A New Approach to Suppress Tip Leakage Flow Utilizing Induced Shock Wave in Tip Region of a TransonicCompressor Rotor  

作　　者：CUI Weiwei YAO Fei LI Zongming WANG Xiaonan CHANG Guozhang WANG Cuiping 

机构地区：[1]College of Energy Storage Technology,Shandong University of Science and Technology,Qingdao 266590,China [2]College of Civil Engineering and Architecture,Shandong University of Science and Technology,Qingdao 266590,China [3]Clean energy laboratory,Shandong University of Science and Technology,Qingdao 266590,China

出　　处：《Journal of Thermal Science》2024年第6期2059-2074,共16页热科学学报（英文版）

基　　金：sponsored by the General Program of National Natural Science Foundation of China (Grant No.52076124);the National Science and Technology Major Project (Grant No.J2019-Ⅱ-0014-0035)

摘　　要：Tip leakage flow affects the flow stability of high-loading compressors significantly.Therefore,a novel approach via induced shock wave near suction-side edge of blade tip was proposed to suppress the strength and influence range of leakage flow in a transonic rotor.Three new schemes with different circumferentially diverging degrees of clearance were designed to reveal the mechanism of the new approach.Through the action of the circumferentially diverging clearance(from the pressure side to the suction side over blade tip),a much more dramatic acceleration of the supersonic leakage jet flow appeared over blade tip of the new schemes.An induced shock wave was produced near the suction side edge of blade tip due to the pressure difference between the discharging leakage flow and the surrounding high-pressure mainflow in tip channel.As a result,both the mass flow rate and the outlet velocity of leakage flow were reduced significantly via the induced shock wave.Meanwhile,the suppressing effect of the new approach on the tip leakage jet flow was closely related to the strength and circumferential location of the induced shock wave.With the aids of the induced shock wave,the largest improvement of tip flow characteristics with an over 5%increase in stall margin was realized in new transonic rotor when the circumferential divergence angle equals 8°,accompanied with no more than a 0.4%decrease in isentropic efficiency.

关 键 词：circumferentially diverging clearance induced shock wave leakage flow low-velocity region st marginenhancement 

分 类 号：V233[航空宇航科学与技术—航空宇航推进理论与工程]