Studies of flow field characteristics during the impact of a gaseous jet on liquid–water column
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摘要
Both experimental and numerical studies were presented on the flow field characteristics in the process of gaseous jet impinging on liquid–water column. The effects of the impinging process on the working performance of rocket engine were also analyzed. The experimental results showed that the liquid–water had better flame and smoke dissipation effect in the process of gaseous jet impinging on liquid–water column. However, the interaction between the gaseous jet and the liquid–water column resulted in two pressure oscillations with large amplitude appearing in the combustion chamber of the rocket engine with instantaneous pressure increased by 17.73% and 17.93%, respectively. To analyze the phenomena, a new computational method was proposed by coupling the governing equations of the MIXTURE model with the phase change equations of water and the combustion equation of propellant. Numerical simulations were carried out on the generation of gas, the accelerate gas flow, and the mutual interaction between gaseous jet and liquid–water column.Numerical simulations showed that a cavity would be formed in the liquid–water column when gaseous jet impinged on the liquid–water column. The development speed of the cavity increased obviously after each pressure oscillation. In the initial stage of impingement, the gaseous jet was blocked due to the inertia effect of high-density water, and a large amount of gas gathered in the area between the nozzle throat and the gas–liquid interface. The shock wave was formed in the nozzle expansion section. Under the dual action of the reverse pressure wave and the continuously ejected high-temperature gas upstream, the shock wave moved repeatedly in the nozzle expansion section, which led to the flow of gas in the combustion chamber being blocked, released, re-blocked, and re-released. This was also the main reason for the pressure oscillations in the combustion chamber.
Both experimental and numerical studies were presented on the flow field characteristics in the process of gaseous jet impinging on liquid–water column. The effects of the impinging process on the working performance of rocket engine were also analyzed. The experimental results showed that the liquid–water had better flame and smoke dissipation effect in the process of gaseous jet impinging on liquid–water column. However, the interaction between the gaseous jet and the liquid–water column resulted in two pressure oscillations with large amplitude appearing in the combustion chamber of the rocket engine with instantaneous pressure increased by 17.73% and 17.93%, respectively. To analyze the phenomena, a new computational method was proposed by coupling the governing equations of the MIXTURE model with the phase change equations of water and the combustion equation of propellant. Numerical simulations were carried out on the generation of gas, the accelerate gas flow, and the mutual interaction between gaseous jet and liquid–water column.Numerical simulations showed that a cavity would be formed in the liquid–water column when gaseous jet impinged on the liquid–water column. The development speed of the cavity increased obviously after each pressure oscillation. In the initial stage of impingement, the gaseous jet was blocked due to the inertia effect of high-density water, and a large amount of gas gathered in the area between the nozzle throat and the gas–liquid interface. The shock wave was formed in the nozzle expansion section. Under the dual action of the reverse pressure wave and the continuously ejected high-temperature gas upstream, the shock wave moved repeatedly in the nozzle expansion section, which led to the flow of gas in the combustion chamber being blocked, released, re-blocked, and re-released. This was also the main reason for the pressure oscillations in the combustion chamber.
Both experimental and numerical studies were presented on the flow field characteristics in the process of gaseous jet impinging on liquid–water column. The effects of the impinging process on the working performance of rocket engine were also analyzed. The experimental results showed that the liquid–water had better flame and smoke dissipation effect in the process of gaseous jet impinging on liquid–water column. However, the interaction between the gaseous jet and the liquid–water column resulted in two pressure oscillations with large amplitude appearing in the combustion chamber of the rocket engine with instantaneous pressure increased by 17.73% and 17.93%, respectively. To analyze the phenomena, a new computational method was proposed by coupling the governing equations of the MIXTURE model with the phase change equations of water and the combustion equation of propellant. Numerical simulations were carried out on the generation of gas, the accelerate gas flow, and the mutual interaction between gaseous jet and liquid–water column.Numerical simulations showed that a cavity would be formed in the liquid–water column when gaseous jet impinged on the liquid–water column. The development speed of the cavity increased obviously after each pressure oscillation. In the initial stage of impingement, the gaseous jet was blocked due to the inertia effect of high-density water, and a large amount of gas gathered in the area between the nozzle throat and the gas–liquid interface. The shock wave was formed in the nozzle expansion section. Under the dual action of the reverse pressure wave and the continuously ejected high-temperature gas upstream, the shock wave moved repeatedly in the nozzle expansion section, which led to the flow of gas in the combustion chamber being blocked, released, re-blocked, and re-released. This was also the main reason for the pressure oscillations in the combustion chamber.
