涡轮转子叶片可靠性提升  

Reliability Improvement of Turbine Rotor Blade

作　　者：李瑜 付瑜[1] 许开富[1] 王振 万金川 王伟光[1] 董飞扬 郭鑫 LI Yu;FU Yu;XU Kaifu;WANG Zhen;WAN Jinchuan;WANG Weiguang;DONG Feiyang;GUO Xing(Xi’an Aerospace Propulsion Institute,Xi’an 710100,Shaanxi,China)

机构地区：[1]西安航天动力研究所,陕西西安710100

出　　处：《上海航天（中英文）》2023年第S01期213-219,共7页Aerospace Shanghai（Chinese&English）

摘　　要：针对某液体火箭发动机试验后涡轮转子叶片根部多次出现的裂纹问题,采用了定常和非定常的数值仿真方法,对涡轮工作全过程进行了计算,结果表明在多次起动工作过程中,叶片根部存在非定常的交变应力载荷,叶片的疲劳安全系数不足,因此试验后叶片根部出现裂纹。提出了在叶片顶部增加卫带结构的改进方案,提高叶片的疲劳安全系数,通过数值仿真计算,涡轮的效率提高了1.5%,静强度基本无影响,转子叶片的最小疲劳安全系数由0.40提高到3.78,满足不小于1.40的设计要求。改进后产品经过多种工况、多次起动的严格考核,试验后转子叶片根部完好无裂纹。结果表明:改进方案合理有效,可以提高涡轮转子叶片的可靠性。The fracture on the root of the turbo rotor blade occurs frequently after the liquid rocket engine test.The stability and non-stability numerical simulation method were conducted in this study for the whole working process of the turbine,and it was found that the fatigue safety factor of the blade was inadequate under the stress loading on the blade root,explaining the blade crack occurred after the liquid rocket engine test.The shroud structure on the roof of the rotor blade was installed to enhance the fatigue safety factor of the blade.The turbine efficiency was increased by 1.5%and the static strength of the turbine was unchanged basically.The minimum fatigue safety factor of the turbine rotor was increased from 0.40 to 3.78 to meet the 1.40 design demand.The improved product was validated by different work conductions and multi-start-up tests,and the structure of the turbo blades was intact and no cracks had been observed.The results prove that the improvement is reasonable and effective,contributing to the reliability of the turbine rotor blade.

关 键 词：转子叶片 多次起动 卫带 疲劳安全系数 

分 类 号：V434.211[航空宇航科学与技术—航空宇航推进理论与工程]