摘要
针对某型飞行器使用的高负荷涡轮增压器,对其涡轮关键件进行强度振动寿命的计算分析,并从力学角度对结构设计进行评估。研究结果表明,涡轮叶轮应力幅值区出现在进气端盘轴连接处,静强度安全系数为1.9,满足静强度设计要求;涡轮叶轮在工作转速下,具有不低于15%的共振裕度,满足动力学设计要求;涡轮叶片对应无限循环疲劳寿命的许用振动应力为116.4 MPa,可以确保其在各工况下满足可靠性设计要求;在标准飞行剖面下,叶轮寿命为5494次工作循环,满足寿命要求。
A series of strength analysis and mechanical evaluation are performed for a certain turbine used in an astronautics product. The results reveal that the maximum stress of the turbine located at the head of the disc, and the strength safety factor is 1.9, which satisfies the static strength＇ s requirement ; the resonance margin is greater than 15%, which satisfies the dynamical requirement; the allowable vibratory stress of the blade is 116.4MPa, which ensures the blade meet the reliability requirements; the operation cycle can reach 5494 times at standard mission profile.
出处
《战术导弹技术》
2014年第5期87-91,共5页
Tactical Missile Technology
关键词
涡轮
有限元
静强度
振动
寿命
turbine
finite element analysis
strength analysis
vibration
operation life
