Abstract: A swirler including an annular housing with limiting walls. At least two vanes are arranged in the annular housing including the sidewalls of the swirler. The leading edge area of each vane has a profile, which is oriented parallel to a main flow direction prevailing at the leading edge position, wherein the profiles of the vanes turn from the main flow direction prevailing at the leading edge position to impose a swirl on the flow, and wherein, with reference to a central plane of the vanes the trailing edges are provided with at least two lobes in opposite transverse directions. A burner for a combustion chamber of a gas turbine including such a swirler and at least one nozzle having its outlet orifice at or in a trailing edge of the vane and to a method of operation of such a burner.

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: The invention concerns a method of operating a gas turbine with staged and/or sequential combustion. The burners of a second stage or a second combustor are singularly and sequentially switched on during loading and switched off during de-loading. The total fuel mass flow and the compressor inlet guide vanes are adjusted at the same time to allow controlling gas turbine operation temperatures and engine power with respect to the required CO emission target.

Abstract: A method for operating a gas turbine plant is provided. According to the method a first fuel gas with a first fuel reactivity and a second fuel gas with a second fuel reactivity which is higher than the first fuel reactivity are injected into a combustor of the gas turbine, and the ratio of the mass flows of the second fuel gas to the first fuel gas is controlled depending on the combustion behavior of the combustor. A gas turbine plant configured to carry out the method is further shown.

Abstract: A plant with a fuel system includes a gas separation system for separating at least a first fuel fraction with high hydrocarbons, which has a higher concentration of high hydrocarbons than an incoming fuel gas. A second fuel fraction with a reduced concentration of high hydrocarbons is provided. A fuel gas supply line for incoming fuel and/or a fuel line for the second fuel fraction leads to the combustor of the gas turbine for feeding fuel gas into the combustor. Further a fuel line for feeding the first fuel fraction leads to the at least one combustor to control the combustion behaviour by controlled addition of the first fuel fraction into the combustor. The disclosure further refers to the operation of such a plant by controlling the combustion behaviour with the controlled addition of a high hydrocarbon fuel.

Abstract: A method and an apparatus are provided for the combustion of gaseous fuel containing hydrogen or consisting of hydrogen, with a burner which provides a swirl generator, into which liquid fuel is fed centrally along a burner axis, at the same time forming a conically shaped liquid fuel column which is surrounded by a rotating combustion air stream which flows tangentially into the swirl generator and into which, additionally, a gaseous and/or liquid fuel is injected so as to form a fuel/air swirl flow which is transferred downstream of the swirl generator, along a transitional portion, into a mixing zone following the transitional portion downstream and which is ignited and burnt in a combustion chamber following downstream, at the same time forming a backflow zone.

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: The invention refers to burner arrangement for producing hot gases to be expanded in a gas turbine, including a burner inside a plenum, where the burner has means for fuel injection, means for air supply and means for generating an ignitable fuel/air mixture inside the burner, and a combustion chamber following downstream said burner having an outlet being fluidly connected to the gas turbine. The invention is characterized in that the means for air supply includes at least two separate flow passages, and that the one of the two flow passages is fed by a first supply pressure and the other flow passage is fed by a second supply pressure.

Abstract: A method for the combustion of hydrogen-rich, gaseous fuels in combustion air in a burner of a gas turbine includes injecting the hydrogen-rich, gaseous fuel at least partially isokinetically with respect to the combustion air such that the partially hydrogen-rich, gaseous fuel is injected at least partially in the same direction and at least partially at the same velocity as the combustion air.

Abstract: A system for controlling NOx emissions and combustion pulsation levels of a gas turbine having a gas turbine combustion system, having a single combustion chamber and multiple burners, includes a cascade structure having a first and second control level (1, 2), the first level (1) having a device to control NOx emissions and generate combustion pulsation target levels based on the difference between measured and target NOx emission levels, and the second level (2) having a device to control pulsation levels and generate a ratio (?) of fuel flow to different types of burners or to different stages of each burner. The fuel flow ratio (?) is based on the difference between the measured and generated target pulsation levels. The control system enables the operation of a gas turbine to meet NOx emission requirements, while maintaining combustion pulsation levels within limits that ensure improved lifetime of the combustion system.

