Laser cladding a turbine engine vane platform
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United States of America Patent
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Dec 5, 2000
Issued Date -
N/A
app pub date -
Aug 16, 1999
filing date -
Aug 16, 1999
priority date (Note) -
Expired
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Abstract
A method of refurbishing turbine engine vanes in which an alloy blend of a cobalt based superalloy and a nickel based superalloy corresponding to the base material of the turbine vane cobalt platform and the base nickel material of the replacement turbine vane airfoils is laser clad to the gaspath surfaces of the turbine vane platform. Laser cladding with the alloy blend allows the use of replacement airfoils with improved castings in the form of improved nickel based superalloys, and allows a coating to be uniformly applied to the gaspath surfaces of the vane. According to the method, the platforms are separated from the airfoils and laser clad with a blend of cobalt based superalloy and nickel based superalloy. The vane is then reassembled using the laser clad platform and at least one replacement airfoil.
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