| 摘要 |
The invention concerns a damper arrangement (112) for reducing combustion-chamber pulsation arising inside a gas turbine (100), wherein the gas turbine (100) essentially comprises at least one compressor (103), a primary combustor (101) which is connected downstream to the compressor (103), and the hot gases of the primary combustor (101) are admitted at least to an intermediate turbine or directly or indirectly to a secondary combustor (102). The hot gases of the secondary combustor (102) are admitted to a further turbine (105) or directly or indirectly to an energy recovery, wherein at least one combustor is arranged in a can-architecture. At least one combustor liner comprising air passages (114), wherein at least one of the air passages (114) is formed as a damper neck (113). The damper neck (113) being actively connected to a damper volume (112), and the damper volume (112) is part of a connecting duct extending between a compressor air plenum and the combustor. |
