Abstract: A rectangular blank has sides X and Y, where a and b are side dimensions, h is height, and r is width, or width reduced by height h, of the periphery region R of the finished packaging. The method includes: producing folding lines B in the blank parallel to side Y at these distances from the latter: B1: a1=h; B2: a2=h+a; B3: a3=2h+a; severing of two severing lines T, each starting from opposite sides X, along one of the folding lines B, or the extension thereof; selecting the distance between two end points ET of the severing lines T which are closer to an axis of symmetry S1 parallel to the side X, such that the distance corresponds to a side B? of the finished packaging or length of a side M of a packaging insert.

Abstract: A rectangular blank has sides X and Y, where a and b are side dimensions, h is height, and r is width, or width reduced by height h, of the periphery region R of the finished packaging. The method includes: producing folding lines B in the blank parallel to side Y at these distances from the latter: B1: a1=h; B2: a2=h+a; B3: a3=2h+a; severing of two severing lines T, each starting from opposite sides X, along one of the folding lines B, or the extension thereof; selecting the distance between two end points ET of the severing lines T which are closer to an axis of symmetry S1 parallel to the side X, such that the distance corresponds to a side B? of the finished packaging or length of a side M of a packaging insert.

Abstract: A method for producing reusable packaging from a carton. A rectangular blank has sides X and Y, a total area xy, 2(a+h)?x?3(a+h)+a, and y?2(h+r)?b?y, where a and b are side dimensions, h is height, and r is width, or width reduced by height h, of the periphery region R of the finished packaging. The method includes: producing folding lines B in the blank parallel to a first side Y at these distances from the latter: B1: a1=h; B2: a2=h+a; B3: a3=2h+a; severing of two severing lines T, each starting from opposite sides X, along one of the folding lines B, or the extension thereof; selecting the distance between two end points ET of the severing lines T which are closer to an axis of symmetry S1, which is parallel to the side X, such that the distance corresponds to a side B? of the finished packaging or length of a side M of a packaging insert.

Abstract: A gas turbine uses a first fuel at full load and an improved emission behavior is achieved by operating the gas turbine (11) at partial load with a second fuel, which has a richer mix of higher-value hydrocarbons (C2+) with 2 and more carbon atoms per molecule like ethane (C2H6) and propane (C3H8).

Abstract: A gas turbine uses a first fuel at full load and an improved emission behavior is achieved by operating the gas turbine (11) at partial load with a second fuel, which has a richer mix of higher-value hydrocarbons (C2+) with 2 and more carbon atoms per molecule like ethane (C2H6) and propane (C3H8).

Abstract: A method for operating a gas turbine uses a first fuel at full load. An improved emission behavior is achieved by operating the gas turbine (11) at partial load with a second fuel, which has a richer mix of higher-value hydrocarbons (C2+) with 2 and more carbon atoms per molecule like ethane (C2H6) and propane (C3H8).

Abstract: In a method for igniting the combustion chamber of a gas turbine unit, a safely working ignition and a long lifetime of the ignition device (10) is achieved by discharging a compressed gas with a supercritical pressure ratio through a nozzle (21) and heating it up to a temperature sufficient to ignite hydrocarbons by interacting with a resonance tube (19) arranged behind said nozzle (21), and using said heated-up gas to directly or indirectly ignite a fuel/air mixture introduced into said combustion chamber.

Abstract: A burner (1) for heat generation, in particular in a gas turbine, is disclosed as well as a method for the stabilization of the flame of a burner (1). The burner (1) comprises inlet openings (3) for a combustion air stream, at least a swirl generator (2) for the combustion air stream and one or more first fuel supplies (4) with first fuel outlet openings (5) for injection of fuel into the combustion air stream. At least one resonance tube (6) with an open (7) and an essentially closed end (8) is arranged in or at the burner (1), whose closed end (8) is positioned in the region of a flame front (9) which forms during operation of the burner (1) on the side of the burner (1). An outlet opening (10) of a supply (11) for a compressible medium is arranged at the open end (7) of the resonance tube (6).

Abstract: A method for operating a gas turbine uses a first fuel at full load. An improved emission behavior is achieved by operating the gas turbine (11) at partial load with a second fuel, which has a richer mix of higher-value hydrocarbons (C2+) with 2 and more carbon atoms per molecule like ethane (C2H6) and propane (C3H8).

