| 摘要 |
The present invention relates to a damper device for reducing combustion-chamber pulsation arising inside a gas turbine, wherein the gas turbine essentially comprises at least one compressor, a primary combustor which is connected downstream to the compressor, and the hot gases of the primary combustor are admitted to an intermediate turbine or directly or indirectly to a secondary combustor. The hot gases of the secondary combustor are admitted to a further gas turbine or directly or indirectly to an energy recovery device, wherein at least one combustor is arranged in a can-architecture. At least one combustor liner comprises air passages, wherein at least one of the air passages is formed as a damper neck. The damper neck is actively connected to a damper volume portion, and the damper volume portion is a part of a connecting duct extending between a compressor air plenum and the combustor. |
