Abstract: A method is disclosed for cooling a gas turbine having a turbine, wherein a rotor, which rotates about a machine axis, carries a plurality of rotating blades, which are mounted by blade roots and extend with their airfoils into a hot gas path of the gas turbine. The rotor is concentrically surrounded by a turbine vane carrier carrying a plurality of stationary vanes, whereby the rotating blades and the stationary vanes are arranged in alternating rows in axial direction. An extended lifetime with external cooling is achieved by providing first and second cooling systems for the turbine.

Abstract: An intake manifold is provided for inducting combustion air for a compressor of a gas turbine. The intake manifold includes a plurality of walls that delimit against the environment. Devices are provided for controllable change of the mechanical rigidity of the walls to reduce noise which is generated or is emitted in an air intake region during operation of the gas turbine. A gas turbine is also provided and includes an air intake to which air to be compressed is fed via an intake manifold. The intake manifold having a plurality of walls that delimit against the environment. Devices are provided to controllably change a mechanical rigidity of the walls to reduce noise which is generated or emitted in an air intake region during operation of the gas turbine.

Abstract: In a support for a turbine, which turbine has an outer casing which is split into an upper section (11) and a lower section (12) in a horizontal parting plane, in which upper section (11) and lower section (12) are screwed to each other on a horizontal flange (13; 13a, 13b) which lies in the parting plane, the support includes a multiplicity of essentially vertical supports (31) which by an upper end act on the outer casing (18) and by the lower end are supported on a foundation. With such a support, optimum points of application on the outer casing are achieved with the threaded flange connection without limitations by one or more of the supports (31) acting by the upper end on the horizontal flange (13; 13a, 13b) and being part of the horizontal threaded flange connection.

Abstract: An intake manifold is provided for inducting combustion air for a compressor of a gas turbine. The intake manifold includes a plurality of walls that delimit against the environment. Devices are provided for controllable change of the mechanical rigidity of the walls to reduce noise which is generated or is emitted in an air intake region during operation of the gas turbine. A gas turbine is also provided and includes an air intake to which air to be compressed is fed via an intake manifold. The intake manifold having a plurality of walls that delimit against the environment. Devices are provided to controllably change a mechanical rigidity of the walls to reduce noise which is generated or emitted in an air intake region during operation of the gas turbine.

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: In a support for a turbine, which turbine has an outer casing which is split into an upper section (11) and a lower section (12) in a horizontal parting plane, in which upper section (11) and lower section (12) are screwed to each other on a horizontal flange (13; 13a, 13b) which lies in the parting plane, the support includes a multiplicity of essentially vertical supports (31) which by an upper end act on the outer casing (18) and by the lower end are supported on a foundation. With such a support, optimum points of application on the outer casing are achieved with the threaded flange connection without limitations by one or more of the supports (31) acting by the upper end on the horizontal flange (13; 13a, 13b) and being part of the horizontal threaded flange connection.

Abstract: Annular or ring-segment-shaped cavities (2, 7) which are formed in particular in multi-shell (11; 12, 13) casings of turbomachines are preferably provided with suitable means for compensating for forming temperature stratifications. According to the invention, an overflow passage (14) connects two points of the cavity to one another which are situated in different circumferential positions. Arranged in the overflow passage (14) is an ejector (17) which can be operated with a motive fluid and which serves to drive a flow through the overflow passage from an upstream end (15) to a downstream end (16).

Abstract: Annular or ring-segment-shaped cavities (2, 7) which are formed in particular in multi-shell (11; 12, 13) casings of turbomachines are preferably provided with suitable means for compensating for forming temperature stratifications. According to the invention, an overflow passage (14) connects two points of the cavity to one another which are situated in different circumferential positions. Arranged in the overflow passage (14) is an ejector (17) which can be operated with a motive fluid and which serves to drive a flow through the overflow passage from an upstream end (15) to a downstream end (16).

Abstract: A device for setting the gap dimension for a turbomachine, in particular a gas turbine, with heat accumulation segments which are arranged on the guide-vane carrier of the rotor arrangement. At least one drive device projects radially through the turbine casing and the guide-vane carrier and is operatively connected kinematically to at least one heat accumulation segment and which, when actuated, causes a radial spacing of the heat accumulation segment. The heat accumulation segment has, in the flow direction of the turbomachine, a conical contour facing the rotor arrangement and is arranged so as to be displaceable parallel to the flow direction, and in that the drive device is connected to the heat accumulation segment directly or via an eccentric unit, in such a way that, when the drive device is actuated, the heat accumulation segment is displaced, with the result that a radial spacing between the heat accumulation segment and the moving-blade tips can be set.

Abstract: What is described is a device for setting the gap dimension for a turbomachine, in particular a gas turbine, with a multiplicity of moving blades arranged in at least one moving-blade row of a rotor arrangement, with a guide-vane carrier surrounding the rotor arrangement and a turbine casing surrounding the guide-vane carrier, with a multiplicity of heat accumulation segments which are arranged on the guide-vane carrier of the rotor arrangement and at least opposite the moving-blade tips and which, together with the moving-blade tips, enclose a gap, and with at least one drive means which projects radially through the turbine casing and the guide-vane carrier and is operatively connected kinematically to at least one heat accumulation segment and which, when actuated, causes a radial spacing of the heat accumulation segment.