IC10合金涡轮叶片叶身不同部位取样的力学性能试验  

Study on Mechanical Properties of IC10 Alloy Specimens from Different Positions of Turbine Blade

作　　者：董自超 迟庆新 王威 王全 刘芳 耿瑞 DONG Zi-chao;CHI Qing-xin;WANG Wei;WANG Quan;LIU Fang;GENG Rui(AECC Shenyang Engine Research Institute,Shenyang 110015,China)

机构地区：[1]中国航发沈阳发动机研究所,沈阳110015

出　　处：《航空发动机》2023年第2期149-154,共6页Aeroengine

基　　金：航空动力基础研究项目资助。

摘　　要：为评估服役前IC10合金涡轮叶片不同部位的真实材料力学性能,与《航空发动机设计用材料数据手册》中采用标准试棒获得的性能数据进行对比。在选取的新叶片的叶身尾缘、叶背和叶盆处沿叶高方向完成小尺寸的工字形试验件取样,通过优化设计的工装在保证加载同轴度和安装一致性的基础上进行单轴加载试验,即900℃拉伸试验以及900℃、342/374 MPa的持久寿命试验。试验结果表明:试样均在平行段断裂,符合试验设计要求;相比于手册中标准试棒的测试数据,试样的抗拉强度下降约20%,持久寿命缩短达76%~85%;不同叶身部位的原始组织形貌相似,试样性能差别不大;应力提高会导致取样的持久寿命明显降低,其中盆侧取样的降低幅度最大,约64%。相比于标准试棒,叶身的本体取样兼具了铸造叶片的晶体取向和薄壁特征,在一定程度上可以真实反映叶片的力学性能,为客观评价IC10合金涡轮叶片材料力学性能奠定了基础。In order to assess the actual material mechanical properties of different parts of IC10 alloy turbine blade before service,a comparison was made with the performance data of standard test bars from the handbook—Material Data for Aeroengine Design.Small-size I-shaped specimens were taken from the trailing edge,concave side,and convex side of the selected new blade along the blade height di⁃rection.The uniaxial loading tests,including the tensile tests and the creep rupture life tests at 900℃and 342/374MPa were carried out on the basis of ensuring loading coaxiality and installation consistency by optimized fixtures.The test results show that all the specimens are broken in the parallel segments,which meets the test design requirements.Compared with the data of standard test bars from the hand⁃book,the ultimate tensile strength of the blade specimens decreases by about 20%,and creep rupture life decreases by 76%to 85%.The morphology and performance of the specimens taken from different positions of the blade are similar.Increased stress will result in a signifi⁃cant reduction of creep rupture life,with the largest decrease of about 64%in the specimen from the convex side.Compared with the stan⁃dard test bars,the specimens taken from the blade combine the crystal orientation and thin-wall characteristics of the cast blade,which can reflect the actual mechanical properties of the blade to a certain extent,laying the foundation for the objective assessment of the materi⁃al mechanical properties of IC10 alloy turbine blade.

关 键 词：涡轮叶片 IC10合金 本体取样 拉伸性能 蠕变断裂寿命 航空发动机 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]