Alstom Technology Limited

Ansaldo Energia Switzerland Ag

Bbc Brown, Boveri & Company, Limited

Alstom (switzerland) Ltd

Asea Brown Boveri Ag

General Electric Technology Gmbh

Bbc Brown Boveri Ag

Crosstown H2r Ag

Jaan Hellat

Adnan Eroglu

Eribert Benz

Felix Guethe

Jakob J Keller

Bruno Schuermans

Mirko Ruben Bothien

Peter Flohr

Stefan Tschirren

Frank Reiss

Pirmin Schiessel

Urs Benz

Christian Oliver Paschereit

Franz Joos

Klaus Doebbeling

Frank Graf

Peter Stuber

Torsten Wind

Andre Burdet

Timothy Albert Griffin

Hans Wettstein

Jürgen Gerhard Hoffmann

Douglas Pennell

Jakob Keller

Ewald Freitag

Stefan Rofka

Roger Suter

Rolf Dittmann

Nicolas Noiray

Marcel Stalder

Franklin Marie Genin

Robert Marmilic

Andreas Huber

Robin Charles Payne

Frank Sander

Robin McMillan

Luis Tay Wo Chong Hilares

Philipp Brunner

Ennio Pasqualotto

Michael Duesing

Jan Cerny

Oliver Riccius

Marta De La Cruz Garcia

Felix Güthe

Richard Smith

Michael Hoevel

Graham Webb

Detlef Viereck

Guenter Sybon

Sriwickrama Prithiviraj Harasgama

Ola Claesson

Werner Kessler

Wilfried Strittmatter

Thierry Lachaux

Douglas Anthony Pennell

Wolfgang Dieter Kappis

Khawar Syed

Franklin Marie Georges Martin Genin

Michael Hövel

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 relates to a gas turbine assembly which substantially includes at least one compressor, at least one first burner, at least one second burner that is connected downstream of the first burner, and at least one turbine that is connected downstream of the second burner. At least the first and second burner form a component of a tubular or quasi-tubular combustion chamber element in the flow direction of the combustion path of the burners. The combustion chamber element being closed or quasi-closed and extending between the compressor and the turbine. The combustion chamber elements are arranged around the rotor of the gas turbine assembly in the shape of a ring.

Gas turbine assembly and corresponding operating method

The invention concerns a damper arrangement for reducing combustion-chamber pulsation arising inside a gas turbine, wherein the gas turbine includes at least one compressor, a primary combustor which is connected downstream to the compressor, and the hot gases of the primary combustor are admitted at least to an intermediate turbine or directly or indirectly to a secondary combustor. The hot gases of the secondary combustor are admitted to a further turbine or directly or indirectly to an energy recovery, wherein at least one combustor is arranged in a can-architecture. At least one combustor liner includes air passages, wherein at least one of the air passages is formed as a damper neck. The damper neck being actively connected to a damper volume, and the damper volume is part of a connecting duct extending between a compressor air plenum and the combustor.

Damper arrangement for reducing combustion-chamber pulsation

The damper arrangement includes a plurality of interconnected volumes and a plurality of necks for connecting the damper to a combustion chamber at a plurality of contact points. The plurality of necks are connected to the plurality of volumes.

Simultaneous broadband damping at multiple locations in a combustion chamber

The invention refers to a sequential combustor arrangement including a first burner, a first combustion chamber, a mixer for admixing a dilution gas to the hot gases leaving the first combustion chamber during operation, a second burner, and a second combustion chamber arranged sequentially in a fluid flow connection. The mixer includes a plurality of injection pipes pointing inwards from the side walls of the mixer for admixing the dilution gas to cool the hot flue gases leaving the first combustion chamber with a low pressure drop. The disclosure further refers to a method for operating a gas turbine with such a combustor arrangement.

Sequential combustion with dilution gas mixer

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

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.

