Abstract: The invention relates to a guide vane assembly of a turbomachine based on a modular structure, wherein the guide vane elements include at least an airfoil, an inner platform, an outer platform, wherein the guide vane airfoil and/or platforms have at its one ending provisions for connection of the guide vane elements among each other. The connections of the guide vane elements among each other are configured as a detachable, permanent or semi-permanent fixation with respect to the radial or quasi-radial extension of the airfoil compared to the rotor axis of the turbomachine. The assembling of the airfoil with respect to at least one platform is based on a force-fit and/or a form-fit connection, or on the use of a metallic and/or ceramic fitting surface, or on force closure means with a detachable, permanent or semi-permanent fixation.

Abstract: A blade arrangement on a wall of a fluid flow path of a turbomachine includes a locating channel disposed in the wall and having undercut flanks. A plurality of blades each having a blade-side root section corresponding to the undercut flanks. A plurality of intermediate filling pieces correspond to the undercut flanks and separate each of the blade-side root sections. The plurality of blade-side root sections and intermediate filling pieces are seated in a form-fitting manner and fixed in a force-locking manner in the locating channel. The plurality of intermediate filling pieces fill out the locating channel so as to form a gas flow-side surface essentially free of a disturbing contour between the blade-side root sections. Each of the plurality of intermediate filling pieces includes a threaded hole disposed essentially perpendicular to a base of the channel. A screw is disposed in the threaded hole.

Abstract: A method is provided for reconditioning a turbomachine rotor, equipped with circumferentially extending grooves for accommodating blades retained in the grooves at a distance from each other by spacers. The method includes removing the blades and spacers from the grooves and hollowing out the exposed grooves, simultaneously widening the grooves to remove damage-inflicted material. At least one circumferentially extending lateral groove is introduced for accommodating a filler piece in the grooves to fill a gap between blades and hollowed-out rotor grooves. New spacers are provided which are matched to the hollowed-out grooves and have recesses which are matched to the introduced lateral grooves. Filler pieces are provided for inserting into the circumferentially extending lateral grooves and recesses of the new spacers. The blades and new spacers are inserted into the hollowed-out rotor grooves and corresponding filler pieces are inserted into the lateral grooves and matched recesses of the new spacers.

Abstract: A method is provided for reconditioning a turbomachine rotor, equipped with circumferentially extending grooves for accommodating blades retained in the grooves at a distance from each other by spacers. The method includes removing the blades and spacers from the grooves and hollowing out the exposed grooves, simultaneously widening the grooves to remove damage-inflicted material. At least one circumferentially extending lateral groove is introduced for accommodating a filler piece in the grooves to fill a gap between blades and hollowed-out rotor grooves. New spacers are provided which are matched to the hollowed-out grooves and have recesses which are matched to the introduced lateral grooves. Filler pieces are provided for inserting into the circumferentially extending lateral grooves and recesses of the new spacers. The blades and new spacers are inserted into the hollowed-out rotor grooves and corresponding filler pieces are inserted into the lateral grooves and matched recesses of the new spacers.

Abstract: A blade arrangement on a wall of a fluid flow path of a turbomachine includes a locating channel disposed in the wall and having undercut flanks. A plurality of glades each having a blade-side root section corresponding to the undercut flanks a plurality of intermediate filling pieces correspond to the undercut flanks and separate each of the blade-side root sections. The plurality of blade-side root sections and intermediate filling pieces are seated in a form-fitting manner and fixed in a force-locking manner in the locating channel. The plurality of intermediate filling pieces fill out the locating channel so as to form a gas flow-side surface essentially free of a disturbing contour between the blade-side root sections. Each of the plurality of intermediate filling pieces includes a threaded hole disposed essentially perpendicular to a base of the channel. A screw is disposed in the threaded hole.

Abstract: A sealing assembly comprises a bore in a housing, a plurality of seal rings and a shaft. The bore comprises a plurality of seats disposed at different seat radius for the seal rings. The bore comprises for each pair of adjacent seats axially inward of an inner end of the outward seat and proximate to the inward seat a chamfer extending radially inwardly over an inward axial distance. The chamfer between each pair of seats allows for the radial contraction of the seal rings upon assembly.

Abstract: An exhaust-gas turbocharger with a compressor casing, turbine housing and bearing housing is supported on a base in the area of the bearing housing by means of a first support and in the area of the turbine housing by means of a second support. The second support is made in at least two parts, whereby the two parts can be moved relative to one another in the support direction. As a result, the length of the supports can be varied and counterbalance a temperature-related raising or lowering of the exhaust-gas turbocharger housing.

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.

Abstract: A heat shield for a gas turbine, which heat shield encloses in particular the rotating blades of a stage of the gag turbine in an annular manner, consists of a plurality of heat-shield segments (13), which are arranged one behind the other in the circumferential direction, are curved in a circular-segment shape and are cooled from outside, and the longitudinal sides of which are designed as correspondingly curved rails running in the circumferential direction and possibly provided with recesses and having in each case a first arm (18) projecting in the axial direction, and which, for fastening to the casing of the gas turbine, are mounted with the first arms (18) in each case in an annular intermediate space (20) of constant width.

Abstract: A coolable casing of a gas turbine or the like, with a plurality of arcuate casing segments (10) which are arranged so as to be contiguous with one another in a circumferential direction, to form an essentially closed casing ring surrounding a rotor (110), in particular of a high-pressure turbine, at least one annular casing cooling chamber (15) which is formed in the radial direction between the casing segments (10) and arcuate guide segments (30) provided with a multiplicity of passage orifices (34), at least one air guide chamber (25) which is formed in the radial direction between the guide segments (30) and at least one carrier segment (20), and at least one air supply duct (26) which is made on the carrier segment (20) and opens into the air guide chamber (25), the guide segments (30) being mounted loosely with radial play. This ensures stress-free reception, even in the case of intensive operations having high temperature gradients.

Abstract: A heat shield for a gas turbine, which heat shield encloses in an annular manner the moving blades, rotating in the hot-gas duct of the gas turbine, of a stage of the gas turbine and consists of a plurality of heat-shield segments which are arranged one behind the other in the circumferential direction, are curved in the shape of a segment of a circle and are cooled from outside, and the longitudinal sides which are designed as correspondingly curved rails running in the circumferential direction and having in each case a pair of arms of which project in the axial direction, run in parallel and are at a distance from one another, the heat-shield segments, while forming a cavity to which cooling air can be admitted, are fastened to the inside of an annular carrier, which concentrically surrounds the heat shield in such a way that in each case a radial gap is formed between the longitudinal sides of heat-shield segments and the adjacent elements which define the hot-gas duct on the outside.