Gas turbine blade for an aircraft engine and method for coating a gas turbine blade
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United States of America Patent
Stats
-
Apr 18, 2017
Issued Date -
N/A
app pub date -
Jan 10, 2013
filing date -
Jan 13, 2012
priority date (Note) -
In Force
status (Latency Note)
Importance
Abstract
Embodiments relate to a gas turbine blade for an aircraft engine, the gas turbine blade having a flow leading edge, a flow trailing edge, a suction side, and a pressure side, where the suction side and pressure side extend from the flow leading edge to the flow trailing edge, wherein the gas turbine blade has a damping layer on the flow leading edge and the damping layer comprising at least one matrix material and particles held in position by this matrix material. Further embodiments relate to a method of coating a gas turbine blade and a gas turbine incorporating a plurality of gas turbine blades in accordance with embodiments of the invention.
First Claim
Other Claims data not available
Family
International Classification(s)
- 2013 Application Filing Year
- F01D Class
- 1696 Applications Filed
- 1490 Patents Issued To-Date
- 87.86 % Issued To-Date
Cited Art Landscape
Patent Citation Ranking
- 1 Citation Count
- F01D Class
- 19.76 % this patent is cited more than
- 8 Age
Maintenance Fees
| Fee | Large entity fee | small entity fee | micro entity fee | due date |
|---|---|---|---|---|
| 11.5 Year Payment | $7400.00 | $3700.00 | $1850.00 | Oct 18, 2028 |
