Abstract: A system for capturing a scene with a simultaneous use of an IR light and a VIS light to create at least one of an alpha channel mask or a relighting effect in a movie post-production transmission. The system includes a lighting system that includes an NIR light source and a VIS light source. The system also includes an electro-optical system configured to simultaneously acquire a video in a NIR spectrum and in a VIS spectrum based on the NIR light source and the VIS light source. The system further includes a post-processing converter configured to generate an alpha channel mask from the video based on the NIR spectrum to distinguish between a foreground object and a background over which the foreground object is positioned. The foreground object is illuminated via the NIR light source.

Abstract: The invention concerns a gas turbine combustion system, including a gas turbine. The gas turbine includes at least one compressor, at least one combustion chamber for generating working gas, wherein the combustion chamber connected to receive compressed air from the compressor, at least one turbine connected to receive working gas from the combustion chamber. The combustion chamber consists of an individual can-combustor or comprising a number of can-combustors arranged in an annular can-architecture, wherein the can-combustor having at least one premixed burner. The ignition of the mixture starts at the premixed burner outlet and the flame is stabilized in the region of the premixed burner outlet by means of a backflow zone. The can-combustor comprising a number of premixed burners arranged uniformly or divided at least in two groups within the can-combustor.

Abstract: An axial swirler for a gas turbine burner includes a vane ring with a plurality of swirler vanes circumferentially distributed around a swirler axis. Each of the swirler vanes includes a trailing edge. In order to achieve a controlled distribution of the exit flow velocity profile and/or the fuel equivalence ratio in the radial direction. The trailing edge is discontinuous with the trailing edge having a discontinuity at a predetermined radius.

Abstract: A system for capturing scene with the simultaneous use IR and VIS light for alpha channel creation and relighting effects in movie postproduction transmission comprising the subsystems of: Lighting sub system, Electro-optical system for simultaneous acquisition of the video in VIS and NIR, and Video post-processing converter for generation of alpha channel from the NIR video signal to perform determination between the foreground objects, illuminated with NIR light source and background. Video post-processing converter uses VIS images to obtain information for more precise alpha channel derivation.

Abstract: An axial swirler for a gas turbine burner includes a vane ring with a plurality of swirler vanes circumferentially distributed around a swirler axis. Each of the swirler vanes includes a trailing edge. In order to achieve a controlled distribution of the exit flow velocity profile and/or the fuel equivalence ratio in the radial direction. The trailing edge is discontinuous with the trailing edge having a discontinuity at a predetermined radius.

Abstract: The invention concerns a gas turbine combustion system, including a gas turbine. The gas turbine includes at least one compressor, at least one combustion chamber for generating working gas, wherein the combustion chamber connected to receive compressed air from the compressor, at least one turbine connected to receive working gas from the combustion chamber. The combustion chamber consists of an individual can-combustor or comprising a number of can-combustors arranged in an annular can-architecture, wherein the can-combustor having at least one premixed burner. The ignition of the mixture starts at the premixed burner outlet and the flame is stabilized in the region of the premixed burner outlet by means of a backflow zone. The can-combustor comprising a number of premixed burners arranged uniformly or divided at least in two groups within the can-combustor.

Abstract: A burner (1) for a combustion chamber of a turbogroup includes a swirl generator (2), a mixer (3), and a lance (4) for introducing pilot fuel into a combustion space (10). In order to stabilize combustion, the lance (4) is designed and/or arranged so that, at least in the pilot mode of the burner (1), it extends far enough into the burner interior (5) for a flame front (16) of a combustion reaction, which takes place in the combustion space (10), to extend at least partially into the burner interior (5).

Abstract: A burner (1) for a combustion chamber of a turbogroup includes a swirl generator (2), a mixer (3), and a lance (4) for introducing pilot fuel into a combustion space (10). In order to stabilize combustion, the lance (4) is designed and/or arranged so that, at least in the pilot mode of the burner (1), it extends far enough into the burner interior (5) for a flame front (16) of a combustion reaction, which takes place in the combustion space (10), to extend at least partially into the burner interior (5).

Abstract: A method for operating a combustion chamber (1) for a gas turbine. The combustion chamber (1) has a combustion space (2) and a plurality of burners (3), which are each arranged at an inlet (13) of the combustion space (2). The burners (3) are divided into two burner groups (4I, 4II). A common oxidant supply (5) is provided for all the burners (3). A common first fuel supply (7) is provided for the burners (3I) belonging to the first burner group (4I). A common second fuel supply (9) and a common additional fuel supply (11) are provided for the burners (3II) belonging to the second burner group (4II). A first fuel stream (8) is fed to the burners (3I) belonging to the first fuel group (4I), in such a manner that a lean fuel/oxidant mix is established. A second fuel stream (10) is fed to the burners (3II) belonging to the second burner group (4II) in such a manner that a lean fuel/oxidant mix is established.

Abstract: The present invention provides compositions and methods relating to vacuolins and their uses. Vacuolins are small molecule agents that affect certain membrane fusion events involving intracellular compartments. The invention further provides compositions and methods for altering antigen presentation mediated by class II MHC molecules, and/or for inhibiting histamine release from mast cells.

Abstract: A method for operating a combustion chamber (1) for a gas turbine. The combustion chamber (1) has a combustion space (2) and a plurality of burners (3), which are each arranged at an inlet (13) of the combustion space (2). The burners (3) are divided into two burner groups (4I, 4II). A common oxidant supply (5) is provided for all the burners (3). A common first fuel supply (7) is provided for the burners (3I) belonging to the first burner group (41). A common second fuel supply (9) and a common additional fuel supply (11) are provided for the burners (3II) belonging to the second burner group (4II). A first fuel stream (8) is fed to the burners (3I) belonging to the first fuel group (4I), in such a manner that a lean fuel/oxidant mix is established. A second fuel stream (10) is fed to the burners (3II) belonging to the second burner group (4II) in such a manner that a lean fuel/oxidant mix is established.