Alstom Technology Limited

General Electric Technology Gmbh

Ansaldo Energia IP UK Limited

Tanguy Arzel

Martin Schnieder

Thomas Heinz-Schwarzmaier

Jörg Krückels

Volker Eppler

Martin Schneider

Jose Anguisola Mcfeat

A gas turbine is provided that includes a rotor which is rotatable around an axis and equipped with rotor blades, and which is concentrically enclosed at a distance by a casing, which is equipped with stator blades, forming an annular hot gas passage. Rings with stator blades and rotor blades are arranged in a manner alternating in the axial direction. Between adjacent stator blades, heat shield segments are arranged, which delimit the hot gas passage on the outside in a region of the rotor blades and are cooled by impingement cooling where a cooling medium from an outer annular cavity flows into the heat shield segment.

Shroud seal segments arrangement in a gas turbine

A continuous-flow machine (), in particular a turbine or a compressor, includes at least one stator blade section () which has a plurality of stator blades () which project into a gas path () of a working gas, and at least one adjacent section (), which has a plurality of adjacent elements (), which bound the working gas path () at the side. A gap (), through which a cooling gas can be introduced into the working gas path (), is formed between the stator blades () of the stator blade section () and the adjacent elements () of the adjacent section (). In order to improve the efficiency of the continuous-flow machine (), lateral seals () are formed in the gap () and prevent or at least impede pressure equalization and/or a gas flow in the gap () in the lateral direction ().

Continuous-flow machine, turbine, or compressor

Growing community of inventors

Ennetbaden, Switzerland

Tanguy Arzel