Gas turbine engine combustion system
US6470684B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Mar 30, 2001 |
| Grant date | Oct 29, 2002 |
| Priority date | — |
| Expiry date | Mar 30, 2021 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R3/286
- WIPO fieldThermal processes and apparatus
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine includes a combustion main chamber into which opens one end of an upstream combustion pre-chamber having a burner face at its opposite end. A swirler assembly has a plurality of generally tangentially extending swirler vanes circumferentially spaced by passages disposed about a center and along which combustion air follows radially inward paths into the pre-chamber. Each passage is provided with a respective liquid fuel injection nozzle including an electrode to be electrostatically charged so each injection nozzle can impart electrostatic charge to droplets of fuel emerging from the nozzles to travel with the combustion air into the pre-chamber. Walls of the passages comprise electrodes which can be charged to the same polarity as the charged fuel. The burner face is preferably formed of two or three electrodes, one being a central electrode at opposite polarity to the charge on the fuel and at least one other electrode surrounding the central electrode and at the same polarity as the charge on the fuel. The pre-chamber has a wall also forming an electrode which may be charged at the same polarity as the charge on the fuel droplets. The disposition of the elec…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.