Alstom Technology Limited

Alstom (switzerland) Ltd

Abb Alstom Power (schweiz) Ag

Abb Alstom Power (switzerland) Ltd.

Ansaldo Energia IP UK Limited

Ulrich Wellenkamp

Herbert Brandl

Ulrich Rathmann

Wolfgang Kappis

Alexander Stankowski

Christof Pfeiffer

Christoph Nagler

Peter Marx

Luis Puerta

Armin Busekros

Kynan Eng

Hartmut Hähnle

Sejko Kolev

Michal Tomasz Prugarewicz

Luis Federico Puerta

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.

Blade arrangement, especially stator blade arrangement

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.

Method for reconditioning a rotor of a turbomachine

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.

Device for setting the gap dimension for a turbomachine

Heat shield for a gas turbine

A coolable casing of a gas turbine or the like, with a plurality of arcuate casing segments (,) 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 (,), in particular of a high-pressure turbine, at least one annular casing cooling chamber (,) which is formed in the radial direction between the casing segments (,) and arcuate guide segments (,) provided with a multiplicity of passage orifices (,), at least one air guide chamber (,) which is formed in the radial direction between the guide segments (,) and at least one carrier segment (,), and at least one air supply duct (,) which is made on the carrier segment (,) and opens into the air guide chamber (,), the guide segments (,) being mounted loosely with radial play. This ensures stress-free reception, even in the case of intensive operations having high temperature gradients.

Coolable casing of a gas turbine or the like

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.

Growing community of inventors

Windisch, Switzerland

Ulrich Wellenkamp