Alstom Technology Limited

Alstom (Switzerland) Ltd

Abb Research Ltd.

Alstom

Technische Unversität Berlin

Other

Asea Brown Boveri Ag

Abb Search Ltd.

General Electric Technology Gmbh

Waldner Laboreinrichtungen Gmbh & Co. Kg

Christian Oliver Paschereit

Ephraim J Gutmark

Wolfgang Weisenstein

Peter Flohr

Bruno Schuermans

Wolfgang Polifke

Adnan Eroglu

Martin Zajadatz

Peter Stuber

Jaan Hellat

Valter Bellucci

Sebastian Schimek

Dirk Bueche

Rolf Dornberger

Peter Stoll

Thomas Sattelmayer

Christian Steinbach

Jakob Keller

Stefano Bernero

Klaus Doebbeling

Hans Peter Knoepfel

Klaus D&ouml;bbeling

Bettina Paikert

Stefan Tschirren

Philipp Brunner

Jens Hermann Wintering

Bernhard Bobusch

Oliver Krüger

Petros Koumoutsakos

Moritz Sieber

Christian Joerg Matz

Francois Meili

Panagiotis Stathopoulos

Daniele Tabacco

Aditya Saurabh

Lipika Kabiraj

Jürgen Liebsch

Kabiraj Lipika

Sebastian GÖKE

Christian Jörg Motz

A method for controlling a combustion apparatus having a combustion state in which a parameter related to the combustion state reflects a chaotic behavior is provided. The method includes the steps of measuring the parameter and determining a time series of the parameter, shifting the time series by a variable time delay for determining a time-shifted signal, and forming a difference between the time-shifted signal and the time series for determining a time dependent first signal, so that a norm of the difference is lowest. A time dependent second signal is determined, wherein determining the time dependent second signal includes at least one of using a frequency of a desired oscillating combustion state, and shifting the time series by a set time delay. The first signal and the second signal are combined to determine a control signal. The control signal is used to influence the combustion apparatus.

Method for controlling a combustion apparatus and control device

A process for the production of nanoparticles from a liquid mixture comprising at least one precursor and at least one solvent in a reactor with continuous through-flow comprises the steps of feeding at least one oxygen-containing gas inflow stream having a temperature into the at least one reactor, adding at least one fuel having a temperature to the oxygen-containing gas inflow stream, wherein the fuel and the oxygen-containing gas inflow stream form a homogeneous ignitable mixture having a temperature, wherein the temperature of the homogeneous ignitable mixture is above the autoignition temperature of the homogeneous ignitable mixture, introducing at least one precursor-solvent mixture into the homogeneous ignitable mixture; autoignition of the ignitable mixture of oxygen-containing gas and fuel after an ignition delay time to form a stabilized flame and reacting the precursor-solvent mixture in the stabilized flame to form nanoparticles from the metal salt precursor, removing the formed nanoparticles.

Method for producing nanoparticles from a liquid mixture

A burner for producing a stabilized flame with an inertisation front upstream from the stabilized flame includes a swirl generator and an inlet device with a passage therethrough. The swirl generator swirls an inert process medium about a swirl axis in a flow direction and one or more openings in the inlet device provide one or more partial mass flows containing combustion educts. The inert process medium inhibits combustion of the combustion educts through the inertisation front to displace the stabilized flame from the one or more openings.

Swirl-stabilised burner having an inertisation front and related methods

A burner for a heat generator comprises a swirl generator () for a combustion-air flow and means for injecting fuel for producing a main flow (). A combustion chamber () is arranged downstream of the burner. A cavity () is arranged between the swirl generator () and the combustion chamber (), in which cavity () a secondary flow () can be produced, and this secondary flow () encloses the main flow ().

Burner and pilot burner

A burner is disclosed which includes a vortex generator for a combustion air stream, means for the admission of fuel into the combustion air stream and air inlet ducts, the combustion air stream enters a vortex chamber of the vortex generator via air inlet ducts. The fuel is injected into the combustion air asymmetrically via the injection means.

