Abstract: A coolable casing of a gas turbine or the like, with a plurality of arcuate casing segments (10) which are arranged so as to be contiguous with one another in a circumferential direction, to form an essentially closed casing ring surrounding a rotor (110), in particular of a high-pressure turbine, at least one annular casing cooling chamber (15) which is formed in the radial direction between the casing segments (10) and arcuate guide segments (30) provided with a multiplicity of passage orifices (34), at least one air guide chamber (25) which is formed in the radial direction between the guide segments (30) and at least one carrier segment (20), and at least one air supply duct (26) which is made on the carrier segment (20) and opens into the air guide chamber (25), the guide segments (30) being mounted loosely with radial play. This ensures stress-free reception, even in the case of intensive operations having high temperature gradients.

Abstract: An apparatus for vitrifying heavy-metal-containing residues having a chlorine content above 10% by mass, in particular from flue gas cleaning, which are melted in a melting furnace, the constituents which cannot be incorporated into the melt are separated in the main furnace into two fractions, the first fraction comprising the readily volatile components and the second fraction comprising the salt-like less volatile components, and the first fraction is evaporated off, conducted out of the furnace together with the exhaust gas and collected as condensate, and the second fraction is separated from the surface of the melt as liquid salt and is discharged.

Abstract: A method of applying a surface coating to a stator vane (1) of a gas turbine, the stator vane (1) comprising a platform (3) with an outer surface (4) connected to the stator of the gas turbine and an airfoil (2) connected to the platform (3), the method comprising the steps of each stator vane (1) is provided as a singlet, a base layer coating (7) affording resistance to oxidation is applied to surfaces of said stator vane (1) and said outer surface (4) of the platform (3) to be exposed to hot gases of the gas turbine, and a top layer coating (8) affording thermal resistance is applied to all coated surfaces of said stator vane (1) and the outer surface (4) of the platform (3), and welding the stator vanes (1) together, wherein a welding filler material (10) is placed between said walls of two adjacent platforms (3) of said stator vane (1), welding said singlets to one another at the margins of walls of said platform (3) to said welding filler material (10).

Abstract: In a premix burner, the swirl-stabilized interior space (18) has a conical inner body (13) running in the direction of flow. The outer casing of the interior space (18) is pierced by tangentially arranged air-inlet ducts (11a, 12a) through which a combustion-air flow (16) flows into the interior space (18). The swirl flow (23) forming in the interior space (18) is enriched with a fuel via at least one fuel lance (17). The mixture of the two media is then formed in the downstream mixing tube (21). The mixing tube (21) then merges into a combustion space (31) via a jump in cross section, a backflow zone (32) forming in the region of the plane of the jump in cross section, which backflow zone (32) ensures the stability of the combustion.

Abstract: In a generator cooling system (10) for a generator used for current generation in a power station, said generator having a generator cooler (11) which is arranged, together with further coolers (12, . . . , 17), in a closed intermediate cooling circuit (18) which transfers heat to a main cooling water system via at least one intermediate cooler (19, 20), increased capability is achieved by providing, in the intermediate cooling circuit (18), means (32) which improve the transmission of heat from the generator cooler (11) into the main cooling water system.

Abstract: A combination power station with power/heat cogeneration. The combination power station includes at least one gas turbine driven by combustion gases from a combustion chamber and at least one steam turbine working in a water/steam circuit. The water/steam circuit converts water into steam in a first apparatus by hot combustion gases emerging from the at least one gas turbine. The steam is supplied to the at least one steam turbine. A separate heat transfer medium is arranged in a heat exchange relationship with a heat consumer and is heated in a second apparatus by thermal energy extracted from the water/steam circuit at a plurality of extraction points each having a different temperature. The combination power station includes means for selectively connecting the second apparatus to the plurality of extraction points depending upon a thermal output and an inlet temperature required by the heat consumer.

Abstract: In a burner for a heat generator, having a swirl generator (100) arranged upstream of the combustion zone (30), fuel injection is connected with the combustion air (115), swirled in the swirl generator, in such a way that the injection angle of the fuel jet (105) belonging to the fuel nozzle (104) corresponds approximately to the setting angle of the sectional bodies forming the swirl generator relative to the axis (60) of the burner.

Abstract: An output stage of an axial-turbine having a high channel divergence has a row of curved vanes and a row of narrowed twisted blades. The curved vanes include, in an axial direction, a positive sweep at their rotor-side end, head and a negative sweep at their stator-side end, with respect to a run of the rotor-side channel boundary. In an area of a stator-side channel boundary a negative sweepback predominates, so that between the curved vanes and the twisted blades an axial diffuser that steadily widens toward the stator-side channel boundary is formed. As a result, an increasing delay of an axial component of a flow agent can occur. The negative sweep at the stator-side end is formed such that at least one of a vane trailing edge and a vane leading edge is directed substantially perpendicularly to the stator-side channel boundary.

