Fuel nozzle for turbine combustion engines having aerodynamic turning vanes
US6883332B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Apr 23, 2003 |
| Grant date | Apr 26, 2005 |
| Priority date | — |
| Expiry date | Aug 19, 2023 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23D2900/11101
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A fuel nozzle for dispensing an atomized fluid spray into the combustion chamber of a gas turbine engine. The nozzle includes a body assembly with an inner fuel passage and an annular outer atomizing air passage. An array of turning vanes is disposed within the outer fuel passage. Each of the vanes is configured generally in the shape of an airfoil in having a pressure side and an opposing suction side, the suction side of each vane being spaced-apart from a juxtaposing pressure side of an adjacent vane to define a corresponding one of a plurality of aligned air flow channels therebetween. Fuel is directed through the fuel flow channels to be issued from the nozzle as a generally helical flow having a substantial uniform velocity profile.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.