Turbine vane airfoil with turning flow and axial/circumferential trailing edge configuration
US8075259B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Feb 13, 2009 |
| Grant date | Dec 13, 2011 |
| Priority date | — |
| Expiry date | Jun 25, 2030 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An airfoil with turning flow comprises a first surface, a second surface, a leading edge and a trailing edge. The first and second surfaces extend from the leading edge to a trailing edge. A chord extends from a midpoint of the leading edge to a midpoint of the trailing edge, defining a duct angle of at least fifteen degrees with respect to a turbine axis. An axial length of the chord defines an aspect ratio of at most one with respect to an average radial span of the leading and trailing edges. In a region of the trailing edge, an axial angle is at most four degrees and a circumferential angle is at most ten degrees, where the circumferential angle is defined in a direction opposite the turning flow.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.