بررسی تجربی تأثیر چیدمان عرضی برآمدگی‌های دوگانه بر بردار پیشرانش در نازل مافوق صوت همگرا-واگرا

نوع مقاله : مقاله پژوهشی

نویسندگان

دانشگاه آزاد اسلامی، واحد نجف آباد

چکیده

در این پژوهش اثرات برآمدگی‌های دوگانه به‌عنوان یک روش جدید، کم‌هزینه و ساده در کنترل بردار پیشرانش در یک نازل همگرا‑واگرا در رژیم مافوق صوت که عدد ماخ اسمی آن 2 است، به‌صورت تجربی بررسی می‌شود. برآمدگی‌های مورد استفاده دو قطعه استوانه‌ای شکل است که جلوی جریان در قسمت واگرای نازل قرار داده می‌شود. این برآمدگی‌ها در موقعیت‌های 80 درصد طول قسمت واگرای نازل از گلوگاه نازل به‌صورت عرضی و با زاویۀ 45 درجه نسبت به یکدیگر نصب شده‌ و به‌صورت هم‌زمان در مسیر جریان اعمال می‌شود. میدان جریان به‌وسیله تصویربرداری شلرین همراه با اندازه‌گیری تغییرات فشار روی دیواره‌های نازل انجام شده است. نتایج نشان می‌دهد چیدمان عرضی برآمدگی‌های دوگانه در نازل می‌تواند زاویۀ بردار پیشرانش را تا 3.5 درجه در شرایط بررسی شده افزایش دهد. همچنین ضمن دستیابی به زاویۀ انحراف مشخص با نسبت نفوذ کمتر در مقایسه با استفاده از یک برآمدگی تا 5.5 درصد افت پیشرانش محوری را کم نمود.

کلیدواژه‌ها


عنوان مقاله [English]

Experimental Investigation of the Influence of Transverse Dual protuberances on the Thrust Vector of a Supersonic C-D nozzle

نویسنده [English]

  • Mohammad Reza Babaeyan
Najafabad Branch, Islamic Azad University
چکیده [English]

In this study, effects of the use of dual transverse protuberances (DTP) as a new, low cost and simple method in controlling the thrust vector in a C-D  nozzle, whose nominal Mach number is 2, was investigated. The protuberances used are two cylindrical shapes that are placed in front of the flow in the divergence part of  nozzle. Protuberances are installed in 80% of the length of the nozzle divergence section from nozzle throat, transversely and at a 45° angle to each other. The flow field was investigated by schlieren imaging, along with measuring the pressure distributions on the nozzle walls. The results show that using the DTP in the nozzle can increase the angle of the thrust vector to 3.5 degrees in the examined conditions. Also,it can be achived in compare to using a single protobrance with lower thrust loss up to 5.5%.

کلیدواژه‌ها [English]

  • TVC
  • C-D Nozzle
  • Supersonic Flow
  • Protuberance
  • Experimental Aerodynamics
1. Sutton, G.P. and Biblarz, O., "Rocket Propulsion Elements", John Wiley & Sons Inc, New York, (2001).
2. Gubse, R.D. "An experimental investigation of thrust vector control by secondary injection," NASA CR-297, (1965).
3. Dhinagaran, R. and Bose, T.K. "Comparison of Euler and Navier-Stokes solutions for nozzle flows with secondary injection", AIAA Paper 96-0453, AIAA 34th Aerospace Sciences Meeting and Exhibit, Reno, NV Jan 15-18, (1996).
4. Lee, S.H., "Characteristics of dual transverse injection in scramjet combustor, Part 1: Mixing", Journal of Propulsion and Power, Vol. 22, No. 5, (2006).
5. Anantesha, S.N. and Vamsidhar, D., "Numerical investigation and parametric study of fluidic thrust vectoring by shock vector control method, " SASTECH ,Vol. 6, No. 2, (2007).
6. Shin, C.S., "A computational study of thrust vectoring control using dual throat nozzle," Journal of Thermal Science, Vol. 19, No. 6 , pp. 486-490, (2010).
7. Deng, R., Kong, F. and Kim, H.D., "Numerical simulation of fluidic thrust vectoring in an axisymmetric supersonic nozzle," Journal of Mechanical Science and Technology, Vol. 28, No. 12, pp. 4979-4987, (2014).
8. Zmijanovic, V., Lago, V., Sellam, M. and Chpoun, A., "Thrust shock vector control of an axisymmetric conical supersonic nozzle via secondary transverse gas injection," Shock Waves, Vol. 24, No. 1, pp. 97-111, (2014).
9. Deng, R., Setoguchi, T. and Kim, H.D., "Large eddy simulation of shock vector control using bypass flow passage," Journal of Heat and Fluid Flow, Vol. 62, pp. 474-481, (2016).
10. Kong, F., Jin, Y. and Kim, H.D. "Thrust vector control of supersonic nozzle flow using a moving plate," Journal of Mechanical Science and Technology, Vol. 30, No. 3, pp. 1209-1216, (2016).
11. Salemi, V.R., Sohrabi, S., Hojaji, M. and Soufivand, M.R., "Experimental study on the effects of secondary injection thrust vector in a Micro-Nozzles", First National Conference on Advances and Challenges in Engineering and Technology, Iran, (2016). (In Persian)
12. Salehifar, M., Tahani, M., Hojaji, M. and Dartoomian, A., "CFD modeling for flow field characterization and performance analysis of HGITVC", Applied Thermal Engineering, Vol. 103, pp. 291-304, (2016).
13. Mokhtari, D., Hojaji, M. and Mokhtari, M., "Experimental study of the effect of Protuberance on the thrust vector in convergent-divergent micro nozzle", 16th International Conference of Iranian Aerospace Society, Khaje Naseerdin Tousi University of Technology, Tehran, (2017). (In Persion)
14. Li, L., Hirota, M., Ouchi, K. and Saito, T., "Evaluation of fluidic thrust vectoring nozzle via thrust pitching angle and thrust pitching moment", Shock Waves, Vol. 27, No. 1, pp. 53-61, (2017).
15. Mokhtari, D., Hojaji, M. and Afrand, M., "Experimental investigation of the effect of cylindrical protuberance with different penetration the thrust vector a C-D nozzle in supersonic regime", Modares Mechanical Engineering, Vol. 19, No. 5, pp. 1145-1154, (2019).
16. Mokhtari, D., Hojaji, M. and Afrand, M., "Experimental investigation of the effect of location of cylindrical protuberance on the thrust vector of a supersonic C-D nozzle", Journal of Solid and Fluid Mechanics, Vol. 9, No. 1, pp. 237-249, (2019).
17. Babaeyan, M.R. and Hojaji, M., "Experimental investigation of the penetration effects of opposite dual protuberances on thrust vector of a supersonic C-D nozzle", Modares Mechanical Engineering, Vol. 19, No. 7, pp. 1741-1750, (2019).
18. Sharafi, A. and Mokhtari, D., "Experimental study of effect of obstacle presence and its geometry on thrust vector and outlet jet in a convergent-divergent micro nozzle", Modares Mechanical Engineering, Vol. 20, No. 5, pp. 1211-1221, (2020).
19. Tahani, M., Hojaji, M. and Mahmoodi, S.V., "Turbulent jet crossflow analysis with LES approach", Aircraft Engineering and Aerospace Technology, Vol. 88, No. 6, pp. 717-728, (2016).
CAPTCHA Image