Patent · US Active

Ductile compensation layer for brittle components

US9551231B2 · kind B2 · utility

2Cited by

4References

20Claims

0Family size

Assignee

MTU Aero Engines AG · DE

Inventors

Erich Steinhardt · Munich, DE
Wilfried Smarsly · Grasbrunn, DE
Andre Werner · Munich, DE

Key dates

Filing date	Aug 9, 2013
Grant date	Jan 24, 2017
Priority date	—
Expiry date	Apr 8, 2035

Classification

Technology area (CPC Y)Emerging Cross-Sectional Technologies
CPC primaryY02T50/60
WIPO fieldEngines, pumps, turbines
WIPO sectorMechanical engineering

Abstract

Disclosed is a blade element of a turbomachine, in particular of a gas turbine, which comprises a fastening element (10) with which the blade element is arranged in a receptacle (11) of the turbomachine. In the region of the fastening element, the blade element has a core region (18) and an envelope region (19) which at least partially envelops the core region. The core region is formed from a blade base material which is more brittle than the envelope material of the envelope region, and the envelope region is formed by a coating. The envelope material is a blade base material which has been modified to achieve a higher ductility or is a pseudoelastic or superelastic material.

Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.