Abstract: A cooling circuit for removing waste heat from a cooling device of an electromechanical converter is provided. The cooling circuit includes a chilling medium, a cooler for extracting heat from the chilling medium, a return connecting the cooling device of the converter to the cooler and conducts warm chilling medium, a feed connecting the cooler to the cooling device of the converter and conducts cool chilling medium, and an absorption chiller for extracting heat from the chilling medium. The absorption chiller is driven by the heat of the warm chilling medium that is in the return.

Abstract: Disclosed is an annular flow duct for a turbomachine, the flow duct arranged concentrically about a machine axis running in the axial direction and defined by a boundary wall of circular cross section for directing a main flow, wherein the boundary wall has a plurality of return flow passages distributed over its circumference and through which in each case a partial flow is detached from the main flow at a bleed position and returned to the main flow at a feed position situated upstream of the bleed position, and having aerofoils, arranged radically in the flow duct, of a blade ring, the aerofoil tips of which lie opposite the boundary wall, with a gap formed in each case, wherein the aerofoils are movable in a predetermined rotation direction along the circumference of the boundary wall. Furthermore, a compressor which is insensitive to pumping and flow separations, as viewed in rotation direction, the bleed position of each return flow passage lies upstream of the corresponding feed position.

Abstract: A power plant including a turbine unit having a turbine, a generator connected to the turbine for power transmission, and a cooling device for cooling the generator is provided. The cooling device is provided to release waste heat from the generator to a device of the power plant. Waste heat may be used in the power plant process, thus attaining increased efficiency.

Abstract: A cooling circuit for removing waste heat from a cooling device of an electromechanical converter is provided. The cooling circuit includes a chilling medium, a cooler for extracting heat from the chilling medium, a return connecting the cooling device of the converter to the cooler and conducts warm chilling medium, a feed connecting the cooler to the cooling device of the converter and conducts cool chilling medium, and an absorption chiller for extracting heat from the chilling medium. The absorption chiller is driven by the heat of the warm chilling medium that is in the return.

Abstract: A method for protecting a burner from being heated excessively during the combustion of a fuel in a combustion chamber is provided. The fuel is injected through a fuel nozzle at the same time as an inert gas in the surroundings of the injected fuel is injected into the combustion chamber in such a manner that the fuel is separated spatially from an oxidizer by the inert gas until an ignitable mixture of the fuel is produced.

Abstract: Burners in prior art exhibit combustion instabilities in certain ranges. The operating range of burners is restricted by said instabilities. In an inventive burner, the combustible has a concentration distribution, whereby the concentration of the combustible reduces in a radial direction from the interior to the exterior.

Abstract: The invention relates to a burner having an annular premixing channel in which fuel can be discharged in a radially distributed manner. The radial distribution of the fuel can be regulated during operation of the burner in that fuel can be supplied, independently of one another, into a first and a second part of admission devices having admission holes varying radially in opposite direction by means of fuel supply lines. The invention also relates to a method for operating a gas turbine in which radial distribution of the fuel is regulated in a premixing channel of a burner.

Abstract: Disclosed is an annular flow duct for a turbomachine, the flow duct arranged concentrically about a machine axis running in the axial direction and defined by a boundary wall of circular cross section for directing a main flow, wherein the boundary wall has a plurality of return flow passages distributed over its circumference and through which in each case a partial flow is detached from the main flow at a bleed position and returned to the main flow at a feed position situated upstream of the bleed position, and having aerofoils, arranged radically in the flow duct, of a blade ring, the aerofoil tips of which lie opposite the boundary wall, with a gap formed in each case, wherein the aerofoils are movable in a predetermined rotation direction along the circumference of the boundary wall. Furthermore, a compressor which is insensitive to pumping and flow separations, as viewed in rotation direction, the bleed position of each return flow passage lies upstream of the corresponding feed position.

Abstract: The invention relates to a method for compensating variations in fuel composition in a gas turbine system consisting of at least two parallel-operated burner stages, wherein the fuel supply to at least two of the burner stages is adjusted in response to variations in fuel composition, wherein the fuel split between the burner stages, i.e. the relative increase in speed of the fuel supplied to the burner stages, is adjusted to a target value or maintained at a target value during adjustment of the fuel supply. The target value can, for example be a constant or a function of one or several variables. More particularly, the gas turbine system can comprise a pilot burner stage and a main burner stage. When the fuel supply is adjusted, the fuel split between the pilot burner stage and the main burner stage is adjusted to a target value or maintained at a target value.

