Low cross-talk gas turbine fuel injector
US8099940B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 18, 2008 |
| Grant date | Jan 24, 2012 |
| Priority date | — |
| Expiry date | May 19, 2030 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R3/36
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A pilot assembly for a fuel injector of a gas turbine engine may include a longitudinal passageway having an outlet end. A mass flow in the longitudinal passageway may generally flow towards the outlet end during operation of the engine. The pilot assembly may also include a liquid fuel nozzle that is positioned to direct a mixture of liquid fuel and air near the outlet end, and a compressed air inlet that is configured to direct air compressed by a compressor of the engine to a compressor discharge pressure into the longitudinal passageway without a substantial loss of pressure. The longitudinal passageway may also include a flow restriction section. The flow restriction section may be a narrowed section of the longitudinal passageway, in which an upstream side of the flow restriction section may have compressed air at substantially the compressor discharge pressure and a downstream side may have air at a lower pressure and a higher velocity. The pilot assembly may further include a nozzle for injecting one of assist air or gaseous fuel into the longitudinal passageway. The nozzle may be positioned at the flow restriction section or on an upstream side of the flow restriction sect…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.