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題名 | 壓縮應力對鋁鋰合金(2090-T8)之疲勞裂縫成長特性研究 |
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作者姓名(中文) | 丁明仁; 林聖朝; 吳以正; | 書刊名 | 材料科學 |
卷期 | 25:3 1993.09[民82.09] |
頁次 | 頁214-217 |
分類號 | 440.39 |
關鍵詞 | 疲勞; 裂縫成長; 鋁鋰合金; 壓縮應力; |
語文 | 中文(Chinese) |
中文摘要 | 鋁鋰合金由於具有高比強度、低密度、高彈性模數及較優之疲勞裂縫成 長速率(FCGR)等特性,可應用於飛機結構件,以取代傳統的2000系與7000系鋁合 金。本實驗選擇2090-T8鋁鋰合金與7075-T73鋁合金做比對,研究壓縮應力(R<0) 同時作用下FCGR性質之差異。再以掃描式電子顯微鏡(SEM)觀察破斷面,以瞭解 影響FCGR性質之破壞機構。 結果顯示,2090-T8鋁鋰合金之FCGR性質優於7075-T73鋁合金約0.3至1次方,唯 7075-T73鋁合金之FCGR性質幾乎不受壓縮應力之影響,而2090-T8鋁鋰合金卻因 壓縮應力造成△Kth降低之趨勢。 由破斷面分析發現,2090-T8鋁鋰合金較優之FCGR性質主要是由於斷面粗糙效應 所引起,但壓縮應力會造成斷面磨擦機率增加,使得粗糙斷面被磨平,降低對裂 縫尖端之遮蔽(Shield)效應。 |
英文摘要 | The properties of aluminum-lithium alloys are higher elastic modulus, lower density and superior fatigue crack growth rate than conventional aluminum alloys. They have been identified as prime candidates for replacing 2000 and 7000 series aluminum alloys currently used in aircraft structural components. The FCGR behavior of 2090-T8 Al-Li and 7075-T73 Al alloy under tension-compression and tension-tension stress conditions were studied, the crack fractography and failure mechanism were also investigated by SEM. The fatigue crack resistance of 2090-T8 is better than 7075-T73 by 0.3-1.0 order of magnitude. The 7075-T73 A1-alloy were insensitive to compression stress. But, compression stress results in decreasing AKth in 2090-T8 A1-Li alloy. The fracture surfaces of 2090-T8 are rough. It results in the crack tip be shielded by the previous rough surface. And the compression stress will increase the probabilities of friction, and decrease the shielding effect of crack tip. |
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