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公开(公告)号：EP0251983B1
公开(公告)日：1989-11-23
申请号：EP87630113.6
申请日：1987-06-25
发明人： Henricks, Robert Jacobi , Marcin, John Joseph , Wahl, Jacqueline Burns , Pinkowish, Alexander Alfons
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.
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2.发明公开Stress relief of single crystal superalloy articles 失效Tempern von einkristallinenSuperlegierungskörpern。
公开(公告)号：EP0251983A1
公开(公告)日：1988-01-07
申请号：EP87630113.6
申请日：1987-06-25
发明人： Henricks, Robert Jacobi , Marcin, John Joseph , Wahl, Jacqueline Burns , Pinkowish, Alexander Alfons
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.
摘要翻译： 经受燃气轮机发动机运行的涂层镍基超级合金单晶涡轮机翼片（1）在暴露于某些腐蚀性介质时，可通过应力腐蚀机制在翻新过程中破裂。 在典型的燃气涡轮发动机运行期间发生的快速热循环导致跨越翼型的高的非均匀应力，在环境温度下在制品中产生大的局部残余应变。 暴露在腐蚀性环境中，例如在涂层去除或侵蚀性清洁过程中，会在暴露的大量翼型件中产生弦向裂纹。 在暴露于腐蚀性介质之前，通过对制品进行预备的应力消除热处理来避免这种开裂，将残余应变降低至不会发生裂纹的水平。
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