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US 9,284,848 B2Granted
Method for integrally connecting blades and disks in order to form a blade-disk unit, as well as correspondingly produced blade-disk unit
AssigneeMTU Aero Engines AG
InventorKarl-Hermann Richter
Life of this patent
Estimating the term…
Abstract
A blade-disk unit for a turbine engine includes a disk and a plurality of blades which are integrally connected to the disk, a welding seam being disposed in the joining region between the blade and the disk, which welding seam is situated entirely either in the blade or in the disk.
Claims14
A blade-disk unit for a turbine engine, comprising:
- a disk;
- a plurality of blades integrally connected to the disk;
- and
- a weld seam provided in a joining region between the blade and the disk and provided entirely either in the blade or the disk,
- wherein the welding seam is located at a distance of greater than 0 to 3 mm from at least one of (a) an edge of a joined disk or blade which is closest to the welding seam and (b) an edge of the blade or the disk which is closest to the welding seam in which the welding seam is located.
2 more elements
A blade-disk unit for a turbine engine, comprising:
- a disk;
- a plurality of blades integrally connected to the disk;
- and
- a weld seam provided in a joining region between the blade and the disk and provided entirely either in the blade or the disk,
- wherein the welding seam is arranged as an I-seam having a centering lip.
2 more elements
A method for producing a blade-disk unit for a turbine engine having a disk and a plurality of blades integrally connected to the disk, comprising:
- placing at least one blade on the disk;
- fusing an edge region of the blade or the disk that is situated adjacent to the disk or the blade to be connected;
- and
- connecting the blade and the disk by at least one of (a) a fused material of either the blade or the disk and (b) an action of heat from a fused region,
- wherein one of the blade and the disk is not fused,
- wherein a welding seam is provided in a joining region between the blade and the disk and provided entirely either in the blade or the disk,
- wherein the welding seam is located at a distance of greater than 0 to 3 mm from at least one of (c) an edge of a joined disk or blade which is closest to the welding seam and (d) an edge of the blade or the disk which is closest to the welding seam in which the welding seam is located.
4 more elements
A blade-disk unit for a turbine engine, comprising:
- a disk;
- a plurality of blades integrally connected to the disk;
- and
- a weld seam provided in a joining region between the blade and the disk and provided entirely either in the blade or the disk,
- wherein the welding seam is located at a distance of greater than 0 to 3 mm from at least one of (a) a joined disk or blade and (b) an edge of the blade or the disk in which the welding seam is located,
- wherein the welding seam is arranged as an I-seam having a centering lip.
3 more elements
Dependencies are inferred from the claim text.