GAS TURBINE COMBUSTION SYSTEM

摘要

A gas turbine combustion system comprises a combustion system wall (25) delimiting a flow path for hot and pressurized combustion gas (29) and at least one resonator (27) with a resonator volume (31). The resonator volume (31) is delimited by resonator walls (25, 33, 35), where one of the resonator walls (25) is located adjacent to or is formed by the 10 combustion system wall (25). The resonator (27) comprises at least one cooling fluid supply opening (41) which is open towards a cooling fluid source. It further comprises a neck opening (37) which is open towards the flow path and which is implemented in the form of a neck slot (37).