Axially staged combustion system for a gas turbine engine
US7631499B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Aug 3, 2006 |
| Grant date | Dec 15, 2009 |
| Priority date | — |
| Expiry date | Jan 30, 2027 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23M2900/05004
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An axially staged combustion system is provided for a gas turbine engine comprising a main body structure having a plurality of first and second injectors. First structure provides fuel to at least one of the first injectors. The fuel provided to the one first injector is adapted to mix with air and ignite to produce a flame such that the flame associated with the one first injector defines a flame front having an average length when measured from a reference surface of the main body structure. Each of the second injectors comprising a section extending from the reference surface of the main body structure through the flame front and having a length greater than the average length of the flame front. Second structure provides fuel to at least one of the second injectors. The fuel passes through the one second injector and exits the one second injector at a location axially spaced from the flame front.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.