Gas turbine ultra low NOx combustor
US5361586A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Apr 15, 1993 |
| Grant date | Nov 8, 1994 |
| Priority date | — |
| Expiry date | Apr 15, 2013 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine combustor having a pre-mixing zone and a combustion zone separated by a barrier plate. A plurality of concentrically arranged annular passages, into which lean mixtures of fuel and air are introduced, are disposed in the pre-mixing zone. Each of the annular passages has a discharge end in which a plurality of swirlers are circumferentially arranged that allow fuel/air mixtures flowing through the annular passages to enter the combustion zone, the swirlers acting as flame holders. A toroidal fuel manifold upstream of each of the annular passages allows the fuel/air ratio in each annular passage to be individually controlled. The firing temperature of the combustor is increased by sequentially supplying fuel to each annular passage in turn, with the innermost passages being supplied with fuel first. A pilot fuel assembly is centrally disposed with respect to the annular passages and has swirler vanes and an ignitor.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.