摘要
机匣处理能够改善压气机稳定裕度,扩大其稳定工作范围。通过对带周向槽机匣处理的NASA低速离心叶轮(LSCC)进行了时间精确的全三维数值模拟,并对周向槽机匣结构和实壁机匣结构在近失速流量点工况下的计算结果进行了比较分析。分析结果表明,周向槽处理机匣对叶顶间隙泄漏涡的抑制是周向槽机匣处理扩稳的主要原因。
To study the mechanism of stall margin improvement, a time accurate 3-dimentional numerical simulation is performed for a low speed centrifugal compressor with the circumferential grooves casing treatment. The computational results with the mass flow rate of 13 kg/s have been compared between the two different cases with the circumferential grooves and with untreated smooth wall. It is because the development of tip leakage vortex is restrained that the circumferential grooves can extend stall margin.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2007年第4期383-387,共5页
Journal of Propulsion Technology
关键词
压气机
周向槽机匣处理
顶部间隙泄漏涡^+
Compressor
Circumferential grooves casing treatment^＋
Tip leakage vortex
