Patent ID: 8869533

Claim:
Combustion system for a gas turbine, the combustion system comprising: a combustion chamber having a pilot injector and a main injector, the pilot injector having a wall section separating an outside of the combustion chamber from an inside of the combustion chamber, wherein the wall section comprises a passage for injecting a combustion medium into the combustion chamber, and a resonator with a neck section and a resonator chamber, wherein the neck section and the resonator chamber form a resonator volume reducing vibrations within the combustion chamber, the main injector having a radial swirler arranged such that fuel/gas is injectable into the combustion chamber, wherein the resonator chamber comprises a first inlet for injecting gaseous medium into the resonator chamber and a second inlet for injecting fuel into the resonator chamber such that a fuel/gas mixture is generated inside the resonator chamber, and wherein the neck section is connected from the outside of the combustion chamber to the passage of the wall section such that the combustion medium comprising the fuel/gas mixture is injectable into the combustion chamber.