Alstom Technology Limited

Asea Brown Boveri Ag

Asea Brown Boveri Inc.

Alstom

Alstom (switzerland) Ltd

Abb Management Ag

Aerobus International, Inc.

Ansaldo Energia Switzerland Ag

Abb Alstom Power (schweiz) Ag

Abb Alstom Power (switzerland) Ltd.

Ansaldo Energia IP UK Limited

Hans Wettstein

Hans Ulrich Frutschi

Timothy Albert Griffin

Bernhard Weigand

Hansulrich Frutschi

Andre O Pugin

Wilhelm Endres

Wilhelm Reiter

Claus Paul Gerdes

Per Aasheim

Mikael Fryklund

Harry Alkelin

Roland Nilsson

Wolfgang Kappis

Mohamed Youssef Nazmy

Jaan Hellat

Reinhard Fried

Ulrich Rathmann

Markus Staubli

Alexander Beeck

Jürgen Gerhard Hoffmann

Dieter Winkler

Eribert Benz

Majed Toqan

Jakob J Keller

Anton Nemet

Gianfranco Ludovico Guidati

Robin Charles Payne

Joachim Krautzig

Ben C Lamoreaux

Manfred Wirsum

Ulrich Waltke

Konrad Vogeler

Pavel Rihak

Hans Peter Knöpfel

Kurt Kugeler

Anders Lindvall

Alfred Hausermann

Herbert Fuchs

Fritz Schaub

Conor Fitzsimons

Mohamed Yousef Nazmy

Steffen Schulz

Per Th&ouml;rnblad

Per Thornblad

Ferdinand Thueringer

Ren&eacute; Bachofner

Jürgen Hoffmann

Hans Peter KNÖPFEL

A method for operating a gas turbine power plant, and a gas turbine power plant in which fresh air is delivered to a compressor inlet and is accelerated in the compressor inlet and a recirculated first exhaust gas substream is delivered into a region of the compressor inlet in which the fresh air is accelerated to an extent such that the difference between total pressure and static pressure in the fresh air is greater than or equal to a pressure difference which is required in order to suck a target mass flow of the recirculated first exhaust gas substream into the compressor inlet.

Gas turbine power plant with exhaust gas recirculation

A method is provided for COseparation from a combined-cycle power plant with exhaust-gas recirculation and COseparation. The hot-gas flow is split into a recirculation flow and an exhaust-gas flow before the final turbine stage in the turbine. A first partial flow remains in the turbine and carries out expansion work in the conventional form, before its waste heat is dissipated, for example in a waste-heat boiler, and the gases are recirculated into the inlet flow of the gas turbine. A second partial flow is diverted before the final turbine stage, and emits its waste heat in an HRSG/heat exchanger, before COis separated from the exhaust-gas flow at an increased pressure level.

Gas turbine with flow separation and recirculation

A method is provided for operating a gas turbine plant, in which compressed air is extracted from a compressor and for cooling is directed in an internal cooling passage through thermally loaded components to the combustion chamber and/or to the turbine, then re-cooled, and added to the compressor main flow in the compressor. At least a portion of the recirculated air is supersaturated, or partially saturated, with drops of water during or before recirculation into the compressor and a cooling mist is created. A gas turbine plant is provided with a closed cooling circuit which, for implementing the method, includes an injection arrangement for introducing water into the recirculated cooling air.

Method for cooling a gas turbine plant and gas turbine plant for implementing the method

A gas turbine generator set includes a compressor unit including at least one compressor, at least one generator and at least one combustion chamber. Exhaust gases from at least one turbine are recirculated for a further thermal utilization. At least one cooling fluid compressor is configured to compress a cooling fluid including at least one of fresh air and a portion of the recirculated exhaust gases for a cooling of thermally loaded parts.

