Gas turbine engine fan blade containment systems
US10550718B2 · kind B2 · utility
0Cited by
180References
22Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Mar 31, 2017 |
| Grant date | Feb 4, 2020 |
| Priority date | — |
| Expiry date | Sep 9, 2037 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Gas turbine engine fan blade containment systems are disclosed. An example fan blade containment system includes a shield to be coupled to an aircraft structure and to at least partially surround a circumference of an aircraft engine. The shield is to be spaced from an outer surface the aircraft engine when the shield is coupled to the aircraft structure. A shield termination fitting is to couple a terminating end of the shield to the aircraft structure.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.