Aircraft engine blading

US9695694B2 · kind B2 · utility

Assignee

• MTU Aero Engines AG · DE

Inventor

• Norbert Huebner · Dachau, DE

Key dates

• Filing date: Nov 30, 2011
• Grant date: Jul 4, 2017
• Expiry date: Mar 25, 2034

Classification

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

Abstract

A blading for a turbine, in particular a gas turbine, is disclosed. The blades of the blading in a section near the tip have a distribution ratio (t/l) of at least 0.70, in particular at least 0.9, and/or at most 0.97, in particular at most 0.95. A downstream flow angle (α) is at most 167°, in particular at most 165°, and at least 155°, in particular at least 160°. In addition, or alternatively, an acceleration ratio (w2/w1) is at least 1.4, in particular at least 1.5.