Alstom Technology Limited

Ansaldo Energia Switzerland Ag

Ansaldo Energia IP UK Limited

Klaus Doebbeling

Christian Oliver Paschereit

Jaan Hellat

Eribert Benz

Felix Guethe

Frank Graf

Torsten Wind

Andreas Rueter

Dieter Winkler

Ewald Freitag

Bettina Paikert

Stefan Rofka

Martin Zajadatz

Hanspeter Zinn

Anton Nemet

Hans Peter Knoepfel

Carlos Jimenez Haertel

Joachim Krautzig

Ken-Yves Haffner

Hans-Erik Hansson

Christopher Michael Robson

Martin Nicklas

Rene Waelchli

Michael Hoevel

Rolf Rüetschi

Massimo Giusti

Christof Pfeiffer

An exemplary gas turbine power plant includes a gas turbine with a compressor having a compressor inlet. A combustion chamber follows the compressor and a turbine follows the combustion chamber. A cross section of the compressor inlet includes an inner sector and an outer sector in relation to the axis of rotation of the compressor. A plurality of feed ducts introduces oxygen-reduced gas into the inner sector of the compressor inlet. The plurality of feed ducts is arranged in the compressor inlet so as to be distributed in a circumferential direction on a circle concentrically with respect to the axis of the gas turbine.

Method of operating a gas turbine power plant with exhaust gas recirculation and corresponding gas turbine power plant

The invention provides a new path of combustion technology for gas turbine operation with multifuel capability, low emissions of NOand CO and high thermal efficiency. Further to the present invention providing a method for operating a combustor for a gas turbine and a combustor for a gas turbine are disclosed. The combustor includes a first combustion chamber with a wide operating range, a subsequent deflection unit for deflecting the hot gas flow of the first combustion chamber at least in circumferential direction and components for injecting and mixing additional air and/or fuel, and a sequential combustion chamber with a short residence time, where the temperature of the hot gases reaches its maximum.

Combustor for a sequential gas turbine having a deflection unit between first and second combustion chambers

The invention relates to a method of operating a gas turbine assembly, which includes a compressor, a combustor and a gas turbine. The method includes operating the gas turbine assembly at a partial load with respect to a base load of the gas turbine assembly; bypassing a portion of blow-off air from the compressor; and introducing the portion of blow-off air into an exhaust gas duct after the gas turbine. The gas turbine assembly, when operating at partial load, can maintain the air-to-fuel ratio approximately constant and hence to control the combustion flame temperature at a level where emissions are kept below the permission limit.

Method of operating a gas turbine assembly and the gas turbine assembly

The present invention relates to a method of decelerating a turbine rotor of a turbine engine. At least one electric motor is engaged with the turbine rotor. A braking system, preferably the starting system, is engaged with the at least one electric motor, preferably the generator of the turbine engine, so as to use the at least one electric motor to apply a negative (braking) torque on the turbine rotor. The method includes after flame off, the braking system being used for dissipating kinetic energy available in the turbine engine after flame off by means of the at least one electric motor.

Method of operating a turbine engine after flame off

The invention relates to a method for operating a gas turbine, in which an oxygen-reduced gas and fresh air are delivered to a compressor of the gas turbine in a radially staged manner, the fresh air being delivered via an outer sector of the inlet cross section in relation to the axis of rotation of the compressor, and the oxygen-reduced gas being delivered via an inner sector of the inlet cross section in relation to the axis of rotation of the compressor. The invention relates, further, to a gas turbine power plant with a gas turbine having a compressor inlet which is followed by the flow duct of the compressor and which is divided into an inner sector and an outer sector, a feed for an oxygen-reduced gas being connected to the inner sector of the compressor inlet, and a fresh air feed being connected to the outer sector of the compressor inlet.

A method and apparatus for the operation of a gas turbine unit with an evaporative intake air cooling system in the intake air pathway, wherein the return water flow of the evaporative intake air cooling system is used for the cooling of components of the gas turbine unit and/or of a generator coupled to the gas turbine unit and/or of another element coupled to the gas turbine unit, and a gas turbine unit adapted to be operated using this method.

Using return water of an evaporative intake air cooling system for cooling a component of a gas turbine

With a method for controlling a gas turbine in a power plant, a multiplicity of operating lines for the gas turbine for different gas turbine inlet temperatures TIT or gas turbine exhaust temperatures TAT and positions of the compressor inlet guide vane cascade VIGV are specified as a function of the load. For minimizing the electricity production costs during operation switching can be optionally carried out between different operating lines during constant or varying power output of the power plant.

