Combustor having means for directing air into the combustion chamber in a spiral pattern
US7260936B2 · kind B2 · utility
24Cited by
27References
18Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Aug 27, 2004 |
| Grant date | Aug 28, 2007 |
| Priority date | — |
| Expiry date | Jul 3, 2025 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R3/54
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine combustor includes a liner having a dome portion with a plurality of openings defined therein for receiving fuel nozzles and a plurality of holes defined around each opening. The holes directing air into the combustion chamber in a spiral pattern around an axis along which fuel is injected into the combustor by the fuel nozzles.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.