Abstract: A machine train includes a drive unit, preferably a steam turbine with axial exhaust flow, a geared turbine machine, and an additional compressor. The geared turbine machine has an integrated gear train with a drive pinion for driving turbine machine rotors via a large gear, and an output pinion of a rotational speed reduction power gear for driving the additional compressor.

Abstract: Apparatus for lateral fitting and removing of a compressor barrel into and out of a casing of a turbocompressor, the barrel having an inner core section with split disks which are bolted together coaxially, a cap rotatably mounted on a bearing block, and a rotor, wherein the disks are bolted to the cap and the rotor, and wherein the casing is vertically split and has a suction connection and a pressure connection. A support arm has a proximal end which can be releasably connected to the bearing block and a distal end which extends beyond the rotor and is displaceably supported on the casing when the proximal end is connected to the bearing block. A support device can be releasably mounted to the bearing block oppositely from the support arm, the supporting device being movable laterally on a guide to move the barrel into and out of the casing.

Abstract: A gas turbine plant having a compressor (1), one or more combustion chambers (2), a high-pressure gas turbine (3) and a power turbine (24) includes a device whereby water or water vapor is injected into the flow of the combustion air compressed by the compressor (1). The injection nozzles (22) are arranged in a bend (20) of an external connection housing (18), which consists of a radial housing part (19) connected to the outlet of the compressor (1) and of an axial housing part (21) connected to the intake of the combustion chamber (2).

Abstract: A multistage turbocompressor, designed as a geared compressor with an integrated gear, contains a central greater wheel (9) that meshes with a plurality of pinions (14, 15), wherein each pinion (14, 15) is mounted, in a manner adapted to rotate in unison, on a pinion shaft (16, 17). A bladed wheel of a compressor stage (II, III, IV, V) is arranged on the ends of each of the pinion shafts. The greater wheel (9) meshes with a driving pinion (8), which is mounted, in a manner adapted to rotate in unison, on a driving shaft 6 connected to a drive unit (1). The axis of the driving pinion (8) is arranged, with the axis of the greater wheel (9), in the same horizontal plane (20), and the driving pinion (8) meshes with a pinion (10) of a first compressor stage (I) mounted, in a manner adapted to rotate in unison, on a pinion shaft (11).

Abstract: A turbine rotor has a row of turbine blades associated with a circumferential groove in a disk, each turbine blade having foot received in the groove, a blade profile above the foot, and a shroud plate above the profile. Each blade foot and each shroud plate have end surfaces and side surfaces which form a rhomboid, the end surfaces of each shroud plate tapering toward each other along respective radii and abutting the end surfaces of adjacent shroud plates to form a closed ring. The blade profiles are torsionally stressed by applying a force to each plate in a direction parallel to the axis of the disk, thereby twisting the cover plates through an angle alpha so that the side surfaces of adjacent cover plates are circumferentially aligned in a plane perpendicular to the longitudinal axis. This force is maintained by clamping devices applied to the combs of adjacent blades.

Abstract: An intake housing for axial fluid flow engines, especially for axial-flow compressors, is proposed. The intake housing comprises an intake shaft (1) with a radial inlet (4) on one side and with an axial, rotationally symmetrical inlet cone (5), which forms an axial flow part (2) together with a jacket (6) protruding into the intake shaft (1) with an inlet edge (7). The axial flow part (2) is in connection with the inlet cross section of the fluid flow engine. The inlet edge (7) of the jacket (6) is connected with an annular diaphragm (9), which is directed at right angles to the axis (10) of the axial flow part (2). Furthermore, the diaphragm (9) is arranged mirror symmetrically at right angles to the axis (10) of the axial flow part (2) and asymmetrically in relation to the axis (10) of the axial flow part (2).

Abstract: Disclosed is a heat-insulating protective layer for a component located within the hot gas zone of a gas turbine. Said protective layer is composed of an adhesive layer, a diffusion layer, and a ceramic layer which is applied to the high temperature-resistant basic metal of the component. The adhesive layer comprises a metal alloy [MCrAlY (M=Ni, Co)] containing Ni, Co, Cr, Al, Y, the diffusion layer is produced by calorizing the adhesive layer, and the ceramic layer is composed of ZrO2 which is partially stabilized by means of yttrium oxide. One or several chemical metal elements that have a large atomic diameter and are selected among the group comprising Re, W, Si, Hf, and/or Ta are alloyed to the material of the adhesive layer. The adhesive layer has the following chemical composition after being applied: Co 15 to 30 percent, Cr 15 to 25 percent, Al 6 to 13 percent, Y 0.2 to 0.

