Burner arrangement for a gas turbine for preventing the ingress of fluids into a fuel passage
US6038863A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Dec 3, 1997 |
| Grant date | Mar 21, 2000 |
| Priority date | — |
| Expiry date | Dec 3, 2017 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23D2900/00016
- WIPO fieldThermal processes and apparatus
- WIPO sectorMechanical engineering
Abstract
The burner arrangement for a gas turbine comprises at least one burner (2), which is arranged in the plenum of the gas turbine and leads with an inner injection space into a combustion chamber and to which compressed air is admitted on the outside from a compressor stage of the gas turbine. Furthermore, a fuel lance (9) for the alternative feeding of liquid and/or gaseous fuels is allocated to the burner (2), which fuel lance (9) has a central liquid-fuel tube (19) and a pilot gas tube (11) concentrically surrounding the liquid-fuel tube (19), the tubes (11, 19) ending in associated outlet openings (22, 23, 23a-c) in a lance head (12) at the tip of the fuel lance (9). In order to provide protection from an ingress of hot gases and/or hot liquid fuel into the outlet openings (22, 23, 23a-c) of the tubes (11, 19) when these tubes are not being used, an additional opening (17) is provided in the lance head (12) in the immediate vicinity of the outlet openings (22, 23, 23a-c), through which additional opening (17) compressed air flows out into the injection space (8). Furthermore, means are provided which direct compressed air from the plenum, surrounding the burner (2), to the additio…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.