Abstract: A rotor (1) of a turbomachine comprises a basic rotor element (2) and a multiplicity of rotor blades (3, 3′, 3″, 3′″). The rotor blades (3, 3′, 3″, 3′″) are arranged in a distributed manner in at least one row on the circumference of the basic rotor element (2). An area for a row of guide vanes is furthermore provided in front of and/or behind the row of rotor blades. A heat shield element (4) or a plurality of heat shield elements (4′, 4′, 4′″) lined up on the circumference of the rotor (1) is arranged in such a way between the basis rotor element (2) and the rotor blades (3, 3′, 3″, 3′″) of the row of rotor blades that the basic rotor element (2) is completely covered in the areas of the row of rotor blades and the row of guide vanes.

Abstract: A multistage turbocompressor is equipped with a tapping point between two compressor stages. The guide-blade cascade of the stage arranged directly upstream or downstream of the tapping point is designed with adjustable geometry. The pressure at the tapping point can be set within wide limits, irrespective of the compressor operating point, by an adjustment of this guide-blade cascade.

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: 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 burner of the double cone type, at least one relief slit (30) is arranged in the front plate (18) locally between the regions having different axial expansions. The flexible connection remaining between the two outlet regions may be made integrally within the same casting or via a further welded-on part. Excessive thermal stresses are advantageously avoided thereby.

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 bladed rotor of an axial-flow turbomachine, the blades essentially consist of a blade body and a blade root. They are fastened with their blade roots in rows in encircling blade grooves having lateral supporting prongs. A shoulder serving to assemble the blades on the rotor is attached between blade body and blade root. The blade grooves are shaped symmetrically to the associated planes of symmetry by a plurality of radii (R1-R4), the preceding radius (R1) in each case being larger than the following radius (R2). The circular arcs formed by the radii (R1-R4) have a common tangent (T) at their contact points.

Abstract: In a drum rotor (1) for an axial-flow turbomachine, the blades are fastened with their roots (3) in rows in encircling blade grooves (10) having lateral supporting prongs. At least the first blade groove (10), on the inlet side of the working medium, is shaped in an axially asymmetrical manner by a plurality of radii (R1-R4). The preceding radius (R1) in each case is larger than the following radius (R2), and the circular arcs (21-24) formed by the radii (R1-R4) have a common tangent (T) at their contact points.

Abstract: In a bladed rotor (1) of a turbo-machine, the blade roots (3) and blade grooves are made pinetree-shaped with a plurality of indentations (10, 21) and teeth (11, 20). A plurality of supporting surfaces (F) extending obliquely are formed thereby. The indentations (10, 21), adjoining the supporting surfaces, in the blade root (3) and in the blade groove are described essentially by a first curve radius (R1) and a second curve radius (R2).The first curve radius (R1) adjacent to the supporting surface (F) is smaller than the second curve radius (R2). The opening angle (W) between a tangent (T) to the circle arc (22), described by the first curve radius R1, at the end point (A, B) of the supporting surface and the supporting surface (F) amounts to at least forty degrees.