بررسی عددی تأثیر مشخصات پاشنده‌های گازی بر ایمپالس ویژه، تراست و فشار محفظه یک راکت هیبریدی

نوع مقاله : مقاله پژوهشی

نویسندگان

1 دانشجوی کارشناسی ارشد، دانشگاه جامع امام حسین(ع)، تهران، ایران

2 استادیار، دانشگاه جامع امام حسین(ع)، تهران، ایران

چکیده

برای پوشش ضعف سامانه‌های هیبریدی در پایین‌بودن نرخ پسرفت ناشی از احتراق پیشرانه غنی از سوخت (جامد) پارافینی از اکسیدکننده دی نیتروژن اکسید استفاده می‌شود. در این پژوهش میدان حل متمرکز بر یک محفظه احتراق منضم به یک ناحیة محیطی در انتها گنجانده شده است. یک شبیه‌سازی سه‌بعدی حالت پایدار با رویکرد ناویراستوکس با میانگین رینولدز (RANS) و بهره‌گیری از مدل آشفتگی κ-ε استاندارد همراه با مدل اتلاف گردابی (EDM) به‌منظور اندر‌کنش شیمی –آشفتگی (TCI) استفاده می‌شود. شبکه‌بندی از نوع منظم و ثابت برای جریان اکسیدکننده و سوخت در فاز گازی در نظر گرفته می‌شود. نتایج شبیه‌سازی با داده‌های تجربی اعتبارسنجی شده است. نتایج نشان می‌دهد با افزایش 71/35 درصد قطر پاشنده‌ها و افزایش 76/27 درصد نسبت O/F در شبیه‌سازی سه‌بعدی میانگین فشار محفظه احتراق 61/37 درصد، میانگین تراست 46/51 درصد و میانگین ایمپالس ویژه 41/19 درصد ‌افزایش‌یافته است. سایر نتایج حاصل از شبیه‌سازی موتور مزبور امیدوارکننده بوده و بررسی عددی اثر تعداد آرایش قرارگیری و قطر روزنه در پاشنده اکسیدکننده (دی نیتروژن اکسید)، درصد جرمی سوخت و نسبت O/F، روی کمیت فشار محفظه و تراست راکت هیبریدی مقایسه شده است.

کلیدواژه‌ها

عنوان مقاله [English]

Numerical investigation of the effect of the injector characteristics on the specific impulse, thrust, and chamber pressure of a hybrid rocket motor

نویسندگان [English]

  • mohammad reza palizvani 1
  • -Ali Akbar Jamali- 2
1 Master's student, Imam Hossein University, Tehran, Iran
2 Assistant Professor, Imam Hossein University, Tehran, Iran
چکیده [English]

To address the low regression rate issue of hybrid propulsion systems utilizing fuel-rich (solid) paraffin combustion, dinitrogen oxide is employed as an oxidizer. This study focuses on a computational domain that includes a combustion chamber coupled with a peripheral exit region. A three-dimensional steady-state simulation is conducted using the Reynolds-Averaged Navier-Stokes (RANS) approach, incorporating the standard k-ε turbulence model along with the Eddy Dissipation Model (EDM) to account for turbulence-chemistry interaction (TCI). A structured and uniform mesh is utilized for the oxidizer and gaseous fuel flow. The simulation results are validated against experimental data. The findings indicate that by increasing the injector diameter by 35.71% and the O/F ratio by 27.76%, the average combustion chamber pressure rises by 37.61%, the average thrust increases by 51.46%, and the specific impulse improves by 19.41% in the three-dimensional simulation. Additional simulation results demonstrate promising outcomes, and a numerical analysis is conducted to compare the effects of injector orifice diameter, oxidizer (dinitrogen oxide) injection arrangement, fuel mass fraction, and O/F ratio on the combustion chamber pressure and hybrid rocket thrust.

