Turbine compressor blade tip resistant to metal transfer
Number of patents in Portfolio can not be more than 2000
United States of America Patent
Stats
-
May 17, 2016
Grant Date -
Dec 19, 2013
app pub date -
Jun 18, 2012
filing date -
Jun 18, 2012
priority date (Note) -
In Force
status (Latency Note)
Importance
Abstract
A gas turbine engine having an engine casing extending circumferentially about an engine centerline axis; and a compressor section, a combustor section, and a turbine section within said engine casing. At least one of said compressor section and said turbine section includes at least one airfoil and at least one seal member adjacent to the at least one airfoil, wherein a tip of the at least one airfoil is metal having a thin film ceramic coating and the at least one seal member is coated with an abradable.
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