این سایت در حال حاضر پشتیبانی نمی شود و امکان دارد داده های نشریات بروز نباشند
Journal of Aerospace Science and Technology، جلد ۱۵، شماره ۱، صفحات ۱۱۶-۱۲۸
عنوان فارسی Numerical study on enhancement of low speed axial compressor rotor performance under radial inlet distortion via DBD plasma actuators
چکیده فارسی مقاله Aero-engine entrance conditions are not always ideal and, for various reasons, inlet distortion may occur and cause inlet blockage and reduction of compressor performance. The aim of this study was to numerically simulate the effects of plasma actuators on the enhancement of low-speed axial compressor rotor performance under radial inlet distortion. First, compressor performance under radial inlet distortion with 15% and 20% blockage and theirs destructive effects on stall margin was investigated. Then, the effect of plasma actuators on rotor loss subjected to inlet distortion was investigated, using an algebraic model based on the plasma actuators physics in form of body force distribution in Naiver-Stokes equations. The results show that radial inlet distortion causes decreasing stall margin of the compressor. In addition, according to the findings, applying plasma actuators boosts the flow momentum behind the distortion screen and reduces the blockage of the rotor tip region, leading to decreasing losses. Furthermore, at 15% blockage, the plasma actuators caused to increase the stall margin from -11% to -5% versus the rotor in clean condition.
کلیدواژه‌های فارسی مقاله
عنوان انگلیسی Numerical study on enhancement of low speed axial compressor rotor performance under radial inlet distortion via DBD plasma actuators
چکیده انگلیسی مقاله Aero-engine entrance conditions are not always ideal and, for various reasons, inlet distortion may occur and cause inlet blockage and reduction of compressor performance. The aim of this study was to numerically simulate the effects of plasma actuators on the enhancement of low-speed axial compressor rotor performance under radial inlet distortion. First, compressor performance under radial inlet distortion with 15% and 20% blockage and theirs destructive effects on stall margin was investigated. Then, the effect of plasma actuators on rotor loss subjected to inlet distortion was investigated, using an algebraic model based on the plasma actuators physics in form of body force distribution in Naiver-Stokes equations. The results show that radial inlet distortion causes decreasing stall margin of the compressor. In addition, according to the findings, applying plasma actuators boosts the flow momentum behind the distortion screen and reduces the blockage of the rotor tip region, leading to decreasing losses. Furthermore, at 15% blockage, the plasma actuators caused to increase the stall margin from -11% to -5% versus the rotor in clean condition.
کلیدواژه‌های انگلیسی مقاله Axial Compressor,Inlet distortion,plasma actuator,Active flow control,Stall Margin
نویسندگان مقاله Ali Khoshnejad |
ّFaculty of Aerospace Engineering K.N.Toosi University of Technology

Reza Ebrahimi |
Faculty of Aerospace Engineering K.N.Toosi University of Technology

Golamhosein Pouryossefi |
Faculty of Aerospace Engineering K.N.Toosi University of Technology

نشانی اینترنتی https://jast.ias.ir/article_139913_228860ec78be584e280c90d9c8aeb12d.pdf
فایل مقاله فایلی برای مقاله ذخیره نشده است
کد مقاله (doi)
زبان مقاله منتشر شده en
موضوعات مقاله منتشر شده
نوع مقاله منتشر شده
برگشت به: صفحه اول پایگاه   |   نسخه مرتبط   |   نشریه مرتبط   |   فهرست نشریات