Gas turbine combustion chamber with fuel injection over an entire combustion chamber annulus
US7966818B2 · kind B2 · utility
0Cited by
7References
20Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Feb 2, 2007 |
| Grant date | Jun 28, 2011 |
| Priority date | — |
| Expiry date | Sep 13, 2029 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine combustion chamber includes an annular combustion chamber (3) confined by an outer (1) and an inner combustion chamber wall (2) and is provided with several fuel injection nozzles (4). Air deflectors (6) are arranged in a front-side area of the annular combustion chamber (3) over the entire combustion chamber annulus (5) concentrically around a combustion chamber axis (12) and fuel injection nozzles (4) are distributed essentially uniformly over the combustion chamber annulus (5).
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.