An exemplary method for the operation of a CCPP with flue gas recirculation to reduce NOx emissions and/or to increase the CO2 concentration in the flue gases to facilitate CO2 capture from the flue gases as well as a plant designed to operate is disclosed. To allow a high flue gas recirculation ration (rFRG) an imposed combustion inhomogeneity ratio (ri) is used for flame stabilization. The imposed combustion inhomogeneity ratio (ri) is controlled as function of the flue gas recirculation rate (rFRG) and/or combustion pressure. Oxygen or oxygen enriched air to the gas turbine inlet gases or to the combustor is admixed to enhance operatability.

Combined cycle power plant with flue gas recirculation

The invention relates to a premix burner of the multi-cone type for a gas turbine that includes a plurality of shells which are arranged around a central burner axis and are parts of a virtual, axially extending common cone, which opens in a downstream direction, whereby said parts are displaced perpendicular to said burner axis such that a tangential slot is defined between each pair of adjacent shells. The flame front of such a burner is stabilized by providing a virtual common cone with a cone angle, which varies in axial direction.

Premix burner of the multi-cone type for a gas turbine

A method is disclosed for operating a gas turbine power plant having a gas turbine, a heat recovery steam generator and an flue gas splitter which splits flue gases into a first flue gas flow for recirculation into an inlet flow of the gas turbine and into a second flue gas flow for discharge to an environment. An oxygen-depleted gas can be used in an open cooling system for cooling hot gas parts of the gas turbine. A split compressor intake can be provided for separate feed of recirculated flue gas and fresh air into a compressor intake. Compressor blades can include a separating band which blocks intermixing of recirculated flue gas and fresh air during compression.

Gas turbine power plant with flue gas recirculation and oxygen-depleted cooling gas

An exemplary system method for the operation of a CCPP with flue gas recirculation to reduce NOx emissions and/or to increase the CO2 concentration in the flue gases to facilitate CO2 capture from the flue gases is disclosed. The flue gas recirculation rate (rFRG) is controlled as function of the combustion pressure and/or the hot gas temperature. Operability is enhanced by admixing of oxygen or oxygen enriched air to the gas turbine inlet gases or to the combustion.

In method for operating a gas turbine (), the compressed air is fed to a combustor () for the combustion of a coal syngas, and the resulting hot gases are expanded in a subsequent turbine (). Some of the compressed air is separated into oxygen and nitrogen, and the oxygen is used for producing the syngas. In a first combustor, () syngas is combusted and the resulting hot gases are expanded in a first turbine (), and in a second combustor syngas is combusted, using the gases which issue from the first turbine (), and the resulting hot gases are expanded in the second turbine (). The two combustors () are operated with undiluted syngas, and the first combustor flame temperature (T) is lowered compared with the operation with natural gas (T), while the second combustor () is operated in the normal operation (T) for natural gas.

Method for operating a gas turbine

In a method for adjusting a Helmholtz resonator (), in which a resonator volume () is connected to a space () to be provided with damping along an axis () via a constriction () having an acoustic impedance, the acoustic impedance of the constriction () is altered in order to adjust the Helmholtz resonator ().

Method for adjusting a Helmholtz resonator and an adjustable Helmholtz resonator

A burner () for a combustion chamber of a turbogroup includes a swirl generator (), a mixer (), and a lance () for introducing pilot fuel into a combustion space (). In order to stabilize combustion, the lance () is designed and/or arranged so that, at least in the pilot mode of the burner (), it extends far enough into the burner interior () for a flame front () of a combustion reaction, which takes place in the combustion space (), to extend at least partially into the burner interior ().

Burner fuel lance configuration and method of use

In a method for operating a gas turbine (GT) with sequential combustion, which has at least one compressor (), a first combustion chamber () with a first turbine () which is connected downstream, and a second combustion chamber () with a second turbine () which is connected downstream, the at least one compressor () draws in air and compresses it. The compressed air is fed to the first combustion chamber () for combusting a first fuel, and the gas which issues from the first turbine () is fed to the second combustion chamber () for combusting a second fuel. Increased flexibility and safety in operation is achieved by different fuels being used as first and second fuel.

Method for operating a gas turbine, method of operation of a combined cycle power plant, and combined cycle power plant

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Baden-Rütihof, Switzerland

Jaan Hellat