Abstract: In a combustion chamber for a gas turbine, noise absorption is achieved over a wide frequency range with simultaneous cooling of the arrangement and low space requirement by the inner wall being formed, at least in a partial region of the inner walls by at least two perforated plates arranged essentially parallel to one another, and by the distances between the perforated plates and the geometrical dimensions of the openings being selected in such a way that a plurality of mutually connected Helmholtz resonators is formed and that, in addition, further expedients are available which act to absorb noise.

Abstract: A casing for a steam or gas turbine comprises a shell and two flanges. The wall thickness of the shell is varied in an upper region facing away from the flange, in two central regions and in two lower regions facing the flanges, such that the upper region facing away from the flanges is reinforced in comparison with the lower regions facing the flanges. The lower regions facing the flanges are more flexible than the flanges which are attached by screws, and the partially reinforced central region and the reinforced upper region, and act as a joint to compensate for deformation, particularly in the radial direction. Consequently, the casing remains considerably more round in operation. The reduced radial clearance (achieved by reduced deformation) between the casing and the ends of the turbine blades leads to considerably increased efficiency during operation of the turbine.

Abstract: In a method of manufacturing a plurality of steam turbines for use in various applications which differ in the respective thermodynamic parameters such as, for example, cooling-water temperature, ambient temperature, given boiler data, process-steam requirement, etc., the steam turbines in each case having at least one high-pressure part with first blading and a control-wheel stage for part-load operation, a simplification and cost saving is achieved owing to the fact that standard blading, which is identical for all the steam turbines, is used as first blading, and in that the adaption of the individual steam turbine to the thermodynamic parameters of the respective application is carried out by appropriate design or variation of the control-wheel stage.

Abstract: The arrangements according to the invention and the method according to the invention serve to cool platforms in turbomachines. To this end, in two platforms 210, 210′ arranged directly next to one another and having a separating gap 211 running between the platforms, at least one cooling passage 230 is arranged along the separating gap 211. In this case, the cooling passage 230 runs approximately parallel to the surface of the platforms 210, 210′. The cooling passage 230 is preferably designed as a slit-like recess in at least one side wall adjacent to the separating gap 211. If blades 220, 220′ are arranged on the platforms 210, 210′, the cooling passage 230 expediently runs approximately centrally between the blades. In addition, the cooling passage 230 preferably has a course similar to the course of the blade profile.

Abstract: In a burner (14) with at least one fuel supply system (15, 16) through which the burner (14) is fed a fuel flow (12), and the fuel fed is injected via fuel nozzles and subsequently burned in a combustion chamber (11), the formation and amplification of pressure fluctuations in the combustion chamber is prevented in a simple way in terms of design by virtue of the fact that means (17) are provided which prevent periodic pressure fluctuations which occur in the combustion chamber from leading to fluctuations in the fuel flow (12) in the fuel supply system (15, 16).

Abstract: Pins (23) consisting of a material having high thermal conductivity are introduced, alternately with blow-out orifices (22) for a coolant (9), into the material, to be cooled, of a component (141), in such a way that said pins project out of the component on the cooling side (12) of the latter. These pins are cooled in the region which projects out of the component whilst heat is supplied to them in the region which is embedded in the component. The alternating arrangement with blow-out orifices ensures that the flow (7) passes around the pins. This point is important particularly when the pins are arranged in a narrow gap, such as occurs especially in the cooling of the trailing edges of gas turbine blades. The necessary number of blow-out orifices and therefore the coolant consumption is reduced.

Abstract: Steam turbines with or without a control stage are constructed with the same number of control valves. There are preferably two control valves in each case. The valve subassembly, the turbine outer casing and parts of the turbine inner casing are of identical design and can be used for steam turbines with or without a control stage. In the case of the steam turbine illustrated with a control stage, the inner casing is provided with integrated nozzle boxes, which are separated from each other by intermediate walls. In the case of a steam turbine without a control stage, the nozzle boxes, and accordingly, also the intermediate walls are missing.

Abstract: A heat shield for a gas turbine, which heat shield encloses in an annular manner the moving blades, rotating in the hot-gas duct of the gas turbine, of a stage of the gas turbine and consists of a plurality of heat-shield segments which are arranged one behind the other in the circumferential direction, are curved in the shape of a segment of a circle and are cooled from outside, and the longitudinal sides which are designed as correspondingly curved rails running in the circumferential direction and having in each case a pair of arms of which project in the axial direction, run in parallel and are at a distance from one another, the heat-shield segments, while forming a cavity to which cooling air can be admitted, are fastened to the inside of an annular carrier, which concentrically surrounds the heat shield in such a way that in each case a radial gap is formed between the longitudinal sides of heat-shield segments and the adjacent elements which define the hot-gas duct on the outside.

