Ueta Riko, Gotoda Hiroshi, Okamoto Hirotaka, Kawano Kazuki, Shoji Takeshi, Yoshida Seiji
Department of Mechanical Engineering, <a href="https://ror.org/05sj3n476">Tokyo University of Science</a>, 6-3-1 Niijuku, Katsushika-ku, Tokyo 125-8585, Japan.
<a href="https://ror.org/059yhyy33">Japan Aerospace Exploration Agency</a>, 7-44-1 Jindaiji-Higashimachi, Chofu-shi, Tokyo 182-8522, Japan.
Phys Rev E. 2024 Jul;110(1-1):014202. doi: 10.1103/PhysRevE.110.014202.
We experimentally clarify the interaction of acoustic pressure and heat release rate fluctuations during a transition to high-frequency combustion instability in a model rocket engine combustor. The dynamical state of acoustic pressure fluctuations undergoes a transition from high-dimensional chaotic oscillations to strongly correlated limit cycle oscillations. The coherent structure in the heat release rate field emerges with the initiation of weakly correlated limit cycle oscillations. The effect of the heat release rate on acoustic pressure fluctuations predominates during high-dimensional chaotic oscillations. In contrast, the effect of acoustic pressure on the heat release rate fluctuations markedly increases during the correlated limit cycle oscillations. These are reasonably shown by an ordinal pattern-based analysis involving the concepts of information theory, synchronization, and complex networks.
我们通过实验阐明了在模型火箭发动机燃烧室向高频燃烧不稳定性转变过程中声压与热释放率波动之间的相互作用。声压波动的动态状态经历了从高维混沌振荡到强相关极限环振荡的转变。热释放率场中的相干结构随着弱相关极限环振荡的开始而出现。在高维混沌振荡期间，热释放率对声压波动的影响占主导地位。相比之下，在相关极限环振荡期间，声压对热释放率波动的影响显著增加。这些通过基于有序模式的分析得到了合理的证明，该分析涉及信息论、同步和复杂网络的概念。
