| 压气机旧叶片超载止裂的探索 |
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| 引用本文： | 侯静泳.压气机旧叶片超载止裂的探索[J].航空动力学报,1987,2(2):131-135,187. |
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| 作者姓名： | 侯静泳 |
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| 作者单位： | 北京航空材料研究所 |
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| 摘 要： | 为了提高压气机叶片的使用寿命,将超载迟滞机理直接用于已有840小时的服役寿命,且表面已有轻度损伤的不锈钢旧叶片上,以观察其对疲劳裂纹形成寿命的影响。结果表明,随超载比m的增加,裂纹形成寿命也增加,当m≥1.6时,叶片的剩余疲劳寿命有明显提高,而m<1.48时则并不显著。
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| 收稿时间： | 1986/10/1 0:00:00 |
RESEARCH ON OVERLOAD TO STOP CRACKING FOR USED COMPRESSOR BLADES |
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| Hou Jingyong.RESEARCH ON OVERLOAD TO STOP CRACKING FOR USED COMPRESSOR BLADES[J].Journal of Aerospace Power,1987,2(2):131-135,187. |
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| Authors: | Hou Jingyong |
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| Institution: | Institute of Aeronautical Materials |
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| Abstract: | In order to increase the service life of compressor blades, the effects of overload on fatigue crack formation life in the stainless steel compressor blades which have served for 840 hours and have had some damage on its surface have been investigated. The results show that the residual fatigue life of blades increases with the increasing overload ratio m, and when the overload ratio m≥1.6, the residual life of blades is obviously increased. But when m< 1.48, the effects of overload on blade life is not pronounced. |
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