COMBUSTION CHAMBER FOR A GAS TURBINE PLANT

A combustion chamber (1) for a gas turbine plant, has a combustion chamber wall (10), which is flowed through by combustion gases in the direction of a downstream expansion turbine, the chamber wall (10) has a device (20) for damping thermoacoustic oscillations caused by the combustion gases. At least one resonator tube (22), interacts with the resonator volume (21) and opens out into the combustion chamber (1) with its mouth (M) opposite from the resonator volume (21) in the combustion chamber inner wall (10). At least one feed opening (23, 23′, 23″) for sealing air for sealing the resonator tube mouth (M) is introduced into the combustion chamber (1) from a compressor plenum (2), surrounding the combustion chamber. The at least one first feed opening (23′, 23″) is provided in a region of the combustion chamber wall (10) close to the resonator tube mouth (M) and is aligned such that the sealing air (S) through the feed opening (23′, 23″) flows over the resonator mouth (M).