CLC number:
On-line Access: 2022-02-28
Received: 2021-05-13
Revision Accepted: 2021-08-03
Crosschecked: 0000-00-00
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Peng-jin CAO, Xiao BAI, Qing-lian LI, Peng CHENG. Experimental and theoretical study on the break phenomenon of self-pulsation for liquid-centered swirl coaxial injectors[J]. Journal of Zhejiang University Science A,in press.Frontiers of Information Technology & Electronic Engineering,in press.https://doi.org/10.1631/jzus.A2100222 @article{title="Experimental and theoretical study on the break phenomenon of self-pulsation for liquid-centered swirl coaxial injectors", %0 Journal Article TY - JOUR
液体中心式气液同轴离心式喷嘴自激振荡间断现象的实验和理论研究创新点:1.通过测量喷嘴缩进室内部多点高频压力,分析压力扰动相位变换关系;2.建立自激振荡理论模型,成功地模拟液膜微元流动过程。 方法:1.通过实验分析,得到喷嘴缩进室内部液膜流动的变化形态,并对比自激振荡和稳态时缩进室内压力振荡关系(图6和7);2.通过理论推导,构建液膜微元运动位置随时间的变化关系(公式(16)),并得到缩进室内压力和气/液动量随时间的变化关系(图12和13)。 结论:1.气液动量通量比增加会使缩进较大的气液同轴离心式喷嘴出现自激振荡间断现象,并且间断前后自激振荡的频率和强度发生显著变化。2.自激振荡间断现象发生时,缩进室内液膜流动模态依次由周期性扩张主导流动转变为稳定流动再转变为周期性收缩主导流动。3.通过自激振荡理论模型,可以较好地预测自激振荡频率,气液两相的能量传递是维持自激振荡过程的重要因素。 关键词组: Darkslateblue:Affiliate; Royal Blue:Author; Turquoise:Article
Reference[1]AhnK, KimJG, ChoiHS, 2014. Effects of injector recess on heat flux in a combustion chamber with cooling channels. Aerospace Science and Technology, 37:110-116. [2]ArmbrusterW, HardiJS, SuslovD, et al., 2018. Experimental investigation of self-excited combustion instabilities with injection coupling in a cryogenic rocket combustor. Acta Astronautica, 151:655-667. [3]ArmbrusterW, HardiJS, MieneY, et al., 2020. Damping device to reduce the risk of injection-coupled combustion instabilities in liquid propellant rocket engines. Acta Astronautica, 169:170-179. [4]BaiX, 2020. The Self-Pulsation and Its Effects on Spray Combustion Characteristics for Gas-Liquid Swirl Coaxial Injector. National University of Defense Technology, Changsha, China(in Chinese). [5]BaiX, LiQL, ChengP, et al., 2018. Investigation of self-pulsation characteristics for a liquid-centered swirl coaxial injector with recess. Acta Astronautica, 151:511-521. [6]BaiX, ChengP, ShengLY, et al., 2019. Effects of backpressure on self-pulsation characteristics of liquid-centered swirl coaxial injectors. International Journal of Multiphase Flow, 116:239-249. [7]BaiX, ShengLY, LiQL, et al., 2020a. Effects of annulus width and post thickness on self-pulsation characteristics for liquid-centered swirl coaxial injectors. International Journal of Multiphase Flow, 122:103140. [8]BaiX, ChengP, LiQL, et al., 2020b. Effects of self-pulsation on combustion instability in a liquid rocket engine. Experimental Thermal and Fluid Science, 114:110038. [9]BaiX, CaoPJ, LiQL, et al., 2021. The break phenomenon of self-pulsation for liquid-centered swirl coaxial injectors. International Journal of Multiphase Flow, 142:103708. [10]BazarovVG, YangV, 1998. Liquid-propellant rocket engine injector dynamics. Journal of Propulsion and Power, 14(5):797-806. [11]ChenXD, YangV, 2014. Effect of ambient pressure on liquid swirl injector flow dynamics. Physics of Fluids, 26(10):102104. [12]ChuW, LiXQ, TongYH, et al., 2020. Numerical investigation of the effects of gas-liquid ratio on the spray characteristics of liquid-centered swirl coaxial injectors. Acta Astronautica, 175:204-215. [13]ChuW, RenYJ, TongYH, et al., 2021. Numerical study of effects of backpressure on self-pulsation of a liquid-centred swirl coaxial injector. International Journal of Multiphase Flow, 139:103626. [14]EberhartCJ, Frederick JrRA, 2017a. Fluid oscillations of a swirl coaxial injector under high-frequency self-pulsation. Journal of Propulsion and Power, 33(4):804-814. [15]EberhartCJ, Frederick JrRA, 2017b. Details on the mechanism of high-frequency swirl coaxial self-pulsation. Journal of Propulsion and Power, 33(6):1418-1427. [16]FuQF, YangLJ, QuYY, 2011. Measurement of annular liquid film thickness in an open-end