تحلیل عددی تأثیر تزریق سوخت بر بردار نیروی پیش‌ران موتور جت با نازل دارای دو گلوگاه

نوع مقاله : مقاله پژوهشی

نویسندگان

1 استادیار، پژوهشگاه هوافضا، تهران، ایران

2 دکتری هوافضا، دانشگاه صنعتی شریف، تهران، ایران

3 دانشگاه هوایی شهید ستاری، تهران، ایران

چکیده

یکی از مؤثرترین روش‌های تغییر بردار پیش‌رانش موتورهای جت، استفاده از نازل دارای دو گلوگاه و تزریق سوخت در گلوگاه بالادستی می­باشد. پژوهش حاضر به بررسی عملکرد یک سیستم کنترل بردار تراست با هندسۀ نازل دارای دو گلوگاه می‌پردازد. تأثیر تزریق جانبی سوخت بر پارامترهای عملکردی نازل شامل ضریب تخلیه، ضریب تراست، زاویۀ برداردهی، بازدهی برداردهی، نسبت تراست به دبی جرمی و درصد افت تراست مورد مطالعه قرار گرفته‌است. در این پژوهش تزریق هفت سوخت مختلف شامل متان، اتان، پروپان، اکتان، سوخت دیزل، کروسین و نفت‌گاز به‌صورت عددی مورد مطالعه قرار گرفته‌است. نتایج نشان می‌دهند که تزریق سوخت‌های سنگین‌تر موجب ایجاد ضریب تخلیۀ بالاتری می‌گردد؛ اما بیشترین زاویۀ برداردهی در جریان غیراحتراقی توسط سوخت دیزل و اکتان ایجاد می‌شود. به‌طور کلی می‌توان گفت که تزریق سوخت‌های سبک از نظر ضریب تراست، بازدهی برداردهی و نسبت تراست به دبی جرمی عملکرد بهتری دارند، ولی سوخت‌های سنگین از نظر ضریب تخلیه، زاویۀ برداردهی و درصد افت تراست بهتر می­باشند.

کلیدواژه‌ها

موضوعات


عنوان مقاله [English]

Numerical Analysis of Fuel Injection Impacts on Thrust-Vectoring in a Dual Throat Nozzle

نویسندگان [English]

  • Mohammad Reza Salimi 1
  • Rasoul Askari 2
  • Majid Hasani 3
1 Assistant professor, Aerospace Research Institute, Tehran, Iran
2 PhD of Aerospace Engineering, Sharif University of Technology, Tehran, Iran
3 University of Shahid Satari, Tehran, Iran.
چکیده [English]

Today, the Dual-throat Nozzles are known as one of the most effective approaches for fluidic thrust vectoring. The present study investigates the performance of a dual throat fluidic thrust-vectoring nozzle. The impacts of fuel secondary injection on performance parameters including discharge coefficient, system thrust ratio, pitch thrust-vector angle, pitch thrust-vectoring efficiency, thrust-to-mass-flow ratio and thrust-loss percentage are presented. Injection of seven different fuels including methane, ethane, propane, octane, diesel fuel, kerosene and gasoil have been investigated. Both reacting and non-reaction conditions have been studied. The results show that heavier fuels provide higher discharge coefficients. On the other hand, light fuels have higher thrust ratios. In the non-reacting conditions, diesel fuel and octane have the largest thrust-vector angle,. In general, light fuels offer a better performance in terms of thrust ratio, thrust-vectoring efficiency and thrust-to-mass-flow ratio, whereas heavy fuels have a better performance in terms of discharge coefficient, thrust-vector angle and thrust-loss percentage.

کلیدواژه‌ها [English]

  • Thrust-vectoring
  • Dual throat nozzle
  • Discharge coefficient
  • Thrust-vector angle
  • Thrust-vectoring efficiency
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