Radial turbine blade
US9777578B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 27, 2012 |
| Grant date | Oct 3, 2017 |
| Priority date | — |
| Expiry date | Oct 25, 2033 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2240/301
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An object is to provide a radial turbine blade that can reduce an impact loss of inflowing gas at a leading edge of the turbine blade and achieve a higher turbine efficiency, even in a case of a flow field corresponding to a low turbine operational velocity ratio U/C0 due to a throttling operation on a variable nozzle mechanism of a variable geometry turbocharger.In a radial turbine blade, a hub-side end portion Pa at a leading edge 51 of a turbine blade 50 is formed to be positioned more on a rear side in a rotation direction R of the turbine blade 50 than a shroud-side end portion Sc at the leading edge 51, and a straight line connecting between the shroud-side end portion Sc and the hub-side end portion Pa is inclined with respect to a straight line extending in a rotation axis direction from the shroud-side end portion Sc at the leading edge 51 onto a hub 17 surface by an angle in a range from 30° to 70° as viewed in the radial direction of the turbine blade 50.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.