Abstract: A method of altering the frequency of blades (1) having an airfoil (2) with a suction side (6), a pressure side (5), a leading edge (10), a trailing edge (7) and a blade tip (9), and including a blade root (3), in particular turbine blades, for thermal fluid-flow machines. A metallic coating (8) formed of a material identical to the parent material is applied to the blade (1), already ready for use, in the region of the blade tip (9), the thickness of the coating (8) tapering continuously at the trailing edge (7) and in the radial direction toward the blade root (3).

Abstract: In a process for producing a turbine blade or vane, a casting (10′) which is in the basic shape of the turbine blade or vane is produced in a casting mold, and the casting (10′) is then subjected to material-removing machining in order to complete the turbine blade or vane.

Abstract: A device for producing a soldered joint between two joining partners which can be joined via a common contact surface (7), using a solder material which can be introduced between the two joining partners. At least one joining partner (1), in the region of the contact surface (7), provides at least one recess, known as a solder reservoir (3), which faces the contact surface and into which the solder material can be introduced, and the solder reservoir (3) is completely delimited and surrounded by the contact surface (7).

Abstract: A device for fastening and fixing components to a cylindrical wall. The cylindrical wall may be both the convex-cylindrical outer contour of a cylinder and the concave-cylindrical inner contour of a hollow cylinder, in which the component is fixed in the radial, axial and circumferential directions. The fastening and fixing is effected by shaped elements which are attached to the component and by a counterpart to each shaped element on the wall. In each case a shaped element and a counterpart interlock, such that the component has at least three shaped elements, of which at least one shaped element has a defined accuracy of fit with its associated counterpart in the radial direction and has clearance in the axial and circumferential directions. At least one shaped element has a defined accuracy of fit with its associated counterpart in the axial direction and has clearance in the radial and circumferential directions.

Abstract: A method is disclosed for reducing the variance in the coolant consumption of components of a turbo-machine, in particular a gas turbine. The components are provided with one or more holes for the passage of a coolant, wherein a surface roughness existing inside the holes is reduced by mechanical finishing. The method is characterized by mechanical finishing that is performed by reshaping rough points that cause the surface roughness using a cold working process such as at least one of beating, pressing and rolling. The method permits a simple reduction of the surface roughness without creating finishing residues that could result in obstructions of the holes.

Abstract: A platelike projecting component portion of a component used in gas turbines or other similar applications includes a surface upon which hot gas acts and cooling bores through which a cooling medium is capable of flowing. Effective cooling is achieved by providing at least one plenum assigned solely to the component portion. The plenum is arranged so as to be directly adjacent to the surface upon which hot gas acts and through which the cooling medium is capable of flowing to provide convective heat transfer. The cooling bores are designed as blow-out orifices which emanate from the plenum and issue the cooling medium onto the surface upon which hot gas acts, thereby forming a cooling film.

Abstract: The invention describes a device for producing a soldered joint between two joining partners which can be joined via a common contact surface (7), using a solder material which can be introduced between the two joining partners.

Abstract: In a gas-turbine guide element (30) around which a hot air flow (23) flows and which, at least in a trailing edge region (21), in which the air flow (23) separates from the guide element (30), comprises at least two walls (10, 11) arranged essentially in parallel and connected to one another by ribs (16, 17, 20) in such a way as to form internal cooling passages (18, 19, 25, 26, 27), and which is cooled on the inside with cooling medium (28, 29) flowing through the cooling passages (18, 19, 25, 26, 27), the cooling medium discharging from the guide element (30) at the trailing edge (21) essentially parallel to and between the walls (10, 11), and in a method of producing it, easier reworking and less susceptibility to foreign particles are achieved owing to the fact that at least some of the ribs are arranged as choke ribs (24) so as to terminate essentially flush with the trailing edge (21).

Abstract: A method is disclosed for reducing the variance in the coolant consumption of components of a turbo-machine, in particular a gas turbine. The components are provided with one or more holes for the passage of a coolant, wherein a surface roughness existing inside the holes is reduced by mechanical finishing. The method is characterized by mechanical finishing that is performed by reshaping rough points that cause the surface roughness using a cold working process such as at least one of beating, pressing and rolling. The method permits a simple reduction of the surface roughness without creating finishing residues that could result in obstructions of the holes.

Abstract: The present invention relates to a tool for casting a shaped part for the production of a turbine blade, with several tool blocks which, when assembled with positive engagement in a predetermined manner, form a cavity for the shaped part, into which cavity flowable material can be introduced by means of one or more access apertures. At least one of the tool blocks receives a rotatable or displaceable insert or inset which borders the cavity with a surface and which can be fixed in different positions and/or orientations of the tool blocks, so that different cavity geometries are formed in the different positions and/or orientations of the insert or inset. The tool makes possible a later change of the geometry of the shaped part, in particular of the attack angle, without having to manufacture new tool blocks for this purpose.

Abstract: A fastening device for a heat-protection shield of a gas turbine is provided with a center mounting element which has a defined installation clearance with a mounting slot in the radial direction. In the normal operating state, this mounting element has no function, such that thermal differential expansions in the radial direction between the heat-protection shield and its counterpart are possible without impairment within the limits of this defined clearance. The mounting element does not start to bear against the counterpart until the radial differential expansion exceeds the size s. The deformation of the heat-protection shield toward a component moving in a relative manner is thus limited and excessive grazing of the components against one another is avoided.

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: A platelike projecting component portion (1) of a gas turbine or the like, with a surface (2) upon which hot gas acts and with cooling bores (12) through which a cooling medium is capable of flowing. Effective cooling is achieved in that at least one plenum (10; 30; 50) assigned solely to the component portion (1) is provided, which is arranged so as to be directly adjacent to the surface (2) upon which hot gas acts and through which the cooling medium is capable of flowing convectively, and in that, to form a cooling film, the cooling bores are designed as blow-out orifices (12; 52) which emanate from the plenum (10; 30, 50) and which issue on the surface (2) upon which hot gas acts.

Abstract: A heat shield for a gas turbine, which heat shield encloses in an annular manner the moving blades, rotating in the hot-gas duct of the gas turbine, of a stage of the gas turbine and consists of a plurality of heat-shield segments which are arranged one behind the other in the circumferential direction, are curved in the shape of a segment of a circle and are cooled from outside, and the longitudinal sides which are designed as correspondingly curved rails running in the circumferential direction and having in each case a pair of arms of which project in the axial direction, run in parallel and are at a distance from one another, the heat-shield segments, while forming a cavity to which cooling air can be admitted, are fastened to the inside of an annular carrier, which concentrically surrounds the heat shield in such a way that in each case a radial gap is formed between the longitudinal sides of heat-shield segments and the adjacent elements which define the hot-gas duct on the outside.

Abstract: In a gas-turbine guide element (30) around which a hot air flow (23) flows and which, at least in a trailing edge region (21), in which the air flow (23) separates from the guide element (30), comprises at least two walls (10, 11) arranged essentially in parallel and connected to one another by ribs (16, 17, 20) in such a way as to form internal cooling passages (18, 19, 25, 26, 27), and which is cooled on the inside with cooling medium (28, 29) flowing through the cooling passages (18, 19, 25, 26, 27), the cooling medium discharging from the guide element (30) at the trailing edge (21) essentially parallel to and between the walls (10, 11), and in a method of producing it, easier reworking and less susceptibility to foreign particles are achieved owing to the fact that at least some of the ribs are arranged as choke ribs (24) so as to terminate essentially flush with the trailing edge (21).