涡轮冷却叶片参数化建模及多学科设计优化  

Parametric modeling and multidisciplinary design optimization for cooling turbine blade

作　　者：虞跨海[1] 岳珠峰[1] 

机构地区：[1]西北工业大学力学与土木建筑学院,西安710072

出　　处：《航空动力学报》2007年第8期1346-1351,共6页Journal of Aerospace Power

基　　金：国家自然科学基金(50375124;10472094);航空科学基金(03B53003)

摘　　要：建立了一个涉及结构、气动、传热、振动、强度和寿命等学科的涡轮冷却叶片多学科设计优化系统,进行了单孔薄壁冷却叶片的多学科设计优化.提出了单孔薄壁冷却叶片的参数化造型方法,叶片叶型采用5次多项式构造,气动与传热为三维耦合分析;叶片体积平均温度与最高温度为优化目标,强度、振动和寿命等学科相关参数为约束,模拟退火与序列二次规划组合算法进行叶片参数空间寻优,在保持冷却气体流量不变的条件下,优化提高了冷却效果,降低了叶片材料的性能要求.A involves structure multidisciplinary design optimization system for gas turbine blade, which ,aerodynamic,heat transfer,vibration and service life,etc, has been developed,serving the purpose of multidisciplinary design optimization of single-hole thin wall cooling blade. A parametric modeling method was also proposed for single-hole thin wall cooling blade. The blade surface geometry is defined by five-order polynomials, while 3-D coupling analysis was made for aerodynamic and heat transfer. The average temperature and maximum temperature of blade volume were optimized, with aerodynamic, vibration and service life as the constraints. A combined algorithm of annealing simulation and SOP（Sequential Quadratic Programming） was used to optimize the blade parameters. While the flow rate of cooling air was kept ment on the blade m unchanged, the cooling effect was improved and the performance requirement on the blade materials was reduced.

关 键 词：航空、航天推进系统 冷却叶片 多学科设计优化 参数化建模 耦合分析 

分 类 号：V232[航空宇航科学与技术—航空宇航推进理论与工程]