Abstract: 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.

Abstract: 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.

Abstract: A sensor 11 detects the acoustic pressure at a first location in a combustion chamber 7 of a test rig 1 and produces an input signal which is a function of the acoustic pressure. A controller 13 receives the input signal and produces an output signal which is a function of the input signal. An acoustic actuator (16-18) receives the output signal and introduces into the combustion chamber 7 at a second location an acoustic pressure which is a function of the output signal. The acoustic actuator may comprise a fuel injector 18 or a loudspeaker.

Abstract: Relating to a model-based active control system for a gas turbine, a method for obtaining the data that are used for deriving an active closed loop controller for the gas turbine includes splitting the combustion system into a number of submodels. The measurement of some submodels is achieved by system identification on a single burner test facility. Other submodels are then determined by using known acoustic models. The different submodels are subsequently combined to form an acoustic network model that is subsequently used to develop a closed loop controller.

Abstract: A premix burner includes a vortex generator (30) for combustion air stream (15), devices (17, 17a, 17b, 31-38, 41-48) to inject fuel into the combustion air stream (15), and tangential air ducts (19, 20). The combustion air (15) enters the cone cavity (14) of the vortex generator (30) via the air ducts. The injection of the fuel into the combustion air is done asymmetrically by injection devices (17, 17a, 17b, 31-38, 41-48). At least one of the injection devices (5) is arranged on a fuel lance (3) that extends into the vortex chamber.

Abstract: In a burner (1) having an interior space (22) surrounded by at least one shell (8, 9) in which burner (1) fuel is injected through fuel nozzles (6) arranged at the burner shells (8, 9) into a combustion air stream (23) flowing within the interior space (22), the fuel/air mix which is formed flows to a flame front (3) in a combustion chamber (2) within a delay time (?), where it is ignited, the formation of combustion-driven thermoacoustic oscillations is avoided by virtue of the fact that means (24), which allow fuel to be injected into the combustion air stream (23) via at least two fuel injection holes (25) distributed over the length of the means (24) are arranged so as to project from the burner base (27) into the interior space (22) substantially in the direction of the combustion chamber (2), so that the delay time (?) between injection of the fuel and its combustion at the flame front (3) corresponds to a distribution (12) which avoids combustion-driven oscillations in premix operation.

Abstract: 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.

Abstract: A reheat combustion system for a gas turbine comprises a mixing tube adapted to be fed by products of a primary combustion zone of the gas turbine and by fuel injected by a lance; a combustion chamber bed by the said mixing tube; and at least one perforated acoustic screen. The or each said acoustic screen is provided inside the mixing tube or the combustion chamber, at a position where it faces, but is spaced from, a perforated wall thereof. In use, the perforated wall experiences impingement cooling as it admits air into the combustion system for onward passage through the perforations of the said acoustic screen, and the acoustic screen damps acoustic pulsations in the mixing tube and combustion chamber.

Abstract: A burner includes a swirl generator (3) for a combustion airflow, has a conical swirl chamber (2) and a device for admitting fuel into the combustion airflow, wherein the swirl generator (3) incorporates combustion air inlet openings for the combustion airflow tangentially entering into the conical swirl chamber (2), and wherein the device for admitting fuel into the combustion airflow includes a first fuel feeding device having a first group (4) of fuel outlet openings substantially disposed in the direction of the burner axis for a first premix fuel quantity.

Abstract: A burner 1 for a heat generator comprises an outlet 10 connectable to a combustion chamber 9, wherein at least part of an inner surface of the outlet 10 is provided with corrugations 11 which are adapted to facilitate the production of axial vorticity in the region of the outlet 10.

Abstract: In the case of swirl-stabilized premix burners (1), an axial mass flow distribution of the fuel introduced which has especially favorable values with respect to characteristics such as NOx emission and maximum amplitudes of pulsations occurring is used. For this purpose, Pareto solutions are determined with respect to the said characteristics, in that a distributing device (5) with control valves is represented by a tree structure with distributing parameters, and values for the distributing parameters on the basis of which the distributing device (5) is set by means of a control unit (10) are iteratively generated in a data-processing system (9) by an evolutionary algorithm. On the basis of the values determined by a measuring unit (11), solutions which are especially favorable with respect to the characteristics mentioned, espectially Pareto-optimal, are selected. The distributing devices or the premix burners of the burner system are then formed in a way corresponding to such a solution.

Abstract: A combustion system for a heat generator, the burner 1 being connected to a combustion chamber 6 by means of an outlet 10, wherein the outlet 10 comprises a multiply stepped transional structure 11 in the direction of flow of fluid 3 in the burner 1 so as to create turbulence in the fluid flow.

Abstract: Arranged upstream of each swirl-stabilized premix burner (1) of a burner system there is respectively an adjustable distributing device (5) with control valves (V1, . . . ,V8) and/or on/off valves (V?1, . . . , V?16), 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 NOx emission 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 (5) is represented by a tree structure with distributing parameters, and values for the distributing parameters on the basis of which the distributing device (5) is set by means of a control unit are iteratively generated in a data-processing system by an evolutionary algorithm.

Abstract: The present invention relates to a method and a device (1) for affecting thermoacoustic oscillations in a combustion system (5) comprising at least one burner (6) and at least one combustor (7), a gas flow forming in the region of the burner (6) being excited acoustically and/or modulated injection of fuel being carried out. In order to improve the action of affecting the thermoacoustic oscillations, the acoustic excitations of the gas flow and/or the modulated injections of the fuel are coordinated in order to affect at least two different interference frequencies of the thermoacoustic oscillations.

Abstract: The present invention relates to a method and a device for affecting thermoacoustic oscillations in a combustion system (1) comprising at least one burner (2) and at least one combustor (3), 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 (7) which forms in the combustor (3).

Abstract: The present invention relates to a method and a device (1) for affecting thermoacoustic oscillations in a combustion system (6) comprising at least one burner (70 and at least one combustor (8). In order to improve the action of affecting the thermoacoustic oscillations, a gas flow forming in the e region of the burner (7) is excited acoustically, modulated injection of fuel is carried out, the acoustic excitation of the gas flow and the modulated injection of the fuel are coordinated in order to affect the same interference frequency.

Abstract: In an annular combustion chamber for a gas turbine, a combustion-chamber dome (14) is arranged upstream of an air-cooled combustion chamber (10). A first portion of an air flow (46) which comes from the compressor is admixed as combustion air to the combustion operation and cooling ducts (22; 24) feed a second portion of the air flow (46) coming from the compressor as cooling air into the combustion chamber (10). In this case, the cooling ducts (22; 24), which run at least in sections along the combustion chamber (10), have an entry (23; 25) into the combustion-chamber dome (14). The cooling ducts (22; 24) are designed for damping combustion-chamber oscillations in such a way that the acoustic impedance at the entry (23; 25) of the cooling ducts (22; 24) into the combustion-chamber dome (14) is minimized.