Abstract: A method of controlling turbomachines is specified, a characteristic signal, in particular a performance signal, normally being fed to the controller as a controlled variable, but this performance signal, together with a number of further signals significant of the performance from the plant circuit, forming a signal set in a comparison and selection unit, and the signals from this signal set being compared with one another. The maximum selection among the signals, formed at the same time in the comparison and selection unit 2.1, yields the signal of the controlled variable that is forwarded to the controller 1.1. In addition, monitoring as to whether the performance signal is the maximum signal is performed. In addition, a device for controlling turbomachines according to the method is specified, which device has a control loop 1 for the output of actuating signals for control devices of the plant, the control loop 1 being preceded by a monitoring loop 2 that has a comparison and selection unit 2.

Abstract: A method for the incineration of refuse in an incineration cylindrical rotary kiln and for treating the resulting slag from the incineration of the refuse. The method includes the steps of removing the slag or ash from the cylindrical rotary kiln in a dry state and immediately separating the slag or ash in a first screening stage into at least two fractions, including a first fraction or screen underflow having a particle size of less than 32 mm. The method includes the further steps of feeding the first fraction or screen underflow to a second classifying stage where the first fraction or screen underflow is separated into a fine function having a particle size of up to 2 mm and the further step of returning at least part of the fine fraction to an air-inlet side of the cylindrical rotary kiln for incineration of the fine fraction.

Abstract: In a method of making a recess termination in a component, the recess (2) extending with its tip (4) from the surface (3) of a wall (1) of the component into the interior of the wall (1), the tip (4) of the recess (2) is deflected in its direction by at least about 180.degree. relative to the main extension direction of the recess (2), the deflection being effected in a curvature (6) which is generously dimensioned from the point of view of notch and fracture mechanics, the maximum radius (4) of curvature being placed at the point of maximum stress in the wall (1), the tip (4) of the recess (2) ending in an at least largely relieved region, and the wall piece in the interior of the arc (6) of curvature remaining connected to the rest of the wall (1) via an adequately dimensioned material bridge (5).

Abstract: In a method of cooling the thermally highly stressed units of a gas turbine, a steam quantity (31, 32) which first of all cools a turbine (3, 5) is used, and then the same steam quantity is directed into a combustion chamber (2, 4). After this combustion chamber has been cooled, this steam quantity is introduced into the burn-out zone of the relevant combustion chamber. In this way, the combustion, designed for low NOx emissions, of the relevant combustion chamber is not affected by this introduction of the steam quantity; furthermore, with this introduced steam quantity, the burn-out zone can be moderated for minimizing the remaining pollutant emissions.

Abstract: Platform cooling having a guide-blade platform (30; 60) which is subjected to a hot-gas stream (20) and is separated by a gap (36; 66) from a combustion-chamber segment (40; 70) arranged upstream, one or more segment cooling bores (42; 72) being made in the combustion-chamber segment (40; 70), which segment cooling bores (42; 72) connect a cooling-air chamber (44; 74) to the gap (36; 66). The guide-blade platform (30; 60) has a surface (34; 64) on the downstream side in the region of the gap (36; 66), the axes of the one or more segment cooling bores (42; 72) running roughly tangentially to said surface (34; 64).

Abstract: An arrangement and method for measuring a distance between rotating and stationary parts of a device, such as a turbine. The arrangement and method allow for the measurement of a distance between the tip of the rotating bodies arranged on a rotor of the turbine, and the inside of a casing that encloses the rotor. The arrangement and method provide for at least one abrasion-tolerant layer of a specified thickness arranged on the inside of the casing opposite the tip of the rotating body at a specified thickness. The at least one abrasion-tolerant layer includes at least one indicator that can be detected in the exhaust gas of the turbine, thereby providing indication of abrasion between the tip of the rotating body and the abrasion-tolerant layer.

Abstract: In a cooling system for the trailing edge region of a hollow gas turbine blade, there extends from the blade root (1) to the blade tip (2) a duct (3) through which the flow passes longitudinally and which, in the region of the blade body (4), is delimited by the inner walls of the trailing edge (5), the suction side (6) and the pressure side (7) and by a web (9), the inner walls of the suction side and of the pressure side being provided with a plurality of ribs (8) running at least approximately parallel. The ribs (8) run obliquely from the web (9) in the direction of the trailing edge (5) and are directed radially outward on at least one of the two inner walls. The suction-side ribs and the pressure-side ribs are offset relative to one another over the blade height. The ratio of the height (h) of the ribs (8) to the local height (H) of the duct (4) is constant over the longitudinal extent of the ribs.

Abstract: In a method of operating a burner of a heat generator, in which the burner essentially includes a swirl generator for a combustion-air flow, a mechanism for injecting at least one fuel into the combustion-air flow, and a number of transition passages for passing a flow formed in the swirl generator into a mixing tube arranged downstream of the transition passages, a predetermined quantity of a second fuel having a good ignition quality is injected into the reaction zone in order to stabilize the combustion in the combustion space.