Abstract: A facility, in particular a power plant, is provided having a steam turbine and a bypass station for diverting a working medium, as required, for the steam turbine around the steam turbine, wherein at least one resonance absorber is provided for the bypass station.

Abstract: A mixing unit for mixing water with steam in a bypass station is provided. The mixing unit has a plurality of Laval nozzles arranged in the mixing unit, which Laval nozzles are displaced axially with respect to one another in a water steam direction, with the result that the noise emissions are reduced overall.

Abstract: Burners in prior art exhibit combustion instabilities in certain ranges. The operating range of burners is restricted by said instabilities. In an inventive burner, the combustible has a concentration distribution, whereby the concentration of the combustible reduces in a radial direction from the interior to the exterior.

Abstract: The invention relates to a method for compensating variations in fuel composition in a gas turbine system consisting of at least two parallel-operated burner stages, wherein the fuel supply to at least two of the burner stages is adjusted in response to variations in fuel composition, wherein the fuel split between the burner stages, i.e. the relative increase in speed of the fuel supplied to the burner stages, is adjusted to a target value or maintained at a target value during adjustment of the fuel supply. The target value can, for example be a constant or a function of one or several variables. More particularly, the gas turbine system can comprise a pilot burner stage and a main burner stage. When the fuel supply is adjusted, the fuel split between the pilot burner stage and the main burner stage is adjusted to a target value or maintained at a target value.

Abstract: The invention relates to a method for compensating variations in fuel composition in a gas turbine system consisting of at least two parallel-operated burner stages, wherein the fuel supply to at least two of the burner stages is adjusted in response to variations in fuel composition, wherein the fuel split between the burner stages, i.e. the relative increase in speed of the fuel supplied to the burner stages, is adjusted to a target value or maintained at a target value during adjustment of the fuel supply. The target value can, for example be a constant or a function of one or several variables. More particularly, the gas turbine system can comprise a pilot burner stage and a main burner stage. When the fuel supply is adjusted, the fuel split between the pilot burner stage and the main burner stage is adjusted to a target value or maintained at a target value.

Abstract: Burners in prior art exhibit combustion instabilities in certain ranges. The operating range of burners is restricted by said instabilities. In an inventive burner, the combustible has a concentration distribution, whereby the concentration of the combustible reduces in a radial direction from the interior to the exterior.

Abstract: A burner configuration with primary and secondary pilot burners is described. The burner configuration is used in a firing installation, in particular a gas turbine combustion chamber, and has a main burner and, disposed centrally within it, a primary pilot burner used for igniting and/or for stabilizing the combustion of the main burner. For additional stabilization, for reducing rumble noises in the firing installation and for avoiding the possible flashback of the flame in a partial region of the burner, which can then sometimes occur, a plurality of outlet openings, which together form a secondary pilot burner, are disposed in the outlet region of the main burner. The flames of the secondary pilot burner surround the main flame like a ring and additionally stabilize the operation under different load conditions.

Abstract: A burner configuration with primary and secondary pilot burners is described. The burner configuration is used in a firing installation, in particular a gas turbine combustion chamber, and has a main burner and, disposed centrally within it, a primary pilot burner used for igniting and/or for stabilizing the combustion of the main burner. For additional stabilization, for reducing rumble noises in the firing installation and for avoiding the possible flashback of the flame in a partial region of the burner, which can then sometimes occur, a plurality of outlet openings, which together form a secondary pilot burner, are disposed in the outlet region of the main burner. The flames of the secondary pilot burner surround the main flame like a ring and additionally stabilize the operation under different load conditions.

Abstract: A method and a device for burning fuel with air in a combustion chamber. The air is fed to the combustion chamber through at least one air inlet and the fuel is fed to the combustion chamber through a plurality of burners. Each burner has an associated delay time corresponding to a period of time after which an acoustic impulse in the combustion chamber causes a thermal impulse during combustion of the fuel fed through the burner. The feeding of the fuel through the burner is controlled in such a way that the delay times of the burners are substantially different from one another. The invention can be used on a combustion chamber of a gas turbine.