Analytical and Experimental Evaluation of the Heat Transfer Distribution over the Surfaces of Turbine Vanes
Analytical and Experimental Evaluation of the Heat Transfer Distribution over the Surfaces of Turbine Vanes
复制标题
DOI：
--
复制
发表时间：
1983-05
期刊：
影响因子：
--
通讯作者：
L. D. Hylton;M. S. Mihelc;E. Turner;D. Nealy;R. York
中科院分区：
文献类型：
--
作者：
L. D. Hylton;M. S. Mihelc;E. Turner;D. Nealy;R. York
三个翼型数据集被选择用于评估目前可用的分析模型，预测翼型表面传热分布在二维流场。另外两种翼型是目前正在设计的高载荷、低实度翼型的代表，被选作模拟发动机条件下的叶栅试验。一些2-D的分析方法进行了检查和版本的STAN 5边界层代码被选择修改。该方法的最终形式采用了与时间相关的跨音速无粘叶栅代码，该代码与具有零阶湍流模型的STAN 5边界层代码的修改版本相耦合。边界层代码的结构，以适应全谱的经验相关解决翼型表面传热分布和边界层过渡行为的压力梯度，翼型曲率和自由流湍流的耦合影响。与该模型的数据库的pedections的比较表明预测能力的显着改善。
Three airfoil data sets were selected for use in evaluating currently available analytical models for predicting airfoil surface heat transfer distributions in a 2-D flow field. Two additional airfoils, representative of highly loaded, low solidity airfoils currently being designed, were selected for cascade testing at simulated engine conditions. Some 2-D analytical methods were examined and a version of the STAN5 boundary layer code was chosen for modification. The final form of the method utilized a time dependent, transonic inviscid cascade code coupled to a modified version of the STAN5 boundary layer code featuring zero order turbulence modeling. The boundary layer code is structured to accommodate a full spectrum of empirical correlations addressing the coupled influences of pressure gradient, airfoil curvature, and free-stream turbulence on airfoil surface heat transfer distribution and boundary layer transitional behavior. Comparison of pedictions made with the model to the data base indicates a significant improvement in predictive capability.