Abstract: The present invention relates to dampers for gas turbines and, for example, to a compensation assembly for a damper of a gas turbine for reducing the pulsations occurring in the combustion chamber. The damper can include a resonator cavity with a neck tube in flow communication with the interior of the combustion chamber, wherein the compensation assembly includes a spherical joint associated to the neck tube and configured to allow relative rotation between the combustion chamber and the resonator cavity, and having a bulb portion disposed around the neck tube and a spherical socket configured to internally host the bulb portion, wherein the spherical socket can have a top collar portion and a bottom collar portion connected to each other.

Abstract: A method of manufacturing a hot gas wall for a gas turbine is described. The method is carried out on a hot gas wall having a wall part with a front side and a back side, the wall part being for exposure to a hot fluid on the front side, and the hot gas wall also having a turbulator structure. In an exemplary embodiment, a turbulator structure is attached to the wall by placing a braze foil on the back side of the wall part, placing a turbulator structure on the braze foil, and brazing to attach the turbulator structure to the wall part. In another embodiment, the turbulator structure is attached by passing a current through the turbulator structure part and the wall part to resistance weld the turbulator structure part to the wall part.

Abstract: A method of manufacturing a hot gas wall for a gas turbine is described. The method is carried out on a hot gas wall having a wall part with a front side and a back side, the wall part being for exposure to a hot fluid on the front side, and the hot gas wall also having a turbulator structure. In an exemplary embodiment, a turbulator structure is attached to the wall by placing a braze foil on the back side of the wall part, placing a turbulator structure on the braze foil, and brazing to attach the turbulator structure to the wall part. In another embodiment, the turbulator structure is attached by passing a current through the turbulator structure part and the wall part to resistance weld the turbulator structure part to the wall part.

Abstract: The present invention relates to dampers for gas turbines and, for example, to a compensation assembly for a damper of a gas turbine for reducing the pulsations occurring in the combustion chamber. The damper can include a resonator cavity with a neck tube in flow communication with the interior of the combustion chamber, wherein the compensation assembly includes a spherical joint associated to the neck tube and configured to allow relative rotation between the combustion chamber and the resonator cavity, and having a bulb portion disposed around the neck tube and a spherical socket configured to internally host the bulb portion, wherein the spherical socket can have a top collar portion and a bottom collar portion connected to each other.