Abstract: In a fuel lance by means of which fuels can be injected, via at least two separate passages, into a combustion chamber alternately or simultaneously at an injection location arranged substantially at the lance tip, reliable operation is achieved, without the risk of flashbacks and also without coking, by virtue of the fact that the fuel lance, in addition to fuel, also passes purge air to the injection location, and that the purge air, at the injection location, is routed between the two fuel systems, in such a manner that these systems are shielded from one another by the purge air.

Abstract: A burner system with staged fuel injection includes at least one burner with a mixing zone. A combustion chamber is disposed downstream of the mixing zone and a first fuel introduction device is provided upstream of the mixing zone. Furthermore, a second fuel introduction device for the direct injection of fuel into the combustion chamber, is disposed downstream of the mixing zone. In addition, at least one sensor for determining combustion parameters is connected to a control device. The control device is designed to control the second fuel introduction device as a function of the parameters determined by the sensors.

Abstract: An injector (4) for liquid fuel (6a) and a premix burner, in particular for combustion chambers of gas turbines which burner includes an injector (4) of this type, includes a swirl nozzle (14) which is surrounded by a shielding-air passage (11) and has an enlarged cross section of flow in the region of a nozzle-internal swirl generator (12) for the liquid fuel (6a), with this enlarged cross section of flow being reduced again toward an exit opening of the swirl nozzle (14). The injector allows the premix burner to operate with a reduced admission pressure and a high atomization quality.

Abstract: A premix burner includes a vortex generator (30) for combustion air stream (15), devices (17, 17a, 17b, 31-38, 41-48) to inject fuel into the combustion air stream (15), and tangential air ducts (19, 20). The combustion air (15) enters the cone cavity (14) of the vortex generator (30) via the air ducts. The injection of the fuel into the combustion air is done asymmetrically by injection devices (17, 17a, 17b, 31-38, 41-48). At least one of the injection devices (5) is arranged on a fuel lance (3) that extends into the vortex chamber.

Abstract: In a fuel lance by means of which fuels can be injected, via at least two separate passages, into a combustion chamber alternately or simultaneously at an injection location arranged substantially at the lance tip, reliable operation is achieved, without the risk of flashbacks and also without coking, by virtue of the fact that the fuel lance, in addition to fuel, also passes purge air to the injection location, and that the purge air, at the injection location, is routed between the two fuel systems, in such a manner that these systems are shielded from one another by the purge air.

Abstract: In a fuel lance by means of which fuels can be injected, via at least two separate passages, into a combustion chamber alternately or simultaneously at an injection location arranged substantially at the lance tip, reliable operation is achieved, without the risk of flashbacks and also without coking, by virtue of the fact that the fuel lance, in addition to fuel, also passes purge air to the injection location, and that the purge air, at the injection location, is routed between the two fuel systems, in such a manner that these systems are shielded from one another by the purge air.