کلیدواژه‌ها [English]

  • Simulation and modeling
  • Hybrid rocket engine
  • paraffin
  • Injector effects
  • trust

Smiley face

 

مراجع

[1]Doustdar M, Ghayoumi M. An Investigation of Applied Techniques to Improve Grid Generation in ICEs Simulations by KIVA. Fluid Mechanics & Aerodynamics. 2022;10(2):195-202.  (In Persian)https://dor.isc.ac/dor/20.1001.1.23223278.1400.10.2.11.8
[2] Sutton GP, Biblarz O. Rocket propulsion elements. John Wiley & Sons. 1976;80(1):579-608. DOI 10.1017/S000192400003431X
[3] Dequick B, Lefebvre M, Hendrick P. Sensitivity analysis of a two phase CFD simulation of a 1 kN paraffin-fueled hybrid rocket motor. Energies. 2021;14(1):6794. DOI 10.3390/en14206794
[4] MAZIDI SHARAFABADI M, Vaezi S.M,  Norouzi E. Performance and Emission Analysis of Combustion Chamber of a Turboprop Engine at Different Operation Regimes.  Fluid mechanics and aerodynamics. 2015;4(1):65-75. Vol. (In Persian)
[5] Altman D, Holzman A. Overview and history of hybrid rocket propulsion. American Institute of Aeronautics. 2007;218(1):1 DOI 10.2514/5.9781600866876.0001.0036
[6] Boardman T.A. Hybrid propellant rockets. Rocket Propulsion Elements. 2001;7(1):597-607.
[7] Barato F, Grosse M, Bettella A. Hybrid rocket fuel residuals an overlooked topic. In 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference. 2014:3753. DOI 10.2514/6.2014-3753
[8] Glaser C, Hijlkema J, Anthoine J. Review of regression rate enhancement techniques for hybrid rocket engines. AIDAA 2021-XXVI International Congres. 2021; 1(1)
[9] Marxman G, Gilbert M. Turbulent boundary layer combustion in the hybrid rocket. In Symposium International on Combustion. 1963;9(1):371-383. DOI 10.1016/S0082-0784(63)80046-6
[10] Chiaverini M. Review of solid fuel regression rate behavior in classical and nonclassical hybrid rocket motors. Progress in Astronautics and Aeronautics. 2007;218(1):37. DOI 10.2514/5.9781600866876.0037.0126
[11] Marquardt T, Majdalani J. Review of classical diffusion limited regression rate models in hybrid rockets. Aerospace. 2019;6(1):75. DOI 10.3390/aerospace6060075
[12] Boiocchi M, Merotto L, Galfetti L . Paraffin Based Fuels Filled with Lithium Based Additives Characterization, In 63rd IAC. 2012;63(1):
[13] MILOVA P. Entrainment effects on combustion processes in paraffin-based hybrid rocket motors. Politecnico di Milano. PhD Dissertation. 2015.
[14] Mazzetti A, Merotto L,  Pinarello G. Paraffin based hybrid rocket engines applications: A review and a market perspective.  Acta Astronautica. 2016;126(1):286-297.DOI 10.1016/j.actaastro.2016.04.036
[15] Nakagawa I, Hikone S. Study on the regression rate of paraffin based hybrid rocket fuels.  Journal of Propulsion and Power. 2011;27(6):1276-1279. DOI 10.2514/1.B34206
[16] Kara O, Karabeyoglu A. Ignition Capability of CO2 in Hybrid Rockets for Mars Ascent Vehicles. Ko¸c University Graduate School of Sciences and Engineering . PhD Dissertation. 2021.
[17] Atayizadeh H. Assessment of the progress variable variance modelling on large eddy simulation of turbulent premixed flames using flamelet generated manifold model .Fuel and Combustion. 2022;14(4):124-145.  DOI 10.22034/JFNC.2022.334445.1311 (In Persian)
[18] PandidehFard M, Mohammadi A. Investigation and Modification of Spalart-allmaras Turbulence Model and Its Application to Flow Over a NACA 0012 Airfoil. Fluid Mechanics & Aerodynamics. 2017;5(2):71-81. (In Persian)https://dor.isc.ac/dor/20.1001.1.23223278.1395.5.2.6.8
