Elliptical air opening at an upstream end of a fuel injector shroud and a gas turbine engine combustion chamber
US9371990B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Nov 26, 2013 |
| Grant date | Jun 21, 2016 |
| Priority date | — |
| Expiry date | Feb 12, 2035 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R3/343
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine lean burn fuel injector includes a fuel injector head which has a first air swirler, a second air swirler arranged around the first air swirler, a pilot fuel injector arranged radially between the first air swirler and the second air swirler. A third air swirler arranged around the second air swirler, a fourth air swirler arranged around the third air swirler and a main fuel injector arranged radially between the third air swirler and the fourth air swirler. A shroud is arranged around the fourth air swirler. A downstream end of the shroud is generally circular in cross-section in a plane perpendicular to the axis (Y) of the fuel injector head and an upstream end of the shroud is generally elliptical in cross-section in a plane perpendicular to the axis (Y) of the fuel injector head.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.