环形燃烧室中凹腔对C2H4/Air旋转爆轰流场影响的数值模拟

doi:10.12382/bgxb.2021.0249

摘要/Abstract

摘要： 为研究环形燃烧室中凹腔对旋转爆轰流场的影响，通过在开源计算流体动力学软件OpenFOAM框架内求解Navier-Stokes方程，对C₂H₄/Air旋转爆轰燃烧室（RDC）进行三维数值模拟研究。保持进气总压为0.6 MPa，分别在总温300 K、600 K和800 K条件下对比同轴圆环形和凹腔基环形两种构型RDC的主要流场特征，研究凹腔对旋转爆轰波传播特性的影响，定量分析不同热释放速率下消耗的燃料占比，对比了不同热释放速率下消耗的燃料比例。结果表明：对于凹腔基环形RDC，在凹腔内存在回流区，导致在凹腔上游流速缓慢，但在凹腔收缩段流动明显加速，RDC出口的面平均马赫数大于与之对应的同轴圆环形RDC；受燃料向RDC出口和凹腔内壁方向侧向膨胀的影响，相对于同轴圆环形RDC，爆轰波在凹腔基环形RDC中传播时具有更高的速度亏损；部分新鲜燃料与燃烧产物在凹腔内混合，提高了爆轰波波前反应物的温度；在相同进气条件下，同轴圆环形RDC以爆轰形式消耗的燃料占比更多。所得研究结果对RDC的结构设计和优化具有一定的指导意义。

关键词: 旋转爆轰流场, 环形燃烧室, 凹腔, 热释放速率, 传播特性

Abstract: The three-dimensional numerical simulation of C₂H₄/Air rotating detonation combustor (RDC) is carried out to study the influence of cavity on the rotating detonation flow field in annular combustor by solving Navier-Stokes equations in the framework of open source computational fluid dynamics software OpenFOAM. The main flow field features of annular and cavity-based annular RDCs are compared under the conditions of total inlet pressure of 0.6 MPa and total temperatures of 300 K, 600 K and 800 K, the influence of cavity on the propagation characteristics of rotating detonation wave is studied, and the proportions of fuel consumed at different heat release rates are quantitatively analyzed. The results show that, for the cavity-based annular RDC, a recirculation zone exists in the cavity, which leads to a slow flow velocity in the upstream of the cavity, but the flow rate significantly accelerates in the contraction section of the cavity. The surface average Mach number at the outlet of RDC is larger than that of the corresponding annular RDC. Due to the lateral expansion of fuel towards the outlet of RDC and the inner wall of cavity, the detonation wave propagating in the cavity-based annular RDC has a higher velocity deficit than that in the annular RDC. Part of the fresh fuel is mixed with the combustion products in the cavity, which increases the temperature of reactant in front of detonation wave. The ratio of fuel consumption under different heat release rates was compared, which shows that the annular RDC consumes more fuel in the form of detonation than the cavity-based annular RDC under the same injection conditions.

Key words: rotatingdetonationflowfield, annularcombustor, cavity, heatreleaserate, propagationcharacteristics

中图分类号:

V321.22

孟豪龙，翁春生，武郁文，郑权，肖强，王放，白桥栋. 环形燃烧室中凹腔对C₂H₄/Air旋转爆轰流场影响的数值模拟[J]. 兵工学报, 2022, 43(5): 1063-1074.

MENG Haolong, WENG Chunsheng, WU Yuwen, ZHENG Quan, XIAO Qiang, WANG Fang, BAI Qiaodong. Numerical Simulation of Cavity Influence on C₂H₄/Air Rotating Detonation Flow Field in Annular Combustor[J]. Acta Armamentarii, 2022, 43(5): 1063-1074.

