Flow sleeve with tabbed direct combustion liner cooling air
US8109099B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 9, 2008 |
| Grant date | Feb 7, 2012 |
| Priority date | — |
| Expiry date | Apr 29, 2030 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/03044
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combustion duct for a gas turbine engine has a combustion liner to receive products of combustion, and deliver the products of combustion downstream toward a turbine rotor. An outer housing is positioned radially outwardly of the combustion liner. A flow sleeve is positioned radially intermediate the outer housing and the combustion liner. A chamber radially outwardly of the flow sleeve receives cooling air. A plurality of holes through the flow sleeve deliver cooling air from the chamber against an outer periphery of the combustion liner. A plurality of tabs are associated with at least some of the holes in the flow sleeve. The tabs are positioned to extend radially inwardly on a downstream side of the holes.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.