Design and Stream Thrust Analysis of a Scramjet Engine for Acceleration Mission from 2 to 3 km/s
Design and Stream Thrust Analysis of a Scramjet Engine for Acceleration Mission from 2 to 3 km/s
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DOI：
10.2514/6.2013-120
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发表时间：
2013-01
期刊：
影响因子：
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通讯作者：
T. Rolim;F. Lu
中科院分区：
文献类型：
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作者：
T. Rolim;F. Lu
采用流推力分析方法，对某氢动力超燃冲压发动机在30公里高空、2~3公里/S加速飞行时的性能进行了初步评估。内置式二维超燃冲压发动机进气道采用轴向喷射与阶梯燃烧室相结合的方式。膨胀过程用准一维流动方程模拟。所有发动机的几何形状都被认为是作为轨迹的函数而变化的。定义了三种加速策略，一种使用恒定的化学计量燃料-空气混合物，另两种使用设置为0.2和0.5的参数。它们在整个加速过程中都产生了高比推力和高比冲。对于第一种情况，比推力随着飞行速度的增加而减小，而后两种情况则相反。比冲降低，在所研究的病例中没有发现明显的差异。总体效率遵循相同的行为。显然，所需的发动机几何形状更改在以下情况下更加突出
Stream thrust analysis was used for preliminary performance evaluation of a hydrogen powered scramjet engine on an acceleration mission from 2 to 3 km/s at 30 km altitude. An inward two-dimensional scramjet inlet was chosen along with an axial injection combined with step combustor. The expansion was modeled with quasi-one-dimensional flow equations. All of the engine geometry was considered variable as a function of the trajectory. Three acceleration strategies were defined, one with a constant stoichiometric fuel-air mixture , and other two with the parameter set as 0.2 and 0.5. All of them produced high specific thrust and high specific impulse throughout the acceleration. For the first case, the specific thrust decreased with flight velocity while the contrary was observed for the latter two cases. The specific impulse decreased and no significant difference was found in the cases studied. The overall efficiency followed this same behavior. The required engine geometry change was clearly more accentuated for the case of