Gas turbine fuel injector
US6082113A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | May 22, 1998 |
| Grant date | Jul 4, 2000 |
| Priority date | — |
| Expiry date | May 22, 2018 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23D2900/11101
- WIPO fieldThermal processes and apparatus
- WIPO sectorMechanical engineering
Abstract
A fuel injector for a combustor and a gas turbine engine, wherein the combustor includes a combustor wall defining a combustion chamber tube surrounded by pressurized air. The injector comprises a nozzle tip assembly protruding through the combustor wall into the chamber, the nozzle tip including a first air passage forming an annular array communicating the pressurized air from outside the wall into the combustion chamber. A second air passage is made up of an annular array of individual air passages spaced radially from the first air passage and communicating the pressurized air from outside the combustor wall into the combustor. A first fuel gallery extends through the fuel injector tip and defines an annular fuel nozzle between the first air passage and the second air passages, whereby the second air passages are arranged to atomize the fuel emanating from the annular fuel nozzle, and third fuel passages are arranged in annular array in the injector tip spaced radially outwardly from the second air passages whereby the third passages are arranged to shape the mixture of atomized fuel and air and to add supplemental air to the mixture.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.