Rotating blade

US10267157B2 · kind B2 · utility

Assignee

• MTU Aero Engines AG · DE

Inventors

• Kaspar Wolf · Munich, DE
• Klaus Wittig · Bobingen, DE
• Marcus Woehler · Inning am Ammersee, DE
• Martin Pernleitner · Dachau, DE
• Wilfried Schuette · Deisenhofen, DE

Key dates

• Filing date: Oct 19, 2016
• Grant date: Apr 23, 2019
• Expiry date: Jun 3, 2037

Classification

• Technology area (CPC Y): Emerging Cross-Sectional Technologies
• CPC primary: Y02T50/60
• WIPO field: Engines, pumps, turbines
• WIPO sector: Mechanical engineering

Abstract

The present invention relates to a rotating blade for a turbomachine, in particular a compressor stage or a turbine stage of a gas turbine, particularly of an aircraft engine, having a blade element for deflecting the flow, with a pressure side and a suction side, these sides being joined by a leading edge and a trailing edge, wherein a stacking axis of the blade element, in the radial direction over a radius r from a root of a blade element at r=0 to a tip of a blade element at r=H, has a course x(r) in a first downstream direction perpendicular to the radial direction and parallel to a principal axis of the turbomachine and has a course y(r) in a second direction perpendicular to the radial direction and to the first direction.