景雪娇,曹杰,查浩,等.异型孔的气膜冷却数值模拟[J].内燃机工程,2025,46(3):107-116.
异型孔的气膜冷却数值模拟
Numerical Simulation of Film Cooling of Shaped Holes
DOI：10.13949/j.cnki.nrjgc.2025.03.012
关键词:气膜冷却  数值模拟  网格  异型孔  吹风比
Key Words:film cooling  numerical simulation  grid  shaped hole  blowing ratio
基金项目:无
作者单位E-mail
景雪娇* 中国空气动力研究与发展中心 计算空气动力研究所，绵阳 621000 15222875309@163.com 
曹杰 中国空气动力研究与发展中心 计算空气动力研究所，绵阳 621000 caojie_971@163.com 
查浩 中国空气动力研究与发展中心 计算空气动力研究所，绵阳 621000 270486729@qq.com 
李白羽 中国空气动力研究与发展中心 计算空气动力研究所，绵阳 621000 2392295678@qq.com 
韩熙 中国空气动力研究与发展中心 计算空气动力研究所，绵阳 621000 18628378038@163.com 
张威龙* 中国空气动力研究与发展中心 计算空气动力研究所，绵阳 621000 zhangweilong2022@163.com 
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摘要:使用自研节点型非结构计算流体力学软件AENS对气膜冷却进行数值模拟研究。针对边界层网格、近孔区网格对气膜冷却仿真的精度影响及不同吹风比下异型孔气膜的冷却效率差异，选用标准单孔气膜冷却模型，在不同吹风比下对不同边界层网格、近孔区网格及圆柱孔、扇形孔和簸箕孔3种孔型的气膜冷却效率进行对比研究。研究结果表明：第一层网格高度对计算结果的影响不显著；近孔区网格在吹风比较低的工况下对计算结果影响较大，近孔区使用O型网格块嵌套O型网格块的方法生成的网格计算效果更好；吹风比较大的工况下，扇形孔和簸箕孔与圆柱孔相比对近孔区的气膜冷却性能提升更为显著。对GE-E3高压涡轮带气膜导叶模型展开计算，证明自研软件具备计算带复杂冷却结构的工程算例的能力，验证了自研软件的实用性和准确性。
Abstract:The self-developed cell-vertex unstructured computational fluid dynamics software AENS was used for the numerical simulation of film cooling. With regard to the influence of boundary layer grid and near-hole zone grid on the accuracy of film cooling simulation and the difference in cooling efficiency of films with shaped holes under different blowing ratios， a standard single-hole film cooling model was adopted， and a comparative study was carried out to investigate the difference in cooling efficiencies of different boundary layer grids， different near-hole zone grids， and three types of holes， namely， cylindrical holes， fan-shoped holes and dustpan holes under different blowing ratios. The results show that the height of the first layer of the grid does not have a great influence on the simulation results. The grid of the near-hole area has a greater influence on the simulation results under lower blowing ratios， and the mesh generated by nesting two O-type blocks in the near-hole area has a better simulation result. Under higher blowing ratios， the fan-shaped holes and laid-back fan-shaped holes have a more obvious increase in the film cooling efficiencies of the near-hole area， compared with the cylindrical holes. The GE-E3 high-pressure turbine with film guide vane model was simulated， which proved that the self-developed software has the ability to calculate engineering examples with complex film-cooling structures. The practicality and accuracy of the self-developed software was verified.
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