Alstom Technology Limited

Other

General Electric Technology Gmbh

Ansaldo Energia Switzerland Ag

Ansaldo Energia IP UK Limited

Martin Zajadatz

Peter Flohr

Christian Oliver Paschereit

Mirko Ruben Bothien

Douglas Pennell

Adnan Eroglu

Bruno Schuermans

Stefano Bernero

Gijsbertus Oomens

Majed Toqan

Klaus Doebbeling

Andreas Brautsch

Anton Nemet

Peter Stuber

Rudolf Lachner

Mauricio Ernesto Garay

Christian Joerg Kreutle

Rene Waelchli

Solaf Sulta

Christian Joerg Matz

Christian Joerg Motz

Simone Camponovo

James Robertson

Berthold Stay

Christian Jörg Motz

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

A method for operating a combustion device includes supplying a fuel and an oxidizer into the combustion device and burning them. According to the method, during at least a part of a transient operation, an additional fluid is supplied together with the fuel, and its amount is regulated to counteract combustion pulsations.

Method for operating a combustion device including injecting a fluid together with diluent fuel to address combustion pulsations

An exemplary method for switching over a combustion device from operation with a first premix fuel to a second premix fuel includes reducing and stopping a first premix fuel supply and then starting a second premix fuel supply. In an intermediate phase, after the first premix fuel supply stop and before the second premix fuel supply start, the combustion device is operated with one or more pilot fuels generating diffusion flames.

Method for switching over a combustion device between a first fuel and a second fuel

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 apparatus are disclosed for operating a combustion device during a transient operation. The combustion device is fed with at least a fuel. The transient operation includes a period having a period length (T) during which the fuel is fed in an amount lower that a designated (e.g., critical) amount (Mc). A limit value (L) is defined for the period length (T), and fuel feed is regulated to keep the period length (T) smaller or equal to the limit value (L).

Method for operating a combustion device during transient operation

A method is provided for operating a combustion device having at least one premix burner equipped with fuel stagings and is connected to a combustion chamber. The method includes changing, during transient operating states, the fuel staging of the at least one premix burner in accordance with combustion-induced pulsations which occur in the combustion chamber. A pulsation level of the pulsations which occur in the combustion chamber is continuously determined, the fuel staging of the at least one premix burner is changed for lowering the pulsation level if the pulsation level exceeds a predetermined maximum value, and, after a predetermined time interval, by the fuel staging being reset to the undisturbed value which determines the respective operating point if within the predetermined time interval the predetermined maximum value is not exceeded.

Controlling a combustion device to lower combustion-induced pulsations by changing and resetting fuel stagings at different rates of change

A burner arrangement is disclosed with a conical swirler in the form of a double cone which is arranged concentric to a burner axis and which encloses a swirl chamber, and with a central fuel lance which lies in the burner axis and projects from the cone point of the swirler into the swirl chamber, wherein a first stage is provided for injecting premix fuel, in which the premix fuel is injected radially outwards into the swirl chamber through injection openings which are arranged on the fuel lance, and wherein a second stage is provided for injecting premix fuel, in which the premix fuel is injected into an air flow, which is guided in the double cone, through injection openings in the double cone. With such a burner arrangement, the gas pressure which is required in the first stage is reduced by the entire premix fuel being injected into the swirl chamber in the first stage through two oppositely-disposed injection openings with increased opening diameter.

Burner arrangement

A fuel distribution system for a gas turbine with multistage burner arrangement is provided having at least one distribution line that branches off from a common fuel feed line and leads to a burner stage, and at least one element is provided in each distribution line for the specific influencing of the fuel mass flow. In such a fuel distribution system simplified controlling is made possible by a control valve being arranged in each case in one section of the distribution lines as an element for the specific influencing of the fuel mass flow, and in that a restrictor, which is preset in a fixed manner, is arranged in each case in the remaining distribution lines as an element for the specific influencing of the fuel mass flow.

