Transition shoulder system and method for diverting boundary layer air
Number of patents in Portfolio can not be more than 2000
United States of America Patent
Stats
-
May 12, 1998
Grant Date -
N/A
app pub date -
May 28, 1996
filing date -
May 28, 1996
priority date (Note) -
In Force
status (Latency Note)
Importance
Abstract
A diverterless engine inlet system that integrates a transition shoulder into a system for diverting air from the inlet of an aircraft engine. ????? The bump includes an isentropic compression surface raised outwardly from the body of the aircraft to form a portion of the inner surface of the inlet. The transition surface works with the compression surface to divert low energy boundary layer air from the inlet during aircraft operation.
First Claim
Family
International Classification(s)
Cited Art Landscape
Patent Citation Ranking
Advertisement
Advertisement
Advertisement
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