参考文献

［1］ KAILASANATH K. Review of propulsion applications of detonation waves［J］. AIAA Journal, 2000, 38(9):1698-1708.
［2］ WOLAAN＇U2SKI P. Detonation propulsion［J］. Proceedings of the Combustion Institute, 2013, 34(1):125-158.
［3］ JIANG Z L, ZHANG Z J, LIU Y F, et al. The criteria for hypersonic airbreathing propulsion and its experimental verification［J］. Chinese Journal of Aeronautics, 2021, 34(3):94-104.
［4］ LU F K, BRAUN E M. Rotating detonation wave propulsion: experimental challenges, modeling, and engine concepts［J］. Journal of Propulsion and Power, 2014, 30(5):1125-1143.
［5］ WANG C, LIU W D, LIU S J, et al. Experimental verification of air-breathing continuous rotating detonation fueled by hydrogen［J］. International Journal of Hydrogen Energy, 2015, 40(30):9530-9538.
［6］ WEI W L, WU Y W, WENG C S, et al. Influence of propagation direction on operation performance of rotating detonation combustor with turbine guide vane［J］. Defence Technology, 2021，17（5）:1617-1624.
［7］ XIA Z J, TANG X M, LUAN M Y, et al. Numerical investigation of two-wave collision and wave structure evolution of rotating detonation engine with hollow combustor［J］. International Journal of Hydrogen Energy, 2018, 43(46):21582-21591.
［8］ XIA Z J, MA H, GE G Y, et al. Visual experimental investigation on stable operating process of the plane-radial rotating detonation engine［J］. Aerospace Science and Technology, 2021, 109:106430.
［9］ KINDRACKI J, WOLANSKI P, GUT Z. Experimental research on the rotating detonation in gaseous detonation in gaseous fuels-oxygen mixtures［J］. Shock Wave, 2011, 21(2):75-84.
［10］ KINDRACKI J. Experimental studies of kerosene injection into a model of a detonation chamber［J］. Journal of Power Technologies, 2012, 92(2):80-89.
［11］刘世杰, 刘卫东, 林志勇, 等. 连续旋转爆震波传播过程研究 (I)：同向传播模式［J］. 推进技术，2014，35(1):138-144.
LIU S J, LIU W D, LIN Z Y, et al. Research on continuous rotating detonation wave propagation process (I): one direction mode［J］. Journal of Propulsion Technology, 2014, 35(1):138-144. (in Chinese)
［12］刘世杰, 林志勇, 刘卫东, 等. 连续旋转爆震波传播过程研究 (II)：双波对撞传播模式［J］. 推进技术，2014，35(2):269-275.
LIU S J, LIU W D, LIN Z Y, et al. Research on continuous rotating detonation wave propagation process (II): two-wave collision propagation mode［J］. Journal of Propulsion Technology, 2014, 35(2):269-275.(in Chinese)
［13］ LIN W, ZHOU J, LIU S J, et al. Experimental study on propagation mode of H₂/air continuously rotating detonation wave［J］. International Journal of Hydrogen Energy, 2015, 40(30):1980-1993.
［14］ WANG Y H，WANG J P. Coexistence of detonation with deflagration in rotating detonation engines［J］. International Journal of Hydrogen Energy, 2016, 41(32):14302-14309.
［15］ WANG Y H，WANG J P. Effect of equivalence ratio on the velocity of rotating detonation［J］. International Journal of Hydrogen Energy, 2015, 40(25):7949-7955.
［16］ FABIAN C, MIRKO C. Study of parasitic combustion in an optically accessible continuous wave rotating detonation engine［C］∥Proceedings of AIAA SciTech Forum.San Diego, CA, US:AIAA, 2019.
［17］ PENG H Y, LIU W D, LIU S J, et al. The competitive relationship between detonation and deflagration in the inner cylinder-variable continuous rotating detonation combustor［J］. Aerospace Science and Technology, 2020, 107:106263.
