摘要
以一单级轴流压气机实验台为研究对象,对其内部流动进行了全工况的数值模拟。数值计算结果与实验测量结果对比分析表明程序很好地预测出了单级压气机的总性能和基元性能。数值分析峰值效率和失速边界工况下动叶和静叶间隙区域流动结构的变化表明:随着压气机的运行工况由峰值效率点向失速边界点移动,动、静叶间隙泄漏涡向下游发展过程中产生的阻塞效应明显增强,该阻塞效应是导致压气机失速的主要原因。
This paper aims at the numerical analysis of the three-dimensional flow fields in a onestage axial flow compressor. The numerical results are firstly compared with the available experimental data to demonstrate the validity of the computations. Then, the numerically obtained flow fields are analyzed to identify the role of the detailed flow structures near the tip region of the rotor and stator on the compressor aerodynamics. It is found that the propagation of tip leakage vortex produces a large blockage effects at near stall condition, which is the main factor leading to the compressor stall.
出处
《工程热物理学报》
EI
CAS
CSCD
北大核心
2006年第6期950-952,共3页
Journal of Engineering Thermophysics
基金
国家自然科学基金项目(No.50506026)
中国博士后科学基金项目(No.2005037790)
航空基金项目(No.05C53016)
西北工业大学青年科技创新基金(No.M010622)资助
关键词
轴流压气机
数值模拟
泄漏涡
axial compressor
numerical simulation
leakage vortex
