摘要
为了降低涡轮盘级间封严发生碰摩的风险,同时保证封严效率不降低和涡轮盘质量不增大,对涡轮盘结构进行优化设计。利用有限元法对稳态下涡轮篦齿径向间隙进行确定性分析,结果表明:3道篦齿的间隙不同;以灵敏度分析的方式确定影响篦齿间隙与涡轮盘质量的关键尺寸,并将其作为优化的设计变量;综合考虑载荷、材料性能、尺寸参数的不确定性和转子不平衡振动进行间隙概率分析,发现第3道篦齿有碰摩的风险;建立以减小前2道篦齿间隙、增大第3道篦齿间隙和不增加涡轮盘质量为约束条件的综合优化模型,并用NSGA-Ⅱ算法进行计算。优化结果表明:篦齿发生碰摩的风险降低了99.07%,涡轮盘质量减小了0.73%,在不同压比下流量系数减小了5.39%~6.01%,证明该综合优化方法可行。
In order to reduce the risk of rubbing between turbine disc stages,and at the same time to ensure that the sealing efficiency was not reduced and the mass of turbine disc was not increased,the optimization design of turbine disc structure was carried out. Deterministic analysis of radial clearance of turbine labyrinth was carried out in steady state using finite element method.The results show that the clearance of the three labyrinths is different.The key dimensions affecting labyrinth clearance and turbine disc mass were determined by sensitivity analysis as optimization design variables.Considering the uncertainty of load,material performance,dimension parameters and unbalanced vibration of rotor,the probability analysis of clearance was carried out.The results show that the third labyrinth has the risk of rubbing.A comprehensive optimization model with the constraint of reducing the first two labyrinth clearance,increasing the third labyrinth clearance and not increasing the mass of turbine disc was established and calculated by NSGA -Ⅱ algorithm.The optimization results show that the rubbing risk of labyrinth is reduced by 99.07%,the mass of turbine disc is reduced by 0.64%,and the flow coefficient decreases 5.39%-6.01% with different pressure ratio,which proves that the comprehensive optimization method is feasible.
作者
陈志英
汪宇峰
刘勇
赵连鹏
CHEN Zhi-ying;WANG Yu-feng;LIU Yong;ZHAO Lian-peng(School of Energy and Power Engineering,Beihang University,Beijing 100191,China)
出处
《航空发动机》
北大核心
2019年第5期19-25,共7页
Aeroengine
基金
国家自然科学基金(51575024)资助
关键词
优化设计
航空发动机
涡轮盘
篦齿封严
概率分析
多目标综合优化
流量系数
optimization design
aeroengine
turbine disc
sealing of labyrinth
probability analysis
multi-objective optimization
flow coefficient
作者简介
陈志英(1960),男,教授,研究方向为航空发动机结构强度可靠性及多学科优化,E-mail:chenzhiying@buaa.edu.cn。
