发明名称 |
STRESS RELIEF OF SINGLE CRYSTAL SUPERALLOY ARTICLES |
摘要 |
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. |
申请公布号 |
EP0251983(B1) |
申请公布日期 |
1989.11.23 |
申请号 |
EP19870630113 |
申请日期 |
1987.06.25 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
HENRICKS, ROBERT JACOBI;MARCIN, JOHN JOSEPH;WAHL, JACQUELINE BURNS;PINKOWISH, ALEXANDER ALFONS |
分类号 |
C22F1/10;C22F1/00;C23F1/00;C30B33/00;F01D5/28;F02C3/06 |
主分类号 |
C22F1/10 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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