Variable contour annular air inlet for an aircraft engine nacelle
US5000399A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Feb 23, 1990 |
| Grant date | Mar 19, 1991 |
| Priority date | — |
| Expiry date | Feb 23, 2010 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An annular nacelle for a turbine engine of an aircraft has a variable contour annular air inlet. The variable contour annular inlet includes annular outer and inner surface-defining radially-spaced structures on the forward portion of the nacelle, an annular member disposed between the annular outer and inner structures and coupled to the annular outer structure for sliding movement along the interiors of the annular outer and inner structures, and a plurality of actuating mechanisms coupled between the nacelle body and the annular member. The actuating mechanisms are operable for moving the annular member between forward and rearward positions. At the forward position, the annular member is located between the forward ends of the annular outer and inner structures with the annular outer structure expanded to an enlarged diameter such that the annular member forms therewith an inlet lip having an aerodynamically blunt exterior contour adapted to reduce drag during takeoff and landing operation of the aircraft. At the rearward position, the annular member is spaced rearwardly from the forward ends of the annular outer and inner structures with the annular outer structure contracted …
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.