单晶涡轮叶片晶体取向优化设计  

Optimization design of crystallographic orientation in single crystal turbine blade

作　　者：卿华[1,2] 江和甫[1] 温卫东[2] 吴长波[1] 胡仁高[1] 覃志贤[1] 孙景国[1] 

机构地区：[1]中国燃气涡轮研究院,成都610500 [2]南京航空航天大学能源与动力学院,南京210016

出　　处：《航空动力学报》2008年第12期2184-2189,共6页Journal of Aerospace Power

摘　　要：采用损伤型晶体蠕变滑移本构模型,对具体工况下某发动机单晶涡轮叶片进行蠕变变形分析.应用多学科优化设计理论采用自适应模拟退火(ASA)算法和非线性序列二次规划(NLSQP)优化算法对单晶叶片晶体取向进行优化设计.叶片分析结果表明:叶片纵向的晶体取向偏角和叶片横向随机取向的晶向角,对单晶叶片的叶尖蠕变变形具有较大的影响.对随机晶向角进行一维优化,当晶向角为76.2°时,叶片具有最小的叶尖径向位移0.077 74 mm,优化幅度为2.0%;叶片纵向偏差角0°时的叶尖径向位移为0.079 29mm,10°时的叶尖最大位移为0.093 52 mm,最大变化幅度为17.9%.A two-damage-variable creep constitutive model was used to analyze the creep deformation of nickel-based single crystal turbine blades. Based on multidisciplinary design optimization theory, the crystallographic orientation optimization was performed by ASA（adaptive simulation annealing） and NLSQP（non linear sequential quadratic programming） algorithm. The analysis results show that controlled orientation and uncontrolled orientation have profound influence on creep deformation of single crystal turbine blades. The minimal radial displacement of blade tip is 0. 07774mm, when one of uncontrolled crystal orientations is 76.2° in one dimensional optimization state. The optimization amplitude is 2.0%. The minimal radial displacement of blade tip is 0. 07378mm, when two uncontrolled crystal orientations are 63.7° and 81.4°, respectively in two dimensional optimization states. The optimization amplitude is 5.4%. The radial displacements of blade tip are 0. 07929mm and 0. 09352 mm when the controlled orientations are 0° and 10°, respectively. The amplitude variation is 17.9%.

关 键 词：镍基单晶 晶体取向 涡轮叶片 优化设计 损伤 

分 类 号：V231.91[航空宇航科学与技术—航空宇航推进理论与工程]