Abstract: A method and a device for the introduction of fuel into a premixing burner, with a pilot gas feed and a premix gas feed for the operation of a gas turbine in the entire load range, in which the pilot gas feed is carried out via a burner lance provided in the premixing burner and the premix gas feed is carried out via side wall shells of the premixing burner. The premix gas feed and the pilot gas feed are carried out in combination, in such a way that a continuous mixture ratio between premix gas and pilot gas can be set within the premixing burner.

Abstract: A burner includes a swirl generator (3) for a combustion airflow, has a conical swirl chamber (2) and a device for admitting fuel into the combustion airflow, wherein the swirl generator (3) incorporates combustion air inlet openings for the combustion airflow tangentially entering into the conical swirl chamber (2), and wherein the device for admitting fuel into the combustion airflow includes a first fuel feeding device having a first group (4) of fuel outlet openings substantially disposed in the direction of the burner axis for a first premix fuel quantity.

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.

Abstract: A method and a device for the introduction of fuel into a premixing burner, with a pilot gas feed and a premix gas feed for the operation of a gas turbine in the entire load range, in which the pilot gas feed is carried out via a burner lance provided in the premixing burner and the premix gas feed is carried out via side wall shells of the premixing burner. The premix gas feed and the pilot gas feed are carried out in combination, in such a way that a continuous mixture ratio between premix gas and pilot gas can be set within the premixing burner.

Abstract: A method and a device for the introduction of fuel into a premixing burner, with a pilot gas feed and a premix gas feed for the operation of a gas turbine in the entire load range, in which the pilot gas feed is carried out via a burner lance provided in the premixing burner and the premix gas feed is carried out via side wall shells of the premixing burner. The premix gas feed and the pilot gas feed are carried out in combination, in such a way that a continuous mixture ratio between premix gas and pilot gas can be set within the premixing burner.

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 includes a swirl generator (3) for a combustion airflow, has a conical swirl chamber (2) and a device for admitting fuel into the combustion airflow, wherein the swirl generator (3) incorporates combustion air inlet openings for the combustion airflow tangentially entering into the conical swirl chamber (2), and wherein the device for admitting fuel into the combustion airflow includes a first fuel feeding device having a first group (4) of fuel outlet openings substantially disposed in the direction of the burner axis for a first premix fuel quantity.

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: The present invention relates to a method of operating a burner, which comprises at least one first fuel supply conduit (5) with a first group of fuel outlet openings (6), essentially arranged in the direction of a burner longitudinal axis (3), for a first premix fuel quantity and one or a plurality of second fuel supply conduits (7) with a second group of fuel outlet openings (8), essentially arranged in the direction of the burner longitudinal axis (3), for a second premix fuel quantity, it being possible to admit fuel to the second fuel supply conduits (7) independently of the first fuel supply conduit (5). In the method, both fuel supply conduits (5, 7) are operated with the same fuel. By means of the present method of operating a burner, optimum mixing conditions can be set even in the case of different loads, gas qualities or gas preheat temperatures.

Abstract: A method and a device are described for the introduction of fuel into a premixing burner, with a pilot gas feed and a premix gas feed for the operation of a gas turbine in the entire load range, in which the pilot gas feed is carried out via a burner lance provided in the premixing burner and the premix gas feed is carried out via side wall shells of the premixing burner.

Abstract: The present invention relates to a method of operating a burner, which comprises at least one first fuel supply conduit (5) with a first group of fuel outlet openings (6), essentially arranged in the direction of a burner longitudinal axis (3), for a first premix fuel quantity and one or a plurality of second-fuel supply conduits (7) with a second group of fuel outlet openings (8), essentially arranged in the direction of the burner longitudinal axis (3), for a second premix fuel quantity, it being possible to admit fuel to the second fuel supply conduits (7) independently of the first fuel supply conduit (5). In the method, both fuel supply conduits (5, 7) are operated with the same fuel. By means of the present method of operating a burner, optimum mixing conditions can be set even in the case of different loads, gas qualities or gas preheat temperatures.

Abstract: A burner system with staged fuel injection includes a burner with a swirl generator (1) for a combustion air stream and device(s) for introducing fuel into the combustion air stream, wherein the fuel introducing devices include at least two separate fuel supply elements (4a, 4b) with groups of fuel outlet openings for corresponding premix fuel amounts, wherein a first group is arranged downstream from a second group. The burner system furthermore includes measurement value probes (8, 9) for measuring the pulsations and emissions of the combustion, as well as a control device (10) that controls the two stages (4a, 4b) for introducing fuel dependent on the measured measuring values. The burner system permits optimized operation of the system even under changing operating and environmental conditions.

Abstract: The invention relates to a damper arrangement for reducing combustion-chamber pulsations arising inside a gas turbine (1), having a combustion-chamber housing (8) which upstream comprises a front plate (2) with a plurality of individual burners (6) and damping elements (7, 7a, 7b) projecting through the front plate (2) and downstream is connected to a turbine stage (9) and is surrounded by a turbine housing (3) which comprises first openings (5a) which are adapted to the burners (6) and through which the burners (6) project upstream. The invention is characterized in that closable second openings (5b), through which it is possible to insert and tune the damping elements (7, 7a, 7b), are provided inside the turbine housing (9) adjacent to the first openings (5a) adapted to the burners (6).

Abstract: A burner system with staged fuel injection includes a burner with a swirl generator (1) for a combustion air stream and device(s) for introducing fuel into the combustion air stream, wherein the fuel introducing devices include at least two separate fuel supply elements (4a, 4b) with groups of fuel outlet openings for corresponding premix fuel amounts, wherein a first group is arranged downstream from a second group. The burner system furthermore includes measurement value probes (8, 9) for measuring the pulsations and emissions of the combustion, as well as a control device (10) that controls the two stages (4a, 4b) for introducing fuel dependent on the measured measuring values. The burner system permits optimized operation of the system even under changing operating and environmental conditions.

Abstract: The invention relates to a damper arrangement for reducing combustion-chamber pulsations arising inside a gas turbine (1), having a combustion-chamber housing (8) which upstream comprises a front plate (2) with a plurality of individual burners (6) and damping elements (7, 7a, 7b) projecting through the front plate (2) and downstream is connected to a turbine stage (9) and is surrounded by a turbine housing (3) which comprises first openings (5a) which are adapted to the burners (6) and through which the burners (6) project upstream.