Abstract: An exhaust gas liner for a gas turbine includes an annular inner shell and an annular outer shell, which are arranged concentrically around a machine axis of the gas turbine to define an annular exhaust gas channel in between. The inner shell and/or said outer shell are composed of a plurality of liner segments, which are attached to a support structure. To compensate thermal expansion and achieving resistance against dynamic loads, the liner segments are fixed to the support structure at certain fixation spots, which are distributed over the area of said liner segments, such that said liner segments are clamped to said support structure through a whole engine thermal cycle without hindering thermal expansion.

Abstract: An exhaust gas liner for a gas turbine includes an annular inner shell and an annular outer shell, which are arranged concentrically around a machine axis of the gas turbine to define an annular exhaust gas channel in between. The inner shell and/or said outer shell are composed of a plurality of liner segments, which are attached to a support structure. To compensate thermal expansion and achieving resistance against dynamic loads, the liner segments are fixed to the support structure at certain fixation spots, which are distributed over the area of said liner segments, such that said liner segments are clamped to said support structure through a whole engine thermal cycle without hindering thermal expansion.

Abstract: A wall structure is provided with noise damping insulation properties, for an air intake manifold of a gas turbine. The wall structure includes a first structure for mechanically supporting an outer sheet, which separates the spaces on both sides of the wall in an airtight manner, and further includes a second structure for establishing noise damping insulation between the spaces on both sides of the wall. The second structure is secured to the first structure. A gas turbine including the wall structure is also provided.

Abstract: The invention relates to a pressure vessel for a machine, especially a turbomachine, which comprises at least 3 casing shell sections, wherein the intersection region of the parting joints is sealed off by a plug which in its interior has a system of holes and passages through which a sealing compound is pressed into the region between plug and casing shell sections, so that after its setting, an elastic, leakproof and non-destructively disassemblable sealing of the intersection region of the parting joints is created. The plug can be fastened on the casing shell sections by means of an integrated flange.

Abstract: A wall structure is provided with noise damping insulation properties, for an air intake manifold of a gas turbine. The wall structure includes a first structure for mechanically supporting an outer sheet, which separates the spaces on both sides of the wall in an airtight manner, and further includes a second structure for establishing noise damping insulation between the spaces on both sides of the wall. The second structure is secured to the first structure. A gas turbine including the wall structure is also provided.

Abstract: The invention relates to a pressure vessel for a machine, especially a turbomachine, which comprises at least 3 casing shell sections, wherein the intersection region of the parting joints is sealed off by a plug which in its interior has a system of holes and passages through which a sealing compound is pressed into the region between plug and casing shell sections, so that after its setting, an elastic, leakproof and non-destructively disassemblable sealing of the intersection region of the parting joints is created. The plug can be fastened on the casing shell sections by means of an integrated flange.

Abstract: A housing (1) for a machine, in particular a turbomachine, includes a first housing shell (2) which bears against a second housing shell (3) along a parting plane (4). In order to avoid an asymmetric deformation of the housing (1) when the machine is in operation, in the region of the parting plane (4) at least one bridge (6) is formed, by which the two housing shells (2, 3) are fastened to one another. In this case, the at least one bridge (6) extends perpendicularly with respect to the parting plane (4). The bridge (6) is firmly connected on one side of the parting plane (4), in a first bridge portion (7), to the first housing shell (2) and on the other side of the parting plane (4), in a second bridge portion (8), to the second housing shell (3).