［18］ ZHAO M J, MATTHEW J C, ZHANG H W. Combustion mode and wave multiplicity in rotating detonative combustion with separate reactant injection［J］. Combustion and Flame, 2021, 225: 291-304.
［19］ ZHENG Q, MENG H L, WENG C, et al. Experimental research on the instability propagation characteristics of liquid kerosene rotating detonation wave［J］. Defence Technology, 2020, 16(6): 1106-1115.
［20］李宝星, 王中, 许桂阳, 等. 煤油燃料旋转爆轰波起爆与传播特性实验研究［J］. 兵工学报, 2020, 40(7): 1340-1346.
LI B X, WANG Z, XU G Y, et al. Experimental research on initiation and propagation characteristics of kerosene fuel rotating detonation wave［J］. Acta Armamentarii, 2020, 40(7):1340-1346.(in Chinese)
［21］ WILHITE J, DRISCOLL R, GEORGE A S T, et al. Investigation of a rotating detonation engine using ethylene-air mixtures［C］∥Proceedings of the 54th AIAA Aerospace Sciences Meeting. San Diego, CA, US:AIAA, 2016.
［22］ GEORGE A S T, DRISCOLL R, ANAND V, et al. Fuel Blending as a Means to Achieve Initiation in a Rotating Detonation Engine［C］∥Proceedings of the 53rd AIAA Aerospace Sciences Meeting.Kissimmee,FL, US:AIAA, 2015.
［23］ PAL P, XU C, KUMAR G, et al. Large-eddy simulations and mode analysis of ethylene/air combustion in a non-premixed rotating detonation engine［C］∥ Proceedings of AIAA SciTech Forum.Orlando,FL, US:AIAA, 2020.
［24］马立坤, 李潮隆, 夏智勋, 等．带凹腔火焰稳定器的固体火箭超燃冲压发动机燃烧室试验研究［J］．推进技术, 2021, 42(2): 319-326.
MA L K, LI C L, XIA Z X, et al. Experimental investigation of solid rocket scramjet combustor with cavity flame holder［J］. Journal of Propulsion Technology, 2021, 42(2):319-326.(in Chinese)
［25］ CAI Z, SUN M, WANG Z, et al. Effect of cavity geometry on fuel transport and mixing processes in a scramjet combustor［J］. Aerospace Science and Technology, 2018, 80:309-314.
［26］ PENG H Y, LIU W D, LIU S J, et al. The effect of cavity on ethylene-air continuous rotating detonation in the annular combustor［J］. International Journal of Hydrogen Energy, 2019, 44(26):14032-14043.
［27］ PENG H Y, LIU W D, LIU S J, et al. Effects of cavity location on ethylene-air continuous rotating detonation in a cavity-based annular combustor［J］. Combustion Science and Technology, 2021, 193(16):2761-27822.
［28］ LIU S J, PENG H Y, LIU W D, et al. Effects of cavity depth on the ethylene-air continuous rotating detonation［J］. Acta Astronautica, 2020, 166:1-10.
［29］ LAPOINTE C, WIMER N T, GLUSMAN J F, et al. Efficient simulation of turbulent diffusion flames in OpenFOAM using adaptive mesh refinement［J］. Fire Safety Journal, 2020, 111:102934.
［30］ KURGANOV A, TADMOR E. New high-resolution central schemes for nonlinear conservation laws and convection-diffusion equations［J］. Journal of Computational Physics, 2000, 160(1): 241-282.
［31］ WESTBROOK C K, DRYER F L. Simplified reaction mechanisms for the oxidation of hydrocarbon fuels in flames［J］. Combustion Science and Technology, 1981, 27（1/2）:31-43.
［32］ COCKS P A, HOLLEY A T, RANKIN B A. High fidelity simulations of a non-premixed rotating detonation engine［C］∥Proceedings of the 54th AIAA Aerospace Sciences Meeting. San Diego, CA, US:AIAA, 2016.