引文
[1] Vuorinen V, Yu J Z, Tirunagari S, Kaario O, Larmi M, Duwig C and Boersma B J 2013 Phys. Fluids 25 016101
[2] Li X P, Zhou R, Chen X P, Fan X J and Xie G S 2018 Chin. Phys. B 27094705
[3] Geery E and Greenwood R 1969 5th Propulsion Joint Specialist June9-13, 1969, Colorado Springs, USA, p. 514
[4] Ignatius J K, Sathiyavageeswaran S and Chakravarthy S R 2015 AIAA J. 53 235
[5] Zoppellari E and Juve D 1998 4th AIAA/CEAS Aeroacoustics Conference, June 2-4, 1998, Toulouse, France, p. 35
[6] Sankaran S, Ignatius J K, Ramkumar R, Satyanarayana T N V,Chakravarthy S R and Panchapakesan N R 2009 J. Spacecr. Rockets46 1164
[7] Jiang Y, Ma Y L, Wang W C and Shao L W 2010 Chin. J. Aeronaut 23653
[8] Li J, Jiang Y, Yu S Z and Zhou F 2015 Energies 8 13194
[9] Kandula M 2008 AIAA J. 46 2714
[10] Fukuda K, Tsutsumi S, Shimizu T and Takaki R 2011 17th AIAA/CEAS Aeroacoustics Conference, June 5-8, 2011, Portland, USA, p. 092407
[11] Wang Z G, Wu L Y, Li Q L and Li C 2014 Appl. Phys. Lett. 105 134102
[12] Zhang L, Wang H and Ruan W J 2016 Acoust. Aust. 44 291
[13] Arghode V K and Gupta A K 2012 Appl. Energy 89 246
[14] Shi H H, Wang B Y and Dai Z Q 2010 Sci. Chin. Phys. Mech. 53 527
[15] Zhao H Y and Bhabra B 2018 Int. J. Multiphase Flow 105 74
[16] Tang Y L, Li S P, Liu Z, Sui X and Wang N F 2015 Acta. Phys. Sin. 64234702(in Chinese)
[17] Xu H, Wang C, Lu H Z and Huang W H 2018 Acta. Phys. Sin. 67014703(in Chinese)
[18] Mohamad T I 2015 Fuel 160 386
[19] Hong S J, Park G C, Cho S and Song C H 2012 Int. J. Multiphase Flow39 66
[20] Li S P, Tang Y L, Tang J N and Wang N F 2017 55th AIAA Aerospace Sciences Meeting, January 9-13, 2017, Grapevine, USA, p. 8
[21] Weil, C and Vlachos P P 2013 Int. J. Multiphase Flow 48 46
[22] Liu G, Wang Y S, Zang G J and Zhao H T 2015 Int. J. Heat Mass Transfer 84 592
[23] Xu H, Fan P F, Ma Y, Guo X S, Yang P, Tu J and Zhang D 2017 Chin.Phys. B 26 024301
[24] Ren G W, Zhang S W, Hong R K, Tang T G and Chen Y T 2016 Chin.Phys. B 25 086202
[2] Li X P, Zhou R, Chen X P, Fan X J and Xie G S 2018 Chin. Phys. B 27094705
[3] Geery E and Greenwood R 1969 5th Propulsion Joint Specialist June9-13, 1969, Colorado Springs, USA, p. 514
[4] Ignatius J K, Sathiyavageeswaran S and Chakravarthy S R 2015 AIAA J. 53 235
[5] Zoppellari E and Juve D 1998 4th AIAA/CEAS Aeroacoustics Conference, June 2-4, 1998, Toulouse, France, p. 35
[6] Sankaran S, Ignatius J K, Ramkumar R, Satyanarayana T N V,Chakravarthy S R and Panchapakesan N R 2009 J. Spacecr. Rockets46 1164
[7] Jiang Y, Ma Y L, Wang W C and Shao L W 2010 Chin. J. Aeronaut 23653
[8] Li J, Jiang Y, Yu S Z and Zhou F 2015 Energies 8 13194
[9] Kandula M 2008 AIAA J. 46 2714
[10] Fukuda K, Tsutsumi S, Shimizu T and Takaki R 2011 17th AIAA/CEAS Aeroacoustics Conference, June 5-8, 2011, Portland, USA, p. 092407
[11] Wang Z G, Wu L Y, Li Q L and Li C 2014 Appl. Phys. Lett. 105 134102
[12] Zhang L, Wang H and Ruan W J 2016 Acoust. Aust. 44 291
[13] Arghode V K and Gupta A K 2012 Appl. Energy 89 246
[14] Shi H H, Wang B Y and Dai Z Q 2010 Sci. Chin. Phys. Mech. 53 527
[15] Zhao H Y and Bhabra B 2018 Int. J. Multiphase Flow 105 74
[16] Tang Y L, Li S P, Liu Z, Sui X and Wang N F 2015 Acta. Phys. Sin. 64234702(in Chinese)
[17] Xu H, Wang C, Lu H Z and Huang W H 2018 Acta. Phys. Sin. 67014703(in Chinese)
[18] Mohamad T I 2015 Fuel 160 386
[19] Hong S J, Park G C, Cho S and Song C H 2012 Int. J. Multiphase Flow39 66
[20] Li S P, Tang Y L, Tang J N and Wang N F 2017 55th AIAA Aerospace Sciences Meeting, January 9-13, 2017, Grapevine, USA, p. 8
[21] Weil, C and Vlachos P P 2013 Int. J. Multiphase Flow 48 46
[22] Liu G, Wang Y S, Zang G J and Zhao H T 2015 Int. J. Heat Mass Transfer 84 592
[23] Xu H, Fan P F, Ma Y, Guo X S, Yang P, Tu J and Zhang D 2017 Chin.Phys. B 26 024301
[24] Ren G W, Zhang S W, Hong R K, Tang T G and Chen Y T 2016 Chin.Phys. B 25 086202