Gas turbine combustor
US8596074B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Apr 4, 2007 |
| Grant date | Dec 3, 2013 |
| Priority date | — |
| Expiry date | Dec 28, 2029 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23D2900/14701
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine combustor is provided, which comprises: a combustion chamber having an axial direction and a radial direction; air passages for feeding an air stream into the combustion chamber which are oriented such that the flowing direction for each air stream flowing into the combustion chamber includes an angle with the combustion chamber's radial direction so as to introduce a swirl in the in-flowing air and an angle of at least 60° with the combustion chamber's axial direction; and fuel injection openings which are located in the air passages. Each air passage defines a turning flow path with a turning between 70° and 150° in a radial direction of the combustion chamber and a turning between 0° and 235° in an axial direction of the combustion chamber.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.