Abstract: A catalytic burner (1) of a combustion chamber (2), in particular of a power plant, includes at least one catalyst (5) and one swirl generator (6). To improve the burner (1), the swirl generator is designed as a radial swirl generator (6) and is arranged radially between an inflow space (7) and an outflow space (8) leading axially to the combustion chamber (2).

Abstract: A description is given of a damping arrangement for reducing resonant vibrations in a combustion chamber (1), with a combustion-chamber wall (2), which is of double-walled design and, with an outer wall-surface part (22) and an inner wall-surface part (21) facing the combustion chamber (1), gastightly encloses an intermediate space (3), into which cooling air can be fed for purposes of convective cooling of the combustion-chamber wall (2).

Abstract: In a method for operating a premix burner a water quantity is introduced into at least one of the burner and the reaction zone of the burner depending on at least one command variable formed from at least one measured value. The method can also be used if a burner is operated dry, i.e., without water injection for nitrogen oxide injection, and the injected water quantity is less than 20% of the fuel quantity. The method can be used advantageously especially if a characteristic value derived from combustion pulsations or material temperatures is used as a command variable. The method enables measured parameters to be kept below a permissible upper limit.

Abstract: A gas turbo group has a combustion chamber comprising a catalytic burner stage (2), a preburner stage (1) located upstream from the catalytic burner stage, as well as a non-catalytic burner stage (11, 5, 6) located downstream from the catalytic burner stage. The preburner stage serves to always maintain a temperature (T1) at the inlet into the catalytic stage that corresponds at least to a minimum temperature (TMIN) necessary for operating the catalytic burner stage. According to the invention, the gas turbo group is operated so that the burner stage located downstream from the catalytic combustion chamber is taken into operation only when the temperature (T2) at the outlet from the catalytic stage has reached an upper limit in the presence of a maximum combustion air mass flow.

Abstract: The present invention relates to a method of operating a burner, which comprises at least one first fuel supply conduit (5) with a first group of fuel outlet openings (6), essentially arranged in the direction of a burner longitudinal axis (3), for a first premix fuel quantity and one or a plurality of second fuel supply conduits (7) with a second group of fuel outlet openings (8), essentially arranged in the direction of the burner longitudinal axis (3), for a second premix fuel quantity, it being possible to admit fuel to the second fuel supply conduits (7) independently of the first fuel supply conduit (5). In the method, both fuel supply conduits (5, 7) are operated with the same fuel. By means of the present method of operating a burner, optimum mixing conditions can be set even in the case of different loads, gas qualities or gas preheat temperatures.

Abstract: In a method for operating a premix burner a water quantity is introduced into at least one of the burner and the reaction zone of the burner depending on at least one command variable formed from at least one measured value. The method can also be used if a burner is operated dry, i.e., without water injection for nitrogen oxide injection, and the injected water quantity is less than 20% of the fuel quantity. The method can be used advantageously especially if a characteristic value derived from combustion pulsations or material temperatures is used as a command variable. The method enables measured parameters to be kept below a permissible upper limit.

Abstract: In a method for igniting a thermal turbomachine, the turbomachine containing a combustion chamber (30), an ignition device (10), a fuel supply (60) and an air supply (70), and the ignition device (10) consisting of an ignition space (50) and of an ignitor (51) arranged in the ignition space (50), the fuel supply (60) and the air supply (70) discharging into the ignition space (50), and the ignition space (50) being connected to the combustion chamber (30) via a flame tube (40), prior to the ignition of the combustion chamber (30), an overall fuel/air mixture ratio &PHgr;overall=1/&lgr;overall greater than 1, with &lgr;overall being the overall air ratio, is set in the flame tube (40) of the ignition device (10).

Abstract: In a method for operating a premix burner a water quantity is introduced into at least one of the burner and the reaction zone of the burner depending on at least one command variable formed from at least one measured value. The method can also be used if a burner is operated dry, i.e., without water injection for nitrogen oxide injection, and the injected water quantity is less than 20% of the fuel quantity. The method can be used advantageously especially if a characteristic value derived from combustion pulsations or material temperatures is used as a command variable. The method enables measured parameters to be kept below a permissible upper limit.

Abstract: The present invention relates to a catalytic burner (1) of a combustion chamber (2), in particular of a power plant, comprising at least one catalyst (5) and one swirl generator (6).

Abstract: The invention relates to a catalytic burner (1) of a combuster (2), in particular of a power station installation, comprising an annular duct (4) leading to the combuster (2), a catalyzer (5) arranged in the annular duct (4), a primary injection device (7) for injecting a fuel into the annular duct (4) upstream of the catalyzer (5), a secondary injection device (3) for directly injecting a fuel into the combuster (2). To stabilize a recirculation zone (29) in the combuster (2), a swirl generation device (6) is provided, which is arranged in the annular duct (4) downstream of the catalyzer (5) and subjects a flow through the catalyzer (5) to a swirl.

Abstract: The present invention relates to a method of operating a burner, which comprises at least one first fuel supply conduit (5) with a first group of fuel outlet openings (6), essentially arranged in the direction of a burner longitudinal axis (3), for a first premix fuel quantity and one or a plurality of second-fuel supply conduits (7) with a second group of fuel outlet openings (8), essentially arranged in the direction of the burner longitudinal axis (3), for a second premix fuel quantity, it being possible to admit fuel to the second fuel supply conduits (7) independently of the first fuel supply conduit (5). In the method, both fuel supply conduits (5, 7) are operated with the same fuel. By means of the present method of operating a burner, optimum mixing conditions can be set even in the case of different loads, gas qualities or gas preheat temperatures.

