Gas turbine engine exhaust diffuser including circumferential vane
US9032721B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 14, 2011 |
| Grant date | May 19, 2015 |
| Priority date | — |
| Expiry date | Mar 18, 2034 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2270/173
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A flow passage defined between an inner and an outer boundary for guiding a fluid flow in an axial direction. A flow control vane is supported at a radial location between the inner and outer boundaries. A fluid discharge opening is provided for discharging a flow of the compressed fluid from a trailing edge of the vane, and a fluid control surface is provided adjacent to the fluid discharge opening and extends in the axial direction at the trailing edge of the vane. The fluid control surface has a curved trailing edge forming a Coanda surface. The fluid discharge opening is selectively provided with a compressed fluid to produce a Coanda effect along the control surface. The Coanda effect has a component in the radial direction effecting a turning of the fluid flow in the flow path radially inward or outward toward one of the inner and outer boundaries.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.