Alstom Technology Limited

Alstom (switzerland) Ltd

General Electric Technology Gmbh

Thomas Kramer

Markus Roland Wiebe

Markus Staubli

Juergen Gerhard Hoffmann

Andreas Kuenzler

Sergei Riazantsev

Sven Olmes

Armin Busekros

Ernst Pauli

Sergey Shchukin

Andreas Künzler

Holger Kiewel

Ulrich Waltke

Joerg Pross

Mohamed Yousef Nazmy

Jochem Fischer

Andrea De Simone

Jonas Fältström

An intake manifold is provided for inducting combustion air for a compressor of a gas turbine. The intake manifold includes a plurality of walls that delimit against the environment. Devices are provided for controllable change of the mechanical rigidity of the walls to reduce noise which is generated or is emitted in an air intake region during operation of the gas turbine. A gas turbine is also provided and includes an air intake to which air to be compressed is fed via an intake manifold. The intake manifold having a plurality of walls that delimit against the environment. Devices are provided to controllably change a mechanical rigidity of the walls to reduce noise which is generated or emitted in an air intake region during operation of the gas turbine.

Gas turbine air intake manifold controllably changing a mechnical rigidity of the walls of said intake manifold

A gas turbine engine includes a compressor with rotor blades having roots connected into seats of a compressor drum. The rotor blade roots and/or the compressor drum have longitudinal passages for a cooling fluid, connecting higher pressure areas to lower pressure areas of the gas turbine engine.

Gas turbine engine and method for cooling the compressor of a gas turbine engine

A rotor () of a gas turbine compressor comprises a multiplicity of welded-together rotor disks (), of which two or more rotor disks (), in a radially outer region (), are welded together, and, in a radially inner central region (), are abutment-joined together. Via the abutment-joining of two rotor disks (), a heat flow () radially outward from the center of the rotor () is achieved so that the material temperature of the rotor () can be kept below a predetermined level during operation. As a result, the service life of the rotor () can be increased. In one embodiment, one rotor disk (), on its surface, additionally has a recess () which can be cooled from outside. The rotor disks () according to the invention, which are welded and abutment-joined together, can especially be used at the last point in the flow direction of the compressor.

Welded rotor of a gas turbine engine compressor

A rotating machine (), in particular a compressor or turbine, has a rotor shaft () which is rotatable about an axis () and is provided with at least one slot (). The mechanical stresses in the region of the slot are reduced in that the at least one slot () has a slot bottom () with an elliptic cross-sectional contour ().

Rotating machine

A rotor shaft, particularly for a gas turbine, includes a cooling air supply disposed inside the rotor shaft and a plurality of cooling air ducts connected to the cooling air supply and extending essentially radially outward toward an outside of the shaft, wherein each of the cooling air ducts has an elliptic cross section.

Rotor shaft, in particular for a gas turbine

The invention relates to a hybrid blade () for thermal turbomachines, having an airfoil () made of a metallic material of a certain density, and having a blade root (). It is characterized in that the blade root (), compared with the airfoil (), is made of a different metallic material having a lower density, and in that the airfoil () is connected to the blade root () in a positive-locking manner. The blade in this case is advantageously a compressor blade, in particular a high-pressure compressor blade, in which the airfoil () is made of a stainless CrNi steel and the blade root () is made of a high-temperature titanium alloy or an intermetallic gamma titanium aluminide alloy or an intermetallic orthorhombic titanium aluminide alloy.

Hybrid blade for thermal turbomachines

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

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Ennetbaden, Switzerland

Thomas Kramer