Alstom Technology Limited

Asea Brown Boveri Ag

Ansaldo Energia Switzerland Ag

General Electric Technology Gmbh

Ansaldo Energia IP UK Limited

Thomas Zierer

Carlos Simon-Delgado

Stefan Rofka

Adnan Eroglu

Herbert Brandl

Reinhard Fried

Hans-Peter Bossmann

Beat Von Arx

Joerg Krueckels

Sven Olmes

Shailendra Naik

Stephen Wilder Jorgensen

Burkhard Schulte-Werning

Martin Schnieder

Robert Marmilic

Gordon David Anderson

Ulrich Robert Steiger

Frank Graf

Sascha Justl

Joshua R McNally

Wilhelm Reiter

Christoph Didion

Marcel Koenig

Stefan Schlechtriem

Jost Braun

Cyrille Bricaud

Dieter Rebhan

Axel Heidecke

Marcos Escudero Olano

Oliver Joseph Taheny

Stephan Strueken

Rene Waelchli

Francesco Garbuglia

Tino-Martin Marling

Joerg Rinn

Isaac-Eliseo Gomez-Lor-Lopez

Afzal Pasha Mohammed

Stefan Biedermann

Cyrille Jerome Bricaud

Reiner Digele

Philippe Lott

Isaac Gomez- Lor- Lopez

Stephen W Jorgensen

A sealing arrangement at an interface between a combustor and a turbine of a gas turbine. The turbine can include deflecting vanes at its inlet, which deflecting vanes are each mounted within the turbine so as to define an inner or outer diameter platform and are in sealing engagement via an inner or outer diameter vane tooth with a seal arranged at the corresponding inner or outer diameter part of the outlet of the combustor. The seal is movable and is pressed on the inner or outer diameter vane tooth by a differential pressure such that the pressure of the mainstream hot gas flow is a lower pressure.

Sealing device arrangement at the interface between a combustor and a turbine of a gas turbine and gas turbine with such a sealing arrangement

A compressor assembly, and more in general relates to a compressor for a gas turbine providing a solution that teaches to locate within a cavity formed by the outer casing of the compressor and the inner vane carrier a separator element, or membrane, such to divide the cavity into two sub-cavities. This advantageously results in a more flexible design with respect to the positioning of the flange blow-off extractor and to the cavity sizing, as the flange position is not necessarily the boundary for the flow anymore as it would be without the separator element.

Compressor assembly for gas turbine

The disclosure pertains to a turbine with a gas turbine blade and a rotor heat shield for separating a space region through which hot working medium flows from a space region inside a rotor arrangement of the turbine. The rotor heat shield includes a platform which forms an axial heat shield section and which is arranged substantially parallel to the surface of a rotor and a radial heat shield section at the upstream end of the axial heat shield section, which is extending in a direction away from the surface of the axial heat shield section towards the hot gas. Further the turbine comprises a blade rear cavity which is delimited by the downstream end of the platform and/or the downstream end of the blade foot, the radial heat shield section. The disclosure further refers to a gas turbine blade and a rotor heat shield designed for such a turbine.

Turbine blade and turbine with improved sealing

A gas turbine includes a rotor concentrically surrounded by a casing, with an annular hot gas channel axially extending between the rotor and the casing. The rotor includes a plurality of blades arranged annularly on the rotor. Each of the blades is mounted with a root in a respective axial slot on a rim of the rotor radially extending with an airfoil into the hot gas channel and adjoining with an axially oriented root surface to an annular rim cavity. A cooling device is provided at the root of each blade to receive cooling air injected into the rim cavity through stationary injectors. An optimized cooling is achieved by providing an essentially plane root surface and the cooling device includes a scoop for capturing and redirecting at least part of the injected cooling air, which scoop is a recess with respect to the root surface.

Gas turbine and turbine blade for such a gas turbine

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

A method for axial thrust control of a gas turbine, and a gas turbine with a device for controlling axial thrust are provided. A gas turbine, with regard to aerodynamic forces and pressure forces, which exert an axial force upon the rotor, is configured such that at no-load and low partial load it has a negative thrust, and at high load it has a positive thrust. In order to ensure a resulting positive thrust upon the thrust bearing within the entire load range of the gas turbine, an additional thrust is applied in a controlled manner. The additional thrust for example can be controlled in dependence upon the gas turbine load. The resulting thrust force at full load is consequently less than in the case of a conventionally designed gas turbine without thrust balance.

Gas turbine with axial thrust balance

A gas turbine includes a compressor for compressing the combustion air, at least one combustion chamber, in which a fuel is burned while compressed combustion air is supplied, and at least one first turbine arranged downstream of the combustion chamber and in which the hot combustion gases from the combustion chamber are expanded to perform work. Part of the compressed combustion air is branched off, cooled in a cooling air cooler, brought to a lower cooling air pressure by a second turbine and supplied to the gas turbine for cooling purposes.

Gas turbine with heat exchanger for cooling compressed air and preheating a fuel

The invention describes a device for separating dust and dirt out of flowing media. A curved flow path () is imposed on the flow (), and heavy foreign bodies are separated out of the main flow by centrifugal force. The partial stream required to carry away the foreign bodies is aftertreated in a filter () and returned in purified form. Unlike with conventional filters, which have to process the entire flow of media, pressure losses during the separation of dust are minimized, and on the other hand no medium is lost for removing the dust load.

Device for separating dust and dirt out of flowing media

A turbomachine, in particular a gas turbine, is in the traditional manner provided with air cooling of the components that are subject to a high thermal stress. The cooling system (21, 31, 41) is provided with elements through which another medium (25, 35, 45), for example water or steam, can be added to the cooling system during peak demand. This medium displaces cooling air (26, 36, 46) from the cooling system, the air being then available additionally in a heat generator (2, 4). This means that more fuel (12, 13) can be added without increasing the hot gas temperature (T.sub.1, T.sub.3) at the turbine inlet (301, 501), and the power is increased. The quantity of the medium added to the cooling system is controlled by control elements (24, 34, 44) as a function of a control deviation (P.sub.set -P.sub.act) of the power.

Turbomachine and method of use

In a premix burner (18) having axial or radial air inflow, in which premix burner (18) the combustion air (15) flows out of a plenum (27), arranged before or around the burner (18), into the burner (18) and fuel (12, 13) is mixed with it on the way through the burner (18), a perforated component (24) having a wall thickness (s) and openings (25) of in each case a diameter (d) and at a distance (t) apart is arranged between the plenum (27) and the burner (18), which component (24) splits the combustion air (15) flowing through into small defined jets which reunite after a certain running length (l), the ratio of wall thickness (s) to the diameter (d) of the openings (25) being greater than/equal to one, and the ratio between the through-flow area of the component (24) and the possible inflow area to the burner (18) being greater than/equal to one as a function of the type of burner.

Premix burner having axial or radial air inflow

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Ennetbaden, Switzerland

Thomas Zierer