Fuel nozzle for a turbine combustor, and methods of forming same
US8474265B2 · kind B2 · utility
10Cited by
6References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jul 29, 2009 |
| Grant date | Jul 2, 2013 |
| Priority date | — |
| Expiry date | May 1, 2032 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/00014
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A fuel nozzle for a turbine engine includes a primary fuel passageway for supplying fuel to a plurality of radially extending fuel injectors arranged around the exterior of the fuel nozzle. A secondary fuel passageway couples an upstream end of the primary fuel passageway to a downstream end of the primary fuel passageway. The secondary fuel passageway acts as a resonator tube to help reduce oscillations in the fuel flowing through the primary fuel passageway.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.