Blade Lean and Tip Leakage Flows in Highly Loaded Compressor Cascades  

作　　者：CAO Zhiyuan SONG Cheng ZHANG Xiang GAO Xi LIU Bo 

机构地区：[1]School of Power and Energy,Northwestern Polytechnical University,Xi’an 710072,China

出　　处：《Journal of Thermal Science》2021年第4期1388-1405,共18页热科学学报（英文版）

基　　金：supported by National Natural Science Foundation of China(No.51806174);the Natural Science Foundation of Shaanxi Province(No.2019-JQ137);the Fundamental Research Funds for the Central Universities(No.G2018KY0303);National Natural Science Foundation of China(No.51790512)。

摘　　要：Blade lean has been intensively utilized in axial compressors.In this study,three families of highly loaded compressor cascades featuring different aspect ratios(AR)with different levels of blade lean were designed and simulated with and without tip clearance.The influences of blade lean on corner separation and tip leakage flow(TLF)were investigated.Results show that blade lean can exert spanwise pressure gradient confined to the fore part,spanwise mass flow rate re-distribution exhibiting differently at fore and rear part of blade,and stage reaction variations.AR has a significant influence on blade lean.With the increase of AR,corner separation grows significantly and requires a higher lean level to be controlled.TLF eliminates corner separation of linear cascades but also increases the loss of leaned cascades;blade lean introduces 22%higher tip leakage mass flow,but exhibits 43%(blade M)and 38%(blade E)lower tip leakage loss.The flow mechanism can be mainly accounted by the reduction of bulk flow velocity,tip leakage velocity and the velocity difference near leading edge(LE).High AR cascade induces re-distribution of TLF along blade chord and reduces leakage loss compared with low AR counterpart.

关 键 词：axial compressor leaned blade tip leakage flow aspect ratio corner separation 

分 类 号：V263.6[航空宇航科学与技术—航空宇航制造工程]