Turbine blade having a fused metal-ceramic abrasive tip

Details Turbine blade having a fused metal-ceramic abrasive tip Turbine blade having a fused metal-ceramic abrasive tip

B - Operations, Transporting

63

H

170/60

B63H 1/26 (2006.01) F01D 5/20 (2006.01)

Patent

CA 1284770

ABSTRACT A gas turbine engine blade has an abrasive material tip with a used superalloy matrix and evenly distributed ceramic particu- late. The matrix will have a desirable metallurgical structure characterized by fine dendrites and remnants of the original powder metal structure from which it was made. Due to the fusion of the tip, the peripheral edge will tend to be curved. To lessen the effect of thermal strains on such an abrasive tip, a sheath of a superalloy, such as a portion of the the turbine blade substrate, extends along the side of the abrasive. The sheath may be present only in the thicker leading edge part of the blade airfoil.

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