swirl injector. Aerospace Science and Technology, 15(2):117-124. [17]GiannadakisA, NaxakisA, RomeosA, et al., 2019. An experimental study on a coaxial flow with inner swirl: vortex evolution and flow field mixing attributes. Aerospace Science and Technology, 94:105373. [18]GometL, RobinV, MuraA, 2014. Lagrangian modelling of turbulent spray combustion under liquid rocket engine conditions. Acta Astronautica, 94(1):184-197. [19]HuangYH, ZhouJ, HuXP, et al., 1998. Experiment and acoustic model for the self-oscillation of coaxial swirl injector and its influence to combustion of liquid rocket engine. Acta Acustica, 23(5):459-465 (in Chinese). [20]ImJH, YoonY, 2013. The effects of the ambient pressure on self-pulsation characteristics of a gas/liquid swirl coaxial injector. Orthopedics & Traumatology, 38(2):435-438. [21]ImJH, KimD, HanP, 2009. Self-pulsation characteristics of a gas-liquid swirl coaxial injector. Atomization and Sprays, 19(2):57-74. [22]KangZT, LiQL, ChengP, et al., 2016a. Effects of recess on the self-pulsation characteristics of liquid-centered swirl coaxial injectors. Journal of Propulsion and Power, 32(5):1124-1132. [23]KangZT, LiQL, ChengP, et al., 2016b. Effects of self-pulsation on the spray characteristics of gas-liquid swirl coaxial injector. Acta Astronautica, 127:249-259. [24]KangZT, WangZG, LiQL, et al., 2018. Review on pressure swirl injector in liquid rocket engine. Acta Astronautica, 145:174-198. [25]KimD, ImJH, KohH, et al., 2007a. Effect of ambient gas density on spray characteristics of swirling liquid sheets. Journal of Propulsion and Power, 23(3):603-611. [26]KimD, HanP, ImJH, et al., 2007b. Effect of recess on the spray characteristics of liquid–liquid swirl coaxial injectors. Journal of Propulsion and Power, 23(6):1194-1203. [27]KimJG, HanYM, ChoiHS, et al., 2013. Study on spray patterns of gas-centered swirl coaxial (GCSC) injectors in high pressure conditions. Aerospace Science and Technology, 27(1):171-178. [28]KimYJ, SohnCH, HongM, et al., 2014. An analysis of fuel–oxidizer mixing and combustion induced by swirl coaxial jet injector with a model of gas–gas injection. Aerospace Science and Technology, 37:37-47. [29]LiHX, YeL, WeiXL, et al., 2017. The design and main performance of a hydrogen peroxide/kerosene coaxial-swirl injector in a lab-scale rocket engine. Aerospace Science and Technology, 70:636-643. [30]LiQL, KangZT, ZhangXQ, et al., 2016. Effect of recess length on the spray characteristics of liquid-centered swirl coaxial injectors. Atomization and Sprays, 26(6):535-550. [31]LuxJ, HaidnO, 2009. Effect of recess in high-pressure liquid oxygen/methane coaxial injection and combustion. Journal of Propulsion and Power, 25(1):24-32. [32]RanadeIS, FrederickRA, 2019. Experimental study of swirl coaxial injector hydrodynamics under high-frequency self-pulsation. Proceedings of the AIAA Propulsion and Energy 2019 Forum. [33]RenYJ, ChuW, TongYH, et al., 2021a. Numerical investigation on spray self-pulsation characteristics of a liquid-centered swirl coaxial injector. Aerospace Science and Technology, 112:106593. [34]RenYJ, GuoKK, ZhaoJF, et al., 2021b. Numerical investigation of spray self-pulsation characteristics of liquid-centered swirl coaxial injector with different recess lengths. International Journal of Multiphase Flow, 138: 103592. [35]YangLJ, FuQF, 2011. Theoretical investigation on the dynamics of a gas-liquid coaxial swirl injector. Journal of Propulsion and Power, 27(1):144-150. [36]YangLJ, GeMH, ZhangMZ, et al., 2008. Spray characteristics of recessed gas-liquid coaxial swirl injector. Journal of Propulsion and Power, 24(6):1332-1339. [37]YuanL, ShenCB, 2016. Large eddy simulation of combustion instability in a tripropellant air heater. Acta Astronautica, 129:59-73. Journal of Zhejiang University-SCIENCE, 38 Zheda Road, Hangzhou
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