Abstract: A fastening device for a heat-protection shield of a gas turbine is provided with a center mounting element which has a defined installation clearance with a mounting slot in the radial direction. In the normal operating state, this mounting element has no function, such that thermal differential expansions in the radial direction between the heat-protection shield and its counterpart are possible without impairment within the limits of this defined clearance. The mounting element does not start to bear against the counterpart until the radial differential expansion exceeds the size s. The deformation of the heat-protection shield toward a component moving in a relative manner is thus limited and excessive grazing of the components against one another is avoided.

Abstract: In a method for the cooling of guide vanes and/or moving blades in the turbine stages of a gas turbine plant, a cooling medium, which contains a first fuel, is fed through the interior of the guide vanes and/or moving blades to be cooled and, using a catalyst, undergoes an endothermal chemical process therein in which the first fuel is converted at least partially into a second fuel. The cooling medium containing the second fuel is used as fuel for driving the gas turbine plant after the cooling medium has flowed out of the guide vanes and/or moving blades. In such a method, a high effectiveness of the cyclic process is highly effective and the cooling of the vanes/blades is simultaneously improved. The first fuel is a methane-containing gas, in particular natural gas, and a mixture of the first fuel with steam is used as the cooling medium and leads to a reforming of the methane in the endothermal chemical process.

Abstract: A coolable blade for a gas turbine or the like, having a blade body and a blade root, in which case the blade body is composed of a suction-side wall and a pressure-side wall, which, while forming a cavity, are connected via a leading edge, at least partly via a trailing edge and via a blade tip, the cavity is subdivided by essentially radially running separating webs into passages which form a continuous, repeatedly deflected flow path for a cooling medium, at least one blow-out opening is provided for the cooling medium, and the separating web adjacent to the trailing edge has one or more through passages close to the blade tip.

Abstract: A component of a fluid-flow machine including a flow-deflecting device which is connected in a root region to a platform, the penetration of the flow-deflecting device with the platform being provided by a pressure-side profile line, a suction-side profile line, and a leading edge base point and a trailing edge base point, and the top view of the platform essentially exhibiting the shape of a parallelogram on which there is arranged a nose running in the circumferential direction, wherein a long side of the parallelogram is arranged as a tangent to the suction-side profile line.

Abstract: A method for active suppression of hydrodynamic instabilities in a combustion system in which liquid or gaseous fuel is premixed with combustion air and the fuel/air mixture is then burnt. The mass flow of the supplied fuel is modulated on the basis of a selected time function. Simplification and increased functional reliability are achieved by the modulation which is carried out using fluidics.

Abstract: In an air-cooled turbine blade which, at the blade tip, has a shroud-band element extending transversely to the longitudinal axis of the blade, a plurality of cooling bores passing through the shroud-band element for the purpose of cooling, which cooling bores are connected on the inlet side to at least one cooling-air passage running through the turbine blade to the blade tip and open on the outlet side into the exterior space surrounding the turbine blade, improved and assured cooling is achieved owing to the fact that the cooling bores run from inside to outside in the shroud-band element at least approximately parallel to the direction of movement of the blade and in each case open upstream of the outer margin of the shroud-band element into a surface recess open toward the exterior space.

Abstract: In a heat-recovery steam generator (10) having individual flow passages (18) and a catalyst apparatus (15) which consists of individual catalyst sections provided with shut-off means, the passages can be shut off in simple manner by flow passages (18) and catalyst sections being allocated to one another in a suitable manner.

Abstract: In a method for burning a liquid fuel in a combustion system (10) which comprises a combustion chamber (11) and at least one injection nozzle (13) through which liquid fuel is injected into the combustion chamber (11) in the form of a fuel spray (16) and is burnt there with combustion air being added, disturbance-free operation in a simple manner is distinguished in that, in order to actively suppress hydrodynamic instabilities in the combustion chamber (11), the injected fuel spray (16) is modulated by having an electrical voltage applied to it during the injection process, governed by a selected time function.

Abstract: In a process for the thermal treatment of solid materials (3), in particular refuse, in which the solid materials (3) are burnt/gasified or pyrolized in a first step (5) with a lack of oxygen, and then, in an afterburning zone (14), the flue gases (6) from the first step (5) are mixed with an oxygen-containing gaseous medium (15) and are burnt with complete burn-off, the flue gases (6) emerging from the first step (5) are firstly actively homogenized in a mixing zone (7) with the addition of a gaseous oxygen-free or low-oxygen medium (8) before they are mixed with the oxygen-containing medium (15). Then, the homogenized flue-gas stream flows through a holding zone (13), in which it stays for at least 0.5 second, before, in an afterburning zone (14), the medium (15) which serves to ensure complete burn-off of the flue gas is added. The process according to the invention is distinguished by simple process steps and by a reduced level of pollutant emissions, in particular NOx, compared to the prior art.

Abstract: A method is disclosed for preventing harm caused by constrictions in the cooling holes of gas-cooled parts, in particular of gas turbines and/or burners. These constrictions form because the walls of the gas-cooled parts through which the cooling holes extend and which are covered on their outside with a protective, first coating are provided during the course of an overhaul with a second, repeat coating, and coating material is deposited in the cooling holes. Constant flow ratios in the cooling holes are achieved in a simple manner in that prior to the overhaul, the cooling holes are constricted with first means to an extent that corresponds to the later constrictions created during the course of the second coating. The first means are removed after the overhaul. The first means takes the form of an insert with holes that constrict the flow through the cooling holes.

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 fuel lance for spraying liquid and/or gaseous fuels into a combustion chamber, which fuel lance is provided with first means for the radial spraying of the liquid fuel from the liquid-fuel passage into the combustion chamber. The first means comprise a first guide tube, which, in the radial direction starting from the liquid-fuel passage, runs outward through a gas passage and an air passage. In addition, second means are provided, which comprise a second guide tube, which, in the radial direction starting from the gas passage, runs outward through the air passage and concentrically surrounds the first guide tube at a distance. Both guide tubes open in the region of a shell opening in the lance shell in such a way that the liquid-fuel jet discharging from the first guide tube discharges as a plain jet into the combustion chamber, and the fuel jets discharging from the guide tubes are surrounded in a sheath-like manner by the air flowing out of the air passage through the shell opening.

Abstract: After the economizer, an injection water pipe branches off the connecting pipe between economizer and evaporator in order to control the steam temperature. The injection water pipe is provided with a control device for controlling the injection water flow. The injection water flowing through the injection water pipe is injected into the steam coming from the evaporator at a mixing point located before the superheater. In order to control the position of the control device in the injection water pipe, the enthalpy at the superheater outlet is calculated from the parameters pressure and temperature and is compared with a desired enthalpy resulting from the desired parameters.

Abstract: In some operating states, supplemental additional sealing steam must be fed to the sealing-steam system of a steam turbine. The feeding of supplemental sealing steam from the live-steam line involves considerable problems. According to the invention, therefore, the sealing-steam system is connected via a feeder line to a bleed point of the superheater of the boiler, so that the temperature of the supplemental sealing steam is well below the live-steam data and, in particular, is compatible with the material temperature in the region of the high-pressure shaft seal.