Gas turbine engine fan blade containment systems
Gas turbine engine fan blade containment systems
- Neue Suche nach: FRACCHIA CARLOS ANGELO
- Neue Suche nach: JOST KAREN M
- Neue Suche nach: HIGGINS MARK DAVID
- Neue Suche nach: HARPER COLLEEN M
- Neue Suche nach: MILTENBERGER DAVID
- Neue Suche nach: FRACCHIA CARLOS ANGELO
- Neue Suche nach: JOST KAREN M
- Neue Suche nach: HIGGINS MARK DAVID
- Neue Suche nach: HARPER COLLEEN M
- Neue Suche nach: MILTENBERGER DAVID
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.
Dokumentinformationen
Gas turbine engine fan blade containment systems
2020-02-04
Patent
Elektronische Ressource
Englisch
| IPC: | F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F04D Strömungsarbeitsmaschinen , NON-POSITIVE-DISPLACEMENT PUMPS |