摘要
为深入探索尾迹与附面层的相互作用机理及其对叶型损失的影响,对IET-LPTA后加载超高负荷低压涡轮叶型的定常与非定常气动特性进行了实验研究。实验在低速二维叶栅风洞上进行,该风洞通过上游辐条对尾迹进行模拟,采用热线探针与三孔气动探针作为测试手段。实验发现上游尾迹在低Re状态下对吸力面分离具有较强的抑制作用,可以降低叶型损失。同时研究了不同雷诺数(Re)与来流湍流度(FSTI)对上游尾迹与附面层相互作用机理的影响,发现Re对叶型损失的影响是单向有利的,发现FSTI对叶型损失的影响是双向的。
In order to study the interaction mechanism of the wakes and boundary layer and the influence on profile loss due to the wakes, the effects of unsteady wakes on an ultra-high-lift after loaded low pressure tur- bine blade IET-LPTA have been investigated experimentally. The measurement is performed on a low speed lin- ear cascade wind tunnel. The upstream wakes is simulated by the moving cylindrical bars upstream of the cas- cade. The three holes aerodynamic probe and hotwire probe are used as the measurement instrument. The separa- tion bubble on the suction side is suppressed efficiently and profile loss is decreased by the upstream wakes at low Reynolds number. The effects of Reynolds number and free stream turbulence intensity (FSTI) on the mech- anism of interaction between upstream wakes and boundary layer have also been investigated. The effect of Re is one-way beneficial to the profile loss and FSTI is in both ways.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2016年第4期653-661,共9页
Journal of Propulsion Technology
基金
国家自然科学基金(51206163
51306176)
国家国际科技合作专项对R项目(2013DFR61080)
中国民航大学科研启动资金(2014QD22X
2014QD21X)
中央高校资助项目(3122015C006
ZXH2012H004)
关键词
低压涡轮
尾迹
附面层
分离
转捩
Low pressure turbine
Upstream wakes
Boundary layer
Separation
Transition