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
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.
대표청구항▼
1. A turbocharger unit for an internal combustion engine, the internal combustion engine having at least one exhaust line for evacuation of exhaust gases from a combustion chamber of the internal combustion engine and at least one inlet line for supply of air to the combustion chamber, the turbochar
1. A turbocharger unit for an internal combustion engine, the internal combustion engine having at least one exhaust line for evacuation of exhaust gases from a combustion chamber of the internal combustion engine and at least one inlet line for supply of air to the combustion chamber, the turbocharger unit comprising: a turbine and a compressor, the turbine interacting with the compressor in order to extract energy from an exhaust-gas flow of the internal combustion engine and to pressurize inlet air of the internal combustion engine, wherein the compressor is a radial compressor and the radial compressor includes: an impeller having an axis of rotation, and,a diffuser disposed downstream from the impeller in a direction of fluid flow through the radial compressor, andthe impeller includes: a central hub disposed along the axis of rotation of the impeller and including backswept full blades and splitter blades both of which are symmetrically spaced about the hub, and each of the backswept full blades and each of the splitter blades being attached to the hub and respectively extending in an outward manner away from the hub, and only one splitter blade of the splitter blades is disposed between each pair of adjacent backswept full blades symmetrically spaced about the hub, and each of the backswept full blades has an inlet edge and each of the splitter blades has an inlet edge,the backswept full blades in which a blade angle, between an imaginary extension of a center line of at least one backswept full blade of the backswept full blades, between a root section and a tip section of the at least one backswept full blade, in a direction of an outlet tangent and a line connecting the rotation axis of the impeller to an outer tip of the at least one backswept full blade of the backswept full blades, is at least 40 degrees, and a ratio between an inlet diameter of the impeller and an outlet diameter of the impeller lies within a range of 0.50-0.62, the inlet edge of each backswept full blade of the backswept full blades extending outwardly from the hub so as to be generally disposed along a plane positioned transverse to the rotation axis of the impeller, and the splitter blades, the inlet edge of each splitter blade of the splitter blades being disposed axially downstream of the inlet edge of each of the backswept full blades, the inlet edge of each splitter blade extending between a radially innermost end disposed adjacent the hub and a radially outermost end spaced apart from the hub and the innermost end, wherein the radially outermost end is located axially upstream of the radially innermost end, a tangent to the inlet edge of each splitter blade defining a non-zero angle relative to a plane perpendicular to the axis of rotation of the impeller at all points along the entire length of the inlet edge of each splitter blade, andthe diffuser being provided with diffuser blades, a ratio of a length of the diffuser blades to a distance between the diffuser blades, along a periphery in a blade inlet, being within a range of 0.7-1.5, for diminishing velocity difference between flow of fluid flowing along a pressure side and a suction side of each of the diffuser blades for increasing efficiency of the radial compressor during operation of the radial compressor of the turbocharger unit in the internal combustion engine. 2. The turbocharger unit as claimed in claim 1, wherein the blade angle is at least 45 degrees. 3. The turbocharger unit as claimed in claim 1, wherein the at least one backswept full blade inclines, at an angle of inclination greater than 0 degrees, in a direction of rotation in an outlet of the impeller. 4. The turbocharger unit as claimed in claim 3, wherein the angle of inclination is at least 30 degrees. 5. The turbocharger unit as claimed in claim 1, wherein the blade angle is between 40-50 degrees. 6. The turbocharger unit as claimed in claim 1, wherein the at least one backswept full blade inclines, at an angle of inclination between 0 and 30 degrees, in a direction of rotation in an outlet of the impeller.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (2)
Ress ; Jr. Robert A., Blade clearance control for turbomachinery.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.