Alstom Technology Limited

Alstom (switzerland) Ltd

Joerg Pross

Jonas Hurter

Thomas Kramer

Valter Bellucci

Ulrich Waltke

Armin Heger

Joern-Axel Glahn

Combustion driven pressure pulsations may limit the range of operating conditions where a modern gas turbine can operate with low emission and high efficiency performance. The control of acoustic vibrations has been consequently growing as an essential issue in gas turbine design, development and maintenance. The basic idea of the present invention is to use cooling air leakage through the gaps () of combustor liner segments () to get acoustic damping of combustion pulsations. The main component of the design is the sealing device () which covers the gap () between the two liner segments () and (). The sealing device () collects in the plenum () some of the cooling air () flowing between the outer casing () and the inner liner structure (). For this purpose the sealing device () is provided with openings () along the side walls () which allow the cooling air () to enter the plenum (). In the plenum () the cooling air () is distributed along the gap () and discharged through openings (), distributed along the top side () of the sealing device (). The jets () discharged through the openings () achieve the additional effect to dampen acoustic pulsations in the combustion chamber ().

Device for efficient usage of cooling air for acoustic damping of combustion chamber pulsations

A rotor for a gas turbine is disclosed. The rotor has a plurality of rotor disks arranged one behind the other on a rotor axis. The rotor extends between a compressor part and a turbine part, and has a central bore running between the compressor part and the turbine part. Fluid passages are arranged to conduct cooling air from the compressor part and direct cooling through the central bore and direct cooling air from the turbine part radially outward through the rotor. The rotor disks have fluid cavities that are connected to the central bore by having an outer diameter that is greater than the inside diameter of the central bore. The fluid cavities are subdivided into individual chambers by a plurality of radial ribs.

Rotor for a gas turbine

Between the rotor and stator of an axial turbo machine, sealing strips of a labyrinth seal that are mortised into sealing strip grooves are provided. Between the sealing strips relief grooves are provided in such a way that the axial stiffness of the rotor or stator is essentially steady. This may be achieved by one or more flat relief grooves, a corrugated surface, or by filling the relief grooves entirely or partially with a suitable, elastic material so that a more even axial tension distribution is achieved between the sealing strip grooves and relief grooves along the rotor or stator section.

Labyrinth seal for rotating shaft

Growing community of inventors

Albbruck, Germany

Joerg Pross