Stress relief of single crystal superalloy articles

Details Stress relief of single crystal superalloy articles Stress relief of single crystal superalloy articles

1986-06-30

1988-03-08

Dean, R.

Metal treatment

Compositions

Heat treating

148 203, 148404, C22F 110

Patent

active

047297999

ABSTRACT:
A coated nickel base superalloy single crystal turbine airfoil blade (1), which is subject to gas turbine engine operation, can crack during refurbishment by a stress corrosion mechanism when exposed to certain corrosive media. The rapid thermal cycling that occurs during typical gas turbine engine operation results in high, non-uniform stresses across the airfoil, producing large localized residual strains in the article at ambient temperatures. Exposure to a corrosive environment, such as during coating removal or agressive cleaning, can produce chordwise cracks in a large number of the airfoils exposed. Such cracking is avoided by subjecting the articles to a preliminary stress relieving heat treatment which reduces the residual strains to a level below which cracking will not occur, prior to exposure to the corrosive media.

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