Low-emission combustion chamber for gas turbine engines
US5816050A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Mar 13, 1997 |
| Grant date | Oct 6, 1998 |
| Priority date | — |
| Expiry date | Mar 13, 2017 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R3/14
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A low-emission combustion chamber for gas turbine engines comprises an outer casing with an upstream end wall with a pilot fuel injector, a first flow swirler, an igniting members for initiating a stable diffusion frame in a pilot zone, at least one second coaxial swirler, main fuel injectors, secondary air inlets, and a main combustion zone. For obtaining a still further reduced emissions of primarily nitrogen oxides, the pilot zone is confined radially outwardly by a surrounding wall which constitutes the radially inner confinement of an axial outlet portion of a radial vaporization channel within the second swirler and a third radial flow swirler is adapted to supply the secondary air in a rotary motion opposite to that of the main flow of fuel and air.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.