Abstract: The burner includes a swirl chamber. The swirl chamber has a substantially conical shape defining a central axis. The swirl chamber is defined by a plurality of wall elements. A combination of nozzles at the pressure, suction side and trailing edge of the wall element are placed for fuel injection. The wall elements define slots between each other. The slots have different widths (w) in consecutive planes in the axial direction, wherein said planes are perpendicular to the central axis.

Abstract: This invention relates to a premix burner for operating a heat generator, the burner at least having a swirl generator, a mixing section downstream of the swirl generator and a transition piece for transferring the swirl flow from the swirl generator into the mixing section. The invention further refers to a transition piece for such a premix burner. The transition piece includes an inlet, connected to the swirl generator, an outlet, connected to the mixing tube, and a continuing flow limiting interior contour between said inlet and said outlet, wherein at least in an inlet section said interior contour is curved radially inwards towards the inner diameter of the mixing tube and wherein at the outlet the interior contour is flush with an interior flow limiting contour of the mixing tube.

Abstract: A lance is presented for introducing fuel into a second burner of a combustion chamber of a gas turbine installation with sequential combustion, having a first and a second combustion chamber. The lance includes a foot and a shank which projects from it. In an installed state of the lance the foot extends perpendicularly or at an angle to a main flow direction of the burner. The shank extends centrally in the burner and generally parallel to the main flow direction. At least one projecting arm, having at least one nozzle for introducing fuel, is arranged such that it extends from the shank. A respective end of the at least one arm is oriented in the main flow direction and extends generally parallel to the main flow direction.

Abstract: The burner includes a swirl chamber. The swirl chamber has a substantially conical shape defining a central axis. The swirl chamber is defined by a plurality of wall elements. A combination of nozzles at the pressure, suction side and trailing edge of the wall element are placed for fuel injection. The wall elements define slots between each other. The slots have different widths (w) in consecutive planes in the axial direction, wherein said planes are perpendicular to the central axis.

Abstract: This invention relates to a premix burner for operating a heat generator, the burner at least having a swirl generator, a mixing section downstream of the swirl generator and a transition piece for transferring the swirl flow from the swirl generator into the mixing section. The invention further refers to a transition piece for such a premix burner. The transition piece includes an inlet, connected to the swirl generator, an outlet, connected to the mixing tube, and a continuing flow limiting interior contour between said inlet and said outlet, wherein at least in an inlet section said interior contour is curved radially inwards towards the inner diameter of the mixing tube and wherein at the outlet the interior contour is flush with an interior flow limiting contour of the mixing tube.

Abstract: A method for producing hot gas for operating a turbomachine fired with at least one combustion chamber includes premixing a fuel with a plurality of operating gases by introducing fuel into the plurality of operating gases in a mixing chamber disposed upstream of the combustion chamber using a burner arrangement, wherein the fuel includes at least one of a combustible gas and a H2-rich fuel; and introducing the premixed fuel into the combustion chamber.

Abstract: A lance for a hybrid burner of a combustor of a gas turbine, includes an inner passage for a liquid fuel, an outer passage coaxially enclosing the inner passage for a gaseous fuel, a plurality of star like arranged outer nozzles branching off radially from the outer passage, a plurality of inner nozzles, which branch off radially from the inner passage and which each extend coaxially inside one of the outer nozzles, and a distributor section, which is arranged upstream of the outer nozzles in the outer passage and has a plurality of star like arranged, coaxially extending through-openings for the gaseous fuel. In order to reduce the flow resistance in the gas path of the lance, the through-openings each have an opening width which is larger in the circumferential direction than in the radial direction.

Abstract: A method for producing hot gas for operating a turbomachine fired with at least one combustion chamber includes premixing a fuel with a plurality of operating gases by introducing fuel into the plurality of operating gases in a mixing chamber disposed upstream of the combustion chamber using a burner arrangement, wherein the fuel includes at least one of a combustible gas and a H2-rich fuel; and introducing the premixed fuel into the combustion chamber.

