Abstract: Suitable means for driving a flow are arranged in annular or ring-segment-shaped cavities that are formed in particular in multi-shell casings of turbomachines. Arranged inside the cavity are ejectors that are supplied via suitable means with a motive-fluid flow which in turn excites the flow, preferably a circumferential flow or a helical flow. The invention is suitable in particular for avoiding casing distortions when turbomachines are at rest.

Abstract: In order to avoid the “buckling” of multi-shell turbomachine casings during a cooling phase following the shutdown, it is proposed to provide means in order to suitably discharge warm medium which collects at a point of the casing cavity situated at the highest geodetic level. In an embodiment, it is proposed to allow the corresponding lines to open out in the stack of a power plant; the stack draft effect assists the flow even further. Regulating members are advantageously provided in the lines in order to shut off these lines during operation of the turbomachine on the one hand and in order not to arrange the flow through the casing cavities too intensively on the other hand.

Abstract: In order to avoid the “buckling” of multi-shell turbomachine casings during a cooling phase following the shutdown, it is proposed to provide means in order to suitably discharge warm medium which collects at a point of the casing cavity situated at the highest geodetic level. In an embodiment, it is proposed to allow the corresponding lines to open out in the stack of a power plant; the stack draft effect assists the flow even further. Regulating members are advantageously provided in the lines in order to shut off these lines during operation of the turbomachine on the one hand and in order not to arrange the flow through the casing cavities too intensively on the other hand.

Abstract: Suitable means for driving a flow are arranged in annular or ring-segment-shaped cavities that are formed in particular in multi-shell casings of turbomachines. Arranged inside the cavity are ejectors that are supplied via suitable means with a motive-fluid flow which in turn excites the flow, preferably a circumferential flow or a helical flow. The invention is suitable in particular for avoiding casing distortions when turbomachines are at rest.

Abstract: A thermal turbomachine, an axial flow gas turbine (10) in particular, includes a rotor (16), which at its exit side is supported on a bearing (15), which is situated on a bearing saddle (14) within an annular inner part (11) of an exhaust casing, the bearing saddle (14) being supported on a foundation of the machine by means of a spring support (25). In such a turbomachine, the stiffness of the bearing support is improved or restored by attaching the bearing saddle (14) to the inner part (11) of the exhaust casing by a spring-loaded bolted connection (19, . . . .,22).

Abstract: A thermal turbomachine, an axial flow gas turbine (10) in particular, includes a rotor (16), which at its exit side is supported on a bearing (15), which is situated on a bearing saddle (14) within an annular inner part (11) of an exhaust casing, the bearing saddle (14) being supported on a foundation of the machine by means of a spring support (25). In such a turbomachine, the stiffness of the bearing support is improved or restored by attaching the bearing saddle (14) to the inner part (11) of the exhaust casing by a spring-loaded bolted connection (19, . . . .,22).

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: A blade carrier for an axial-flow compressor is provided with cooling passages, through which a cooling medium flows in a closed circuit. The cooling passages run at least approximately in the peripheral direction inside the blade carrier and are located in a closed water circuit which essentially comprises a circulating pump (31), a pressure-keeping vessel (32) and a heat exchanger (35).The cooling passages are arranged in a ring shape, each cooling ring (27) being provided with a feed line (28) and a discharge line (29). At least every second successive cooling ring is attached to a separate cooling path in the longitudinal direction of the blade carrier.

Abstract: A gas turbine having guide blades arranged between the combustion chamber and turbine rotor is improved by the guide blades 1.1 being integrated in the respectively associated combustion chamber 1.2. That is, the guide blades 1.1 and the associated combustion-chamber wall 1.2.1 are designed essentially in one piece and are constructed as a combustion-chamber/guide-blade unit 1. The latter sits in cold supporting structures 3.1 of the gas-turbine plant 3 and both together form cooling-air passages which allow the combustion chamber to be cooled in counterflow.

Abstract: An arrangement for the thermal protection of a rotor, fitted with moving blades, of a high-pressure compressor. The roots of the moving blades are inserted and locked in peripheral grooves which are at an axial distance from one another. The rotor has, between two adjacent peripheral grooves for the moving blades, at least one further peripheral groove having a hook extending over the entire periphery of the rotor. At least two plate-shaped heat-accumulation segments, each having at least one root which has a contour adapted to the hook of the rotor so that both form a contact area, are pushed radially one after the other into the further peripheral groove and locked therein. A cavity forming an insulating layer extends between the heat-accumulation segments and the rotor and between the moving-blade roots and the rotor, in which insulating layer the velocity of the compressor air is greatly reduced.

Abstract: In a screw securing device for a screw (1) by means of which a first component (2a) and a second component (2b) are clamped together, a bushing (5a, 5b), includes a cylinder (5a) and a base (5b) which contains a bore, the bushing being arranged in a first bore (3a) of the first component (2a). The first bore (3a) opens into a smaller, second bore (3b) of the first component (2a), and said second bore (3b) is provided with a left-handed thread (8) in which there is screwed a tubular extension (5c) which is arranged coaxially with the bore in the base (5b). The screw (1) is screwed, through the bushing (5a, 5b) and the tubular extension (5c), into the second component (2b) by means of its right-handed thread (7). A cap (6a), having an insert (6b) which is connected to the screw head in a positively locking manner, is fastened on the bushing (5a, 5b) by a welding bead (4).

