Gas turbine blade for an aircraft engine and method for coating a gas turbine blade
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United States of America Patent
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Apr 18, 2017
Issued Date -
N/A
app pub date -
Jan 10, 2013
filing date -
Jan 13, 2012
priority date (Note) -
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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.
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