Low observable engine air inlet system
US5697394A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Mar 2, 1993 |
| Grant date | Dec 16, 1997 |
| Priority date | — |
| Expiry date | Mar 2, 2013 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T137/0645
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A turbine engine inlet system includes a duct 14 to deliver air to the engine, inlet lips 16 and 52 to smooth the entry of air flowing into the duct, a screen 50 between the lips 52 and 16 for passage of inlet air, a forward inlet section 18 submerged within the aircraft skin contour to provide a degree of ram recovery to the duct, and a movable air deflector 20 which is positionable in a retracted position during normal flight, is extendable outward to a second position substantially flush with the screen 50 for maximum protection against foreign object damage (FOD), and is further extendable outward to a third position beyond the screen to provide an air bypass path when the screen is iced-over.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.