[19] Bellomo N, Barato F, Faenza M, Lazzarin M, Bettella A,  Pavarin D. Numerical and experimental investigation of unidirectional vortex injection in hybrid rocket engines. Journal of Propulsion and Power. 2013;29(5):1097-1113. DOI 10.2514/1.B34506
[20] Lazzarin M, Faenza M, Barato F, Bellomo N, Bettella A, Pavarin D. Computational fluid dynamics simulation of hybrid rockets of different scales. Journal of Propulsion and Power. 2015;31(5):1458-1469. DOI 10.2514/1.B35528
[21] Gelain R. CFD Simulations of Self-Pressurized Nitrous Oxide Hybrid Rocket Motors. University of Padua DEPARTMENT OF INDUSTRIAL ENGINEERING . Master's Degree in Aerospace Engineering. 2017.
[22] Ranuzzi G, Cardillo D, Invigorito M. Numerical investigation of a N2O-paraffin hybrid rocket engine combusting flowfield, In 6th EUCASS. 2015.
[23] Bianchi D, Nasuti F,  Delfini D. Modeling of gas–surface interface for paraffin-based hybrid rocket fuels in computational fluid dynamics simulations. Progress in Propulsion Physics. 2019;11(11):3-24. DOI 10.1051/eucass/201911003
[24] Bianchi D, Nasuti F, Delfini D. Modeling of Gas-Surface Interface for Paraffin-Based Hybrid Rocket Fuels in CFD Simulations. 6th EUCASS. 2015.
[25] Leccese G, Bianchi D, Nasuti F. Modeling and simulation of paraffin based hybrid rocket internal ballistics. In 2018 Joint Propulsion Conference, Cincinnati. 2018:4533. DOI 10.2514/6.2018-4533
[26] Leccese G. Gas-Surface interaction radiative heat transfer and thermochemistry modeling in the simulation of paraffin-based hybrid rocket engines. Sapienza University DIMA Mechanical and Aerospace Engineering Department. PhD Dissertation. 2018.
[27] Di Martino G.D, Mungiguerra S, Carmicino C,  Savino R. Computational Fluid Dynamic Simulations of the Internal Ballistics of Hybrid Rocket Burning Paraffin based Fuel. In 2018 Joint Propulsion Conference. 2018:4532. DOI 10.2514/6.20184532
[28] Dequick B, Lefebvre M, Hendrick P. CFD Simulation of a 1kN Paraffin Fueled Hybrid Rocket Engine.  In AIAA Propulsion and Energy 2020 Forum. 2020:3763. DOI 10.2514/6.2020-3763
[29] Bouziane M, Bertoldi A.E.D.M, Hendrick P, Lefebvre M. Experimental investigation of the axial oxidizer injectors geometry on a 1-kN paraffin-fueled hybrid rocket motor. FirePhysChem. 2021;1(4).231-243. DOI 10.1016/j.fpc.2021.11.012
[30] Waxman B.S. An investigation of injectors for use with high vapor pressure propellants with applications to hybrid rockets. Stanford University. PhD Dissertation. 2014.
[31] Saniinejad M. A comprehensive investigation and sensitivity assessment of the capability of k-ε and k-ω turbulence models in capturing the flow physics in the turbulent ultrasonic boundary layer formed on smooth and rough flat plates at very high Reynolds numbers.
Fluid mechanics and aerodynamics. 2009;1(2):55-72. (In Persian).
[32] Doustdar M, Gharezi S. Investigating the effects of secondary and dilution air holes and chamber diameter on the performance of ramjet engine combustion chamber. Fluid Mechanics & Aerodynamics. 2023;12(1):129-137. (In Persian).https://dor.isc.ac/dor/20.1001.1.23223278.1402.12.1.10.9
[33] Palizvani M.R, Jamali A.A. Numerical study of the effect of mass flow rate and ratio of fuel to oxidizer on thrust, specific impulse and chamber pressure of a hybrid rocket based on paraffin fuel combustion. JFNC. 2024;17(3):97-122. DOR  https://doi.org/ 10.22034/jfnc.2025.459143.1395 (In Persian).
مکانیک سیالات و آیرودینامیک
دوره 13، شماره 2 - شماره پیاپی 33
پاییز و زمستان 1403
آذر 1403
صفحه 125-144

فایل ها

سابقه مقاله

  • تاریخ دریافت: 08 خرداد 1403
  • تاریخ بازنگری: 10 مهر 1403
  • تاریخ پذیرش: 22 آبان 1403
  • تاریخ انتشار: 11 آذر 1403

هم رسانی

ارجاع به این مقاله

آمار