Abstract: A lance is presented for introducing fuel into a second burner of a combustion chamber of a gas turbine installation with sequential combustion, having a first and a second combustion chamber. The lance includes a foot and a shank which projects from it. In an installed state of the lance the foot extends perpendicularly or at an angle to a main flow direction of the burner. The shank extends centrally in the burner and generally parallel to the main flow direction. At least one projecting arm, having at least one nozzle for introducing fuel, is arranged such that it extends from the shank. A respective end of the at least one arm is oriented in the main flow direction and extends generally parallel to the main flow direction.

Abstract: A premix burner, for example for a gas turbine, having a conical swirl generator (1) and a cylindrical mixing section (2) which follows it in the direction of flow, includes a high-pressure atomizer nozzle (10) with one or more fuel feed passages. The high-pressure atomizer nozzle (10) includes at least two outlet passages, through which liquid fuel enters the swirl generator (1), these passages being arranged off-center with respect to the longitudinal axis of the nozzle and being configured in such a way that the spray cone (11) of the fuel is oriented at an angle (?) with respect to the longitudinal axis of the swirl generator (1) which is smaller than the cone half-angle (?) of the swirl generator (1). The outlet passages in particular have an internal geometry with a conically narrowed section.

Abstract: A lance for a hybrid burner of a combustor of a gas turbine, includes an inner passage for a liquid fuel, an outer passage coaxially enclosing the inner passage for a gaseous fuel, a plurality of star like arranged outer nozzles branching off radially from the outer passage, a plurality of inner nozzles, which branch off radially from the inner passage and which each extend coaxially inside one of the outer nozzles, and a distributor section, which is arranged upstream of the outer nozzles n the outer passage and has a plurality of star like arranged, coaxially extending through-openings for the gaseous fuel. In order to reduce the flow resistance in the gas path of the lance, the through-openings each have an opening width which is larger in the circumferential direction than in the radial direction.

Abstract: A premix burner, for example for a gas turbine, having a conical swirl generator (1) and a cylindrical mixing section (2) which follows it in the direction of flow, includes a high-pressure atomizer nozzle (10) with one or more fuel feed passages. The high-pressure atomizer nozzle (10) includes at least two outlet passages, through which liquid fuel enters the swirl generator (1), these passages being arranged off-center with respect to the longitudinal axis of the nozzle and being configured in such a way that the spray cone (11) of the fuel is oriented at an angle (?) with respect to the longitudinal axis of the swirl generator (1) which is smaller than the cone half-angle (?) of the swirl generator (1). The outlet passages in particular have an internal geometry with a conically narrowed section.

Abstract: The invention relates to a vortex generator in a flow duct to which a fluid medium is applied, as well as method for controlling the wake flow of such a vortex generator. The task of safely avoiding the formation of a return flow zone in the core of the wake vortex (11) even under changing flow conditions is realized according to the invention in that an axial impulse is introduced in a targeted manner into the core flow of the wake vortex (11). According to a preferred embodiment of the invention, for this purpose a secondary flow is introduced at least approximately in the direction of the main flow into the core flow of the wake vortex (11) via outlet openings (12) on the vortex generator (2).

Abstract: In a premixing burner (1) for a gas turbine or hot-gas generation for the combustion of liquid or gaseous fuel, in which fuel is mixed with combustion air (9a, 9b) in a burner interior (14), is fed to a combustion chamber (3) and is burnt in this combustion chamber (3), stabilization in the part-load model is achieved in a simple and efficient way in that means (15) are provided which make it possible to recirculate hot exhaust gas (17) out of the combustion chamber (3) into the burner interior (14) and to stabilize the flame by means of selfignition processes. The means (15) are preferably a recirculation line which picks up hot exhaust gas (17) from the outer backflow zone (10) and feeds it to the burner interior (14) in the region of a burner tip (2) facing away from the combustion chamber (3), additional fuel (pilot fuel 21) being admixed with the exhaust gas (17) in the recirculation line upstream of the feed to the burner interior (14).

