火箭推进

为获得来流速度条件对RBCC发动机引射特性的影响,采用数值模拟方法研究了支板式RBCC构型在亚声速范围的引射流场特性。结果表明:有/无速度条件的引射过程均存在两个阶段,即反压影响阶段和自维持阶段,在自维持阶段,内流道存在全为超声速的截面,环境压力不会对二次流流量产生影响; 当处于反压影响阶段,由于环境压力不同,不同速度条件的内流场存在差异,二次流流量也存在差别,随马赫数增加,RBCC所引射的空气流量增加; 当处于自维持阶段时,不同速度条件的内流场十分相似,二次流流量也基本相同,说明二次流总温、总压相同时,马赫数对引射过程没有影响,有速度条件的引射过程可以等效为相同总温、总压的零速引射过程,这为有速度条件的二次流流量评估以及试验来流参数配置提供了便利。

In order to obtain the influence of the speed condition on the ejecting process of a RBCC(rocket based combined cycle)engine, numerical simulation was performed to investigate the ejector mode of a strut-based RBCC model at subsonic speed.The results show that the operation regimes contains two stages under the investigated speed conditions are back pressure dominating stage and self-sustaining stage.At self-sustaining stage, due to the existence of all-supersonic flow, the ambient pressure can not influence the ejecting process.When working at back pressure dominating stage, due to the different ambient pressure(the total pressure is the same), the internal flow pattern and the mass flow rate of the secondary flow are different at different Mach number; while instead, the internal flow pattern and the mass flow rate of the secondary flow are almost the same at self-sustaining stage, which further shows the parameters of the secondary flow that determine the ejection process are the total pressure and temperature, irrelevant to Mach number.So, the ejection process at some speed condition can be equivalent to the ejection process at zero speed provided that their total pressure and temperature are the same, which provides the convenience for the assessment of the mass flow rate of the secondary flow at subsonic speed and the preparation for flow condition of wind tunnel test.

引言
1 研究对象及研究方法
2 引射流场特性
3 二次流流量特性
4 结论

图1 RBCC全流道构型<br/>Fig.1 Sketch of the whole RBCC flow path

图1 RBCC全流道构型
Fig.1 Sketch of the whole RBCC flow path

图2 计算和试验的壁面压力分布比较<br/>Fig.2 Comparison of the pressure curve between numerical calculation and test

图2 计算和试验的壁面压力分布比较
Fig.2 Comparison of the pressure curve between numerical calculation and test

图3 不同网格密度下的壁面压力分布<br/>Fig.3 Pressure distribution of different mesh

图3 不同网格密度下的壁面压力分布
Fig.3 Pressure distribution of different mesh

图4 边界条件设置及网格<br/>Fig.4 The solution domain and mesh

图4 边界条件设置及网格
Fig.4 The solution domain and mesh

$表1 火箭射流组分及其质量分数<br/>Tab.1 Components of rocketjet and mass fraction$

表1 火箭射流组分及其质量分数
Tab.1 Components of rocketjet and mass fraction

表2 火箭喷管入口气流参数<br/>Tab.2 Flow parameters at rocket nozzle inlet

表2 火箭喷管入口气流参数
Tab.2 Flow parameters at rocket nozzle inlet

图5 不同火箭流量下的马赫数云图(Ma=0)<br/>Fig.5 The Mach contours varied with rocket mass flow rate when(Ma=0)

图5 不同火箭流量下的马赫数云图(Ma=0)
Fig.5 The Mach contours varied with rocket mass flow rate when(Ma=0)

$图6 不同火箭流量下的CO的摩尔分数云图(Ma=0)<br/>Fig.6 The mole fraction contours of CO varied with rocket mass flow rate when(Ma=0)$

图6 不同火箭流量下的CO的摩尔分数云图(Ma=0)
Fig.6 The mole fraction contours of CO varied with rocket mass flow rate when(Ma=0)

表3 远场气流参数<br/>Tab.3 Flow parameters at far-field inlet

表3 远场气流参数
Tab.3 Flow parameters at far-field inlet

图7 Ma=0.2不同火箭流量下的马赫数云图<br/>Fig.7 The Mach contours varied with rocket mass flow rate when Ma=0.2

图7 Ma=0.2不同火箭流量下的马赫数云图
Fig.7 The Mach contours varied with rocket mass flow rate when Ma=0.2

图8 Ma=0.4不同火箭流量下的马赫数云图<br/>Fig.8 The Mach contours varied with rocket mass flow rate when Ma=0.4

图8 Ma=0.4不同火箭流量下的马赫数云图
Fig.8 The Mach contours varied with rocket mass flow rate when Ma=0.4

图9 Ma=0.6不同火箭流量下的马赫数云图<br/>Fig.9 The Mach contours varied with rocket mass flow rate when Ma=0.6

图9 Ma=0.6不同火箭流量下的马赫数云图
Fig.9 The Mach contours varied with rocket mass flow rate when Ma=0.6

图10 Ma=0.8不同火箭流量下的马赫数云图<br/>Fig.10 The Mach contours varied with rocket mass flow rate when Ma=0.8

图10 Ma=0.8不同火箭流量下的马赫数云图
Fig.10 The Mach contours varied with rocket mass flow rate when Ma=0.8

图11 处于不同阶段的火箭射流流量随马赫数变化<br/>Fig.11 The rocket mass flow rate at some stage varied with Mach number

图11 处于不同阶段的火箭射流流量随马赫数变化
Fig.11 The rocket mass flow rate at some stage varied with Mach number

图12 不同马赫数下的气流参数随火箭流量变化<br/>Fig.12 The flow parameters varied with rocket mass flow rate at different Mach number

图12 不同马赫数下的气流参数随火箭流量变化
Fig.12 The flow parameters varied with rocket mass flow rate at different Mach number

图13 一次流喷管参数<br/>Fig.13 The parameters of primary nozzle

图13 一次流喷管参数
Fig.13 The parameters of primary nozzle

图14 不同马赫数下的二次流流量及引射比随火箭流量变化(喷管膨胀比增加至10)<br/>Fig.14 The mass flow rate of secondary flow and ejecting ratio varied with rocket mass flow rate at different Mach number(the area ratio of the nozzle increased to 10)

图14 不同马赫数下的二次流流量及引射比随火箭流量变化(喷管膨胀比增加至10)
Fig.14 The mass flow rate of secondary flow and ejecting ratio varied with rocket mass flow rate at different Mach number(the area ratio of the nozzle increased to 10)

图15 设定出口反压计算域的网格及边界条件设置<br/>Fig.15 The mesh and boundary conditions of the solution domain when setting outlet back-pressure

图15 设定出口反压计算域的网格及边界条件设置
Fig.15 The mesh and boundary conditions of the solution domain when setting outlet back-pressure

表4 不同出口背压的二次流流量<br/>Tab.4 Mass flow rate of the secondary flow at different outlet pressure

表4 不同出口背压的二次流流量
Tab.4 Mass flow rate of the secondary flow at different outlet pressure

图16 不同马赫数下的二次流量流量及相对差值<br/>Fig.16 The mass flow rate and relative deviation value of the secondary flow at different Mach number

图16 不同马赫数下的二次流量流量及相对差值
Fig.16 The mass flow rate and relative deviation value of the secondary flow at different Mach number

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备注

引言

1 研究对象及研究方法

2 引射流场特性

3 二次流流量特性

4 结论

期刊信息