A review and analysis of boundary layer transition data for turbine application
A review and analysis of boundary layer transition data for turbine application
复制标题
涡轮机应用边界层转变数据的回顾和分析
DOI：
10.1115/85-gt-83
复制
发表时间：
1985
期刊：
影响因子：
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通讯作者：
R. Gaugler
中科院分区：
文献类型：
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作者：
R. Gaugler
在美国宇航局刘易斯研究中心举行了一次关于涡轮机过渡的研讨会。工作组的一项建议是收集现有的过渡数据，以提供可用来测试模型的标准案例。回顾和分析了一些公开文献中的数据集，这些数据集包括明显过渡边界层中的传热数据，特别适用于涡轮环境，以从传热数据中提取过渡信息。审查的数据集涵盖了广泛的流动条件，从低速平板测试到在模拟涡轮发动机条件下运行的全尺寸涡轮翼型。结果表明，自由流湍流和压力梯度对过渡区的起始点位置和过渡区长度有很强的反作用。
A symposium on transition in turbines was held at the NASA Lewis Research Center. One recommendation of the working groups was the collection of existing transition data to provide standard cases against which models could be tested. A number of data sets from the open literature that include heat transfer data in apparently transitional boundary layers, with particular application to the turbine environment, were reviewed and analyzed to extract transition information from the heat transfer data. The data sets reviewed cover a wide range of flow conditions, from low speed, flat plate tests to full scale turbine airfoils operating at simulated turbine engine conditions. The results indicate that free stream turbulence and pressure gradient have strong, and opposite, effects on the location of the start of transition and on the length of the transition zone.