High frequency stabilised combustion in aviation gas turbines

The invention relates to a gas turbine with a combustion chamber (104) and a microwave source (110) for generating microwave radiation. The gas turbine is configured to introduce the microwave radiation into a cavity (119) of the combustion chamber. By means of the microwave radiation in the cavity (119) of the combustion chamber (104), combustion in the cavity (119) can be supported and thus a lean operation of the gas turbine can be enabled.