Gas turbine generator set

A gas turbine plant is provided with exhaust gas recirculation and includes a main gas turbine having a main compressor and main turbine driving a main generator, and a combustion chamber, with an outlet connected to the inlet of the main gas turbine, has a fuel feed, and via the recuperator's high-pressure side obtains combustion air from the main gas turbine's compressor outlet. The outlet of the main turbine and the inlet of the main compressor are connected via the recuperator's low-pressure side and a cooler for exhaust gas recirculation. On the recuperator's low-pressure side, a charging unit, with a compressor and a turbine is arranged, and draws in air via an air intake and by the outlet of its compressor is connected to the recuperator's low-pressure side outlet and by the inlet of its turbine is connected to a surplus-gas extraction line on the recuperator's low-pressure side.

Gas turbine plant with exhaust gas recirculation and also method for operating such a plant

A gas turbine installation (), in particular in a power plant for generating electricity, includes a turboset () having a turbine (), a compressor () and a combustion chamber () arranged in a gas path () connecting the compressor () to the turbine (), and a flue gas recirculation device (), which passes combustion flue gas from the turbine () from a flue gas path () connected to the turbine () via a recirculation path () to a fresh gas path () connected to the compressor (). To improve the efficiency of the gas turbine installation (), a control device () controls a volumetric flow and/or a temperature of the recirculated combustion flue gases in such a way that a fresh gas/flue gas mixture which enters the compressor () is at a predetermined desired temperature.

Gas turbine installation

A turbine blade or vane () has a shell (), including a first side wall () and a second side wall (), which are connected together at a leading edge () and at a trailing edge (), which extend longitudinally from a root () to a tip () and which are connected together between leading edge () and trailing edge () by a plurality of inner ribs (). In the inner region () of the turbine blade/vane (), the ribs () form at least one cooling gas path (), which guides a cooling gas flow from the root () to the tip () and, in the process, is deflected a plurality of times in serpentine shape from the outside to the inside and from the inside to the outside. In order to increase the life of the turbine blade/vane (), at least one bypass opening () and/or at least one outlet opening () are arranged in the region of at least one rib (), which deflects the cooling gas flow from the outside to the inside, the bypass opening () penetrating the rib () at the shell () and the outlet opening () penetrating the shell ().

Cooled turbine blade or vane

A gas turbine system comprises a compressor that takes in suction air on the inlet side and compresses it to compressor end air that is available on the outlet side, a combustor in which a fuel is burned by using the compressor end air while resulting in the formation of hot gas, as well as a turbine in which the hot gas is expanded while providing work output. In a method for cooling this gas turbine system, compressed air is removed from the compressor, is fed as cooling air for cooling inside an internal cooling channel through thermally loaded components of the combustor and/or the turbine, is then compressed and added to the compressor end air. An improved cooling without disadvantage for the efficiency of the system is achieved in that, in the manner of a targeted leakage, a small part of the cooling air is fed for film cooling into the turbine stream through drilled film cooling openings provided on the components.

Method for cooling a gas turbine system and a gas turbine system for performing this method

In a method for operating a power plant by means of a COprocess, isentropic compression first takes place, subsequently an isobaric heat supply, then isentropic expansion, and finally isobaric heat discharge. The COprocess broken down here takes place with internal combustion, a fuel () and the oxygen () necessary for oxidization being supplied. After the charging of the COcircuit () has been carried out, the excess COformed from combustion is discharged continuously, in that this gas is led through a cooler (), in which said gas is condensed. In order to dispose of this condensed CO(), there are available here, for example, the possibilities of storing this COon the ocean floor or of introducing the condensed COinto a worked-out deposit of natural gas.

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The invention relates to an axial-flow thermal turbomachine having a metallic rotor (), in which rotor blades () made of an intermetallic compound are mounted in a circumferential groove to form a row of blades. The invention is characterized in that at least two rotor blades (') which are at a uniform distance from one another and are made of a more ductile material are arranged in the said row of blades between the intermetallic rotor blades (), the rotor blades (&#x2032;) made of the more ductile material either being considerably longer than the intermetallic blades () or, if they are of the same length, having a different blade tip shape than the intermetallic blades ().

