摘要
提出了一种针对涡轮机匣挂钩槽疲劳寿命的试验方案.该方案首先对涡轮机匣进行数值分析,得到危险部位的应力分布,再通过常温下机械加载来模拟危险部位总应力场,并在该载荷下获取涡轮机匣挂钩槽疲劳寿命.利用该方案,对新制作的涡轮机匣结构改进措施、原有涡轮机匣维修措施以及腐蚀影响进行了试验研究.结果表明:1新制作的涡轮机匣挂钩槽增加倒圆半径为0.8mm的圆角后,安全寿命在50%,95%置信度下可分别增加69%和198%;2原有涡轮机匣挂钩槽铣倒圆半径为1.5mm的内圆角后可以获得与新制作的涡轮机匣挂钩槽相近的疲劳寿命;3腐蚀会严重影响涡轮机匣挂钩槽的疲劳寿命.
An experimental scheme of studying the fatigue life of the turbine casing slot was presented.With the scheme,the stress field of the critical section was obtained by numerical analysis,and mechanical loading was applied to simulate the total stress field of the critical section at room temperature.Under the load,the fatigue life of the turbine casing slot can be obtained.Using the proposed scheme,structural improvement measure of new turbine casing,modification measure of old turbine casing and the effect of corrosion were evaluated experimently.The results show that：（1）rounding the new turbine casing slotcorner with a 0.8mm-radius can increase the safe life by 69% and 198% with confidence of50% and 95%,respectively;（2）a fatigue life similar to the new turbine casing slot can be obtained through cutting a 1.5mm-radius corner on the old turbine casing slot;（3）corrosion can affect the fatigue life of the turbine casing slot significantly.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2014年第11期2735-2742,共8页
Journal of Aerospace Power
基金
国家自然科学基金(11272025)
