Alstom Technology Limited

General Electric Technology Gmbh

General Electric Company

Ansaldo Energia Switzerland Ag

Ansaldo Energia IP UK Limited

Stefano Bernero

Martin Erwin Gassner

Adnan Eroglu

Christian Oliver Paschereit

Richard Carroni

Christian Steinbach

Ewald Freitag

Martin Zajadatz

Peter Stuber

Weiqun Geng

Bruno Schuermans

Madhavan Narasimhan Poyyapakkam

Peter Flohr

Ken Yves Haffner

Fernando Biagioli

Bettina Paikert

Felix Guethe

Franklin Marie Genin

Khawar Syed

Frank Graf

Klaus Knapp

John Martin Nilsson

Mengbin Zhang

Gijsbertus Oomens

Xiao-Yi Zhang

Ennio Pasqualotto

Marcel Rieker

Sebastian Lipari

Tobias Spitzmueller

Dirk Therkorn, Sr

Mauricio Ernesto Garay

Thierry Lachaux

Michael Kenyon

Tobias Spitzmüller

Marco Alexander Weingaertner

Benjamin Meyer

Mariah Couzzi Carneiro

Manuel Ramirez-Espana-Mejia

Andreas Jan Schesny

Vincent Georges Christian Daniel Lonneux

Paula Beneyto Satorres

Ronghai Mao

Tom Strebel

Christian Jörg Motz

Martin Gassner

Vincent Lonneux

Dirk Therkorn

A method for operating a gas turbine system includes utilizing a gas turbine controller to determine a schedule for a firing temperature for operative burners of a second combustor located downstream of a first combustor when the gas turbine system is operating in a low part load mode. During the low part load mode, multiple burners for the second combustor are switched-off. Further, the schedule is determined based on a position of inlet guide vanes of a compressor of the gas turbine system located upstream of both the first and second combustors. The method also includes controlling the firing temperature of the operative burners utilizing the schedule during the low part load mode to keep the gas turbine system within relevant operational limits of the gas turbine system.

Method and system for controlling a sequential gas turbine engine

A method is disclosed for operating a gas turbine having a compressor, a combustor, a turbine downstream of the combustor, and a total number of turbine outlet temperature measurements. The method includes locally measuring the turbine outlet temperature of the turbine with the turbine outlet temperature measurements of the respective turbine, and averaging measured temperatures of the selected turbine outlet temperature measurements to obtain an average turbine outlet temperature. The gas turbine operation is controlled depending on the determined average turbine outlet temperature.

Method for controlling the operation of a gas turbine with an averaged turbine outlet temperature

A system for regulating condensation of a flue gas in a steam generator is provided. The system includes a temperature controller and a flue gas analyzer. The temperature controller is configured to control a temperature of a component of the steam generator, the component being in heating-contact with the flue gas. The flue gas analyzer is configured to communicate with the temperature controller and to obtain a measurement of an amount of an acid-forming compound in the flue gas. The temperature controller adjusts the temperature of the component based at least in part on the measurement such that the temperature of the component is above an acid dew point of the flue gas when the component is in heating-contact with the flue gas.

System and method for regulating condensation of flue gas in a steam generator

A method for controlling emissions from a power plant having an ammonia injection grid that includes a plurality of ammonia injection points includes the steps of injecting ammonia into a flow of exhaust gas at an injection location, the injection of ammonia defining a spatial distribution of ammonia across an exhaust gas flowpath, measuring at least one parameter of the exhaust gas downstream from the injection location, comparing a measured value for the at least one parameter of the exhaust gas to a threshold value for the at least one parameter and, if the measured value for the at least one parameter exceeds the threshold value for the at least one parameter, automatically modifying the spatial distribution of ammonia injection across the exhaust gas flowpath.

System and method for improving the performance of a selective catalyst reduction system in a heat recovery steam generator

A heat recovery steam generator includes a gas inlet for receiving a flow of exhaust gas from a gas turbine, a gas outlet opposite the gas inlet, at least one heat exchanger intermediate the gas inlet and the gas outlet, the heat exchanger having a plurality of heat transfer surfaces configured to transfer heat from the exhaust gas to a fluid within the heat exchanger, and a valve associated with the heat exchanger and configured to regulate a flow of the fluid through the heat exchanger. The valve is controllable from an open position to a closed position to decrease the flow of the fluid through the heat exchanger in order to effect an increase in a temperature of the heat transfer surfaces of the heat exchanger to clean the heat transfer surfaces.

System and method for improving the performance of a heat recovery steam generator

Methods, apparatus, systems and articles of manufacture are disclosed for closed loop control of a gas turbine. An example apparatus includes a frequency band splitter to separate a combustion pulsation signal into a plurality of frequency bands. The example apparatus includes a plurality of subcontrollers, each subcontroller corresponding to one of the frequency bands. Each subcontroller is to be activated at an amplitude threshold associated with the normal operating set point of the frequency band and to generate a correction value while the corresponding frequency band is operating beyond the amplitude threshold. The example apparatus includes a net correction output calculator to aggregate the correction values to generate an aggregated correction value. The example apparatus includes a subcontroller limiter having a maximum limit and/or a minimum limit to inhibit subcontroller(s) from increasing their respective correction values when aggregated correction value is to exceed the maximum limit and/or minimum limit.

