Abstract: A burner (23) for operating a heat generator includes a swirler (2) for a combustion air flow (9), and also devices (7, 12) for injecting at least one fuel into the combustion air flow (9), wherein a mixing path (3) is arranged downstream of the swirler (2), and wherein at least one nozzle (20) for feeding liquid pilot fuel is arranged in the region radially outside the discharge opening of the mixing path (3) 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 (20) is arranged in a burner front plate (32), wherein at least one discharge opening (15), through which the pilot fuel discharges into the combustion chamber (16), is provided in a front face (34) of the burner front plate (32), which is arranged essentially parallel to a combustion chamber rear wall (28).

Abstract: 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.

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: 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.

Abstract: 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.

Abstract: A burner (23) for operating a heat generator includes a swirler (2) for a combustion air flow (9), and also devices (7, 12) for injecting at least one fuel into the combustion air flow (9), wherein a mixing path (3) is arranged downstream of the swirler (2), and wherein at least one nozzle (20) for feeding liquid pilot fuel is arranged in the region radially outside the discharge opening of the mixing path (3) 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 (20) is arranged in a burner front plate (32), wherein at least one discharge opening (15), through which the pilot fuel discharges into the combustion chamber (16), is provided in a front face (34) of the burner front plate (32), which is arranged essentially parallel to a combustion chamber rear wall (28).

Abstract: 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.

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. 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.

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 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.

Abstract: 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.

Abstract: An injector (4) for liquid fuel (6a) and a premix burner, in particular for combustion chambers of gas turbines which burner includes an injector (4) of this type, includes a swirl nozzle (14) which is surrounded by a shielding-air passage (11) and has an enlarged cross section of flow in the region of a nozzle-internal swirl generator (12) for the liquid fuel (6a), with this enlarged cross section of flow being reduced again toward an exit opening of the swirl nozzle (14). The injector allows the premix burner to operate with a reduced admission pressure and a high atomization quality.

Abstract: 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.

Abstract: 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.

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: 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: 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.