Abstract: The invention relates to a method for compensating variations in fuel composition in a gas turbine system consisting of at least two parallel-operated burner stages, wherein the fuel supply to at least two of the burner stages is adjusted in response to variations in fuel composition, wherein the fuel split between the burner stages, i.e. the relative increase in speed of the fuel supplied to the burner stages, is adjusted to a target value or maintained at a target value during adjustment of the fuel supply. The target value can, for example be a constant or a function of one or several variables. More particularly, the gas turbine system can comprise a pilot burner stage and a main burner stage. When the fuel supply is adjusted, the fuel split between the pilot burner stage and the main burner stage is adjusted to a target value or maintained at a target value.

Abstract: The invention relates to a burner having an annular premixing channel in which fuel can be discharged in a radially distributed manner. The radial distribution of the fuel can be regulated during operation of the burner in that fuel can be supplied, independently of one another, into a first and a second part of admission devices having admission holes varying radially in opposite direction by means of fuel supply lines. The invention also relates to a method for operating a gas turbine in which radial distribution of the fuel is regulated in a premixing channel of a burner.

Abstract: The invention relates to a burner apparatus (1) for burning fuel (5) with air (4) to combustion gas, in particular within a combustion turbine, comprising a premixing chamber (3) for premixing fuel (5) and air (4) with. The premixing chamber (3) having an air inlet (8) for air (4) to enter said premixing chamber (3), a fuel inlet (11) for a gaseous or liquid fuel (5) to enter said premixing chamber (3), and an outlet (12) for a mixture of air (4) an fuel (5) wherein, the fuel inlet (11) being located between said air inlet (8) and said outlet (12). The burner apparatus (1) Further comprises at least one air blocking member (2) situated at the air inlet (8) for stabilising a burner premixing flame by locally blocking the flow of air (4) entering said premixing chamber (3) so that downstream said outlet (12) a locally inhomogeneous fuel concentration (23) results generating a locally hot stream of combustion gas being hotter than the average flame temperature.

Abstract: Burners in prior art exhibit combustion instabilities in certain ranges. The operating range of burners is restricted by said instabilities. In an inventive burner, the combustible has a concentration distribution, whereby the concentration of the combustible reduces in a radial direction from the interior to the exterior.

Abstract: The invention relates to a premix burner for burning fuel with air to combustion gas, in particular within a combustion turbine. Profiling means are provided for profiling the mass stream of the combustion air in a direction radial to an annular shaped air channel in order to generate a radial varying fuel/air mixture that stabilises the combustion. Accordingly, the invention also relates to a gas turbine and a process for burning fuel in air.

Abstract: The invention relates to a burner apparatus (1) for burning fuel (5) with air (4) to combustion gas, in particular within a combustion turbine, comprising a premixing chamber (3) for premixing fuel (5) and air (4) with. The premixing chamber (3) having an air inlet (8) for air (4) to enter said premixing chamber (3), a fuel inlet (11) for a gaseous or liquid fuel (5) to enter said premixing chamber (3), and an outlet (12) for a mixture of air (4) an fuel (5) wherein, the fuel inlet (11) being located between said air inlet (8) and said outlet (12). The burner apparatus (1) Further comprises at least one air blocking member (2) situated at the air inlet (8) for stabilising a burner premixing flame by locally blocking the flow of air (4) entering said premixing chamber (3) so that downstream said outlet (12) a locally inhomogeneous fuel concentration (23) results generating a locally hot stream of combustion gas being hotter than the average flame temperature.

Abstract: The invention relates to a premix burner (1) for burning fuel (5) with air (4) to combustion gas, in particular within a combustion turbine. Profiling means (2) are provided for profiling the mass stream of the combustion air (4) in a direction radial to an annular shaped air channel (3) in order to generate a radial varying fuel/air mixture that stabilises the combustion. Accordingly, the invention also relates to a gas turbine (110) and a process for burning fuel in air.