Axial-flow thermal turbomachine

The invention relates to an axial-flow thermal turbomachine, having a rotor () made from a metallic material with a first density (D), in which rotor blades (') and intermediate pieces () are mounted alternately in a circumferential groove. It is characterized in that said intermediate pieces () consist of a material with a second density (D), which is lower than the first density (D). Particularly suitable materials for the intermediate pieces () are intermetallic compounds, preferably intermetallic &#x3b3;-titanium aluminide alloys or intermetallic orthorhombic titanium aluminide alloys, but also titanium alloys.

In a method for the operation of a power plant with a closed or quasi-closed cycle, the power plant substantially comprises at least one compressor unit () or a pump, at least one combustion chamber (), at least one turbine () and at least one heat sink (). In the combustion chamber (), a fuel mass flow () reacts with at least one oxygen flow (), the excess combustion products which are formed as a result (CO, HO) are removed from the cycle at a suitable location (), and the oxygen stream () fed to the combustion chamber is obtained by means of an air fractionation installation (). Means () for coarse fractionation of the supplied air () are connected upstream of the air fractionation installation () in order to supply oxygen-enriched air () to the air fractionation installation ().

Method for the operation of a power plant

A rotor ( ) for a turbomachine, comprising at least one first, preferably disk-like rotor section ( ), which is exposed to high operating temperatures and consists of a particularly creep-resistant material, in particular a nickel-based alloy, and at least one second, preferably disk-like rotor section ( ), which is exposed to lower operating temperatures and consists of a less creep-resistant material, in particular steel, the first and second rotor sections ( ) being joined to one another by welding. In a rotor of this type, a crack-free welded joint is achieved by the fact that, to join the two rotor sections ( ), a transition region ( ) is arranged between the two rotor sections ( ), which transition region is produced by powder metallurgy, is welded to one of the two rotor sections ( ) at least on one side, and on this side has the same composition as the rotor section to which it is welded.

Rotor for a turbomachine, and process for producing a rotor of this type

Described is a fixation device for blading of a turbo-machine, in which, longitudinally to a mounting groove ( ), a plurality of blades ( ) is positioned, and in which, between at least two blades ( ) positioned adjacent to each other inside the mounting groove ( ), a mounting gap is provided, having two insertion elements constructed as collar halves ( ) that can be inserted into the mounting gap, and each of which has a width adapted to the width of the mounting gap and which enclose between themselves a gap space ( ) into which a wedge element ( ) can be inserted that can be wedged in such a way that both collar halves ( ) are fixed in a force-derived manner by means of the wedge element ( ) inside the mounting groove ( ). The invention is characterized in that the wedge element ( ) is provided with at least one connecting element ( ) towards the side of a blade ( ) and that at least one of the two blades ( ) adjoining the wedge element ( ) is provided with a counter-contour ( ) corresponding to the connecting element ( ), so that the wedge element ( ) and the blade enter ( ) into an intimate shape-mated connection with each other.

Fixation device for blading of a turbo-machine

An improved cableway system for providing a track over which a vehicle traverses is disclosed. The improved system includes a catenary cable system and a pair of track cable systems. The track cable systems are hung from the catenary cable system and support tracks over which a vehicle traverses. A plurality of hangers is employed to suspend the track cable systems from the catenary cable system. A plurality of pylons support the catenary and track cable systems. A pylon includes a base pylon, a lower saddle, and an upper saddle. The lower saddle is pivotally mounted to the base pylon and supports the track cable systems. Preferred embodiments of the lower saddle include apparatuses that dampen the application of loads to the pylon by the vehicle traversing the system. The upper saddle is supported by the base pylon and supports the catenary cable system while providing for deflection of the catenary cable system in response to forces applied to the cableway system. A preferred embodiment of the cableway system includes a force equalizing assembly for joining the catenary cable system to the track cable system at points between support pylons to equalize the tension in the cables among the various cables.

Elevated cableway system

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Fislisbach, Switzerland

Hans Wettstein