Gas turbine blades

Details Gas turbine blades Gas turbine blades

C - Chemistry, Metallurgy

25

D

204/24, 57/4

C25D 15/00 (2006.01) B24D 99/00 (2010.01) B24D 3/06 (2006.01) C23C 10/02 (2006.01) C25D 7/00 (2006.01) F01D 5/20 (2006.01)

Patent

CA 2036904

A method of producing a gas turbine blade having an abrasive tip comprising producing a binding coat on the tip of the blade body by electrodeposition, the binding coat comprising MCrAlY where M is one or more of iron, nickel and cobalt, anchoring to the binding coat coarse particles of an abrasive material by composite electrodeposition of the particles and an anchoring coat from a bath of plating solution having the abrasive particles suspended therein, and then plating an infill around the abrasive particles. The anchoring coat may be of cobalt or nickel or MCrAlY as above defined and preferably has a thickness less than 30 µm. The infill material may also be MCrAlY as above defined. Preferably, deposition of the infill is accompanied by vibration of the blade in a direction which is substantially vertical and substantially along the axis of the blade.

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