Abstract: What is described is a burner system with a premix burner (1), in which is provided at least one vortex generator (2), through which passes an air-containing gaseous main flow (ZL) which flows axially through the premix burner (1) and into which gaseous and/or liquid fuel is injected, downstream of the vortex generator (2), as a secondary flow for generating a fuel/air mixture, and with a combustion chamber (5) which adjoins the premix burner (1) downstream of the latter and has a combustion chamber cross section (C2) which is larger than the flow cross section (C1), delimited by the premix burner (1), directly upstream of the combustion chamber (5).

Abstract: What is described is a burner system with a premix burner (1), in which is provided at least one vortex generator (2), through which passes an air-containing gaseous main flow (ZL) which flows axially through the premix burner (1) and into which gaseous and/or liquid fuel is injected, downstream of the vortex generator (2), as a secondary flow for generating a fuel/air mixture, and with a combustion chamber (5) which adjoins the premix burner (1) downstream of the latter and has a combustion chamber cross section (C2) which is larger than the flow cross section (C1), delimited by the premix burner (1), directly upstream of the combustion chamber (5).

Abstract: In a premixing burner (1) for a gas turbine or hot-gas generation for the combustion of liquid or gaseous fuel, in which fuel is mixed with combustion air (9a, 9b) in a burner interior (14), is fed to a combustion chamber (3) and is burnt in this combustion chamber (3), stabilization in the part-load mode is achieved in a simple and efficient way in that means (15) are provided which make it possible to recirculate hot exhaust gas (17) out of the combustion chamber (3) into the burner interior (14) and to stabilize the flame by means of selfignition processes. The means (15) are preferably a recirculation line which picks up hot exhaust gas (17) from the outer backflow zone (10) and feeds it to the burner interior (14) in the region of a burner tip (2) facing away from the combustion chamber (3), additional fuel (pilot fuel 21) being admixed with the exhaust gas (17) in the recirculation line upstream of the feed to the burner interior (14).

Abstract: A premix burner consisting essentially of a swirl generator for a combustion air stream or another gaseous oxidizing medium and of conduits for injecting fuel into the swirl flow thus generated. As a result of a discontinuous cross-sectional widening at the transition to the combustion space, the swirl flow bursts open and a backflow bubble is formed, which serves for flame stabilization. For use under extreme thermal conditions, the burner front is provided with a heat shield which is fastened to a carrier structure in such a way as to allow, as unimpeded as possible, differential thermal expansions. The carrier structure is preferably provided with orifices, through which cooling air for the impact cooling of the heat shield flows. In a preferred variant, the fuel gas supply is designed as pipes which are led through orifices of the swirl generator without any fixed connection. As a result of this design, thermal stresses in the material of the burner are avoided as far as possible.

Abstract: A structured packing (which may or may not include a catalyst) formed from a mesh material having pore openings of less than 50 microns wherein the packing is provided with turbulence generators to promote flow of fluid through the pore openings and may be further provided with additional openings larger than the pores to improve bulk mixing.

Abstract: A low pressure drop, highly efficient structured packing comprises sheet material formed into vertical preferably square channels containing vortex generators formed from the sheet material. The channels, while vertically linear, are periodically interrupted by the vortex generators providing tortuous fluid paths along the channels. The thus formed vortex generators form openings between adjacent channels providing fluid communication between and uniform flow within the different channels. The packing can be utilized in fluid mixing or those operations that require multiphase mass transfer, such as absorption or distillation. The addition of a catalyst makes the structure suitable for catalytic distillation. Turbulence is provided the fluids by the tortuous vertical path with low pressure drops transversely and vertically, with optimum liquid holdup.