فناوری در مهندسی هوافضا

فناوری در مهندسی هوافضا

بررسی عددی تاثیر اعوجاج دینامیکی فشار کل ورودی بر پایداری و عملکرد فن محوری یک موتور هوایی

نوع مقاله : علمی پژوهشی

نویسندگان
1 دانشیار، مجتمع دانشگاهی هوافضا، دانشگاه صنعتی مالک‌اشتر، تهران، ایران
2 استادیار، مجتمع دانشگاهی هوافضا، دانشگاه صنعتی مالک‌اشتر، تهران، ایران
چکیده
این مطالعه در نظر دارد تا بتواند برای اولین بار تاثیر اعوجاج دینامیکی فشار کل بر مشخصه های فن را به صورت عددی مورد بررسی قرار دهد. این پژوهش، این امکان را ایجاد خواهد نمود تا طراحان درک بهتری از اعوجاج دینامیکی در طراحی کمپرسور داشته باشند. تحلیل پایداری مبتنی بر استال دورانی که در این مطالعه تشریح می شود، نحوه کمی سازی پایداری کمپرسور را تحت شرایط تمیز و دارای اعوجاج نشان می دهد. سرعت سلول های استال در شرایط تمیز و دارای اعوجاج دینامیکی به ترتیب معادل 37 و 35 درصد سرعت روتور محاسبه شده است. نتایج کاهش سرعت سلول های استال را تحت شرایط اعوجاج فشار دینامیکی نشان می دهد. تعداد سلول های استال در شرایط تمیز 1.82 و در شرایط دارای اعوجاج دینامیکی 2.01 می باشد. با اعمال اعوجاج دینامیکی، سایزسلول های استال در کل دامنه جریان روتور رشد می کند. به طور کلی اعوجاج دینامیکی فشار کل موجب کاهش پایداری فن از طریق تشدید پدیده استال دورانی می شود.
کلیدواژه‌ها
موضوعات

عنوان مقاله English

A Numerical Study on the Impact of Dynamic Distortions in Total Inlet Pressure on the Stability and Performance of an Aero-Engine's Axial Fan

نویسندگان English

mostafa mahmoodi 1
mehdi jahromi 2
jamasb pirkandi 1
sajad ghasemloo 1
1 Faculty of Aerospace, Malek Ashtar University of Technology, Tehran, Iran
2 Faculty of Aerospace, Malek Ashtar University of Technology, Tehran, Iran
چکیده English

In preliminary jet engine design, uniform inlet conditions are typically assumed for the compression section, although real-world engines operate under non-uniform inflows that significantly affect the compressor and overall engine performance. For aerodynamic engineers, minimizing performance degradation under such variations is critical. Previous numerical investigations have modeled inlet distortions as temporally invariant. This study presents the first assessment of fan performance under dynamic total pressure distortion. The results enable detailed characterization of unsteady distortion effects and their implications for compressor design. A stability analysis based on the rotational stall mechanism quantifies compressor response under clean and distorted inflow scenarios. The propagation speed of stall cells decreases from 37% of rotor speed in clean conditions to 35% under dynamic distortion. Stall cells increase from 1.82 to 2.01 while their size expands across the entire rotor passage. Overall, dynamic total pressure distortion compromises fan stability by amplifying the severity and onset of rotational stall.

کلیدواژه‌ها English

Inlet distortion
axial fan
turbofan engine
rotating stall
stall cell
dynamic distortion
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  • تاریخ دریافت 10 مرداد 1403
  • تاریخ بازنگری 17 آبان 1403
  • تاریخ پذیرش 19 آبان 1403
  • تاریخ اولین انتشار 26 آبان 1403