摘要
以NASA Rotor 37为研究对象,采用数值模拟的方法研究了自循环机匣处理的引气位置在不同转速下对转子性能的影响。研究结果表明:自循环机匣处理的引气位置和转子转速对转子性能的影响具有交互性,其本质原因在于转子在不同转速下处于近失速状态时,转子叶顶区域的流动状态不同,从而造成引气位置和叶顶堵塞区域的相对位置会随着转子转速的变化而变化,进而对转子的性能影响呈现出交互性。通过对三种转速下自循环机匣处理的引气位置对转子稳定性的影响分析知,引气位置位于转子叶顶堵塞区尾缘处时对转子叶顶区的流动堵塞抑制能力最强,极大地改善了转子叶顶区域的流通状况,对转子的失速裕度改进量最为有利,在100%、90%和70%设计转速下,失速裕度改进量的最大值分别为7.46%、8.52%、6.14%。此外,通过对转子叶顶的流场细节分析得知,不同转速下自循环机匣处理的引气位置位于转子近失速工况的叶顶堵塞区尾缘处时,在叶顶造成的高比熵区最少,对转子效率的降低幅度最小,于效率最为有利。
Taking NASA Rotor 37 as the research object,the influence of the bleeding position of self-circulating treatment casing(SCT)on the rotor performance at different speeds was studied by numerical simulation.The researches show that the influences of the bleeding positions of the SCT and the rotor speed on the rotor performance are interactive.The essential reason lies in that,when the rotor is in near stall condition at different speeds,the flow condition is different in the rotor tip region,so that the relative position changes between the bleeding positions and the blade tip blockage as the rotor speed changes,resulting in an interactive effect on the rotor performance.Through the analysis of the influence of the bleeding positions of the SCT on the rotor stability at different speeds,it is found that when the bleeding position is at the trailing edge of the blade tip blockage region,there exists the best inhibition of the low-velocity blockage zone,greatly improving the flow ability of the rotor tip region,and contributing most to the stall margin improvement(SMI)of rotor.At100%,90%and 70% design speeds,the maximum value of the SMI is 7.46%,8.52%and6.14%,respectively.In addition,through detailed analysis of the flow field at the rotor tip region,it is found that when the bleeding position of the SCT is located at the trailing edge of the blade tip blockage region of the near-stall operating condition of the rotor at different speeds,the high specific entropy zone caused by the SCT is the least,bringing about minimal reduction in rotor efficiency,and making it most beneficial to the performance.
作者
晏松
楚武利
YAN Song;CHU Wuli(School of Power and Energy,Northwestern Polytechnical University,Xi'an 710072,China;Collaborative Innovation Center for Advanced Aero-Engine,Beijing 100191,China)
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2019年第11期2516-2528,共13页
Journal of Aerospace Power
基金
国家自然科学基金（51576162）
关键词
自循环机匣处理
转子
引气
失速裕度
叶顶堵塞
self-circulating treatment casing
rotor
bleeding
stall margin
blade tip blockage