Method for controlling a gas turbine in a power plant and power plant for carrying out the method

A rotor of a thermally loaded turbomachine, in particular of a compressor or a gas turbine, is mounted such that it can rotate about a rotor axis and is concentrically surrounded by a hot-gas duct or cooling-air duct. A significant improvement to the ability of the rotor to withstand thermal loads is achieved, with little increased outlay in terms of materials, by virtue of the fact that the rotor comprises a rotor core made of a first material, that the rotor core is concentrically surrounded by shielding rings made of a second material, which shield the rotor core from the temperature in the hot-gas duct or cooling-air duct, the second material having a higher heat resistance than the first material, and that the shielding rings are cohesively joined to the rotor core.

Rotor with core surrounded by shielding rings

Relevant fuel-gas properties (X) are measured on an ongoing basis while a gas turbine group is operating. The Calkane content of the fuel gas is of particular interest in this context, since it has a significant influence on the ignitability of the fuel gas in the combustion chamber. The operating parameters of the gas turbine group are acted on directly as a function of the measured fuel-gas properties. In particular, in the case of the example of a gas turbine group with sequential combustion, the distribution of the fuel mass flows ({dot over (m)}, {dot over (m)}) between the combustion chambers () of the gas turbine group is varied. Furthermore, if there is provision for inert media, such as water or steam, to be introduced, it is possible for the mass flow of inert media ({dot over (m)}) to be controlled as a function of the measured fuel properties.

Method for operating a turbine group

In a method of operating a compressor, a gaseous medium is compressed in a first compressor stage. The partially compressed medium is sent from the first compressor stage into an intermediate cooler where it is cooled before being directed into the second compressor stage where it is compressed further. A liquid medium is sprayed into the gaseous medium in the intermediate cooler so that a two-phase mixture with a liquid phase and a gaseous phase is formed in the intermediate cooler. The liquid phase is separated again before adding it to the second compressor stage.

Method for operating a compressor

The invention relates to a method of operating a gas turbine installation ( ), compressed fresh air ( ) is branched off after a compressor ( ) and supplied to an evaporator device ( ), in the evaporator device ( ) feed water ( ) is evaporated, while heat is supplied, and is mixed with the fresh air ( ) in order to generate a steam/air mixture ( ), the steam/air mixture ( ) is fed back upstream of a gas turbine ( ), the heat required for the evaporation of the feed water ( ) is at least partially extracted from an exhaust gas ( ) of the gas turbine ( ). In order to improve the efficiency of the gas turbine installation ( ), the feed water ( ) runs down along a wall arrangement ( ) heated by the exhaust gas ( ) and is subjected to the fresh air ( ). The feed water ( ) evaporates and mixes with the fresh air ( ), by which means the steam/air mixture ( ) forms for the recirculation.

Gas turbine installation and an associated operating method

A process is described for the operation of an annular combustion chamber and also an annular combustion chamber is shown with numerous circularly arranged premix burners, in which a fuel-air mixture is produced before it is ignited and the fuel-air mixture is used as a hot gas stream to drive at least one turbine stage of a gas turbine plant. At least one premix burner is operated such that it has a spatial mixing profile deviating within the fuel-air mixture from all other premix burners.

Process for the operation of an annular combustion chamber, and annular combustion chamber

In a premixing burner ( ) for a gas turbine or hot-gas generation for the combustion of liquid or gaseous fuel, in which fuel is mixed with combustion air ( ) in a burner interior ( ), is fed to a combustion chamber ( ) and is burnt in this combustion chamber ( ), stabilization in the part-load model is achieved in a simple and efficient way in that means ( ) are provided which make it possible to recirculate hot exhaust gas ( ) out of the combustion chamber ( ) into the burner interior ( ) and to stabilize the flame by means of selfignition processes. The means ( ) are preferably a recirculation line which picks up hot exhaust gas ( ) from the outer backflow zone ( ) and feeds it to the burner interior ( ) in the region of a burner tip ( ) facing away from the combustion chamber ( ), additional fuel (pilot fuel ) being admixed with the exhaust gas ( ) in the recirculation line upstream of the feed to the burner interior ( ).

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Windisch, Switzerland

Klaus Doebbeling