燃烧室非线性压力振荡及其产生机理研究  

Study on nonlinear pressure oscillation and its mechanism in combustion chamber

作　　者：汪广旭 付秀文[1] 石晓波[1] 刘占一[1] 杨建文[1] 

机构地区：[1]西安航天动力研究所,陕西西安710100

出　　处：《火箭推进》2016年第2期29-34,58,共7页Journal of Rocket Propulsion

基　　金：航天支撑技术项目(617010423)

摘　　要：当燃烧不稳定现象发生时,燃烧室内部往往伴随有较大幅值的压力振荡,其表现形式是非线性的。为了加深对其产生机理的认识,在能量平衡方法的基础上,通过求解包含高阶非线性项的各阶能量平衡方程,模拟了燃烧室非线性压力振荡曲线,给出了不稳定状态下,燃烧室压力的陡峭化过程以及各阶模态的"极限环"幅值分布。在此基础上,进一步对初始线性增长率α以及非线性效应对"极限环"幅值的影响规律进行了参数化研究,获得相应的分布规律曲线。最后,作为验证,对不同稳定工况下的"爆炸弹"压力振荡过程进行了数值模拟。研究表明,不稳定燃烧过程中,各阶模态之间存在相互作用,且随着α的增加,"极限环"幅值呈线性递增趋势,而非线性效应对"极限环"幅值的影响规律则相反。此外,"爆炸弹"数值实验表明,在进一步完善非线性项后,能量平衡方法具有模拟非线性燃烧不稳定现象的潜力。When the combustion instable phenomenon happens, the high amplitude pressure oscillation often occurs simultaneously in combustion chamber, which behaves in nonlinear form. In order to make it more clear about the mechanism of production, the nonlinear oscillating .curve for chamber pressure was simulated based on the energy balance method through solving the energy equations including high-order nonlinear term of each mode. The pressure steepening process and the distribution of ＂limited cycle＂ amplitudes in the unstable status are also presented. Based on this, the parameterized study is conducted on the influence of initial linear growth rate a and the nonlinear effect on ＂limited cycle＂ amplitude, and the corresponding distribution curves are also showed in this paper.Then, as a validation, the pressure oscillating process of ＂bomb＂ under different stable conditions are simulated as well. It indicates that during the unbalanced combustion, interactive effects exist between the oscillating modes. Although ＂limited cycle＂ amplitude assumes progressive increase tendency with the increase of ot the nonlinear effect on ＂limited cycle＂ amplitude has the opposite tendency. Except for this, the numerical experiment results show that if the nonlinear term can be further perfect properly, the energy balance method can be applied to the simulation of nonlinear combustion instable.

关 键 词：燃烧不稳定现象 非线性压力振荡 能量平衡方法 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]