带二次流增推尾喷管的脉冲爆震发动机数值模拟研究 -- 西北工业大学学报,2015,33(2):271-277
论文:2015,Vol:33,Issue(2):271-277
引用本文:
邱华, 龚婷婷, 熊姹, 郑龙席. 带二次流增推尾喷管的脉冲爆震发动机数值模拟研究[J]. 西北工业大学学报
Qiu Hua, Gong Tingting, Xion Cha, Zheng Longxi. Numerical Simulation of Pulse Detonation Engine(PDE) with Fluidic Nozzle[J]. Northwestern polytechnical university

带二次流增推尾喷管的脉冲爆震发动机数值模拟研究
邱华, 龚婷婷, 熊姹, 郑龙席
西北工业大学动力与能源学院, 中国西安 710072
摘要:
为提升现有脉冲爆震发动机增推喷管性能,对带二次流尾喷管发动机分别在定常流和爆震多循环过程进行了数值模拟,研究了二次流尾喷管的流场并计算了其推进性能。结果表明,定常流动中,随着主流压力的升高,注入二次流对尾喷管推进性能的提升幅度逐渐降低;当爆震室内压力很高时,二次流的瞬时流量会自动降低或者停止注入,当爆震室压力较低时,二次流流量又会自动恢复;单管注入二次流对PDE平均推力和平均单位推力的提升率分别达到2.63%和0.36%;双管注入二次流达到5.96%和0.75%。
关键词:    计算机模拟    有限体积法    流场    流量    射流装置    马赫数    网格生成    纳维斯托克斯方程    尾喷管    压力    脉冲爆震发动机    二次流    激波    定常流    温度    二维    湍流模型    二次流尾喷管    多循环爆震    落压比    单位推力   
Numerical Simulation of Pulse Detonation Engine(PDE) with Fluidic Nozzle
Qiu Hua, Gong Tingting, Xion Cha, Zheng Longxi
Department of Aero-Engines, Northwestern Polytechnical University, Xi'an 710072, China
Abstract:
In order to increase the nozzle's propulsion performance of PDE, numerical studies of fluidic nozzles have been carried out to study the flow field and the propulsion performance of fluidic nozzles in steady flow and during the cyclic operation. Simulation results and their analysis show preliminarily that:(1) in steady flow, with the use of secondary injection, when the core flow's pressure increases, the augmented ratio of the nozzle's propulsion performance will decrease; (2) when the detonation chamber's pressure is very high, the instantaneous flow rate of the secondary flow will dynamically reduce or stop injecting; (3) when the detonation chamber's pressure is low, the secondary flow will dynamically restore. The augmented ratio of average thrust and that of specific average thrust with single injector are respectively 2.63%, 0.36%, and 5.96%, 0.75% with dual injector.
Key words:    computer simulation    finite volume method    flow fields    flow rate    fluidic devices    Mach number    mesh generation    Navier Stokes equations    nozzles    pressure    pulse detonation engines    secondary flow    shock waves    steady flow    temperature    two dimensional    turbulence models    fluidic nozzle    multi-cycle detonation    NPR    specific average thrust   
收稿日期: 2014-09-23     修回日期:
DOI:
基金项目: 中央高校基本科研业务费专项资金(3102014JCY01003)与国家自然科学基金(50906072、51306154)资助
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作者简介: 邱华(1978-),西北工业大学副教授、博士,主要从事脉冲爆震发动机的应用基础研究。
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