Burner

A premixing burner is disclosed for operating a combustion chamber with a liquid and/or gaseous fuel, with a swirl generator for a combustion inflow air stream for forming a swirl flow, and with injection of fuel into the swirl flow. The swirl generator is adjacent to the combustion chamber indirectly via a mixing zone or directly, in each case via a burner outlet, a cross-sectional widening at the burner outlet being provided which, is discontinuous in the flow direction of the swirl flow and through which the swirl flow bursts open so as to form a backflow zone. A contour locally narrowing the flow cross section of the swirl generator or of the mixing zone in the flow direction can be provided upstream of the burner outlet.

Premixing burner arrangement for operating a combustion chamber in addition to a method for operating a combustion chamber

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

The present invention relates to a method and a device for affecting thermoacoustic oscillations in a combustion system (i) comprising at least one burner () and at least one combustor (), modulated injection of fuel being carried out. In order to improve the action of affecting the thermoacoustic oscillations, the modulated injection of the fuel is carried out into a recirculation zone () which forms in the combustor ().

Method and device for affecting thermoacoustic oscillations in combustion systems

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.

Burner having a burner lance and staged fuel injection

A premix burner is disclosed, with a swirl generator which delimits a conical swirl space and provides at least two conical part shells which are arranged, offset to one another, along a burner axis, mutually enclose in each case air inlet slits running longitudinally with respect to the burner axis and have in combination a conically widening premix burner outer contour having a maximum outside diameter which narrows axially into a region with a minimum outside diameter. At least one conical part shell provides, in the region between the maximum and the minimum outside diameter, a reception unit which deviates from the conically widening premix burner outer contour and locally elevates the premix burner outer contour radially outward and which has a maximum radial extent which is dimensioned smaller than half the maximum outside diameter of the premix burner outer contour. Within the reception unit, at least one hollow duct is provided, with at least one duct orifice facing away from the swirl space and with a duct longitudinal extent which runs essentially parallel to the burner axis.

Premix burner with a swirl generator delimiting a conical swirl space and having sensor monitoring

A premix burner has a swirl generator and two perforated through flow elements are arranged at a defined distance from one another in the inflow region for the combustion air. The through flow elements are preferably arranged in such a way that substantially the entire combustion airstream has to flow through the through flow elements. The degree of perforation of the through flow elements and the distance between these elements are preferably adapted to one another in such a way that a reflection free condition for combustion pulsation frequencies which may be expected is present at the exit from the burner into the combustion chamber.

In a burner () having an interior space () surrounded by at least one shell () in which burner () fuel is injected through fuel nozzles () arranged at the burner shells () into a combustion air stream () flowing within the interior space (), the fuel/air mix which is formed flows to a flame front () in a combustion chamber () within a delay time (&#x3c4;), where it is ignited, the formation of combustion-driven thermoacoustic oscillations is avoided by virtue of the fact that means (), which allow fuel to be injected into the combustion air stream () via at least two fuel injection holes () distributed over the length of the means () are arranged so as to project from the burner base () into the interior space () substantially in the direction of the combustion chamber (), so that the delay time (&#x3c4;) between injection of the fuel and its combustion at the flame front () corresponds to a distribution () which avoids combustion-driven oscillations in premix operation.

Burner with stepped fuel injection

The present invention relates to a method and a device () for affecting thermoacoustic oscillations in a combustion system () comprising at least one burner () and at least one combustor (). In order to improve the action of affecting the thermoacoustic oscillations,

Arranged upstream of each swirl-stabilized premix burner () of a burner system there is respectively an adjustable distributing device () with control valves (V, . . . , V) and/or on/off valves (V&#x2033;, . . . , V&#x2033;), by means of which various axial mass flow distributions of the fuel introduced can be set. Preferably, those which have particularly favorable values with respect to characteristics such as NOemission and maximum amplitudes of pulsations occurring are chosen. For this purpose, Pareto solutions are determined with respect to the said characteristics, in that a distributing device () is represented by a tree structure with distributing parameters, and values for the distributing parameters on the basis of which the distributing device () is set by means of a control unit are iteratively generated in a data-processing system by an evolutionary algorithm. On the basis of the values determined by a measuring unit, solutions which are especially favorable with respect to the characteristics mentioned, especially Pareto-optimal, are selected. The distributing devices are then set during operation on the basis of the solutions of this type corresponding to respective requirements.

Burner unit and method for operation thereof

Growing community of inventors

Berlin, Germany

Christian Oliver Paschereit