Loading patent…
AssigneeALSTOM Technology Ltd
InventorsMirko Ruben BOTHIEN, Jaan HELLAT, Bruno SCHUERMANS
Estimating the term…
The invention concerns a damper arrangement for reducing combustion-chamber pulsation arising inside a gas turbine, wherein the gas turbine includes at least one compressor, a primary combustor which is connected downstream to the compressor, and the hot gases of the primary combustor are admitted at least to an intermediate turbine or directly or indirectly to a secondary combustor. The hot gases of the secondary combustor are admitted to a further turbine or directly or indirectly to an energy recovery, wherein at least one combustor is arranged in a can-architecture. At least one combustor liner includes air passages, wherein at least one of the air passages is formed as a damper neck. The damper neck being actively connected to a damper volume, and the damper volume is part of a connecting duct extending between a compressor air plenum and the combustor.
A damper arrangement 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 at least to an intermediate turbine or directly or indirectly to a secondary combustor, wherein the hot gases of the secondary combustor are admitted to a further turbine or directly or indirectly to an energy recovery, wherein at least one combustor liner comprising air passages, wherein at least one of the air passages is formed as a damper neck, wherein the damper neck being connected to a damper volume, and wherein the damper volume is part of a connecting duct extending between a compressor air plenum and the combustor.
Dependencies are inferred from the claim text.