主动填充式搅拌摩擦腐蚀坑修复件疲劳性能研究
|
摘要
采用主动填充式搅拌摩擦修复技术对含预制腐蚀坑的2A12铝合金板进行修复试验。通过对修复试样的微观组织、截面硬度进行观察与测试,并对修复试样与未修复试样以及母材进行疲劳寿命试验,研究其疲劳性能的变化。结果表明:根据修复区的组织特征,修复区可以分成母材、热影响区、热机影响区和修复核心区四部分。修复试样修复区的截面硬度分布呈"W"形,最小值出现在热机影响区附近;修复后试样的平均寿命有了很大提升,是未修复试样寿命的6.6倍左右,未修复试样和修复试样的疲劳寿命分别达到母材的6.28%和41.3%。疲劳断口显示未修复试样稳定扩展区的疲劳条带间距比修复试样的稳定扩展区间距大,说明未修复试样的裂纹扩展的比已修复的快,而且修复试样的稳定扩展区中出现大量脱落的第二相粒子。
The 2 A12 aluminum alloy plate with prefabricated corrosion pit was repaired by active filling friction stir repair technology. The microstructure and cross-section hardness of the repaired specimens were observed and tested, and the fatigue life tests of the repaired specimens, the unrepaired specimens and the base metal were tested to study the change of fatigue property. The results show that according to the microstructure of the repair zone, the repair zone can be divided into four parts: base metal, heat affected zone, heat mechanical affected zone and repair core zone. The hardness distribution of the cross section of repair zone of the repaired specimen presents "W" shape, and the minimum value appears near the heat mechanical affected zone. The average life of the sample after repair improves significantly, which is 6.6 times of that of the unrepaired sample, and the fatigue lives of unrepaired and repaired samples reach 6.28% and 41.3% of that of the base material, respectively. The fatigue fracture shows that the spacing of fatigue bands in the stable growth zone of the unrepaired specimens is larger than that of the repaired specimens, which indicates that the crack growth of the unrepaired specimens is faster than that of the repaired specimens, and a large number of second phase particles appear in the stable growth zone of the repaired specimens.
The 2 A12 aluminum alloy plate with prefabricated corrosion pit was repaired by active filling friction stir repair technology. The microstructure and cross-section hardness of the repaired specimens were observed and tested, and the fatigue life tests of the repaired specimens, the unrepaired specimens and the base metal were tested to study the change of fatigue property. The results show that according to the microstructure of the repair zone, the repair zone can be divided into four parts: base metal, heat affected zone, heat mechanical affected zone and repair core zone. The hardness distribution of the cross section of repair zone of the repaired specimen presents "W" shape, and the minimum value appears near the heat mechanical affected zone. The average life of the sample after repair improves significantly, which is 6.6 times of that of the unrepaired sample, and the fatigue lives of unrepaired and repaired samples reach 6.28% and 41.3% of that of the base material, respectively. The fatigue fracture shows that the spacing of fatigue bands in the stable growth zone of the unrepaired specimens is larger than that of the repaired specimens, which indicates that the crack growth of the unrepaired specimens is faster than that of the repaired specimens, and a large number of second phase particles appear in the stable growth zone of the repaired specimens.
引文
[1] Moreira P,Jesus D,Ribeiro S,et al. Fatigue crack growth in friction stir welds of 6082-T6 aluminum alloys[J]. Theoretical and Applied Fracture Mechanics,2008,50(2):81-91.
[2] Adamowski J,Szkodo M. Friction stir welds(FSW)of aluminum alloy 6082-T6[J]. Journal of Achievements in Materials and Maufacturing Engineering,2007,12(5):44-48.
[3]王希靖,韩晓辉,郭瑞杰,等.搅拌摩擦焊接过程温度场数值模拟[J].焊接学报,2005,26(12):17-20.
[4] Jaroslav M. Mechanics of components with treated or coated surfaces[M]. Netherlands:Kluwer Academic Publishers,1996:5-1.
[5]徐崇义,李念奎. 2×××系铝合金强韧化的研究与发展[J].轻合金加工技术,2005,33(8):13-17.
[6]王池权,熊峻江,马少俊,等.航空铝合金材料腐蚀裂纹扩展性能试验[J].北京航空航天大学学报,2017,43(5):935-941.
[7]王荣.金属材料的腐蚀疲劳[M].西安:西北工业大学出版社,2001:2-6.
[8] Shekhter A,Crawford B R,Loader C,et al. The effect of pitting corrosion on the safe-life prediction of the royal Australian air force P-3C Orion aircraft[J].Engineering Failure Analysis,2015,55:193-207.
[9]穆志韬,李旭东,刘治国.飞机结构材料环境腐蚀与疲劳分析[M].北京:国防工业出版社,2014:3-6.
[10] Schmidt H B,Hattel J H.Thermal modelling of friction stir welding[J]. Scripta Materialia,2008,58(5):332-337.
[11]姬书得,孟庆国,史清宇,等.搅拌针形状影响搅拌摩擦焊过程金属塑性流动规律的数值模拟[J].焊接学报,2013,34(2):93-96.
[12] Wan L, Huang Y X, Lu Z L, et al.Effect of self-support friction stir welding on microstructure and microhardness of6082-T6 aluminum alloys joint[J].Materials and Design,2014,55:197-203.
[2] Adamowski J,Szkodo M. Friction stir welds(FSW)of aluminum alloy 6082-T6[J]. Journal of Achievements in Materials and Maufacturing Engineering,2007,12(5):44-48.
[3]王希靖,韩晓辉,郭瑞杰,等.搅拌摩擦焊接过程温度场数值模拟[J].焊接学报,2005,26(12):17-20.
[4] Jaroslav M. Mechanics of components with treated or coated surfaces[M]. Netherlands:Kluwer Academic Publishers,1996:5-1.
[5]徐崇义,李念奎. 2×××系铝合金强韧化的研究与发展[J].轻合金加工技术,2005,33(8):13-17.
[6]王池权,熊峻江,马少俊,等.航空铝合金材料腐蚀裂纹扩展性能试验[J].北京航空航天大学学报,2017,43(5):935-941.
[7]王荣.金属材料的腐蚀疲劳[M].西安:西北工业大学出版社,2001:2-6.
[8] Shekhter A,Crawford B R,Loader C,et al. The effect of pitting corrosion on the safe-life prediction of the royal Australian air force P-3C Orion aircraft[J].Engineering Failure Analysis,2015,55:193-207.
[9]穆志韬,李旭东,刘治国.飞机结构材料环境腐蚀与疲劳分析[M].北京:国防工业出版社,2014:3-6.
[10] Schmidt H B,Hattel J H.Thermal modelling of friction stir welding[J]. Scripta Materialia,2008,58(5):332-337.
[11]姬书得,孟庆国,史清宇,等.搅拌针形状影响搅拌摩擦焊过程金属塑性流动规律的数值模拟[J].焊接学报,2013,34(2):93-96.
[12] Wan L, Huang Y X, Lu Z L, et al.Effect of self-support friction stir welding on microstructure and microhardness of6082-T6 aluminum alloys joint[J].Materials and Design,2014,55:197-203.