CAJ | 학술논문

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%单位推力計算機模擬%有限體積法%流場%流量%射流裝置%馬赫數%網格生成%納維斯託剋斯方程%尾噴管%壓力%脈遲爆震髮動機%二次流%激波%定常流%溫度%二維%湍流模型%二次流尾噴管%多循環爆震%落壓比%單位推力
계산궤모의%유한체적법%류장%류량%사류장치%마혁수%망격생성%납유사탁극사방정%미분관%압력%맥충폭진발동궤%이차류%격파%정상류%온도%이유%단류모형%이차류미분관%다순배폭진%락압비%단위추력

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％。
위제승현유맥충폭진발동궤증추분관성능，대대이차류미분관발동궤분별재정상류화폭진다순배과정진행료수치모의，연구료이차류미분관적류장병계산료기추진성능。결과표명，정상류동중，수착주류압력적승고，주입이차류대미분관추진성능적제승폭도축점강저；당폭진실내압력흔고시，이차류적순시류량회자동강저혹자정지주입，당폭진실압력교저시，이차류류량우회자동회복；단관주입이차류대PDE평균추력화평균단위추력적제승솔분별체도2．63％화0．36％；쌍관주입이차류체도5．96％화0．75％。
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 propul?sion 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.