Methods and apparatus for closed-loop control of a gas turbine

A heat recovery steam generator includes a gas inlet for receiving a flow of exhaust gas from a gas turbine, a gas outlet opposite the gas inlet and configured to transport the flow of exhaust gas to atmosphere, and a sorbent injection device intermediate the gas inlet and the gas outlet, the sorbent injection device including at least one injection port configured to inject a sorbent into the flow of exhaust gas. The sorbent is configured to react with an acid gas within the flow of exhaust gas to neutralize the acid gas and inhibit the formation of salt deposits.

The invention refers to burner arrangement for producing hot gases to be expanded in a gas turbine, including a burner inside a plenum, where the burner has means for fuel injection, means for air supply and means for generating an ignitable fuel/air mixture inside the burner, and a combustion chamber following downstream said burner having an outlet being fluidly connected to the gas turbine. The invention is characterized in that the means for air supply includes at least two separate flow passages, and that the one of the two flow passages is fed by a first supply pressure and the other flow passage is fed by a second supply pressure.

Burner arrangement including an air supply with two flow passages

The burner includes a swirl chamber. The swirl chamber has a substantially conical shape defining a central axis. The swirl chamber is defined by a plurality of wall elements. A combination of nozzles at the pressure, suction side and trailing edge of the wall element are placed for fuel injection. The wall elements define slots between each other. The slots have different widths (w) in consecutive planes in the axial direction, wherein said planes are perpendicular to the central axis.

Burner including a swirl chamber with slots having different widths

A swirler including an annular housing with limiting walls. At least two vanes are arranged in the annular housing including the sidewalls of the swirler. The leading edge area of each vane has a profile, which is oriented parallel to a main flow direction prevailing at the leading edge position, wherein the profiles of the vanes turn from the main flow direction prevailing at the leading edge position to impose a swirl on the flow, and wherein, with reference to a central plane of the vanes the trailing edges are provided with at least two lobes in opposite transverse directions. A burner for a combustion chamber of a gas turbine including such a swirler and at least one nozzle having its outlet orifice at or in a trailing edge of the vane and to a method of operation of such a burner.

Swirler having vanes provided with at least two lobes in opposite transverse directions with reference to a vane central plane

A burner system with staged fuel injection includes at least one burner with a mixing zone. A combustion chamber is disposed downstream of the mixing zone and a first fuel introduction device is provided upstream of the mixing zone. Furthermore, a second fuel introduction device for the direct injection of fuel into the combustion chamber, is disposed downstream of the mixing zone. In addition, at least one sensor for determining combustion parameters is connected to a control device. The control device is designed to control the second fuel introduction device as a function of the parameters determined by the sensors.

Burner system with staged fuel injection

A method and an apparatus are provided for the combustion of gaseous fuel containing hydrogen or consisting of hydrogen, with a burner which provides a swirl generator, into which liquid fuel is fed centrally along a burner axis, at the same time forming a conically shaped liquid fuel column which is surrounded by a rotating combustion air stream which flows tangentially into the swirl generator and into which, additionally, a gaseous and/or liquid fuel is injected so as to form a fuel/air swirl flow which is transferred downstream of the swirl generator, along a transitional portion, into a mixing zone following the transitional portion downstream and which is ignited and burnt in a combustion chamber following downstream, at the same time forming a backflow zone.

Method for operating a burner

A method for the combustion of hydrogen-rich, gaseous fuels in combustion air in a burner of a gas turbine includes injecting the hydrogen-rich, gaseous fuel at least partially isokinetically with respect to the combustion air such that the partially hydrogen-rich, gaseous fuel is injected at least partially in the same direction and at least partially at the same velocity as the combustion air.

Method for combusting hydrogen-rich, gaseous fuels in a burner, and burner for performing said method

A system for controlling NOx emissions and combustion pulsation levels of a gas turbine having a gas turbine combustion system, having a single combustion chamber and multiple burners, includes a cascade structure having a first and second control level (), the first level () having a device to control NOx emissions and generate combustion pulsation target levels based on the difference between measured and target NOx emission levels, and the second level () having a device to control pulsation levels and generate a ratio (&#x3b3;) of fuel flow to different types of burners or to different stages of each burner. The fuel flow ratio (&#x3b3;) is based on the difference between the measured and generated target pulsation levels. The control system enables the operation of a gas turbine to meet NOx emission requirements, while maintaining combustion pulsation levels within limits that ensure improved lifetime of the combustion system.

System for controlling a combustion process for a gas turbine

A burner () for operating a heat generator includes a swirler () for a combustion air flow (), and also devices () for injecting at least one fuel into the combustion air flow (), wherein a mixing path () is arranged downstream of the swirler (), and wherein at least one nozzle () for feeding liquid pilot fuel is arranged in the region radially outside the discharge opening of the mixing path () of the burner. With such a burner, an operating mode which is as pollutant-free and overheating-free as possible can be enabled even at low load and under transient conditions if the at least one nozzle () is arranged in a burner front plate (), wherein at least one discharge opening (), through which the pilot fuel discharges into the combustion chamber (), is provided in a front face () of the burner front plate (), which is arranged essentially parallel to a combustion chamber rear wall ().

Burner for the operation of a heat generator and method of use

Growing community of inventors

Oberrohrdorf, Switzerland

Stefano Bernero