Abstract: A swirler including an annular housing with limiting walls. At least two vanes are arranged in the annular housing including the sidewalls of the swirler. The leading edge area of each vane has a profile, which is oriented parallel to a main flow direction prevailing at the leading edge position, wherein the profiles of the vanes turn from the main flow direction prevailing at the leading edge position to impose a swirl on the flow, and wherein, with reference to a central plane of the vanes the trailing edges are provided with at least two lobes in opposite transverse directions. A burner for a combustion chamber of a gas turbine including such a swirler and at least one nozzle having its outlet orifice at or in a trailing edge of the vane and to a method of operation of such a burner.

Abstract: A method for the combustion of hydrogen-rich, gaseous fuels in combustion air in a burner of a gas turbine includes injecting the hydrogen-rich, gaseous fuel at least partially isokinetically with respect to the combustion air such that the partially hydrogen-rich, gaseous fuel is injected at least partially in the same direction and at least partially at the same velocity as the combustion air.

Abstract: The combustion chamber has a body with nozzles to inject a fuel to be burnt therein. The nozzles define a plurality of groups to be fed in parallel. The nozzles of each group define at least two stages that are differently operated according to the different operating conditions. The combustion chamber also has a manifold for collecting a fuel to be distributed among the groups, a plurality of supply elements distributing the fuel originating from the manifold to each group, for each group, splitters for diverting the fuel coming from the supply elements between the stages.

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 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 system (S) for controlling nitrogen oxide (NOx) emissions and combustion pulsation levels of a gas turbine having a gas turbine combustion system, having a single combustion chamber and multiple burners, includes a cascade structure having a first and second control level (1, 2), the first level (1) having a device to control NOx emissions and generate combustion pulsation target levels based on the difference between measured and target NOx emission levels, and the second level (2) having a device to control pulsation levels and generate a ratio (?) of fuel flow to different types of burners or to different stages of each burner. The fuel flow ratio (?) is based on the difference between the measured and generated target pulsation levels. The control system (S) enables the operation of a gas turbine to meet NOx emission requirements, while maintaining combustion pulsation levels within limits that ensure improved lifetime of the combustion system.

Abstract: A method and an apparatus are provided for the combustion of gaseous fuel containing hydrogen or consisting of hydrogen, with a burner which provides a swirl generator, into which liquid fuel is fed centrally along a burner axis, at the same time forming a conically shaped liquid fuel column which is surrounded by a rotating combustion air stream which flows tangentially into the swirl generator and into which, additionally, a gaseous and/or liquid fuel is injected so as to form a fuel/air swirl flow which is transferred downstream of the swirl generator, along a transitional portion, into a mixing zone following the transitional portion downstream and which is ignited and burnt in a combustion chamber following downstream, at the same time forming a backflow zone.

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 lance for introducing fuel into a combustion chamber of a burner, in particular of a turbine plant is provided. The lance includes a lance head, a fuel feed, an oxidator feed and a control device. The lance head projects into the combustion chamber and includes a fuel nozzle and an oxidator outlet orifice. The fuel feed extends in the lance and is connected to the fuel nozzle. The oxidator feed extends in the lance head and is connected to the oxidator outlet orifice. The control device controls a flow cross sectional area of the oxidator feed. The control device has a control piston installed in the lance head with stroke adjustability for stroke-dependent controlling of the flow cross sectional area of the oxidator feed.

Abstract: In a fuel lance by means of which fuels can be injected, via at least two separate passages, into a combustion chamber alternately or simultaneously at an injection location arranged substantially at the lance tip, reliable operation is achieved, without the risk of flashbacks and also without coking, by virtue of the fact that the fuel lance, in addition to fuel, also passes purge air to the injection location, and that the purge air, at the injection location, is routed between the two fuel systems, in such a manner that these systems are shielded from one another by the purge air.