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    • Influences of Self-Recirculation Casing Treatment on the Stability Range and Aerodynamic Performance of A Diesel Engine Supercharger Compressor
    DOI：10.13949/j.cnki.nrjgc.2023.06.001
    Key Words:supercharger compressor  self-recirculation casing treatment  full-channel numerical simulation  stable operating range  aerodynamic performance
    Author NameAffiliationE-mail
    TIAN Jinjin* School of Mechanical Engineering， Tianjin University of Commerce， Tianjin 300134， China tianjj@tjcu.edu.cn 
    WU Caixia School of Mechanical Engineering， Tianjin University of Commerce， Tianjin 300134， China 15978198492@163.com 
    LI Xiaojian School of Mechanical Engineering， Tianjin University， Tianjin 300350， China lixiaojian@tju.edu.cn 
    ZHANG Zhe School of Mechanical Engineering， Tianjin University of Commerce， Tianjin 300134， China zhangzhe@tjcu.edu.cn 
    ZHAO Yijia* School of Mechanical Engineering， Tianjin University of Commerce， Tianjin 300134， China zhaoyijia@tjcu.edu.cn 
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    Abstract:For a certain type of diesel engine supercharger compressor， based on the full-channel， whole stage numerical simulation method and orthogonal experiment， the potential of self-recirculation casing treatment （SRCT） for the enhancement of stability and efficiency of high subsonic compressor stage was studied. The results show that the SRCT can delay the instability without reducing the aerodynamic performance of the design point， at the expense of reducing the choke flow rate. The stall and choke flow rates of the compressor are related to the degree of blockage in the blade leading edge and the vaned diffuser， respectively. In the small flow region， the SRCT relieves blockage and delays instability by sucking the low-momentum flow near the shroud. However， in the large flow region， the injection of SRCT increases the incidence angle of diffuser inlet， aggravates the flow separation of the diffuser vanes， and reduces the choke flow rate. Both suction and injection depend on the position and width of the bleeding slot， and the stability and chock flow rate of compressor are negatively correlated to them. The influences of SRCT on aerodynamic performance include two aspects. Upstream the bleeding slot， the mixing of the fluid flowing through the reinjecting slot with the main stream and the resulting inlet distortion will bring additional efficiency and pressure ratio loss， and the loss can be reduced by appropriately reducing the reinjecting slot angle. Downstream the bleeding slot， thanks to the improvement of the flow state near the shroud， the high entropy zone near the bleeding slot and downstream of the compressor is reduced， the blade work capacity is improved， and the aerodynamic loss is greatly reduced. With the above two effects combined， the aerodynamic performance of the compressor at design point can be improved.
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