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US 10,094,227 B2Granted
Gas turbine engine blade tip treatment
AssigneeUnited Technologies Corporation
InventorZhongfen Ding
Life of this patent
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Abstract
A fan blade and method of manufacturing a fan blade includes a metallic fan blade body with a crystalline oxidation layer and immersing the crystalline oxidation layer in a solution of ceramic nanosheets in suspension. A fan blade for a gas turbine engine includes a metallic fan blade body having a tip with a crystalline oxidation layer, wherein the crystalline oxidation layer includes pores containing ceramic nanosheets.
Claims20
A method of manufacturing a fan blade comprising:
- immersing at least a crystalline oxidation layer of a metallic fan blade body in a solution of ceramic nanosheets in suspension, the ceramic nanosheets having a charge of a first polarity;
- and
- applying a potential of a second polarity to the fan blade body while the crystalline oxidation layer is immersed in the solution of ceramic nanosheets in suspension, wherein the second polarity is different than the first polarity.
A fan blade for a gas turbine engine comprising:
- a metallic fan blade body including a tip with a crystalline oxidation layer;
- wherein the crystalline oxidation layer includes a plurality of pore channels;
- and
- wherein at least some of the plurality of pore channels include ceramic nanosheets.
1 more element
Dependencies are inferred from the claim text.