摘要
变循环发动机可调涡轮导向叶片面临着恶劣的热负荷环境,而导向叶片自身开度的变化会影响叶片表面的压力分布规律和气膜冷却特性。针对导向叶片叶型,开展了不同开度下叶片表面压力系数分布变化和气膜冷却特性的研究。结果表明,随着开度角增大,流动阻力减小,流速增加,压力面压力系数降低,吸力面压力系数在较大开度角时呈现先急剧降低后缓慢升高的趋势。随着开度角减小,前缘和吸力面气膜孔的压差系数逐步增大,气膜孔出流效果改善;压力面气膜孔压差系数在靠前位置逐渐减小,靠后位置逐渐增大。在小开度角工况,压力面前部区域的气膜出流效果明显恶化。与开大工况(开度角为8°)相比,关小工况(开度角为-12.5°)的前缘气膜冷却效率降低了13.2%,压力面气膜冷却效率降低了63.3%,吸力面气膜冷却效率增加了50.1%;全表面的气膜冷却效率随开度角减小而单调递减,最大降幅为19.1%。
Variable cycle engines adjustable guide vanes are subject to harsh thermal load conditions,and the changes in the opening angle of attack also affect the pressure distribution on the vane surface and the characteristics of film cooling.Therefore,the variation in the surface pressure coefficient distribution and the film cooling characteristics was investigated based on different vane angles for a particular guide vane profile.The results show that as the opening angle increases,flow resistance decreases,flow velocity increases,and the pressure coefficient on the pressure side decreases.At larger angles,the pressure coefficient on the suction side exhibits a trend of initially decreasing sharply and then slowly increasing.As the opening angle decreases,the pressure differential coefficient at the leading edge and suction side film holes increases,improving the film hole outflow performance;the pressure differential coefficient at the pressure side film holes decreases in the forward region and increases in the rear region.Under small angle conditions,the film cooling effectiveness at the front of the pressure side deteriorates significantly.Compared to the wide-open condition(angle of attack θ=8°),the front-edge film cooling effectiveness in the closed condition(θ=-12.5°)decreases by 13.2%,the pressure side film cooling effectiveness decreases by 63.3%,and the suction side film cooling effectiveness increases by 50.1%.The overall surface film cooling effectiveness decreases monotonically as the opening angle decreases,with a maximum reduction of 19.1%.
作者
靳合龙
辛秋睿
杜英杰
李鹏刚
张振华
白晓辉
刘存良
JIN Helong;XIN Qiurui;DU Yingjie;LI Penggang;ZHANG Zhenhua;BAI Xiaohui;LIU Cunliang(School of Power and Energy,Northwestern Polytechnical University,Xi’an 710129,China;AECC Sichuan Gas Turbine Establishment,Chengdu 610500,China)
出处
《燃气涡轮试验与研究》
2025年第6期64-74,共11页
Gas Turbine Experiment and Research
基金
航空发动机及燃气轮机基础科学中心项目(P2022-B-II-026-001)。
关键词
航空发动机
变循环
可调导向叶片
压力系数
气膜孔出流特性
气膜冷却效率
aero-engine
variable cycle
adjustable guide vane
pressure coefficient
film hole outflow characteristics
film cooling effectiveness
