Combustion chamber of a gas turbine and method of operating it
US4967561A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Nov 6, 1990 |
| Grant date | Nov 6, 1990 |
| Priority date | — |
| Expiry date | Nov 6, 2010 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23D2900/00008
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
In the combustion chamber of a gas turbine, an air distribution chamber (19) and a combustion space (7) are locationally separated from one another within the combustion chamber shell (1). A multiplicity of tubular elements (2) are located between the distibution chamber and the combustion space, in which elements a premixing and pre-evaporation of the fuel oil supplied via the premixing nozzles (15') and/or a premixing of the fuel gas supplied through the premixing nozzles (15") takes place with compressor air. Each tubular element (2) is provided with a flameholder (3) in the direction towards the combustion space (7). A diffusion nozzle (8) for fuel directed into the combustion space (7) is located within the flameholder. In operation on load, only a small part of the fuel supplied to each element (2) is burned by means of the diffusion nozzle (8), the major proportion, on the other hand, being burnt by means of the premixing nozzles (15' of 15").
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.