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 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.

Abstract: The present invention creates a layer system for the rotor/stator seal of a turbomachine, in particular a compressor, which is disposed between components of the turbomachine and can be run in with a movement of the components relative to one another, in such a way that at least one of the components is run into the layer system, having: a first adhesive layer disposed on at least one of the components; a protective layer disposed on the first adhesive layer; a second adhesive layer disposed on the protective layer; and a running-in layer, which is formed softer than the protective layer and which is disposed on the second adhesive layer. The present invention further provides a method for producing a layer system for the rotor/stator seal of a turbomachine, as well as a turbomachine.

Abstract: The present invention creates a layer system for the rotor/stator seal of a turbomachine, in particular a compressor, which is disposed between components of the turbomachine and can be run in with a movement of the components relative to one another, in such a way that at least one of the components is run into the layer system, having: a first adhesive layer disposed on at least one of the components; a protective layer disposed on the first adhesive layer; a second adhesive layer disposed on the protective layer; and a running-in layer, which is formed softer than the protective layer and which is disposed on the second adhesive layer. The present invention further provides a method for producing a layer system for the rotor/stator seal of a turbomachine, as well as a turbomachine.

Abstract: A gas turbine, such as an aircraft engine, has at least one compressor, at least one turbine, a combustion chamber, and a fuel pump to supply fuel to the combustion chamber. Upon identification of a break of a shaft that couples a compressor with a turbine, the gas turbine is shut off. For this purpose, at least one electrical current conductor is arranged on the shaft, whereby this current conductor is a component of a current supply for the fuel pump or for a fuel pump regulation. When the integrity of the current conductor is disrupted, thereby the current supply of the fuel pump or of the fuel pump regulation is interrupted in order to automatically shut off the gas turbine.

Abstract: The invention relates to a gas turbine, especially an aircraft engine, with at least one compressor, at least one turbine and one combustion chamber, whereby fuel is supplyable to the combustion chamber by a fuel pump, and whereby upon identification of a break of a shaft, which couples a compressor with a turbine, the gas turbine can be shut off. According to the invention, at least one current conductor is arranged on the or each shaft, which current conductor is a component of a current supply for the fuel pump or a component of a current supply for a fuel pump regulation, whereby the integrity of the or each current conductor is monitored in such a manner that upon a change of the integrity of the or each current conductor the current supply of the fuel pump or of the fuel pump regulation is interrupted in order to automatically shut off the gas turbine.