نوع مقاله : یادداشت تحقیقاتی

نویسندگان

1 دانشجوی کارشناسی ارشد، دانشکده مهندسی هوافضا، دانشگاه صنعتی خواجه نصیرالدین طوسی، تهران، ایران

2 استادیار، دانشکده مهندسی هوافضا، دانشگاه خواجه نصیرالدین طوسی ، تهران، ایران

چکیده

هدف از انجام این تحقیق، بررسی اثر سه پارامتر زاویه تزریق جریان ثانویه، مکان تزریق جریان ثانویه و شکل هندسی مقطع کانال کنارگذر بر روی انحراف زاویه بردار تراست می‌باشد. این بررسی به صورت دو بعدی و سه بعدی برای یک نازل دو گلوگاهه مورد شبیه-سازی واقع شده است. نتایج شبیه‌سازی دوبعدی حاکی از آن است که با افزایش زاویه تزریق جریان ثانویه نسبت به افق، میزان انحراف زاویه بردار تراست، حداکثر حدود 27 درصد نسبت به بیشترین مقدار آن کاهش می‌یابد. همچنین، با قرارگیری محل تزریق جریان ثانویه در بعد از گلوگاه، میزان انحراف زاویه بردار تراست نسبت به حالت قبل از گلوگاه افزایش می‌یابد. بیشترین اختلاف بین حالت تزریق در گلوگاه و تزریق بعد از گلوگاه حدود 25 درصد و بیشترین انحراف زاویه بردار تراست، در زاویه 45 درجه و در محل تزریق در گلوگاه اتفاق افتاده است.

کلیدواژه‌ها

موضوعات

عنوان مقاله [English]

Simulation of the Bypass Dual Throat Nozzle and investigation of parameters affecting the change of thrust vector angle

نویسندگان [English]

  • Amir Mohammad Neyzan Hosseini 1
  • Hossein Mahdavy-Moghaddam 2

1 M. Sc. Student, Faculty of Aerospace Engineering, Khwaja Nasiruddin Toosi University of Technology, Tehran, Iran

2 Assistant Professor, Faculty of Aerospace Engineering, Khwaja Nasiruddin Toosi University of Technology, Tehran, Iran

چکیده [English]

The aim of this study was to investigate the effects of three parameters including secondary flow injection angle, secondary flow injection location and bypass section geometry on the deflection angle of the thrust vector. The model is simulated in both two and three dimensional for a Dual Throat Nozzle. The results show that by increasing injection angle of the secondary flow, the deflection angle of the thrust vector decreases by about 27%. Also, by placing the location of secondary flow injection after the throat, we can see the deviation of the thrust vector angle is more than the flow injection before the throat. The largest difference between the injection mode in the throat and the injection after the throat is about 25% and the largest deviation of the thrust vector angle occurred at an angle of 45 degrees at the injection position in the throat.

کلیدواژه‌ها [English]

  • Thrust vector control system
  • Bypass double nozzle
  • Thrust vector deflection angle
[1] M. H. Hamedi, "Design, construction and testing of a thrust vector control system with an axially symmetric bypass double-port nozzle for a special microjet,", Khwaja Nasiruddin Tousi University of Technology.," PhD thesis, Khwaja Nasiruddin Tousi University of Technology (in persian).
[2] J. D. Flamm, K. A. Deere, M. L. Mason, B. L. Berrier, S. K. Johnson, “Design Enhancements of the Two-Dimensional, Dual Throat Fluidic Thrust Vectoring Nozzle Concept,” 3rd AIAA Flow Control Conference, San Francisco, California, 2006.
[3] J. D. Flamm, K. A. Deere, M. L. Mason, B. L. Berrier, S. K. Johnson, “Experimental Study of an Axisymmetric Dual Throat Fluidic Thrust Vectoring Nozzle for a Supersonic Aircraft Application,” 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Cincinnati, OH, 2007.
[4] E. G. Bellandi, A. J. Slippey, “Preliminary Analysis and Design   Enhancements of a Dual-Throat FTV Nozzle Concept, Fluid Dynamics,” 39th AIAA Fluid Dynamics Conference, San Antonio, 2009.
[5] C.S. Shin, H. D. Kim, T. Setoguchi, S. Matsuo, “A Computational Study of Thrust Vectoring Control Using Dual Throat Nozzle”, Journal of Thermal Science, Vol. 19, Issue 6, 2010, pp. 486-490.
 [6] M. H. Hamedi, "design and numerical simulation of thrust vector control using fluid flow," master's thesis, Malik Ashtar University of Technology (In Persian).
[7] M. H. Hamedi, "Designing a high-efficiency thrust vector control system with a new method for a microjet engine," presented at the 16th International Conference of Iran Aerospace Society (In Persian).
 [8] Y.-S. Wang, J.-L. Xu, S. Huang, Y.-C. Lin, and J.-J. Jiang, "Experimental and numerical investigation of an axisymmetric divergent dual throat nozzle," Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, vol. 234, no. 3, pp. 563-572, 2020.
[9] K. Wu, T. H. Kim, and H. D. Kim, "Performance Assessment of the Dual-Throat Nozzle Thrust Vector Control in a 3D Rectangular Nozzle," Journal of the Korean Society of Propulsion Engineers, vol. 24, no. 4, pp. 12-24, 2020.
[10] R. Gu, J. Xu, Sh. Guo, “Experimental and Numerical Investigations of a Bypass Dual Throat Nozzle.” ASME. J. Eng. Gas Turbines Power. August 2014; 136(8): 084501.
[11] Fluent, “User Guide Fluent 6.326, Fluent Incorporated”, Lebanon, NH, 2006.