摘要
提出含冲击、孔排及尾缘劈缝气膜、扰流柱复合冷却方式的燃气涡轮导向叶片多学科设计优化的一种方法.介绍了研究对象的结构特点、换热系数计算方法并给出了部分计算公式.建立了一种一类冷却导向叶片的多学科设计优化模型,以某燃气涡轮导向叶片为例,进行了多学科设计优化,获得了较好的效果.
A multidisciplinary design optimization （MDO） procedure for a vane with jet impinging cooling, film cooling of slots and holes, pin fin array cooling was proposed in this paper. The structure of the vane and the prediction method of heat transfer were discussed and some of the formulas are presented. A mathematic model is established formultidisciplinary design optimization of a vane. A vane of a gas turbine is taken as an example to be opti mized by using the procedure presented in this report. The obtained results show that the presented procedure is efficient.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2008年第11期1982-1987,共6页
Journal of Aerospace Power
基金
湖南省自然科学基金(05JJ30002)
航空科学基金(05c52013)
关键词
燃气涡轮
导向叶片
冷却
多学科优化设计
gas turbine
vane
cooling
muhidisciplinary design optimization
