| 涡轮叶片复合疲劳特性曲线及其规律的试验 |
| |
| 引用本文： | 闫晓军,孙瑞杰,邓瑛,刘芝娜,聂景旭.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. |
| |
| 作者姓名： | 闫晓军 孙瑞杰 邓瑛 刘芝娜 聂景旭 |
| |
| 作者单位： | 北京航空航天大学能源与动力工程学院,北京,100191 |
| |
| 基金项目： | 国家自然科学基金(10872015); 教育部“新世纪优秀人才支持计划”(NCET-06-0178); 航空科学基金(2008ZB51017); 全国优秀博士学位论文作者专项资金(200351) |
| |
| 摘 要： | 为了解高周振动载荷对于涡轮叶片高温疲劳性能的影响，对某型涡轮叶片进行高低周复合疲劳试验．试验结果表明，在低周载荷基础上叠加高频振动载荷，显著缩短了叶片的疲劳寿命；复合疲劳的分散性很大，且不存在疲劳极限，当叶片高周循环次数超过10^7时，继续试验叶片仍会发生断裂；在双对数坐标下，叶片的振动应力与其高周循环寿命成线性关系，即复合疲劳特性曲线（应力-寿命曲线、概率应力-寿命曲线）服从双对数线性规律，进一步研究发现该规律对于高温合金材料的复合疲劳特性曲线具有普遍性．
|
| 关 键 词： | 涡轮叶片 高低周复合疲劳 振动应力 疲劳特性曲线 双对数线性 |
| 收稿时间： | 2010/7/28 0:00:00 |
| 修稿时间： | 2010/11/2 0:00:00 |
Experimental study on fatigue curve law of turbine blade under combined high and low cycle loading |
| |
| YAN Xiao-jun,SUN Rui-jie,DENG Ying,LIU Zhi-na and NIE Jing-xu.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. |
| |
| Authors: | YAN Xiao-jun SUN Rui-jie DENG Ying LIU Zhi-na and NIE Jing-xu |
| |
| Institution: | School of Jet Propulsion, Beijing University of Aeronautics and Astronautics,Beijing 100191,China;School of Jet Propulsion, Beijing University of Aeronautics and Astronautics,Beijing 100191,China;School of Jet Propulsion, Beijing University of Aeronautics and Astronautics,Beijing 100191,China;School of Jet Propulsion, Beijing University of Aeronautics and Astronautics,Beijing 100191,China;School of Jet Propulsion, Beijing University of Aeronautics and Astronautics,Beijing 100191,China |
| |
| Abstract: | The effect of the high cycle vibration load on the high-temperature fatigue properties of the turbine blade were addressed.Combined high and low cycle fatigue tests were carried out on several blade specimens.The results show that the superposition of high-frequency vibration on low-cycle load can significantly reduce the fatigue life of the blade.It is noteworthy that combined high and low cycle fatigue has two features:great dispersion and no fatigue limit.The former is exhibited by much broader life range than the low cycle fatigue (LCF) test,and the latter indicated by fracture of the blades over 107 high cycles (which is considered as the life limit of the metal materials for the invariable-amplitude fatigue).In addition,the fatigue data suggest a double logarithmic linear relationship between vibration stress level and the combined fatigue life.Further research has found that the law for superalloys operates universally. |
| |
| Keywords: | turbine blade combined high and low cycle fatigue vibration stress fatigue curve double logarithmic linear |
| 本文献已被 CNKI 万方数据 等数据库收录！ |
| 点击此处可从《航空动力学报》浏览原始摘要信息 |
| 点击此处可从《航空动力学报》下载免费的PDF全文 |
|
