摘要
在低速大尺寸单级压气机实验台上,利用SPIV技术测量了设计状态下压气机转子尖区多个截面的三维瞬态速度场。基于瞬态场测量结果,详细阐述了设计状态下压气机转子叶尖泄漏涡产生、发展、失稳、破碎的演化过程,导致叶尖泄漏涡失稳的4种主要因素:主流的逆压梯度、哥氏力、端壁的剪切流动和来流湍流度的影响,分析了压气机内泄漏涡的失稳破碎机制,以及泄漏涡与主流的相互作用等。
SPIV is applied to a large-scale low-speed compressor facility. The instantaneous velocity and vorticity distributions in several cross sections are successfully measured in the tip region of the compressor rotor at design condition. Based on the measurement results, the generation, evolution, unsteadiness and breakdown of the tip leakage vortex are analyzed in detail, and four main factors on the instability of the tip leakage vortex (adverse pressure gradient, Coriolis force, casing shear flow and turbulence intensity) are also discussed.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2004年第1期1-8,共8页
Acta Aeronautica et Astronautica Sinica
基金
国家自然科学基金(50006001)
国家重点基础研究发展规划项目(G1999022305)资助项目
