Numerical simulations of ignition by soak-back heat through the injection panel in a premixed C2H4/N2O thruster

WANG Weilong; ZHANG Huiqiang

doi:10.16511/j.cnki.qhdxxb.2019.26.033

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Journal of Tsinghua University(Science and Technology) ›› 2020, Vol. 60 ›› Issue (3) : 206-211. DOI: 10.16511/j.cnki.qhdxxb.2019.26.033

SPECIAL SECTION: AEROSPACE AND ENGINEERING MECHANICS

Numerical simulations of ignition by soak-back heat through the injection panel in a premixed C₂H₄/N₂O thruster

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Abstract

The premixed C₂H₄/N₂O propulsion system has significant potential for attitude and orbit control thrusters since the propellant is not toxic and the systems are efficient and simple. However, methods are needed to prevent flashback. This study used a numerical model to analyze ignition in a thruster chamber with a single injector unit with a premixed C₂H₄/N₂O propellant. The model included the plenum chamber, injection panel, combustion chamber and nozzle. The numerical model included a detailed chemical reaction mechanism for the ignition in the combustor and plenum chamber by coupling the reacting flow in the entire model and the heat transfer in the injection panel. The model predicts the spatio-temporal evolution of the unsteady ignition process in the thruster chamber and the steady characteristics are consistent with the results of chemical equilibrium calculations. Reducing the hole to the panel area ratio significantly increased the soak-back heat from the combustion chamber to the plenum chamber through the injection panel which eventually led to ignition of the premixed C₂H₄/N₂O propellant in the plenum chamber. This is a new flashback mode induced by structural heat transfer through the injection panel. This process has a critical hole to panel area ratio for this propellant with a conventional chamber head. Thus, a new constraint criterion is given for the injection panel design of a premixed C₂H₄/N₂O propulsion system.

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liquid rocket engine / propellant / flashback / soak-back heat

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WANG Weilong, ZHANG Huiqiang. Numerical simulations of ignition by soak-back heat through the injection panel in a premixed C₂H₄/N₂O thruster[J]. Journal of Tsinghua University(Science and Technology). 2020, 60(3): 206-211 https://doi.org/10.16511/j.cnki.qhdxxb.2019.26.033

References

[1] TAYLOR R. Safety and performance advantages of nitrous oxide fuel blends (NOFBX) propellants for manned and unmanned spaceflight applications[C]//Proceedings of the 5th IAASS Conference A Safer Space for Safer World. Noordwijk, Netherlands:European Space Agency, 2012:67-69.
[2] ZAKIROV V, SWEETING M, LAWRENCE T, et al. Nitrous oxide as a rocket propellant[J]. Acta Astronautica, 2001, 48(5-12):353-362.
[3] WHITMORE S A, CHANDLER S N. Engineering model for self-pressurizing saturated N₂O propellant feed systems[J]. Journal of Propulsion and Power, 2010, 26(4):706-714.
[4] WERLING L K, HOCHHEIMER B, BARAL A L, et al. Experimental and numerical analysis of the heat flux occurring in a nitrous oxide/ethene green propellant combustion demonstrator[C]//Proceedings of the 51st AIAA/SAE/ASEE Joint Propulsion Conference. Orlando, USA:AIAA, 2015:4061-4065.
[5] KARABEYOGLU A, DYER J, STEVENS J, et al. Modeling of N₂O decomposition events[C]//Proceedings of the 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Hartford, CT, USA:AIAA, 2008:4933-4936.
[6] SACKHEIM R L, MASSE R K. Green propulsion advancement:Challenging the maturity of monopropellant hydrazine[J]. Journal of Propulsion and Power, 2014, 30(2):265-276.
[7] GOHARDANI A S, STANOJEV J, DEMAIRÉ A, et al. Green space propulsion:Opportunities and prospects[J]. Progress in Aerospace Sciences, 2014, 71:128-149.
[8] THOMPSON B F, STRACK D F, MUNGAS G. Determining electrical ignition characteristics of a gas propulsion system[J]. Journal of Spacecraft and Rockets, 2016:960-968.
[9] WERLING L, PERAKIS N, MULLER S, et al. Hot firing of a N₂O/C₂H₄ premixed green propellant:First combustion tests and results[C]//Proceedings of the Space Propulsion Conference. Rome, Italy:European Space Agency, 2016.
[10] PERAKIS N, HOCHHEIMER B, WERLING L, et al. Development of an experimental demonstrator unit using nitrous oxide/ethylene premixed bipropellant for satellite applications[C]//Proceedings of the Meet the Space Conference. Krakow, Poland:Institute of Transport Research, 2014.
[11] PERAKIS N, WERLING L, CIEZKI H, et al. Numerical calculation of heat flux profiles in a N₂O/C₂H₄ premixed green propellant combustor using an inverse heat conduction method[C]//Proceedings of the Space Propulsion Conference. Rome, Italy:European Space Agency, 2016.
[12] BANGALORE VENKATESH P, GRAZIANO T, BANE S P, et al. Deflagration-to-detonation transition in nitrous oxide-ethylene mixtures and its application to pulsed propulsion systems[C]//Proceedings of the 55th AIAA Aerospace Sciences Meeting. Grapevine, Texas, USA:AIAA, 2017:6.2017-0372.
[13] 张文普, 李宇斌. 燃气轮机燃烧回火机理与数值模拟的研究进展[J]. 燃烧科学与技术, 2016, 22(5):385-401.ZHANG W P, LI Y B. Progress in mechanisms and numerical simulation of flame flashback for gas turbine[J]. Journal of Combustion Science and Technology, 2016, 22(5):385-401. (in Chinese)
[14] LIEUWEN T, MCDONELL V, PETERSEN E, et al. Fuel flexibility influences on premixed combustor blowout, flashback, autoignition, and stability[J]. Journal of Engineering for Gas Rurbines and Power, 2008, 130(1):011506.
[15] PLEE S L, MELLOR A M. Review of flashback reported in prevaporizing/premixing combustors[J]. Combustion and Flame, 1978, 32:193-203.
[16] QIN J X, ZHANG H Q, WANG B. Numerical evaluation of acoustic characteristics and their damping of a thrust chamber using a constant-volume bomb model[J]. Chinese Journal of Aeronautics, 2018, 31(3):470-480.
[17] 覃建秀. 姿轨控发动机推力室声学特性及燃烧不稳定性数值研究[D]. 北京:清华大学, 2017.QIN J X. Numerical investigation of acoustic characteristics and combustion instability in the attitude and orbit control thruster[D]. Beijing:Tsinghua University, 2017. (in Chinese)
[18] WANG W L, ZHANG H Q. Laminar burning velocities of C₂H₄/N₂O flames:Experimental study and its chemical kinetics mechanism[J]. Combustion and Flame, 2019, 202:362-375.
[19] ULAS A, BOYSAN E. Numerical analysis of regenerative cooling in liquid propellant rocket engines[J]. Aerospace Science and Technology, 2013, 24(1):187-197.