DZ125定向凝固合金的喷丸工艺

doi:10.13251/j.issn.0254-6051.2021.01.028

摘要/Abstract

摘要： 针对DZ125合金开展铸钢丸喷丸强化研究,分析了多种喷丸强度、覆盖率条件下合金700 ℃旋弯疲劳性能、表面残余应力和硬度梯度。结果表明:随喷丸强度的增大,中值疲劳寿命估计量逐渐增大,高喷丸强度时,700 ℃/500 MPa中值疲劳寿命估计量是原始试样的2倍;随表面覆盖率的增大,中值疲劳寿命估计量呈现先增大后稳定的趋势,当覆盖率达到400%时,中值疲劳寿命估计量达到稳定;高喷丸强度且表面覆盖率达到400%时疲劳极限为480 MPa,较原始试样疲劳极限(400 MPa)提高20%。残余应力和组织强化机制是DZ125合金喷丸的强化因素,随着喷丸强度的增大,残余压应力数值略有减小,但均明显大于原始状态;高喷丸强度时,覆盖率400%时DZ125合金表面产生超过200 μm深度的硬度场,且表面硬度较基体(430 HV0.1)提高37%。当缺口部位实际载荷大于屈服强度时,疲劳过程中残余应力和硬度都将明显松弛,经历700 ℃/600 MPa/1.5×10⁵周次的断裂试样,表面残余应力降低54%,表面硬度下降14%。

关键词: DZ125合金, 喷丸强度, 表面覆盖率, 疲劳, 应力松弛

Abstract: Cast-steel shot peening was employed on directionally solidified alloy DZ125 to analyze the fatigue property,surface residual stress and microhardness profile under various shot peening intensity and coverage conditions.The results show that with the increase of shot peening intensity,the estimated median fatigue life increases gradually.At high intensity,the estimated median fatigue life at 700 ℃/500 MPa is 2 times that of the original specimen.Moreover,with the increase of surface coverage,the estimated median fatigue life increases first and then stabilizes,and when the coverage reaches 400%,the estimated median fatigue life is stable.When the shot peening intensity is high and at the coverage rate of 400%,the fatigue limit is 480 MPa,which is 20% higher than the original value (400 MPa).Residual stress and microstructure strengthening mechanism are the strengthening factors of shot peening for DZ125 alloy.With the increase of shot peening intensity,the residual compressive stress decreases slightly,but it is still obviously larger than the original state.When the shot peening intensity is high and at the coverage rate of 400%,the surface hardness field of DZ125 alloy exceeds 200 μm in depth,and the surface hardness is 37% higher than that of the matrix (430 HV0.1).When the actual load at the notch is greater than the yield strength,the residual stress and hardness are relaxed obviously during fatigue process;the surface residual stress of the fractured specimen decreases by 54% and the surface hardness decreases by 14% after 700 ℃/600 MPa/1.5×10⁵ cycles.

Key words: DZ125 alloy, shot peening intensity, surface coverage, fatigue, stress relaxation

中图分类号:

TG668
V263.5

王欣, 杨清, 于鹏, 马世成. DZ125定向凝固合金的喷丸工艺[J]. 金属热处理, 2021, 46(1): 149-153.

Wang Xin, Yang Qing, Yu Peng, Ma Shicheng. Shot peening process of directionally solidified DZ125 alloy[J]. Heat Treatment of Metals, 2021, 46(1): 149-153.

