line (12) for supplying air to said combustion chamber, the turbocharger system includes a high-pressure turbine (17) interacting with a high-pressure compressor (19) and a low-pressure turbine (21) interacting with a low-pressure compressor (23) for extracting energy from the exhaust flow of the engine and pressurizing the inlet air of the engine, both compressor stages are of the radial type and are provided with compressor wheels having backswept blades (35) in which the blade angle (βb2), between an imaginary extension of the centerline of the blade between root section and tip section in the direction of the outlet tangent and a line (36) connecting the center axis of the compressor wheel to the outer point of the blade, is at least about 40 degrees, the high-pressure turbine (17) is of the radial type and is connected to the low-pressure turbine by a short intermediate duct (20) and the low-pressure turbine (21) is provided with inlet guide rails (34) and the internal combustion engine (10) is further provided with exhaust gas recirculation, in which exhaust gases can be removed after the outlet of the low-pressure turbine (21) and recirculated to the inlet side of the engine before the inlet of the low-pressure compressor.
Dependencies are inferred from the claim text.