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Numerical Investigation on the Dual Effect of Upstream Steps and Transverse Trenches on Film Cooling Performance

机译:上游步骤与横沟对膜冷却性能的数值研究

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摘要

This paper presents a numerical investigation of a concept for improving film cooling performance by setting a step upstream the transverse trench. The step, which is placed upstream the transverse trench, is used to modify the approaching boundary-layer flow and its interaction with coolant to improve the lateral spreading of coolant. Five different relative distances between the steps and transverse trenches (upstream distances) are investigated, including -20, 0, 5, 10, and 15 mm. The film cooling performance is evaluated at a density ratio of 0.97, with the blowing ratios ranging from 0.5 to 2.0. The numerical results of film cooling with an upstream step and the numerical results of film cooling with holes embedded in transverse trenches show an agreement with the experimental data when three-dimensional average Navier-Stokes equations are solved with the standard k-epsilon model. Detailed adiabatic cooling effectiveness and total pressure loss coefficients are simulated. Results obtained indicate that film cooling performance in the region downstream from the film hole is sensitive to upstream distances. In the case with an upstream distance of 0 mm, the lateral spreading of coolant is superior to that in other cases, which leads to a higher lateral adiabatic cooling effectiveness. The case with an upstream distance of 0 mm is a better choice when the improved lateral adiabatic cooling effectiveness and the reduced total pressure loss penalty are taken into account. (c) 2019 American Society of Civil Engineers.
机译:本文通过在横沟上游设置步骤,提出了一种用于改善膜冷却性能的概念的数值研究。放置在横沟上游的步骤,用于改变接近的边界层流动及其与冷却剂的相互作用,以改善冷却剂的横向扩展。研究了步骤和横沟之间的五个不同的相对距离(上游距离),包括-20,0,5,10和15mm。薄膜冷却性能以0.97的密度比评价,吹出比率为0.5至2.0。用上游步骤的薄膜冷却的数值结果和嵌入横向沟槽的孔的薄膜冷却的数值结果显示了与标准K-EPSILON模型一起解决三维平均Navier-Stokes方程时的实验数据的协议。模拟详细的绝热冷却效果和总压力损失系数。得到的结果表明,薄膜孔下游的区域中的膜冷却性能对上游距离敏感。在0mm上游距离的情况下,冷却剂的横向扩散优于其他情况,这导致较高的横向绝热冷却效果。上游距离0 mm的情况是当考虑改善的横向绝热冷却效果和减少的总压力损失罚分时是更好的选择。 (c)2019年美国土木工程学会。

著录项

  • 来源
    《Journal of aerospace engineering》 |2019年第4期|04019028.1-04019028.10|共10页
  • 作者单位

    Xi An Jiao Tong Univ Inst Turbomachinery Shaanxi Engn Lab Turbomachinery & Power Equipment 28 Xianning West Rd Xian 710049 Shaanxi Peoples R China;

    Xi An Jiao Tong Univ Inst Turbomachinery Shaanxi Engn Lab Turbomachinery & Power Equipment 28 Xianning West Rd Xian 710049 Shaanxi Peoples R China;

    Xi An Jiao Tong Univ Inst Turbomachinery Shaanxi Engn Lab Turbomachinery & Power Equipment 28 Xianning West Rd Xian 710049 Shaanxi Peoples R China|Hunan Univ Coll Mech & Vehicle Engn Changsha 410082 Hunan Peoples R China;

    Xi An Jiao Tong Univ Inst Turbomachinery Shaanxi Engn Lab Turbomachinery & Power Equipment 28 Xianning West Rd Xian 710049 Shaanxi Peoples R China;

  • 收录信息
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

    Numerical simulation; Film cooling performance; Step location; Adiabatic cooling effectiveness;

    机译:数值模拟;薄膜冷却性能;步进位置;绝热冷却效果;

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