Boundary Layer Development on Turbine Airfoil Suction Surfaces
Boundary Layer Development on Turbine Airfoil Suction Surfaces
复制标题
涡轮机翼型吸力表面的边界层发展
DOI：
10.1115/1.3227334
复制
发表时间：
1981
期刊：
影响因子：
--
通讯作者：
D. Bailey
中科院分区：
文献类型：
--
作者：
O. Sharma;R. A. Wells;R. Schlinker;D. Bailey
本文介绍了由NASA在节能发动机计划下资助的一项研究的结果，该研究旨在研究模拟两种最先进涡轮机翼型吸力面的速度分布影响下的附面层发展。一种速度分布代表前加载翼型（“方形"设计），而另一种代表后加载翼型（”后加载“设计）。这些速度分布是在专门为边界层研究设计的低速、大展弦比风洞中模拟的。本文提供的详细数据可用于开发适用于涡轮机翼型设计的改进湍流模型。
The results of a study supported by NASA under the Energy Efficient Engine Program, conducted to investigate the development of boundary layers under the influence of velocity distributions that simulate the suction sides of two state-of-the-art turbine airfoils, are presented. One velocity distribution represented a forward loaded airfoil ('squared-off' design), while the other represented an aft loaded airfoil ('aft loaded' design). These velocity distributions were simulated in a low-speed, high-aspect-ratio wind tunnel specifically designed for boundary layer investigations. It is intended that the detailed data presented in this paper be used to develop improved turbulence model suitable for application to turbine airfoil design.