Alstom Technology Limited

Man Energy Solutions Se

Thomas Mokulys

Giorgio Zanazzi

Vishal Borikar

Davor Kriz

Luca Marie Ripamonti

Martin Reigl

Maurus Herzog

Jian Chen

Jozo Drmic

Rabiye Bekyigit

Said Havakechian

Pierre-Alain Masserey

Andreas Ehrsam

Thomas Schreier

Philipp Brunner

Ludwig Boxheimer

Bob Mischo

Rolf Döbler

Viktor Salit

Reto Birrer

Annika Klaas

Silvia Gafner

Sebastiano Mauri

Marcel Bühler

Damian Schärz

Christian Rufer

Patrick Vu

Hans-Ludwig Boxheimer

Rolf Doebler

Martin Scholtysik

Beate Grzondziel

Michael Sell

Christoph Pfoster

A rotor blade of a turbomachine, having a blade root, a blade airfoil which has a flow leading edge, a flow trailing edge, and flow-guiding surfaces extending between the flow leading edge and the flow trailing edge. The blade root and a radially inner section of the blade airfoil are made of a steel material, and a radially outer section of the blade airfoil is made of a more lightweight material.

Moving blade of a turbo machine and method for producing the same

A fluid flow machine, in particular turbocompressor, with a housing, having a rotor mounted in the housing, and with a dry gas seal for sealing the rotor relative to the housing. The housing at least one recess or bore for a gaseous medium is introduced, via which the gaseous medium for temperature-controlling the dry gas seal can be conducted in the direction of the same. The gaseous medium can be directly conducted into a gas space formed between the housing and the dry gas seal via the or each recess or bore. Additionally or alternatively, the or each recess or bore receives a guide tube for the gaseous medium.

Fluid flow machine using a gaseous medium for temperature control of a dry gas seal

In a radial compressor stage for a radial compressor having a rotor side, the radial compressor stage includes a stator; and an impeller configured to rotate relative to the stator. The impeller has multiple impeller blades on the rotor side. Each of the multiple impeller blades has: a flow inlet edge, a flow outlet edge, a suction side extending between the flow inlet edge and the flow outlet edge, a pressure side, and an outer surface facing the stator. At least one groove is arranged in the outer surface of at least one of the multiple impeller blades, the at least one groove being bounded by a longitudinal web both on the suction side and on the pressure side. Each of the longitudinal webs forms a sealing tip of the respective impeller blade towards the stator.

Radial compressor stage

The disclosure relates to a radially fed axial steam turbine with a cold inlet duct, axially displaced from a hot inlet duct such that is it further away from a first blade row than the hot inlet duct. The cold inlet duct receives a cold steam from a cold inlet spiral and directs it into the hot inlet duct in such a way that a boundary layer of cold steam is formed over the rotor circumferential surface between the outlet end of the cold inlet duct and the blade and vane rows. The rotor circumferential surface is also adapted to promote and maintain the boundary layer. In this way, a maximum temperature to which the rotor is exposed can be reduced.

High temperature radially fed axial steam turbine

A steam turbine is provided having a relief groove which is arranged in the region of the equalizing piston and extends in the circumferential direction of the rotor. The relief groove, with regard to an inlet passage, is arranged in the axial upstream direction so that it is arranged on the rotor outside a region in which the steam flow enters the bladed flow path via the inlet passage. The relief groove, with regard to the first blade row, is arranged in a region in which the greatest thermal stresses can arise in the rotor. As an option, the relief groove has a cover for reducing vortex flows, and also devices for reducing heating of the groove or devices for active cooling. The steam turbine allows an increased number of risk-free running up and running down operations of the steam turbine with minimum detriment to the turbine performance.

Steam turbine with relief groove on the rotor

An axial turbine () has a plurality of expansion stages () each defined by stator blades () and rotor blades. The expansion stages () are followed by an exhaust diffuser () for collecting the flow passing through the expansion stages () and discharging it to the outside. The expansion stages () and/or the diffuser () have at least a non-axial symmetric portion. The stator blades () define different openings () along the circumference of the turbine.

Axial turbine and method for discharging a flow from an axial turbine

A steam turbine (), especially for the high-pressure range or intermediate-pressure range, includes a rotor () which is rotatably mounted around an axis and concentrically enclosed at a distance by an inner casing (), wherein between the rotor () and the inner casing () a flow passage () is formed, which on the inlet side is axially delimited by a balance piston () which is arranged on the rotor (), and into which flow passage rotor blades () and stator blades (), alternating in the direction of flow, radially project, and wherein, at the entry of the flow passage (), an inlet scroll (), through which steam is guided from the outside radially inwards and deflected in a deflection region () in the axial direction to the inlet of the flow passage (), is formed on the inner casing (). A reduction of the thermal loads and stresses is achieved by a stress-relief slot () in the deflection region () upstream of the first rotor blade row () for reducing stresses in the fastening slot () of the first rotor blade row () in the rotor (), and by a heat shield () arranged in the region of the stress-relief slot () for protecting the rotor () against high temperatures.

Steam turbine

An exemplary control stage of a steam turbine is disclosed, which includes plural staging valves circumferentially distributed around the turbine for regulating steam admission flow so as to control the loading of the turbine. Nozzle chambers are connected to a downstream end of each staging valve. An arc of admission forms the downstream portion of each nozzle chamber, and control stage nozzles in the arcs of admission define the downstream end of the nozzle chamber. Each nozzle chamber has at least two arcs of admission, each with a different circumferential dimension.

Multifrequency control stage for improved dampening of excitation factors

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Wuerenlingen, Switzerland

Thomas Mokulys