Fluid reaction surfaces (i.e. – impellers) – Specific blade structure – Coating – specific composition or characteristic
Patent
1986-12-29
1989-02-07
Lieberman, Paul
Fluid reaction surfaces (i.e., impellers)
Specific blade structure
Coating, specific composition or characteristic
51293, 51295, 51308, 415172A, 415174, 416228, 291568B, B63H 126, B64C 1116, B64C 2746, F03B 312
Patent
active
048028282
ABSTRACT:
A gas turbine engine blade has an abrasive material tip with a fused superalloy matrix and evenly distributed ceramic particulate. The matrix will have a desirable metallurgical structure characterized by fine dendrites and remanants 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 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.
REFERENCES:
patent: 3779726 (1973-12-01), Fisk et al.
patent: 4249913 (1981-02-01), Johnson et al.
patent: 4589823 (1986-05-01), Koffel
patent: 4610698 (1986-09-01), Eaton et al.
patent: 4689242 (1987-08-01), Pike
patent: 4744725 (1988-05-01), Matarese et al.
Johnson Edward L.
Lee Edward
Rutz David A.
Schaefer Robert P.
Lieberman Paul
Nessler C. G.
Thompson Willie J.
United Technologies Corporation
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