摘要
以某火箭发动机涡轮为对象,研究了涡轮叶片带冠、不带冠、带部分冠及叶片空心等典型结构形式对叶片低周疲劳寿命的影响。结果表明:叶片不带冠可以消除叶片顶部的疲劳损伤,但使叶背根部损伤增大,危险点位于叶背根部,叶片寿命与带冠叶片相当;带部分冠叶片在消除叶顶疲劳损伤的同时,还可以减缓叶背根部的低周疲劳,危险点位于前缘根部,寿命比原叶片高约116%;叶片空心结构可以有效降低叶片的应力应变水平,减缓叶片疲劳的效果最好,空心叶片危险点位于前缘根部,寿命比原叶片高约370%。
Effects of shrouded blade,unshrouded blade,blade with partial-shroud and hollow blade on blade life for rocket engine turbine were studied.Results reveal that unshrouded blade avoids fatigue at blade tip,while damage at root on suction side increases.The critical point locates at root on suction side.Life of unshrouded blade is close to shrouded blade.Blade with partial shroud not only eliminates fatigue at blade tip nearing trailing edge,but also mitigates fatigue at root on suction side.The critical point locates at root nearing leading edge.Life of blade with partial shroud is larger than the shrouded blade by 116%.Thermal strain and stress could be effectively reduced by using hollow blade,and thus low cycle fatigue damage decreases.The critical point locates at root nearing leading edge.Life of hollow blade is 370%larger than the shrouded blade.
作者
姜金朋
刘志超
刘筑
巩帆
王珏
JIANG Jinpeng;LIU Zhichao;LIU Zhu;GONG Fan;WANG Jue(Science and Technology on Space Physics Laboratory,China Academy of Launch Vehicle Technology,Beijing 100076,China;China Academy of Launch Vehicle Technology,Beijing 100076,China)
出处
《宇航总体技术》
2020年第5期51-64,共14页
Astronautical Systems Engineering Technology
关键词
火箭发动机
涡轮叶片
低周疲劳寿命
叶冠
空心叶片
Rocket engine
Turbine blade
Low cycle fatigue life
Blade shroud
Hollow blade
