Patent · US Active

Compressor blade of a gas-turbine engine with a self-sharpening leading-edge structure

US8827654B2 · kind B2 · utility

2Cited by

9References

20Claims

0Family size

Assignees

ROLLS-ROYCE DEUTSCHLAND LTD & CO KG · DE
FormTech GmbH · DE

Inventors

Karl Schreiber · Zossen, DE
Werner Beck · Weyhe, DE

Key dates

Filing date	Jul 22, 2011
Grant date	Sep 9, 2014
Priority date	—
Expiry date	Nov 2, 2032

Classification

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

Abstract

A compressor blade 1 of a gas-turbine engine has a flow-exposed leading edge 2. A component 3, made of wear-resistant material and featuring a higher erosive wear resistance than the base material, is attached to at least part of a length of the leading edge 2 The component 3 forming the flow-exposed leading edge 2 is strip-shaped, has an essentially rectangular cross-section and, with reference to a sectional plane perpendicular to the radial direction, is arranged only on an inflow side of the compressor blade profile in a partial area of a sectional surface of the inflow area.

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