摘要
选用涡轮静叶栅作为原型叶片,通过对原型叶栅改变轴向掠角和掠高,构造不同掠型的叶片,研究轴向掠对涡轮静叶栅气动性能的影响。改型计算的掠角包括前后掠10°和30°,掠高包括10%和30%叶片高度,用CFD数值仿真软件对轴向掠叶栅的气动性能进行模拟。结果表明;与原型叶片比较,静叶栅轴向前掠增大了低能流体在端壁角区的集聚,增加了端壁横向二次流,引起损失增大,而叶展中部的损失减小;静叶栅轴向后掠减小了低能流体在端壁的堆积,减小了端壁二次流,低能流体被卷入到主流区内,减小了端壁损失,而增大了主流区的损失。
With a turbine stationary cascade serving as a prototype cascade and through a change of axially-swept angles and heights of the prototype to form blades with various swept blade profiles,the influence of axially-swept blades on the aerodynamic performance of the turbine stationary cascade was studied. The remodeled and calculated swept angles include forward-and-back-swept ones of 10 degrees and 30 degrees respectively,while the swept heights,10% and 30% of the blade height respectively. CFD (Computational Fluid Dynamics) numerical simulation software was employed to simulate the aerodynamic performance of the axially-swept cascade. The simulation results show that compared with the prototype blade,the axial forward-swept stationary cascade has intensified the concentration of low-energy fluid at end-wall corners,leading to an increase of transversal secondary flows on the endwalls. This caused a rise of losses,but a decrease of losses in the middle of the blade chord. The axial back-swept stationary cascade has lessened the concentration of low-energy flu-id at end-wall corners,diminishing the secondary flows at the endwalls. As a result,the losses at the endwalls have been reduced due to the low-energy fluid being drawn into a main flow zone,and the losses in the main flow zone,increased.
出处
《热能动力工程》
CAS
CSCD
北大核心
2009年第1期19-23,共5页
Journal of Engineering for Thermal Energy and Power
关键词
涡轮
静叶栅
掠角
掠高
数值计算
turbine,stationary cascade,swept angle,swept height,numerical calculation
