Alstom Technology Limited

Ansaldo Energia Switzerland Ag

Ansaldo Energia IP UK Limited

General Electric Technology Gmbh

Axel Heidecke

Carlos Simon-Delgado

Ulrich Robert Steiger

Robert Marmilic

Thomas Zierer

Sven Olmes

Sascha Justl

Cyrille Bricaud

A method and a cooling system for cooling blades of at least one blade row in a rotary flow machine includes an axial flow channel which is radially limited on the inside by a rotor unit and at the outside by at least one stationary component, the blades are arranged at the rotary unit and provide a shrouded blade tip facing radially to said stationary component. Pressurized cooling air is fed through from radially outside towards the tip of each of said blades in the at least one blade row, and the pressurized cooling air enters the blades through at least one opening at the shrouded blades' tip.

Method and cooling system for cooling blades of at least one blade row in a rotary flow machine

A labyrinth seal is provided for sealing the annular interspace between the rotor and the stator of a steam turbine or gas turbine. The labyrinth seal includes a multiplicity of sealing strips which are arranged in series in the axial direction and fastened on the stator and project into the interspace. The sealing strips interact, with sealing effect, with rotor-side sealing elements which are arranged in a staggered manner. An improved sealing effect is achieved by the sealing strips in the cold installed state being offset in relation to a symmetrical position, wherein the offset has the reverse direction and the same amount as the distance by which the sealing strip is displaced relative to adjacent rotor-side sealing elements as a result of thermal expansions of the stationary and rotating components and support structure when being heated from the cold installed state to a hot steady-state operating condition.

Labyrinth seal

A gas turbine () includes a combustion chamber () followed by a stator airfoil row () defining a plurality of guide vanes and separated by the combustion chamber () by a first gap (), and a rotor airfoil row () separated by the stator airfoil row () by a second gap (). The stator airfoils () of the stator airfoil row () are connected to guide vane boxes () collecting a cooling fluid (A) and injecting it through nozzles () in the second gap () to make it to enter rotor airfoil inlets (). The guide vane boxes () are provided with passages () connecting a zone () upstream of the guide vane boxes () to a zone () of the second gap () downstream of the guide vane boxes (). Moreover, the mouths () of the passages () facing the rotor airfoil row () are closer to a hot gases path than the nozzles ().

Gas turbine

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Wettingen, Switzerland

Axel Heidecke