Gas turbine engine blade containment assembly
US6575694B1 · kind B1 · utility
43Cited by
14References
26Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Aug 8, 2001 |
| Grant date | Jun 10, 2003 |
| Priority date | — |
| Expiry date | Aug 8, 2021 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbofan gas turbine engine (10) comprises a fan rotor (32) carrying a plurality of radially extending fan blades (34). A fan blade containment assembly (38) surrounds the fan blades (34) and the fan blade containment assembly (34) comprises a generally annular, or frustoconical, cross-section casing (52). At least one corrugated sheet metal ring surrounds the casing (52) wherein the corrugations extend with axial and/or circumferential components.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.