Flow passage for gas turbine engine
US8517686B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Nov 20, 2009 |
| Grant date | Aug 27, 2013 |
| Priority date | — |
| Expiry date | Jun 14, 2032 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Inefficiencies associated with the formation of horseshoe vortices in a gas turbine engine having a row of radially extending airfoils, are mitigated with an improved flow passage defined by the suction and pressure surface of two adjacent airfoils and endwalls (disposed proximal to the radially inner and outer ends of the airfoils). The flow passage includes a ridge disposed in one of the endwalls adjacent a suction surface of one of the airfoils, the ridge extending longitudinally from a location at or near the maximum circumferential extent of the airfoil suction side to a downstream location proximal to the trailing edge of the suction surface.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.