Linear stability assessment of a cryogenic rocket engine
Linear stability assessment of a cryogenic rocket engine
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DOI：
10.1177/1756827717695281
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发表时间：
2017-05
影响因子：
1.6
通讯作者：
M. Schulze;T. Sattelmayer
中科院分区：
文献类型：
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作者：
M. Schulze;T. Sattelmayer
DLR低温H2/O2 BKD试验室的线性高频稳定性采用混合计算流体动力学/计算气动声学方法进行评估，该方法基于单火焰模拟，以产生足够的平均流量，并用于校准反馈模型以及频率空间变换线性化欧拉方程。应用含燃烧的实际平均流场解释了横向模态在空间上向近端板模态的分离，发现在一定的运行条件下，第一横向模态和尾部模态是线性不稳定的。轴向模态长度和特征频率受推进剂喷射规格的影响，从而决定性地影响压力和横向速度敏感的动态火焰响应。最后将稳定性评估程序应用于四种工况，并对第一横模的线性稳定性进行了预测。
The linear high frequency stability of DLR’s cryogenic H2/O2 BKD test chamber is assessed using a hybrid computational fluid dynamic/computational aeroacoustic methodology, which is based on single flame simulations for the generation of an adequate mean flow and for the calibration of feedback models as well as on frequency space transformed linearized Euler equations. The application of a realistic mean flow field including combustion explains the spatial separation of transverse modes into a near face plate mode, which is found linearly unstable under certain operation conditions for the first transverse and a rear part mode. The axial mode shape length as well as eigenfrequencies is affected by propellant injection specifications and, in consequence, decisively influence pressure and transverse velocity sensitive dynamic flame response. The stability assessment procedure is finally applied to four operation conditions and the linear stability is predicted for the first transverse mode.