论文部分内容阅读
为获得多阶声模态振荡共同作用下的压强耦合响应函数特性,考虑固体火箭发动机中多阶声模态振荡的非线性燃烧不稳定特点,在线性均质推进剂准稳态分析模型(QSHOD)的基础上,建立了二阶声模态作用下的非线性压强耦合响应模型,并对模型进行了理论分析和定性的实验验证。模型分析结果表明,基频振荡幅值对压强耦合响应函数特性影响较大;随着基频振荡幅值的增大,压强耦合响应函数由线性变为非线性,响应函数从单峰变成双峰,在高频区域形成非线性响应函数峰;在基频振荡的同时,二阶模态振荡使得响应函数的非线性特性更加显著,对非线性响应函数峰值影响较大。该模型结果与典型T型燃烧器实验结果基本相同。
In order to obtain the characteristics of pressure-coupled response function under multi-order acoustic mode oscillation, considering the characteristics of nonlinear combustion instability of multi-order acoustic mode oscillations in solid rocket motors, the quasi-steady-state analytical model of linear homogeneous propellant (QSHOD ), The nonlinear pressure-coupled response model under the second-order acoustic mode is established. The theoretical analysis and qualitative experimental verification of the model are also made. The results of the model analysis show that the amplitude of the fundamental frequency has a significant effect on the characteristics of the pressure-coupled response function. As the amplitude of the fundamental frequency increases, the pressure-coupled response function changes from linear to nonlinear and the response function changes from unimodal to bis Peak, forming a non-linear response function peak in the high-frequency region. At the same time of fundamental frequency oscillation, the second-order mode oscillation makes the nonlinearity of the response function more significant and greatly affects the non-linear response function peak. The results of this model are basically the same as those of a typical T burner.