The effects of leading edge and downstream film cooling on turbine vane heat transfer
The effects of leading edge and downstream film cooling on turbine vane heat transfer
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发表时间：
1988-11
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通讯作者：
L. D. Hylton;V. Nirmalan;B. Sultanian;R. Kaufman
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作者：
L. D. Hylton;V. Nirmalan;B. Sultanian;R. Kaufman
根据合同NAS 3 -24619，为建立相关数据库，以提高涡轮机叶片外部热传递的预测设计能力，包括采用和不采用前缘喷淋头薄膜冷却的下游薄膜冷却效果，而取得的进展。实验测量是在一个二维叶栅中进行的，该叶栅以前用于获得合同NAS 3 -22761下的非薄膜冷却翼型和合同NAS 3 -23695下的前缘喷头薄膜冷却翼型上的叶片表面传热分布。主要独立参数（马赫数、雷诺数、紊流度、壁面与燃气温度比、冷却剂与燃气温度比和冷却剂与燃气压力比）保持在与实际发动机条件一致的范围内，试验矩阵的结构可提供有关参数（即出口马赫数、出口雷诺数、冷却剂与燃气温度比、和冷却剂与气体的压力比。数据为下游气膜冷却涡轮机叶片提供了数据基础，并扩展了前两项研究中生成的数据基础。获得的叶片外部传热表明，相当大的冷却效益，可以通过利用下游薄膜冷却。所获得和提供的数据说明了变量之间的相互作用，并应向翼型设计者和计算分析人员提供改进薄膜冷却涡轮机翼型传热设计能力所需的信息。
The progress under contract NAS3-24619 toward the goal of establishing a relevant data base for use in improving the predictive design capabilities for external heat transfer to turbine vanes, including the effect of downstream film cooling with and without leading edge showerhead film cooling. Experimental measurements were made in a two-dimensional cascade previously used to obtain vane surface heat transfer distributions on nonfilm cooled airfoils under contract NAS3-22761 and leading edge showerhead film cooled airfoils under contract NAS3-23695. The principal independent parameters (Mach number, Reynolds number, turbulence, wall-to-gas temperature ratio, coolant-to-gas temperature ratio, and coolant-to-gas pressure ratio) were maintained over ranges consistent with actual engine conditions and the test matrix was structured to provide an assessment of the independent influence of parameters of interest, namely, exit Mach number, exit Reynolds number, coolant-to-gas temperature ratio, and coolant-to-gas pressure ratio. Data provide a data base for downstream film cooled turbine vanes and extends the data bases generated in the two previous studies. The vane external heat transfer obtained indicate that considerable cooling benefits can be achieved by utilizing downstream film cooling. The data obtained and presented illustrate the interaction of the variables and should provide the airfoil designer and computational analyst the information required to improve heat transfer design capabilities for film cooled turbine airfoils.