Abstract: A turbomachine includes an inner housing which radially defines the flow channel of the turbomachine. A thermal barrier coating is arranged about the inner housing. The thermal barrier coating of the inner housing is made of microporous plastic coating which can be added to hollow spheres made of different materials and have different sizes. A method for applying a thermal barrier coating to the inner casing of a turbomachine includes preparing a material having a base material which has a microporous plastic; coating the outside of the wall of the inner casing by applying the base material to the inner casing; and curing the applied material, thus forming the thermal barrier coating.

Abstract: A tubular housing for a turbomachine is provided. The tubular housing includes two half-tube shells which, lying against one another in two connecting regions overlap partially in each case in the tangential direction of the tubular housing. In order to specify a particularly reliable and permanent connection of the two half-tube shells which additionally develop a particularly satisfactory sealing action, it is proposed that, in order to interlock the half-tube shells in the tangential direction, in relation to the tube axis of the housing, at least one eccentric pin is provided in one or both connecting regions.

Abstract: An arrangement for axially securing blades of a rotor of a gas turbine is provided. The arrangement includes a sealing element arranged on the end side surface of the rotor, which may be particularly reliably attached to the rotor by means of a sheet metal strip, the sheet metal strip including a shape-memory alloy.

Abstract: An axial turbine for a gas turbine including a rotor blade cascade is provided. The rotor blade cascade is formed from rotor blades each including, a front edge, a blade tip, and an annular space wall that surrounds the rotor blade cascade and includes an annular space inner side, enabling the annular space wall to be arranged directly adjacent to the blade tip forming a radial gap between the covering of the blade tip and the annual space inner side. When the turbine is in operation, the area of the blade tip with the highest pressure load is disposed in the region of the front edges, and the rotor blades in the region of their front edges include a radial projection and the annular space wall includes on the annular space inner side, a peripheral radial recess that interacts with the radial projections such that a minimum is established in the direction of the main through-flow of the turbine.

Abstract: An arrangement for axially securing blades of a rotor of a gas turbine is provided. The arrangement includes a sealing element arranged on the end side surface of the rotor, which may be particularly reliably attached to the rotor by means of a sheet metal strip, the sheet metal strip including a shape-memory alloy.