Fuel nozzle for a combustor of a gas turbine engine
US9291103B2 · kind B2 · utility
5Cited by
20References
12Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Dec 5, 2012 |
| Grant date | Mar 22, 2016 |
| Priority date | — |
| Expiry date | Jul 17, 2034 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R3/32
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A fuel nozzle for a gas turbine generally includes a main body having an upstream end axially separated from a downstream end. The main body at least partially defines a fuel supply passage that extends through the upstream end and at least partially through the main body. A fuel distribution manifold is disposed at the downstream end of the main body. The fuel distribution manifold includes a plurality of axially extending passages that extend through the fuel distribution manifold. A plurality of fuel injection ports defines a flow path between the fuel supply passage and each of the plurality of axially extending passages.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.