Abstract: Moving blades of a fluid-flow machine are fastened in a circumferential slot on the rotor by means of blade roots. For the installation of the last moving blade, a gap is provided between the first and penultimate blade. After the latter has been fitted, a residual gap remains in the circumferential slot, and this residual gap is filled by means of whole intermediate pieces and halved intermediate pieces (7a, 7b), which are arranged between the moving-blade roots. According to the invention, the inner sides (8) of the halved intermediate pieces (7a, 7b), which inner sides (8) face the center of the circumferential slot, are of hook-shaped design. In this case, the inner side (8) of one half (7a) of a halved intermediate piece forms the geometric negative of the inner side (8) of the other half (7b) of the halved intermediate piece. As a result, the two halves (7a, 7b) can be connected to one another in a positive-locking manner.

Abstract: The arrangements and the methods serve for the efficient and reliable cooling of components 210, in particular in turbomachines, even in the event of a local increase in the static pressure 234 of a hot fluid which flows over the component. In order to ensure sufficient cooling of the components 210, the distance between the cooling holes 240 is in each case selected in such a way that the cooling holes 240 in the region of increased static pressure 234 of the hot fluid are at a smaller distance from one another than in the regions of lower static pressure. A typical design of the invention is shown in FIG. 3.

Abstract: An apparatus for the generation of energy by means of a fluid-flow machine is described, for the drive of which a compressor arrangement for compressing a compressible medium, preferably air, is provided, which medium, via a feed-line system, can be fed to the fluid-flow machine directly or after the interposition of a combustion chamber, in which the compressed medium can be ignited with the addition of fuel. The invention is distinguished by the fact that the compressor arrangement provides at least one compressor stage, in which the medium can be compressed isothermally.

Abstract: The present invention relates to an apparatus and a method for bending hard-drawn copper conductor bars for rotor windings of turbo-generators and engines. This method makes it possible to prevent heating up and accompanying transformation of hard-drawn copper into soft copper, which leads to a reduction in the stability with respect to centrifugal forces and thermal expansions. The apparatus and the method permit automatic, step-by-step bending of hard-drawn copper conductor bars, with sensing of the bending radius achieved and correction in the direction of the desired bending radius. For this purpose, initially a hard-drawn copper conductor bar is bent by means of a pair of bending cylinders to a previously set bending radius, the bending radius actually achieved is measured and a correction of the bending radius used in the next step takes place, in order to achieve an approximation to the desired bending radius.

Abstract: A combustor system for a gas turbine is disclosed in which fuel is mixed with an air stream entering the combustor and is then burned, and the resulting combustion air stream is fed downstream from the combustor to a turbine. A quick and efficient mixing of the air stream and fuel is achieved in that the combustor has an annular diffuser into which the air stream enters. Downstream from the diffuser and communicating with it, at least one essentially annular, toroidal chamber is provided. Mixing pipes extend downstream from the annular, toroidal chamber and are distributed over the periphery of the toroidal chamber. Downstream from the mixing pipes, an annular combustion chamber is provided into which the mixing pipes merge.

Abstract: Process of plugging cooling holes (4) of a gas turbine component (1) with an external surface (7), having a cavity (2) and a plurality of cooling holes (4) before coating the gas turbine component (4), characterised in that mask material (6) is applied to the external surface (7) of the component (1) while a fluid is forced through the cooling holes (4), the mask material (6) is thickened while the fluid is forced through the cooling holes (4), the cooling holes (4) are plugged with plug material (6b), the mask material (6a) is removed from the external surface (7) of the component (1), the component (1) and the plugged cooling holes (4) are coated and the plug material (6b) is removed from the cooling holes (4).

Abstract: A separator (8) is arranged downstream of the superheater section (4) of the once through heat recovery steam generator (1). A branch line (9) running to the separator (8) is branched off from an outflow line (5) running from the superheater section (4) to the steam turbine (6). An outflow line (11) for separated water runs from the separator (8) to the once through heat recovery steam generator (1). The steam separated in the separator (8) can flow through a bypass line (13) to the condensor/hotwell (14). For starting up the once through heat recovery steam generator (1), the latter is filled with water, the water is loop-circulated through the separator (8) and the outflow line (11) in the once through heat recovery steam generator (1) or water steam cycle and the supply of heat is initiated. In this case, the main shutoff member (7) upstream of the steam turbine (6) is closed, and the branch shutoff member (10) in the branch line (9) upstream of the separator (8) is open.

Abstract: A securing fixture for a screw or a nut includes a holding device for holding the head of the screw or the nut and is provided with a projection which comprises a parting location which can be parted by means of a chisel. The projection also has a projection end which can be welded or adhesively bonded.

Abstract: The invention relates to a plate valve (1) as used for the actuator of a control valve. It comprises an inlet (2) with a sealing seat (3) around which the openings of the outlet (7) are arranged, and it has two plates (4), (5), between which there is an interspace (13). Both plates (4), (5) are attached to the housing (11) by springs (6) in a spring space (12). The spring space (12) is operatively connected to a proportional valve by an opening (14) and a line (9). If the pressure in the spring space (12) is lowered by the proportional valve, the additional plate (5) first of all drops as a result and thereby exposes the outflow openings (10) in the large plate (4). There is a slight flow of the oil from the inlet (2) through the orifice plates (8) situated in the plate (4) and through the outflow openings (10) to the openings of the outlet (7). In a second stage, the plate (4) then drops and thereby exposes the openings of the outlet (7).