Fuel nozzle assembly for reduced exhaust emissions
US6389815B1 · kind B1 · utility
Assignee
Inventors
Key dates
| Filing date | Sep 8, 2000 |
| Grant date | May 21, 2002 |
| Priority date | — |
| Expiry date | Sep 8, 2020 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23C2201/401
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A two-stage fuel nozzle assembly for a gas turbine engine. The primary combustion region is centrally positioned and includes a fuel injector that is surrounded by one or more swirl chambers to provide a fuel air mixture that is ignited to define a first stage combustion zone. A secondary combustion region is provided by an annular housing that surrounds the primary combustion region, and it includes a secondary fuel injector having a radially outwardly directed opening and surrounded by an annular ring that includes openings for providing a swirl chamber for the secondary combustion region. Cooling air is directed angularly between the primary and secondary combustion zones to delay intermixing and thereby allow more complete combustion of the respective zones prior to their coalescing further downstream. The primary combustion region is activated during idle and low engine power conditions and both the primary and secondary combustion regions are activated during high engine power conditions.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.