Abstract: The invention relates to a method for coating a component, which is provided for the hot gas duct of a turbomachine, wherein the coating material is applied onto the uncoated component surface in the form of particles in mixture with a binding agent, and the component with the particle-treated binding agent thereupon then undergoes thermal treatment in such a way that the binding agent is released and the coating material remains on the component.

Abstract: A supporting device (10) for a casing (12) of a turbomachine (100), for bracing against forces acting on the casing (12) that occur during operation of the turbomachine (100), having at least one hub element (40), and at least one supporting element (20) for holding the hub element (40) on the casing (12). The supporting device (10) includes at least one rotary joint (30) which is used to rotatably connect the hub element (40) to the supporting element (20). Other aspects of the present invention relate to a casing (12) for a turbomachine (100), and to a turbomachine (100).

Abstract: The invention relates to a method for coating a component, which is provided for the hot gas duct of a turbomachine, wherein the coating material is applied onto the uncoated component surface in the form of particles in mixture with a binding agent, and the component with the particle-treated binding agent thereupon then undergoes thermal treatment in such a way that the binding agent is released and the coating material remains on the component.

Abstract: A sealing assembly for a turbomachine is provided, in particular for a gas turbine, having an annular groove G, in which at least one sealing ring (2) is located to seal a gap (S), at least one spiral ring (3) being located in the annular groove to axially support the sealing ring (2) against a first end face (11) of the annular groove.

Abstract: A gas turbine duct casing, in particular for an aircraft engine, is disclosed. The duct casing has a first wall segment and a second wall segment which is connected to the first wall segment by a clamp arrangement. The clamp arrangement has at least one clamp and one bolt which passes through a hole in the clamp and is screwed to a nut on a side of the clamp facing away from the wall segments. The nut braces at least one first leg of the clamp against the first wall segment, in particular by an intermediate element, and braces at least one second leg of the clamp against the second wall segment. The bolt has a head which is guided in a form-fitting manner in a groove on the outside of the first wall segment facing away from the gas duct.

Abstract: A gas turbine duct casing, in particular for an aircraft engine, is disclosed. The duct casing has a first wall segment and a second wall segment which is connected to the first wall segment by a clamp arrangement. The clamp arrangement has at least one clamp and one bolt which passes through a hole in the clamp and is screwed to a nut on a side of the clamp facing away from the wall segments. The nut braces at least one first leg of the clamp against the first wall segment, in particular by an intermediate element, and braces at least one second leg of the clamp against the second wall segment. The bolt has a head which is guided in a form-fitting manner in a groove on the outside of the first wall segment facing away from the gas duct.