Two-stage compressor with asymmetric second-stage inlet duct
US10190596B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Nov 3, 2016 |
| Grant date | Jan 29, 2019 |
| Priority date | — |
| Expiry date | Mar 1, 2037 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T10/12
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A multi-stage compressor for a turbocharger includes a compressor housing that defines an aperture for receiving a compressor wheel for successively compressing air in first and second stages. First- and second-stage inlets are fluidly connected to the aperture in opposite axial directions, and first- and second-stage volutes extend at least partially annularly therearound so that each volute is configured to receive gas flowing generally radially outward from the compressor wheel. First and second passages fluidly connect the first-stage volute to the second-stage inlet. The passages approach the second-stage inlet from opposite radially inward directions, and are asymmetric with respect to any pair of orthogonal axes having an origin lying on the turbocharger rotary axis as viewed on a transverse cross-section that is normal to the turbocharger axis.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.