Combustion chamber assembly for dampening thermoacoustic oscillations, gas turbine and method for operating such a gas turbine

摘要

The arrangement has a combustion chamber comprising a combustion chamber wall with a hot gas side and a cold side, where the hot side is subjected to hot gas. A fixed heat shield element (10) is arranged on the hot side on a supporting structure (2) and designed as a resonator i.e. Helmholtz resonator. The resonator comprises a resonator neck (15) and an area (S), where length (L) of the resonator neck is adjustable. The heat shield element is made of metal or metal alloy, and a thermal barrier coating (TBC) is formed on the hot gas side of the combustion chamber wall. An independent claim is also included for a method for operating a gas turbine with a combustion chamber arrangement.