Gas turbine engine fan blade containment systems
US10487684B2 · kind B2 · utility
0Cited by
180References
17Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Mar 31, 2017 |
| Grant date | Nov 26, 2019 |
| Priority date | — |
| Expiry date | Nov 23, 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. The shield is to form a laminated clevis at an end of the shield. A retention rod is to be positioned in the laminated clevis of the shield. The retention rod is to engage a lug hook of the aircraft structure to anchor the shield to the aircraft structure.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.