Abstract: In a method for igniting the combustion chamber of a gas turbine unit, a safely working ignition and a long lifetime of the ignition device (10) is achieved by discharging a compressed gas with a supercritical pressure ratio through a nozzle (21) and heating it up to a temperature sufficient to ignite hydrocarbons by interacting with a resonance tube (19) arranged behind said nozzle (21), and using said heated-up gas to directly or indirectly ignite a fuel/air mixture introduced into said combustion chamber.

Abstract: A burner (1) for heat generation, in particular in a gas turbine, is disclosed as well as a method for the stabilization of the flame of a burner (1). The burner (1) comprises inlet openings (3) for a combustion air stream, at least a swirl generator (2) for the combustion air stream and one or more first fuel supplies (4) with first fuel outlet openings (5) for injection of fuel into the combustion air stream. At least one resonance tube (6) with an open (7) and an essentially closed end (8) is arranged in or at the burner (1), whose closed end (8) is positioned in the region of a flame front (9) which forms during operation of the burner (1) on the side of the burner (1). An outlet opening (10) of a supply (11) for a compressible medium is arranged at the open end (7) of the resonance tube (6).

Abstract: In a thermal turbomachine with a housing, a combustion chamber, an ignition device, a fuel supply, and an air supply, the ignition device includes an ignition space and an igniter arranged in the ignition space. The fuel supply and the air supply open into the ignition space. The ignition space is connected to the combustion chamber, and the ignition device is arranged outside the housing of the thermal turbomachine. A process is shown for the ignition of the thermal turbomachine outside the housing.

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: A method for running up a gas turbine plant (1) is disclosed. In the method, a fuel (6) is injected into the combustion chamber (5) via a plurality of pilot burners (10) and premix burners (11). During the start-up and in a lower load range, the combustion chamber (5) is operated in the pilot mode, and, at a specific time point, the combustion chamber (5) is changed over from the pilot mode to the premix mode. The changeover time point from the pilot mode to the premix mode depends on a variable changeover temperature (TSWO), and this changeover temperature (TSWO) is determined from pulsations occurring in the flame of the combustion chamber (5).

Abstract: A combustion chamber includes a mixing zone and a combustion zone within which self-ignition of a fuel and air mixture can occur. Fuel and support air are injected laterally at the sidewall of the mixing zone into hot gases passing through the mixing zone. The operating range of the combustion chamber can be increased while noxious substances are reduced by injecting differently controlled fuel/support air mixture jets into different target spaces within the mixing zone.

Abstract: In a combustion chamber (1) that consists of a mixing zone (11) and a combustion zone (12) and which works due to self-ignition, fuel (3) and support air (4) are injected laterally at the sidewall (6) of the mixing zone (11) into hot gases (5). By injecting differently controlled fuel/support air mixture jets (7) into different target spaces within the mixing zone (11), the operating range of the combustion chamber (1) can be increased while noxious substances are reduced. The invention relates both to the combustion chamber (1) as well as to the method for operating this combustion chamber (1).

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: A method for running up a gas turbine plant (1) is disclosed. In the method, a fuel (6) is injected into the combustion chamber (5) via a plurality of pilot burners (10) and premix burners (11). During the start-up and in a lower load range, the combustion chamber (5) is operated in the pilot mode, and, at a specific time point, the combustion chamber (5) is changed over from the pilot mode to the premix mode. The changeover time point from the pilot mode to the premix mode depends on a variable changeover temperature (TSWO), and this changeover temperature (T-SWO) is determined from pulsations occurring in the flame of the combustion chamber (5).

Abstract: In a thermal turbomachine with a housing (80), a combustion chamber (30), an ignition device (10), a fuel supply (60), and an air supply (70), in which the ignition device (10) consists of an ignition space (50) and an igniter (51) arranged in the ignition space (50); in which the fuel supply (60) and the air supply (70) open into the ignition space (50); and in which the ignition space (50) is connected to the combustion chamber (30), the ignition device (10) is arranged outside the housing (80) of the thermal turbomachine. The invention also relates to a process for the ignition of the thermal turbomachine outside the housing (80).

Abstract: A damping device for reducing the vibration amplitude of acoustic waves and a burner for operating an internal combustion engine, the burner having a mixing region, in which an air flow and a fuel flow are mixed with one another to form an air/fuel mixture, and a combustion chamber, which in the direction of flow of the fuel/air mixture is arranged downstream of the mixing region, in which the fuel/air mixture can be ignited. A Helmholtz resonator directly connected to the mixing region of the burner such that acoustic waves formed in the burner are suppressed in the Helmholtz resonator and are not reflected back into the burner.