Thrust reverser with adjustable section nozzle for aircraft jet engine
Number of patents in Portfolio can not be more than 2000
United States of America Patent
Stats
-
Dec 29, 1998
Grant Date -
N/A
app pub date -
Dec 17, 1996
filing date -
Dec 19, 1995
priority date (Note) -
Expired
status (Latency Note)
Importance
Abstract
The invention relates to a thrust reverser for a bypass jet engine that reverses the fan flow. The thrust reverser is installed in the fixed outer cowl and is comprised of pivoting doors that block the fan flow in order to create reverse thrust. A translating annular nozzle is located aft of the pivoting doors in the stowed position, preventing in flight inadvertent deployment. When the nozzle are translated aft, the doors are free to pivot and, at the same time, the section of the fan nozzle can be adjusted to produce more or less fan flow.
First Claim
Family
International Classification(s)
Cited Art Landscape
Patent Citation Ranking
Recipient Email Address
Recipient Email Address
Comment
Recipient Email Address
Add to Portfolio(s)
To add this patent to one, or more, of your portfolios, simply click the add button.
This Patent is in these Portfolios:
Add to additional portfolios:
Last Refreshed On:
Changes done successfully