关键词：TC17钛合金；超声冲击强化；表面状态；高周疲劳；演化规律 中图分类号：V261 DOI：10.3969/j.issn.1004-132X.2025.04.016 开放科学（资源服务）标识码（OSID）：

Investigation on Evolution Laws for Surface States of TC17 Alloy Induced by UIT during High-cycle Fatigue at 400^∘C （204号

TAN Liang1，2*FAN Yi³ YAO Changfeng1.2 1.Key Laboratory of High Performance Manufacturing for Aero Engine，Ministry of Industry and Information Technology，Northwestern Polytechnical University，Xi'an，710072 2.Engineering Research Center of Advanced Manufacturing Technology for Aero Engine， Ministry of Education，Northwestern Polytechnical University，Xi'an，710072 3.Shaanxi Aikespu Electromechanical Technology Co.，Ltd.，Xi'an，710061

Abstract： Based on UIT experiments， surface state measurement and tension-tension high cycle fatigue tests at 400^∘C ，the evolution laws of surface roughness， surface morphology，residual stress， microhardness，and microstructure of TC17 alloy were investigated. Results show that，compared with the surface states of the UIT processed specimen，after 1h heating treatment at 400°C ，the value of surface roughness Ra increases from 0.46μm to 0.67μm ，the surface microhardness decreases from to 450HV0.025 ，the surface compressive residual stress decreases from -640MPa to -525MPa ，the maximum value of compressive residual stress decreases from -1088MPa to -776 （20 MPa ，and the depth of plastic deformation layer decreases from 20μm to 13μm . After fatigue failure of the specimen at 400^∘C ， the value of surface roughness Ra is as 1.22μm ， the depth of compressive residual stress layer is as 70μm ，the depth of plastic deformation layer is as 9μm ，and the subsurface equiaxed α phase transforms into elongated strips，the average grain area increases from 11.8μm² to 34μm² ：

Key words： TC17 titanium alloy; ultrasonic impact treatment（UIT）； surface state; high-cycle fatigue;evolution law

0 引言

航空发动机是国之重器，体现了国家的科技水平和综合实力。TC17钛合金因具有强度高、塑性好、耐腐蚀、高温性能优异等特点，被广泛应用于制造航空发动机风扇和压气机叶片和整体叶盘等关键重要转动构件[1]。该类构件要求在集高速、高压、高温、复杂振动于一体的极端环境条件下服役寿命达上万小时，先进航空发动机末级高压压气机温度可达 1000K ，压力接近40个标准大气压。在如此极端服役工况下，该类转动构件极易发生疲劳失效。现有资料表明，航空构件疲劳失效中 80% 以上的疲劳裂纹起始于表面加工缺陷或损伤，如切削刀痕、表面微裂纹、表层应变硬化、表层组织损伤、表层残余拉应力等。因此，表面状态对构件疲劳性能有着至关重要的影响。

为改善该类转动构件的加工表面状态，提高疲劳性能，通常采用表面强化对构件进行处理，但表面强化引入的表面状态在构件服役过程中不断演化，不同特征演化规律复杂，衰减速率各不相同。超声冲击强化（ultrasonic impact treatment，UIT）是一种新型的表面强化方法，该工艺可降低构件表面粗糙度，同时在表层引入较深的残余压应力和应变硬化层[2-4]。在超声冲击强化工艺参数对表面状态和疲劳性能影响研究方面，PANIN等[5]研究了纯钛试件经超声冲击强化后表层纳米结构中的非晶体学变形机制，在试样表面下20μm 和 50μm 处观察到含有位错和孪晶的 α -Ti晶粒；……