Abstract: The present invention relates to a damping device for a combustor of a gas turbine for suppressing combustion instabilities. More specifically, the invention relates to a design of a broadband damping device for a low emission combustor having at least one resonator for damping pressure fluctuations in the combustion chamber. It is an object of the invention to provide a damping device with a quarter wave damper having broadband characteristics.

Abstract: A combustion chamber of a gas turbine includes an optimized arrangement of acoustic dampers.

Abstract: An acoustic damper includes a neck and a damping volume. The neck has a mouth being in fluid connection with a chamber. The chamber is limited by an inner surface of at least one wall. The acoustic damper device includes a recess located between the mouth of the neck and the inner surface of the wall.

Abstract: The damper arrangement includes a plurality of interconnected volumes and a plurality of necks for connecting the damper to a combustion chamber at a plurality of contact points. The plurality of necks are connected to the plurality of volumes.

Abstract: The invention relating to a A damper for combustion oscillation damping for a gas turbine, includes a resonator cavity with a box or cylinder shape, a neck in flow communication with the resonator cavity and a combustion chamber. The length Lneck of the neck is equal or greater than a maximum distance lmax that a hot gas ingested from the combustion chamber reaches in the neck. The maximum distance lmax is determined according to the following equation: l max = ? t 1 t 2 ? U - p ^ ? ? ? U ? ? ? ? sin ? ( ? ? ? t ) ? ? ? t . With the solution of the present invention, the damper used to damping combustion oscillation may prevent hot gas ingestion during normal operations by uniquely determining the dimensions of the neck connecting the resonator cavity and the combustion chamber.

Abstract: The damper arrangement include two concentric hollow shapes, each having a wall, wherein the walls form an annular volume therebetween. The damper arrangement further includes one or more necks for connecting to a combustion chamber at corresponding one or more contact points. The one or more necks are connected to the annular volume.

Abstract: A mountable attachment for positioning a sensor in an environment, like a combustion chamber of a gas turbine is disclosed. The mountable attachment includes a mounting member having a hollow elongated configuration for incorporating the sensor therewithin. The attachment further includes at least one primary resilient member disposed within the mounting member in a coordinating manner with the sensor for applying an axially outward force on the mounting member to prevent thereto from loosening from a counterpart , and providing a mounting torque for mounting the sensor at a target position within the environment . The attachment may also include additional resilient member, such as a secondary resilient member, which may in combination with the primary resilient members attain a resulting mounting force to prevent the mounting member from loosening from the counterpart.

Abstract: The invention relates to a damper for reducing pulsations in a gas turbine, which includes an enclosure, a main neck extending from the enclosure, a spacer plate disposed in the enclosure to separate the enclosure into a first cavity and a second cavity and an inner neck with a first end and a second end, extending through the spacer plate to interconnect the first cavity and the second cavity. The first end of the inner neck remains in the first cavity and the second end remains in the second cavity. A flow deflecting member is disposed proximate the second end of the inner neck to deflect a flow passing through the inner neck. With the solution of the present invention, as a damper according to embodiments of the present invention operates, flow field hence damping characteristic in the second cavity constant regardless the adjustment of the spacer plate in the enclosure.

Abstract: The invention relates to a damping device for a gas turbine combustor with significantly reduced cooling air mass flow requirements. The damping device includes a wall with a first inner wall and a second outer wall, arranged in a distance to each other. The inner wall is subjected to high temperatures on a side with a hot gas flow. A plurality of cooling channels extend essentially parallel between the first inner wall and the second outer wall, and at least one damping volume bordered by cooling channels. Furthermore, the damping device includes a first passage for supplying a cooling medium from a cooling channel into the damping volume and a second passage for connecting the damping volume to the combustion chamber. An end plate, fixed to the inner wall, separates the damping volume from the combustion chamber.

Abstract: The disclosure relates to a combustor transition adapted to guide combustion gases in a hot gas flow path extending between a can combustor and a first stage of turbine in a gas turbine. The combustor transition includes a duct having an upstream end adapted for connection to the can combustor and a downstream end adapted for connection to a first stage of a turbine, wherein the downstream end comprises an outer wall, an inner wall, a first and a second side wall. At least one side wall has a side wall extension, which extends in a downstream direction beyond the outlet. The side wall extension at least partly encloses a first resonator volume and at least one side wall extension includes a resonator hole, which is configured as a neck of a Helmholtz-damper.

Abstract: The disclosure relates combustor transition adapted to guide combustion gases in a hot gas flow path extending between a can combustor and a first stage of turbine in a gas turbine. The combustor transition includes a duct having an upstream end adapted for connection to the can combustor and an downstream end adapted for connection to a first stage of a turbine, wherein the downstream end comprises an outer wall, an inner wall, a first and a second side wall. The combustor transition is, characterized in that at least one side wall has a side wall extension, which is extending in a downstream direction beyond the outlet. Besides the combustor transition a gas turbine includes such a combustor transition, a method for retrofitting a gas turbine with such a combustor transition as well as a method for borescope inspection of a GT with such a combustor transition are disclosed.

Abstract: 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.

Abstract: An acoustic damper arrangement for a combustor which has an inner liner configured for use at a first temperature during operation and an outer liner configured for operation at a second temperature lower than the first temperature during operation is disclosed, the acoustic damper arrangement comprising: a plurality of flexible sheets; and at least one hollow body having an interior volume, each of said at least one hollow body being fixed to one of the plurality of flexible sheets, wherein the acoustic damper arrangement is configured to be fixed to both the inner liner and the outer liner such that the interior volume of the at least one hollow body is in communication with a chamber formed by the inner liner, and the plurality of flexible sheets accommodate expansion and contraction of the inner liner relative to the outer liner.

Abstract: An acoustic damper arrangement for a combustor which has an inner liner configured for use at a first temperature during operation and an outer liner configured for operation at a second temperature lower than the first temperature during operation is disclosed, the acoustic damper arrangement comprising: a plurality of flexible sheets; and at least one hollow body having an interior volume, each of said at least one hollow body being fixed to one of the plurality of flexible sheets, wherein the acoustic damper arrangement is configured to be fixed to both the inner liner and the outer liner such that the interior volume of the at least one hollow body is in communication with a chamber formed by the inner liner, and the plurality of flexible sheets accommodate expansion and contraction of the inner liner relative to the outer liner.

Abstract: The invention concerns a method for mixing a dilution air with a hot main flow in sequential combustion system of a gas turbine, wherein the gas turbine essentially comprises at least one compressor, a first combustor which is connected downstream to the compressor, and the hot gases of the first combustor are admitted to at least one intermediate turbine or directly or indirectly to at least one second combustor. The hot gases of the second combustor are admitted to a further turbine or directly or indirectly to an energy recovery, wherein at least one combustor runs under a caloric combustion path having a can-architecture. At least one dilution air injection is introduced into the first combustor, and wherein the direction of the dilution air injection is directed against or in the direction of the original swirl flow inside of the first combustor.

Abstract: An exemplary method for switching over a combustion device from operation with a first premix fuel to a second premix fuel includes reducing and stopping a first premix fuel supply and then starting a second premix fuel supply. In an intermediate phase, after the first premix fuel supply stop and before the second premix fuel supply start, the combustion device is operated with one or more pilot fuels generating diffusion flames.

Abstract: A method for operating a combustion device includes supplying a fuel and an oxidizer into the combustion device and burning them. According to the method, during at least a part of a transient operation, an additional fluid is supplied together with the fuel, and its amount is regulated to counteract combustion pulsations.