Abstract: A method for manufacturing a contoured hole, the hole being manufactured in a wall, the wall comprising a first, a second surface, and a wall thickness between the wall first and second surface. The comprises manufacturing a first non-penetrating hole extending from the first surface and into the wall, wherein a distal end of the first hole is located within the wall such that the first hole does not penetrate the wall second surface, and manufacturing a through hole, wherein the through hole is fluidly connected with first hole and penetrates the wall second surface.

Abstract: The blade for a gas turbine includes a root, a platform and an airfoil. The blade further has a cooling channel with an inlet located at the root or platform and outlets. The outlets are located at the platform.

Abstract: A method for manufacturing a contoured hole, the hole being manufactured in a wall, the wall comprising a first, a second surface, and a wall thickness between the wall first and second surface. The comprises manufacturing a first non-penetrating hole extending from the first surface and into the wall, wherein a distal end of the first hole is located within the wall such that the first hole does not penetrate the wall second surface, and manufacturing a through hole, wherein the through hole is fluidly connected with first hole and penetrates the wall second surface.

Abstract: The invention relates to a method for closing an aperture on a blade of a gas turbine, wherein the blade of the gas turbine comprises a tip end with a top surface and a bottom surface. The aperture is formed on the tip end of the blade, and the aperture includes a peripheral edge. The method includes closing the aperture with a weld formed by means of a Tungsten Inert Gas(TIG) welding process without an insert placed in the aperture. With the technical solution of the present invention, it provides a simple and cost effective solution to close the aperture on the tip end of the blade, dispensing with the conventionally utilized “letter-box”, insert, tip cap and the like. In view of this, process of closing the aperture may be simplified, and the cost incurred may be reduced. Further, premature failure of the blade is prevented.

Abstract: The present invention relates to a blade of turbine having an aerofoil, a platform and a root portion configured to be slidingly received in mounting slots of a rotor disc. The blade further includes a locking member disposed on the root portion and engaged with the rotor disc to make axial fixation of the blade to the rotor disc. With the technical solution of the present invention, it provides a blade with simple and cost effective axial locking system to make axial fixation of the blade relative to the rotor disc, and also a fail-safe solution during assembly process.

Abstract: The invention relates to a method for the parametric production of a drilled hole in a component, in particular for the parametric production of a drilled cooling hole in a blade of a gas or steam turbine. In the case of the method according to the invention, in a first method step (21) an actual wall thickness of the component is measured at the location at which the drilled hole is to be introduced. Subsequently, at least one parametric drilled-hole geometry value is determined on the basis of an adjustment of the measured, actual wall thickness with an assumed, ideal wall thickness (method step 23). The drilled hole is then produced according to the determined parametric drilled-hole geometry value (method step 24). Furthermore, the invention relates to a drilling device, in particular for carrying out the method, and to a component into which one or more drilled holes have been introduced according to the method.

Abstract: The invention relates to a method for the parametric production of a drilled hole in a component, in particular for the parametric production of a drilled cooling hole in a blade of a gas or steam turbine. In the case of the method according to the invention, in a first method step (21) an actual wall thickness of the component is measured at the location at which the drilled hole is to be introduced. Subsequently, at least one parametric drilled-hole geometry value is determined on the basis of an adjustment of the measured, actual wall thickness with an assumed, ideal wall thickness (method step 23). The drilled hole is then produced according to the determined parametric drilled-hole geometry value (method step 24). Furthermore, the invention relates to a drilling device, in particular for carrying out the method, and to a component into which one or more drilled holes have been introduced according to the method.

Abstract: In a method of forming a cooling bore in a wall of a workpiece, the configuration of a feed section and a diffuser section is selected, a throughbore is produced with a cross-sectional area within the cross-sectional area of the feed section, and the diffuser section is cut out by a beam- or jet-drilling method in such a way that the drilling beam or jet in the region of the feed section remains essentially within the cross-sectional area of the latter.

Abstract: A compressor having an axially divided casing, includes a plurality of casing halves. Guide vanes are fastened by their roots in peripheral grooves. Distributed over the periphery, bolts are introduced, which are anchored in the groove base of the peripheral groove. These bolts preferably project radially into the peripheral groove and divide the guide vanes into aggregates and end aggregates situated at the partition plane of the casing.