Angled vanes in combustor flow sleeve
US8516822B2 · kind B2 · utility
9Cited by
16References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Mar 2, 2010 |
| Grant date | Aug 27, 2013 |
| Priority date | — |
| Expiry date | Jun 27, 2032 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/03045
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbine combustor liner assembly includes a combustor liner having upstream and downstream ends; a transition duct attached to the downstream end of the combustor liner; a first flow sleeve surrounding the combustor liner, with a first radial flow passage therebetween; and a first annular inlet at an aft end of the flow sleeve, the inlet provided with a plurality of circumferentially spaced, angled flow vanes arranged to swirl air entering the first radial flow passage via the annular inlet.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.