Nozzle ring for an aircraft engine gas turbine
Number of patents in Portfolio can not be more than 2000
United States of America Patent
Stats
-
Apr 8, 2003
Grant Date -
N/A
app pub date -
Aug 25, 2000
filing date -
Aug 30, 1999
priority date (Note) -
Expired
status (Latency Note)
Importance
Abstract
A nozzle ring for a gas turbine, more particularly for an aircraft engine, has at least one shroud with a circumferential surface and at least one blade with a surface. The shroud has at least one opening for fastening the blade. The blade has at least one end section with a platform which projects at least partially over its circumference and which has a transition curve and which is inserted into the opening.
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