Abstract: In a compressor (1), in particular for a gas turbine, which compressor includes a rotor (3), which is rotatably supported about a compressor center line and possesses at its periphery a plurality of rotor blades (5a-d), and a compressor casing (2), which concentrically surrounds the rotor (3), a radial clearance being provided between the outer ends of the rotor blades (5a-d) and the inner wall of the compressor casing (2), the possibility of a warm start without sacrificing efficiency is achieved by configuring the compressor casing (2) so that it can be heated in order to reduce the fluctuations in the radial clearance and by connecting it to a separate heating appliance (22, 25, 27), which is independent of the operation of the compressor and by means of which the compressor casing can be heated in the case of a warm start.

Abstract: In an axial-flow compressor, the appliance for extracting secondary air using a peripheral extraction slot which is at least partially configured as a diagonal diffuser is such that means which make it possible to utilize the kinetic energy of the peripheral component of the flow velocity are arranged in or directly at the extraction slot (4). These can, for example, be a mini-cascade (7) integrated in the extraction slot (4) or an extraction slot (4) which is designed as a diagonal diffuser (8) and merges into a volute (9), the volute (9) opening directly into the extraction tube (6). The total pressure loss is minimized and the efficiency of the installation is increased by these arrangements.

Abstract: In a process for operating a fluid flow engine, a conditioning medium is conducted through the rotor, which consists of several shaft parts (1, 2) welded together; this medium is capable of evening out the temperature difference established between the stator (3) and the rotor in the transient operating ranges, depending on whether heating or cooling of the rotor is suited to the characteristic curve of the stator temperature course.

Abstract: In a gas turbine combustion chamber with an annular flame tube, the latter is essentially composed of wall pieces (18) which overlap in the circumferential direction. The wall pieces (18) are elements, curved in the turbine axial direction, the cooling air being directed in a circumferential direction along the external sides thereof facing towards the collector volume (6). The cooling air flowing out of the overlap gaps (22) is deflected in a cascade (29) before entry into the combustion volume (15).

Abstract: In this multi-cylinder steam turbine, compensation is provided for the axial thermal expansion, from the bearing housing (5) of the medium pressure partial turbine (1), of the low pressure part of the shafting (4) by the low pressure steam feed pipe (15, 16) rigidly connected to the medium pressure partial turbine (1) being rigidly connected to the inner casing (11, 12) of the two-casing low pressure partial turbines (2, 3). Because of the equal temperatures, the part of the shafting (4) mentioned and the low pressure steam feed pipes (15, 16) expand equally so that the axial clearances between the nozzle guide vane and rotor blade rings of the low pressure partial turbines (2, 3) are also substantially retained. The otherwise conventional connecting elements between the medium pressure partial turbines and the low pressure partial turbines with their associated sealing problems on the outer casings disappear.

Abstract: In order to compensate for the axial displacements of the rotors of steam turbines occurring in operation by simultaneous displacement of the inner casing (11, 12) and, by this means, to keep the axial clearance between the stator and rotor blading rows constant, the inner casing (11, 12) of a double-casing turbine is supported in its outer casing (9, 10) so that it can be displaced relative to it. Lever pairs (18, 19), each having a two-arm displacement lever (20, 27), which is supported on bearing blocks (21, 28) fixed relative to the outer casing, and an expansion lever (22, 29) interacting with it are used for the displacement. An extension (.DELTA.l), occurring due to the operational heating in a section of length (1) of the inner casing (11, 12), between two bearing trunnions (23, 26) is transmitted by the expansion levers (22, 29) to the displacement lever (20, 27), whose pivoting about the bearing trunnion (26) in the clockwise direction achieves the necessary displacement (.DELTA.x, .DELTA.x2).

Abstract: In order to clamp blades (1, 2, n) of turbomachines to influence the blade vibration occuring in such machines, the shroud plates (1a, 2a, na) are dimensioned in such a way that they are in contact with one another in the installed condition without clearance and without contact force or else they are dimensioned so that they exhibit a gap (3) relative to each other. A prestressed or pretorsioned, clearance-free connection occures between the shroud plates (1a, 2a, na) due to plastic deformation of the shroud plates (1a, 2a, na) in the region of their boundries or of the gap (3).

Abstract: A method of joining shafts is disclosed in which a welded joint is formed between the shaft ends of, for example, a turbine and a generator inside of an assembled turbogenerator structure. A built-up weld portion is provided on the end of each shaft, which is machined to form a welding groove. During installation of the equipment, such as a turbogenerator arrangement, a welding ring is placed onto the end of one shaft. Welding powder is deposited in recesses formed between the shafts and the welding ring. The second shaft is then pressed against the welding ring. The shaft sections are preheated and the groove is supplied with welding material to join the sections while the shafts are being rotated. After completion of the weld, the seam is checked for structural integrity.

Abstract: A housing structure for a steam turbine includes inner and outer housings and a hinged portion of one of those housings is structured for being lowered or raised into a horizontal plane to serve as a working platform to facilitate servicing. The hinged housing portion includes a hinged upstanding rim to prevent tools from sliding off and a protective railing is secured to the rim.