US 11,725,518 B2
Method for machining a blade and a blade for a turbomachine
Krzysztof Skura, Majdan Krolewski (PL); Martin Pernleitner, Dachau (DE); Christian Eichler, Olching (DE); and Lutz Friedrich, Munich (DE)
Assigned to MTU Aero Engines AG, Munich (DE)
Filed by MTU Aero Engines AG, Munich (DE)
Filed on Feb. 8, 2021, as Appl. No. 17/170,309.
Claims priority of application No. 20156507 (EP), filed on Feb. 11, 2020.
Prior Publication US 2021/0246793 A1, Aug. 12, 2021
Int. Cl. F01D 5/14 (2006.01); F01D 5/22 (2006.01); B23P 15/02 (2006.01); B23H 9/10 (2006.01); B23C 3/18 (2006.01)
CPC F01D 5/141 (2013.01) [F05D 2230/10 (2013.01)] 4 Claims
OG exemplary drawing
 
1. A blade for a turbomachine having a rotation axis, comprising a shroud which is positioned on a tip side of the blade having an outer surface with at least one circumferential fin arranged thereon, comprising:
a rib structure having a top surface; the top surface having a first section and a second section;
the first section of the top surface being cylindrical in shape and extending circumferentially about the rotation axis of the turbomachine; at the first section, the shroud having a constant radial thickness; and
the second section of the top surface being entirely linear in shape; at the second section, the shroud having a varying radial thickness, and
wherein the first section extends from a first shroud edge and transitions to the second section, wherein the second section extends to a second shroud edge.