Fuel staging in a gas turbine engine
US10480792B2 · kind B2 · utility
Assignees
Inventors
Key dates
| Filing date | Mar 2, 2016 |
| Grant date | Nov 19, 2019 |
| Priority date | — |
| Expiry date | Jan 31, 2038 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine system includes a turbine combustor. The turbine combustor includes one or more first fuel injectors coupled to a head end of the turbine combustor and configured to deliver a first portion of a fuel to a first axial position of a combustion section of the turbine combustor. The turbine combustor also includes one or more second fuel injectors coupled to the turbine combustor axially downstream of the head end and configured to deliver a second portion of the fuel to a second axial position of the combustion section of the turbine combustor, the second axial position being downstream of the first axial position. The gas turbine system also includes a controller configured to deliver the first and the second portions of the fuel such that combustion of the fuel and oxidant within the overall combustion section of the turbine combustor is at a defined equivalence ratio.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.