Abstract: A shaft seal for a transmission expander or compressor having at least one rotor which rotates in a housing and is arranged in a floating manner on a shaft, the shaft seal having a seal arrangement with seal tips attached on the hub of the rotor. A stationary sealing ring surrounds the seal tips which are arranged in three seal sections. An annular chamber is arranged between in each adjacent pair of seal sections. The annular chamber which faces the interior of the transmission expander or compressor is equipped with a feed means for a sealing gas, the pressure of which is higher than the pressure in the interior of the transmission expander or compressor. The annular chamber which faces away from the interior of the transmission expander or compressor is provided with an extraction means for the sealing gas.

Abstract: An intercooler (3) is provided with heat exchanger surfaces (6) and is arranged in the gas stream between two compressors (1, 2) or two compressor stage groups for compressing a gas. An aftercooler (5) is also provided with heat exchanger surfaces (7) and is arranged after the second compressor (2). To utilize the waste heat generated in the coolers (3, 5), the heat exchanger surfaces (6, 7) of the intercooler (3) and of the aftercooler (5) are integrated in a steam generator (9) in such a way that the heat exchanger surfaces are connected with the feedwater pump (40, 59) of the steam generator (9).

Abstract: An exhaust gas chimney, especially an exhaust gas chimney installed directly downstream of a gas turbine or downstream of the waste heat recovery boiler of a gas turbine, includes an inner shell formed as a metal tube and surrounded by a sound absorption ring filled with bulk material for sound absorption. The sound absorption ring is formed as a ring jacket provided with a lower end plate that slopes downward and is permanently joined with the inner shell of the chimney, and with an upper end plate that slopes upward toward the inner shell. Ribs are joined to the inner shell of the chimney inside the annular jacket.

Abstract: The rotor (5) of a gas turbine containing a compressor part (1) and a turbine part (3) is mounted in an axial thrust bearing (19) and in two radial journal bearings (16, 17). One of the bearings is a journal bearing (16) arranged in the intake area of the compressor part (1) and the other journal bearing (17) together with the thrust bearing (19) is arranged in the area of the turbine part (3).

Abstract: A rotor of a steam or gas turbine is equipped with rotor blades, which are held in the rotor (6) in a plurality of radial rows and comprise a blade foot 1 installed in the rotor (6), a blade leaf (2) and a cover plate (3). An open pocket (5) is prepared in the sloping surfaces of the cover plates (3) of a row of rotor blades, which the sloping surfaces are located opposite each other. The pockets (5) of two adjacent cover plates (3) form together an essentially closed cavity, which expands in the radial direction of the rotor (6). A pin, whose largest cross section is smaller than the largest cross section of the cavity but larger than the smallest cross section of the cavity, is placed freely movably into each cavity.

Abstract: A process for the reliable operation of turbocompressors with a surge limit control and a surge limit control valve is described, in which the compressor delivers gases with different compositions and the composition of the gas (molecular weight) affects the performance characteristic of the turbocompressor and hence the position of the surge limit in the performance characteristic. The different compositions of the gases are compensated here with the effect on the position of the surge limit and consequently on the position of the surge limit control line by using predetermined design values for the gas constant R, the isentropic exponent k and the compressibility number z within the surge limit control for the determination of the delivery head ?h and the volume flow V and plotting them in the form of a predetermined surge limit line (FIG. 2, FIG.

Abstract: A gas collection pipe (1) carrying hot gas establishes the connection between the combustion chambers (9) of a gas turbine plant and the flow channel (13) of the gas turbine. The gas collection pipe (1) has two inlet pipe connections (2), which open via an elbow (3) axially into a gas ring channel (4), which is joined to the flow channel (13). Cooling air is guided on the outside along the elbow (3). A plurality of ribs (8) are arranged at spaced locations from one another on the outside on the gas collection pipe (1) in the area of the elbow (3) on the side facing away from the flow channel (13).

Abstract: A rhomboidal blade includes a blade footing (2) of rhomboidal cross section and a blade body (1) for axial turbo engines is worked out from a solid blank (3) by machining. The blank (3) is cut off as a bar from a hot-rolled, bar-shaped input stock, whose cross section has the shape of a rhomboid which is adapted to the shape of the cross section of the rhomboidal blade footing (2). The blank is larger on all size than the maximum cross section of the blade by only the minimum oversize (5) for machining.