Fuel distribution system for a gas turbine with multistage burner arrangement

A premix burner with staged liquid fuel supply is described having at least two partial cone shells which on the radial side form the boundary of a swirl chamber which axialwards conically widens, which partial cone shells are arranged in a partially overlapping manner, the center axes of the partial cone shells of which extend with offset effect in relation to each another, and the mutually overlapping partial cone shell sections of which enclose in each case an air inlet slot which extends tangentially to the swirl chamber, with a burner lance which projects axialwards into the swirl chamber, which lance provides means for feed of liquid fuel into the swirl chamber, and also with further means for feed of liquid fuel which are provided in the region of the air inlet slots. As such, additional means for feed of liquid fuel along at least one air inlet slot are formed and arranged in such a way that the liquid fuel delivery, which is conditioned by the further means, takes place in the form of a fuel spray which propagates perpendicularly to the tangential longitudinal extent of the air inlet slot, and also a fuel spray which propagates perpendicularly to an air flow which is directed through the air inlet slot.

Premix burner with staged liquid fuel supply and also method for operating a premix burner

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

What are described are a multiple burner arrangement and a method for operating such a multiple burner arrangement with a multiplicity of individual burners which are designed as premix burners and which serve for firing a combustion chamber of a thermal engine and each have a swirl space into which combustion supply air and fuel can be introduced so as to form a swirl flow, the swirl flow forming downstream of the premix burner, within the combustion chamber, a backflow zone in which a burner flame is formed.

Multiple burner arrangement for operating a combustion chamber, and method for operating the multiple burner arrangement

A premix burner includes a vortex generator () for combustion air stream (), devices (--) to inject fuel into the combustion air stream (), and tangential air ducts (). The combustion air () enters the cone cavity () of the vortex generator () via the air ducts. The injection of the fuel into the combustion air is done asymmetrically by injection devices (--). At least one of the injection devices () is arranged on a fuel lance () that extends into the vortex chamber.

Premix burner

A method for operating a gas turbine set comprises the compression of an air mass flow in a compressor, feeding the compressed air mass flow into a first combustion chamber, burning the first mass fuel flow in the first combustion chamber in the compressed mass air flow, expanding the resulting hot gas in the first turbine, feeding the partially expanded hot gas into a second combustion chamber, and burning a second mass fuel flow in the second combustion chamber in the partially expanded hot gas. The method furthermore comprises supplying to the gas turbine set the first mass fuel flow and the second mass fuel flow preferably in a common supply line with a fuel supply pressure, and stipulating division of the total mass flow into a first and second mass fuel flow according to a normal operation concept. When the boundary value of the fuel supply pressure for example in the preferably common supply line is not reached, there is a deviation from the division according to the normal operating concept. Relative to the normal operation concept the first mass fuel flow is reduced by the difference mass flow and the second mass fuel flow is increased at least by the difference mass flow.

Method for the operation of a gas turbo group

A sensordetects the acoustic pressure at a first location in a combustion chamberof a test rigand produces an input signal which is a function of the acoustic pressure. A controllerreceives the input signal and produces an output signal which is a function of the input signal. An acoustic actuator (-) receives the output signal and introduces into the combustion chamberat a second location an acoustic pressure which is a function of the output signal. The acoustic actuator may comprise a fuel injectoror a loudspeaker. By using an appropriate control algorithm, acoustic boundary conditions corresponding to a particular gas turbine combustion chamber may be produced, at least in a certain frequency range.

Apparatus and method for testing combustion

A burner includes a swirl generator () for a combustion airflow, has a conical swirl chamber () and a device for admitting fuel into the combustion airflow, wherein the swirl generator () incorporates combustion air inlet openings for the combustion airflow tangentially entering into the conical swirl chamber (), and wherein the device for admitting fuel into the combustion airflow includes a first fuel feeding device having a first group () of fuel outlet openings substantially disposed in the direction of the burner axis for a first premix fuel quantity. The burner incorporates at least one second fuel feeding device having at least one second group () of fuel outlet openings that are substantially disposed in the direction of the burner axis for a second premix fuel quantity, which can be supplied with fuel independently from the first fuel feeding device, a burner lance () along a burner axis (A) projects from the side of the swirl chamber () with the smallest swirl chamber cross section into the swirl chamber (), and the device for supplying fuel into the combustion airflow additionally incorporates at least one fuel outlet opening () within the burner lance (), through which fuel is dischargeable along the burner axis.

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Kuessaberg/Dangstetten, Germany

Martin Zajadatz