Abstract: A pressure casing has a plurality of casing shells (10a, b) which can be connected in a pressure-tight manner in a parting plane (11) by a flange (13). The casing shells (10a, b) are pressed together with sealing effect in the parting plane (11) in the region of the flange (13) by at least one threaded bolt (19; 19a-d) which extends through the flange (13) perpendicularly to the parting plane (11). A reduced thermal loading of the threaded bolts (19; 19a-d) of the flanged joint is achieved by the at least one threaded bolt (19; 19a-d) being exposed over a part of its length towards the inner side of the casing (10).

Abstract: A pressure casing has a plurality of casing shells (10a, b) which can be connected in a pressure-tight manner in a parting plane (11) by a flange (13). The casing shells (10a, b) are pressed together with sealing effect in the parting plane (11) in the region of the flange (13) by at least one threaded bolt (19; 19a-d) which extends through the flange (13) perpendicularly to the parting plane (11). A reduced thermal loading of the threaded bolts (19; 19a-d) of the flanged joint is achieved by the at least one threaded bolt (19; 19a-d) being exposed over a part of its length towards the inner side of the casing (10).

Abstract: Described is a fixation device for blading of a turbo-machine, in which, longitudinally to a mounting groove (1), a plurality of blades (31, 32) is positioned, and in which, between at least two blades (31, 32) positioned adjacent to each other inside the mounting groove (1), a mounting gap is provided, having two insertion elements constructed as collar halves (41, 42) that can be inserted into the mounting gap, and each of which has a width adapted to the width of the mounting gap and which enclose between themselves a gap space (5) into which a wedge element (43) can be inserted that can be wedged in such a way that both collar halves (41, 42) are fixed in a force-derived manner by means of the wedge element (43) inside the mounting groove (1).

Abstract: A device is shown for fixing blades of a turbo-machine having a plurality of blades positioned longitudinally relative to a mounting groove. At least two blades are positioned adjacent to each other inside the mounting groove, and a mounting gap is defined between the blades. Two insertion elements constructed as collar halves can be inserted into the mounting gap, and each insertion element has a width adapted to the width of the mounting gap such that a gap space is defined between the insertion elements when they are inserted into the mounting gap. A wedge element can be inserted in the mounting gap to fix both collar halves inside the mounting groove. At least one connecting element is provided on the wedge element towards the side of a blade, and at least one of the two blades adjoining the wedge element is provided with a mating recess corresponding to the connecting element so that the wedge element and the blade are connected by a shape-mated connection.

Abstract: In a method for visualizing and processing a value assembly process, the value assembly process is visualized as a set of value assembly lines (VAL) arranged on different hierarchy levels. Each value assembly line receives value packages via input interfaces and consolidates these to form a value added package (VAP), an added value being created, and makes the added value package available at an output interface. The added value package can be used by a value assembly line of a higher-order hierarchy level as input value package. Likewise, the input value packages of the value assembly lines can be value added packages made available by lower-order value assembly lines, the lower-order value assembly lines being value assembly lines of a lower-order hierarchy level. All value assembly lines and all value packages have an identical structure; only the processed data differ from one another.

Abstract: The gas turbine has a bladed rotor welded together from a plurality of disks. Hollow spaces are present between the disks and axial passages are present in the periphery of the rotor between the rotor surface and platforms formed by the rotor blades and segmental heat barrier plates. In accordance with the invention, these axial passages are fed with cooling air from at least one hollow space between two rotor disks. The at least one hollow space is in connection with the axial passages mentioned, preferably by of connecting openings. It is fed from a central cooling air supply passage starting from the downstream end of the rotor. The cooling air is preferably tapped from the cycle air at the central part of the compressor so that low-pressure cooling occurs.