Abstract: A combustion chamber (10, 20) for a gas turbine (1) having a housing (12, 23), a combustion zone (21, 22, 47) surrounded by the housing (12, 23), and at least one burner arrangement (11, 25), which has at least one pre-mixing passage (28) opening into the combustion zone (21, 22) for preparation of a fuel/air mixture. To enable suppression of combustion chamber pressure fluctuations, at least one interference body (50) is provided against which a flow can take place and to which a Strouhal number can be assigned, the flow generating fluidically induced sound waves. The interference body (50) is in a passage (48, 59) opening into the combustion zone (21, 22, 47). A fluid (51, 62) flowing through the passage (48, 59) in the direction of the combustion zone generates a sound wave with a frequency f by flowing against the interference body (50), wherein the frequency f substantially corresponds to a dominant frequency of the combustion chamber.

Abstract: An injector (8) for introducing a fuel-air mixture into a combustion chamber: has a longitudinal axis (44) and includes a number of annular curved flow passages. Each flow passage comprises a fuel inlet opening (43), air inlet openings (42) and a fuel-air mixture outlet opening (9). The fuel inlet opening (43) is connected to a fuel distributor (41) and has a central axis (55) which runs perpendicular or parallel to the longitudinal axis (44) of the injector (8). The fuel-air mixture outlet opening (9) has a central axis which runs perpendicular to the longitudinal axis (44) of the injector (8). The air inlet openings (42) each have a central axis (54) which runs parallel to the longitudinal axis (44) of the injector (8).

Abstract: A combustion chamber (10, 20) for a gas turbine (1) with at least two combustion zones (23, 24) and at least one burner arrangement (11, 28) for the combustion of a fuel/air mixture in the combustion zones (23, 24). The burner arrangement (11, 28) has at least one premixing passage (29) that opens into the combustion zones (23, 24) to provide a fuel/air mixture, and an air supply (32) and at least one fuel supply (33) encompassed in the burner arrangement (11, 28) and open into the premixing passage (29). The combustion chamber permits a particularly effective damping of combustion chamber pressure fluctuations. To this end, the air supply (32) is designed in a stepped manner such that the outlet openings (34, 34a, 34b, 34c) of the stepped air supply that open into the premixing passage can be assigned different delay times (?1, ?2, ?3), which damps the fluctuations.

Abstract: A gas turbine combustion chamber is provided. The gas turbine includes a combustion chamber interior and a combustion chamber wall which has a substantially rotationally symmetrical cross-section, wherein on the side of the combustion chamber wall facing away from the combustion chamber interior there is arranged over the entire cross-sectional circumference of the combustion chamber wall a corrugated component which, in combination with the combustion chamber wall, embodies a plurality of separate resonance chambers and wherein openings are incorporated in the combustion chamber wall in such a way that a fluidic connection is established in each case between the combustion chamber interior and one of the resonance chambers and wherein the corrugated component has two locking rings which are connected to the combustion chamber wall in order to seal off the resonance chambers.

Abstract: A gas turbine combustion chamber is provided. The gas turbine includes a combustion chamber interior and a combustion chamber wall which has a substantially rotationally symmetrical cross-section, wherein on the side of the combustion chamber wall facing away from the combustion chamber interior there is arranged over the entire cross-sectional circumference of the combustion chamber wall a corrugated component which, in combination with the combustion chamber wall, embodies a plurality of separate resonance chambers and wherein openings are incorporated in the combustion chamber wall in such a way that a fluidic connection is established in each case between the combustion chamber interior and one of the resonance chambers and wherein the corrugated component has two locking rings which are connected to the combustion chamber wall in order to seal off the resonance chambers.

Abstract: A method for protecting a burner from being heated excessively during the combustion of a fuel in a combustion chamber is provided. The fuel is injected through a fuel nozzle at the same time as an inert gas in the surroundings of the injected fuel is injected into the combustion chamber in such a manner that the fuel is separated spatially from an oxidizer by the inert gas until an ignitable mixture of the fuel is produced.

Abstract: A heat shield according to the invention on a support structure comprises a number of heat shield elements, which are configured and arranged on the support structure such that they abut each other leaving gaps. The support structure of the heat shield according to the invention has a peripheral direction and an axial direction, the heat shield elements abutting each other in the peripheral direction of the support structure leaving a gap, hereafter referred to as a peripheral gap, and in the axial direction of the support structure leaving a gap, hereafter referred to as an axial gap. Both the peripheral gaps and the axial gaps are also sealed by sealing elements, the sealing elements sealing the axial gaps being at a different distance from the support structure from the sealing elements sealing the peripheral gaps.

Abstract: A heat shield according to the invention on a support structure comprises a number of heat shield elements, which are configured and arranged on the support structure such that they abut each other leaving gaps. The support structure of the heat shield according to the invention has a peripheral direction and an axial direction, the heat shield elements abutting each other in the peripheral direction of the support structure leaving a gap, hereafter referred to as a peripheral gap, and in the axial direction of the support structure leaving a gap, hereafter referred to as an axial gap. Both the peripheral gaps and the axial gaps are also sealed by sealing elements, the sealing elements sealing the axial gaps being at a different distance from the support structure from the sealing elements sealing the peripheral gaps.