Turbo compressor system for an internal combustion engine comprising a compressor of radial type and provided with an impeller with backswept blades
US8424305B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Nov 15, 2005 |
| Grant date | Apr 23, 2013 |
| Priority date | — |
| Expiry date | Mar 1, 2028 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T10/40
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbocharger unit (18) for an internal combustion engine (10) with at least one exhaust line (15, 16) for conducting exhaust gases away from the combustion chamber (11) of the engine and at least one inlet line (12) for supplying air to the combustion chamber. The turbocharger unit includes a turbine (17) which interacts with a compressor (19) for extracting energy from the exhaust gas flow of the engine and pressurizing the inlet air of the engine. The compressor (19) is of radial type and provided with an impeller with backswept blades (35) where the blade angle (βb2) 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 (36) which connects the center axis of the impeller to the outer tip of the blade is at least roughly 45°. The turbine (17) which drives the compressor (19) is of radial type.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.