参考文献

[1] 陈荣章,佘力,张宏炜,等.DZ125定向凝固高温合金的研究[J].航空材料学报,2000,20(4):14-19.
Chen Rongzhang,She Li,Zhang Hongwei,et al.Investigation of directionally solidified alloy DZ125[J].Journal of Aeronautical Materials,2000,20(4):14-19.
[2] 陈荣章,王罗宝,佘力,等.DZ125定向凝固涡轮叶片合金研究[J].材料工程,1997(9):9-12.
Chen Rongzhang,Wang Luobao,She Li,et al.Directionally solidified blade superalloy DZ125[J].Journal of Materials Engineering,1997(9):9-12.
[3] 闫晓军,孙瑞杰,邓瑛,等.涡轮叶片复合疲劳特性曲线及其规律的试验[J].航空动力学报,2011,26(8):1824-1829.
Yan Xiaojun,Sun Ruijie,Deng Ying,et al.Experimental study on fatigue curve law of turbine blade under combined high and low cycle loading[J].Journal of Aerospace Power,2011,26(8):1824-1829.
[4] 张国栋,刘绍伦,何玉怀,等.定向合金DZ125热/机械疲劳寿命预测模型评估[J].航空动力学报,2004,19(1):17-22.
Zhang Guodong,Liu Shaolun,He Yuhuai,et al.Life predication of thermomechanical fatigue in DS superalloy DZ125[J].Journal of Aerospace Power,2004,19(1):17-22.
[5] 张国栋,刘绍伦,何玉怀,等.相位角对定向合金DZ125热/机械疲劳行为与寿命影响的试验研究[J].航空动力学报,2003,18(3):383-387.
Zhang Guodong,Liu Shaolun,He Yuhuai,et al.Influence of crystal-orientation on the behavior and life of thermal-mechanical fatigue in DS superalloy DZ125[J].Journal of Aerospace Power,2003,18(3):383-387.
[6] 顾玉丽,陶春虎,佘力,等.DZ125高温合金超高周疲劳裂纹萌生与扩展[J].失效分析与预防,2014,9(6):323-329.
Gu Yuli,Tao Chunhu,She Li,et al.Analysis on ultra-high cycle fatigue crack initiation and propagation characteristics of DZ125 superalloy[J].Failure Analysis and Prevention,2014,9(6):323-329.
[7] 顾玉丽,滕旭东,刘昌奎,等.DZ125定向凝固高温合金长期时效后的显微组织和超高周疲劳行为[J].航空学报,2012,33(11):2136-2142.
Gu Yuli,Teng Xudong,Liu Changkui,et al.Microstructures and ultra-high cycle fatigue behaviors of directionally solidified superalloy DZ125 after long-term aging[J].Acta Aeronautica et Astronautica Sinica,2012,33(11):2136-2142.
[8] 刘金龙,杨晓光,石多奇,等.不同保载时间作用下的定向凝固合金DZ125的高温低循环疲劳试验研究[J].航空材料学报,2010(5):88-92.
Liu Jinlong,Yang Xiaoguang,Shi Duoqi,et al.Experimental study on low cycle fatigue of directionally solidified superalloy DZ125 with different holding time[J].Journal of Aeronautical Materials,2010(5):88-92.
[9] 宋颖刚,高玉魁,陆峰,等.GH4169合金喷丸强化层组织结构研究[J].金属热处理,2010,35(9):100-103.
Song Yinggang,Gao Yukui,Lu Feng,et al.Investigation of microstructure of GH4169 alloy surface layer after shot peening[J].Heat Treatment of Metals,2010,35(9):100-103.
[10] 张在玉,梁益龙,袁顺金,等.水射流喷丸处理对20CrMnTi钢表面性能的影响[J].金属热处理,2018,43(7):174-179.
Zhang Cunyu,Liang Yilong,Yuan Shunjin,et al.Effect of water jet shot peening on surface properties of 20CrMnTi steel[J].Heat Treatment of Metals,2018,43(7):174-179.
[11] 姜涛,刘建平,于洋,等.喷丸对DZ4合金旋转弯曲疲劳断裂特征的影响[J].宇航材料工艺,2013,43(3):120-125.
Jiang Tao,Liu Jianping,Yu Yang,et al.Effect of shot peening on rotary bending high-cycle fatigue fracture features of superalloy DZ4[J].Aerospace Materials and Technology,2013,43(3):120-125.
[12] 高玉魁,姜涛.喷丸强化对DZ4定向凝固高温合金高温旋转弯曲疲劳性能的影响[J].航空材料学报,2010(6):35-38.
Gao Yukui,Jiang Tao.Influence of shot peening on high temperature fatigue property of DZ4 directionally solidified superalloy[J].Journal of Aeronautical Materials,2010(6):35-38.
[13] HB/Z 26-2011.航空零件喷丸强化工艺[S].2011.
[14] HB 5153-1996.金属高温旋转弯曲疲劳试验方法[S].1996.
[15] HB/Z 112-1986.材料疲劳试验统计分析方法[S].1986.
[16] 王欣,胡云辉,赵振业,等.喷丸强度对两种耐热合金表面完整性和高温疲劳性能的影响[C]//第十八届全国疲劳与断裂学术会议论文摘要集.郑州,2016.
[17] 王仁智.金属材料的喷丸强化原理及其强化机理综述[J].中国表面工程,2012,25(6):1-9.
Wang Renzhi.Overview on the shot peening principle and its strengthening mechanisms for metallic materials[J].China Surface Engineering,2012,25(6):1-9.
[18] 王欣,尤宏德,李嘉荣,等.陶瓷弹丸喷丸强化对DD6单晶高温合金表面完整性的影响[J].材料工程,2014,21(4):53-57.
Wang Xin,You Hongde,Li Jiarong,et al.Influence of ceramic-shot-peening on surface integrity of DD6 single crystal superalloy[J].Journal of Materials Engineering,2014,21(4):53-57.