Gas-Turbine Aircraft Engine With Structural Surface Cooler
Number of patents in Portfolio can not be more than 2000
United States of America Patent
Stats
-
N/A
Issued Date -
Jan 10, 2013
app pub date -
Jul 5, 2012
filing date -
Jul 8, 2011
priority date (Note) -
Abandoned
status (Latency Note)
Importance
Loading Importance Indicators... 
Abstract
The present invention relates to a gas-turbine aircraft engine with a core engine surrounded by a bypass duct, with a substantially annular cooling element being provided in the area of a radially inner wall of the bypass duct downstream of stator vanes of the bypass duct.
Loading the Abstract Image...
OK
First Claim
Family
Loading Family data...
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