The invention relates to a gas turbine comprising a combustor that extends into a combustion chamber. The port of the combustor is surrounded in a ring-shaped manner by a Helmholtz resonator, whereby combustion oscillations are effectively suppressed due to close contact with the flame while irregularities in temperature are prevented.
1. A gas turbine, comprising: a combustion chamber; a combustor that leads into the combustion chamber at a combustor port and is connected to the combustion chamber via a combustor insert distinct from both the combustor port and the combustor; and a Helmholtz resonator surrounding the combustor port, wherein, the Helmholtz resonator is integrated in the combustor insert, having a resonator volume connected to the combustion chamber by a resonator port, and including a small tube extending from the port into the resonator volume.
2. The gas turbine as claimed in claim 1 , wherein the small tube is curved or twisted in form.
3. The gas turbine as claimed in claim 1 , wherein the small tube is curved and twisted in form.
4. The gas turbine as claimed in claim 1 , wherein the resonator volume is adjustable.
5. The gas turbine as claimed claim 1 , wherein the combustion chamber is designed as an annular combustion chamber.
6. The gas turbine as claimed in claim 1 , wherein the resonator surrounds the combustor port annularly.
7. The gas turbine as claimed in claim 6 , wherein the resonator port includes multiple holes with a tube extending from each hole into the resonator volume.
8. The gas turbine as claimed in claim 1 , wherein the resonator includes a plurality of air inlets allowing the resonator impedance to be adapted.
9. The gas turbine as claimed in claim 1 , wherein combustor airflow is directed through the Helmholtz resonator.