计算涡轮叶片尾缘对开缝喷气的数值方法

推进技术 ›› 2002, Vol. 23 ›› Issue (4): 315-317.

计算涡轮叶片尾缘对开缝喷气的数值方法

王掩刚,梅运焕,刘波,曹志鹏

西北工业大学航空动力与热力工程系陕西西安710072;西北工业大学航空动力与热力工程系陕西西安710072;西北工业大学航空动力与热力工程系陕西西安710072;西北工业大学航空动力与热力工程系陕西西安710072

发布日期:2021-08-15
基金资助:
国家自然科学基金资助项目 (5 9976 0 32 )

Numerical approach for turbine blade with trailing edge ejection

Dept of Aeroengine Engineering, Northwestern Polytechnical Univ , Xi’an710072,China;Dept of Aeroengine Engineering, Northwestern Polytechnical Univ , Xi’an710072,China;Dept of Aeroengine Engineering, Northwestern Polytechnical Univ , Xi’an710072,China;Dept of Aeroengine Engineering, Northwestern Polytechnical Univ , Xi’an710072,China

Published:2021-08-15

摘要/Abstract

摘要： 为探讨涡轮叶片尾缘对开缝喷气对叶栅性能的影响 ,发展了可与主流场求解有机耦合 ,且能准确反应射流与主流相互干扰过程的喷气模型 ,结合涡轮叶片流场数值模拟 ,得到了不同喷气量下涡轮叶栅性能参数。计算与实验结果有较好的一致性 ,表明所采用的喷气模型能够较准确地模拟射流与主流的掺混过程 ,预测掺混效应

关键词: 涡轮叶片;涡轮叶栅;喷流干扰;气动模型;耦合

Abstract: An ejection model was developed to investigate the effects of ejection from the symmetry slot of trailing edge for a turbine cascade This model can be coupled with the calculation of main flow field easily and correctly simulate the process of mixing between the ejection and the main flow The performance parameters were obtained by this method The consistence of the results between calculation and test shows that this method is effective

Key words: Turbine blade;Turbine cascade;Jet interference;Aerodynamic model;Coupling

王掩刚,梅运焕,刘波,曹志鹏. 计算涡轮叶片尾缘对开缝喷气的数值方法[J]. 推进技术, 2002, 23(4): 315-317.