［33］ ZHANG L F, MA J Z, ZHANG S J, et al. Three-dimensional numerical study on rotating detonation engines using reactive Navier-Stokes equations［J］. Aerospace Science and Technology, 2019, 93:105271.
［34］刘朋欣, 郭启龙, 赵炜, 等. 基于旋转爆震三维流场结构分析的计算模型对比研究［J］. 推进技术，2020, 41(12):2757-2765.
LIU P X, GUO Q L, ZHAO W, et al. Computational models based on analysis of three-dimensional flow field structures in rotating detonation［J］. Journal of Propulsion Technology, 2020, 41(12):2757-2765.(in Chinese)
［35］ LAWSON J, SHEPHERD J. Shock and detonation toolbox installation instructions［M］. Pasadena, CA，US：California Institute of Technology, 2020:1-8.
［36］ WILLIAMS F A. Chemical kinetic mechanism for combustion application ［M］. San Diego,CA, US: University of California at, 2014.
［37］ XU C, KONNOV A A. Validation and analysis of detailed kinetic models for ethylene combustion［J］. Energy, 2012, 43(1): 19-29.
［38］ XIAO Q, RADULESCU M I. Role of instability on the limits of laterally strained detonation waves［J］. Combustion and Flame, 2020, 220:410-428.
［39］ DAMAZO J, SHEPHERD J. Observations on the normal reflection of gaseous detonations［J］, Shock Waves, 2017, 27:795-810.
［40］ XIAO Q, SOW A, MAXWELL B, et al. Effect of boundary layer losses on 2D detonation cellular structures［J］. Proceedings of the Combustion Institute, 2021, 38(3):3641-3649.
［41］ GORDON S, MCBRIDE B J. Computer program for calculation of complex chemical equilibrium composition and applications［M］. Washington, DC, US:National Aeronautics and Space Administration, 1996.
［42］孟豪龙, 翁春生, 武郁文, 等. 基于OpenFOAM的三维H₂/Air连续旋转爆轰流场数值模拟［J］. 推进技术, 2020, 41(6): 1351-1360.
MENG H L, WENG C S, WU Y W, et al. Three-dimensional numerical simulation of H₂/air continuous rotating detonation flow field based on OpenFoam［J］. Journal of Propulsion Technology, 2020, 41(6):1351-1360.(in Chinese)
［43］ WANG F, WENG C S, WU Y W, et al. Effects of total pressure and equivalent ratio on kerosene/air rotating detonation engines using a paralleling CE/SE method［J］. Defence Technology, 2021,17(6): 1805-1816.
［44］杨鹏飞, 牟乾辉, 滕宏辉, 等. 旋转爆轰波中多波流动模式的数值研究［J］. 推进技术, 2019, 40(2): 398-406.
YANG P F, MOU Q H, TENG H Y, et al. Numerical investigation on multiple wave propagation mode of rotating detonation waves［J］. Journal of Propulsion Technology, 2019, 40(2):398-406. (in Chinese)
［45］ MA Z, ZHANG S J, LUAN M Y, et al. Experimental research on ignition, quenching, reinitiation and the stabilization process in rotating detonation engine［J］. International Journal of Hydrogen Energy, 2018, 43(39):18521-18529.
［46］周朱林, 刘卫东, 刘世杰, 等. 受侧向膨胀影响的爆震波传播过程研究［J］. 推进技术, 2013, 34(5):713-720.
ZHOU Z L, LIU W D, LIU S J, et al. Investigation on propagation process of detonation wave influenced by lateral expansion［J］. Journal of Propulsion Technology, 2013, 34(5):713-720.(in Chinese)
［47］ ORAN E S,GAMEZO V N.Origins of the deflagration-to-detonation transition in gas-phase combustion［J］.Combustion and Flame,2007, 148(1/2):4-47.

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环形燃烧室中凹腔对C₂H₄/Air旋转爆轰流场影响的数值模拟

Numerical Simulation of Cavity Influence on C₂H₄/Air Rotating Detonation Flow Field in Annular Combustor

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