Abstract: A device and a method for mounting a turbine engine, e.g., a gas turbine system, are described, in which a rotor unit is mounted to rotate inside a stationary external housing, having at least two supports for taking up the weight of the turbine engine, these supports being arranged at a spacing from one another in an axial longitudinal direction in relation to the external housing and at one side being articulated directly or indirectly on the external housing and at the other being supported directly or indirectly on a base frame. At least one support provides at least one support face which is supported exclusively in partial regions on at least two support plate elements. The at least one support face of the support is in operational engagement with the base frame by way of the support plate elements.

Abstract: A device and a method for mounting a turbine engine, e.g., a gas turbine system, are described, in which a rotor unit is mounted to rotate inside a stationary external housing, having at least two supports for taking up the weight of the turbine engine, these supports being arranged at a spacing from one another in an axial longitudinal direction in relation to the external housing and at one side being articulated directly or indirectly on the external housing and at the other being supported directly or indirectly on a base frame. At least one support provides at least one support face which is supported exclusively in partial regions on at least two support plate elements. The at least one support face of the support is in operational engagement with the base frame by way of the support plate elements.

Abstract: Means for driving a flow are arranged in cavities which are formed, in particular, in multishell casings of turbo engines. In one embodiment, within the cavity, ejectors are arranged which are supplied via suitable means with a propellant flow which, in turn, activates the flow, for preference a circumferential flow. Preferably, during the operation of the turbo engine a propelling fluid which is colder than the fluid content of the cavity is injected via the ejectors. In this way, at the same time, the cavity is cooled and an equalization of the temperature of the fluid content of the cavity is brought about.

Abstract: Means for driving a flow are arranged in cavities which are formed, in particular, in multishell casings of turbo engines. In one embodiment, within the cavity, ejectors are arranged which are supplied via suitable means with a propellant flow which, in turn, activates the flow, for preference a circumferential flow. Preferably, during the operation of the turbo engine a propelling fluid which is colder than the fluid content of the cavity is injected via the ejectors. In this way, at the same time, the cavity is cooled and an equalization of the temperature of the fluid content of the cavity is brought about.