초록 ▼

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. Furtherm

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 additional opening (17).

대표청구항 ▼

[ What is claimed as new and desired to be secured by Letters Patent of the United States is:] [1.] A burner arrangement for a gas turbine, comprising: at least one burner arranged in a plenum of the gas turbine and including an inner injection space which leads into a combustion chamber and into wh

[ What is claimed as new and desired to be secured by Letters Patent of the United States is:] [1.] A burner arrangement for a gas turbine, comprising: at least one burner arranged in a plenum of the gas turbine and including an inner injection space which leads into a combustion chamber and into which compressed air is admitted from outside the burner from a compressor stage of the gas turbine, a fuel lance attached to the burner, the fuel lance including a central liquid-fuel tube and a pilot-gas tube concentrically surrounding the central liquid-fuel tube, the central liquid-fuel tube and the pilot-gas tube having outlet openings in a lance head located at a tip of the fuel lance, the fuel lance being inserted with the lance head into an inner tube which is in fluid communication with the injection space of the burner, an outer periphery of the lance head engaging an inner periphery of the inner tube, the lance head including an additional opening in an immediate vicinity of the outlet openings of the tubes for the flow of compressed air into the injection space and the lance head including means for directing compressed air from the plenum to the additional opening, the means for directing compressed air including an intermediate space arranged upstream of the lance head and located between the pilot-gas tube and the inner tube of the burner, the intermediate space being in fluid communication with the plenum surrounding the burner via at least one inlet bore extending through the burner into the inner tube, and the intermediate space being connected to the additional opening via at least one compressed air passage directed through the lance head the flow of compressed air through the additional opening preventing ingress of hot gases or hot liquids into the outlet openings of the liquid-fuel and pilot-gas tubes when either of the respective fuels exiting the fuel lance are not in use.