Abstract: The invention relates to a damper arrangement for reducing combustion-chamber pulsations arising inside a gas turbine (1), having a combustion-chamber housing (8) which upstream comprises a front plate (2) with a plurality of individual burners (6) and damping elements (7, 7a, 7b) projecting through the front plate (2) and downstream is connected to a turbine stage (9) and is surrounded by a turbine housing (3) which comprises first openings (5a) which are adapted to the burners (6) and through which the burners (6) project upstream. The invention is characterized in that closable second openings (5b), through which it is possible to insert and tune the damping elements (7, 7a, 7b), are provided inside the turbine housing (9) adjacent to the first openings (5a) adapted to the burners (6).

Abstract: In a method for igniting a thermal turbomachine, the turbomachine containing a combustion chamber (30), an ignition device (10), a fuel supply (60) and an air supply (70), and the ignition device (10) consisting of an ignition space (50) and of an ignitor (51) arranged in the ignition space (50), the fuel supply (60) and the air supply (70) discharging into the ignition space (50), and the ignition space (50) being connected to the combustion chamber (30) via a flame tube (40), prior to the ignition of the combustion chamber (30), an overall fuel/air mixture ratio &PHgr;overall=1/&lgr;overall greater than 1, with &lgr;overall being the overall air ratio, is set in the flame tube (40) of the ignition device (10).

Abstract: In a method for operating a premix burner a water quantity is introduced into the burner and/or the reaction zone of the burner depending on at least one command variable formed from at least one measured value. The method in particular should also be used if a burner is operated in the actual sense dry, i.e., without water injection for nitrogen oxide injection, and the injected water quantity is less than 20% of the fuel quantity. The method can be used advantageously especially if a characteristic value derived from combustion pulsations or material temperatures is used as a command variable; such parameters are then kept below a permissible upper limit.

Abstract: The invention relates to a catalytic burner (1) of a combuster (2), in particular of a power station installation, comprising

Abstract: The invention relates to a damper arrangement for reducing combustion-chamber pulsations arising inside a gas turbine (1), having a combustion-chamber housing (8) which upstream comprises a front plate (2) with a plurality of individual burners (6) and damping elements (7, 7a, 7b) projecting through the front plate (2) and downstream is connected to a turbine stage (9) and is surrounded by a turbine housing (3) which comprises first openings (5a) which are adapted to the burners (6) and through which the burners (6) project upstream.

Abstract: In a gas turbine (10) with a plurality of individual burners (B1, . . . , B6; Bn) which are connected to a fuel distribution system (21) and are supplied with fuel from a common fuel feed (28) via the fuel distribution system (21), there being provided, within the fuel distribution system (21), means by which the fuel mass flows to the individual burners (B1, . . . , B6; Bn) can be varied in order to improve the operating parameters of the gas turbine (10), an improvement in the operating parameters is achieved in a simple way in that a fixed throttle member, determining the fuel mass flow to at least one of the burners (B1, . . . , B6; Bn), is arranged in the fuel distribution system (21) upstream of the at least one burner, and in that the reduction in cross section of the throttle member is selected in such a way that existing inequalities in the fuel distribution system (21) as regards the fuel mass flows to the individual burners (B1, . . . , B6; Bn) are reduced.

Abstract: The object of the invention is to provide a method for operating a premix burner which has improved operational reliability and functioning during certain types of operation. In addition, it is intended to specify a corresponding premix burner for carrying out the method. According to the invention, this is achieved by the fact that at least one liquid fuel (2) is injected into the inner chamber (9) of the premix burner (4) in a plain jet (26, 26′) with an injection angle &agr; of less than 10°. For this purpose, the liquid-fuel nozzle (17) has a simple injection opening (19) with a guide length (1) and with a diameter (d).

Abstract: In the combustion space of a combustion chamber of a gas turbine operated with liquid fuel, at least one after-burner (4) is employed in each case in combination with one or more primary burners (2, 2a). The after-burner (4) and at least its fuel spray cone (15), which acts directly into the central combustion chamber (6), are screened by an unswirled enveloping airstream (14) against the hot gases (13) from the combustion in the primary burners (2, 2a). The after-burner (4) itself is not automatically operating, i.e. the ignition of its mixture (14/15) takes place further downstream, preferably at the beginning of the mixing chamber (7), as a result of which a turbulence-free flow with uniform pressure and temperature profile is provided for acting on the turbine (9).

Abstract: The combustion chamber is characterized by an annular-cylindrical space, which consists of two reaction chambers (8), arranged at the end, and a collision chamber (12) placed therebetween. The reaction chambers (8) are fitted at their face-sided ends with a number of burner elements (A, B), arranged axially parallel, their number depending on the output of the combustion chamber, which burner elements are in each case mirror-symmetrical to each other in relation to the central axis of the collision chamber (12). From the collision chamber (12), an annular mixing chamber (15) goes off to the turbine inlet (17). Each burner element (A, B) is provided with a twist member (6, 11), which in each case is orientated in opposed sense of rotation compared with the mirror-symmetrically arranged twist member.