The internal flow stability of the compressor in the aeroengine has always been the top priority for the development of the aviation industry. Rotating stall is one of the most common instability problems in compressors, and stall margin is also an important parameter to measure the aerodynamic performance of compressors. In an actual compressor, it is difficult to achieve an ideal uniform inlet air condition, and inlet distortion will affect the operating conditions of the compressor. In this paper, a three-dimensional simulation of rotor 37 is conducted to study the development process of circumferential distortion and the aerodynamic performance of the compressor. The research results show that as the backpressure increases in the channel corresponding to the circumferentially distorted area, the blockage will occur first, and it will develop in the whole channel, leading to a complete stall. From the perspective of aerodynamic performance, circumferential distortion has an impact on stall margin and adiabatic efficiency, and different types of circumferential distortion have different effects on aerodynamic performance.


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    Titel :

    An Investigation on Rotating Stall in an Aeroengine Transonic Compressor with Inlet Distortion


    Weitere Titelangaben:

    Lect. Notes Electrical Eng.


    Beteiligte:
    Jing, Zhongliang (Herausgeber:in) / Strelets, Dmitry (Herausgeber:in) / Zhu, Zhongyu (Autor:in) / Liu, Xiaohua (Autor:in)

    Kongress:

    International Conference on Aerospace System Science and Engineering ; 2021 July 14, 2021 - July 16, 2021



    Erscheinungsdatum :

    09.07.2022


    Format / Umfang :

    15 pages





    Medientyp :

    Aufsatz/Kapitel (Buch)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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