Investigation on propagation characteristics of rotating detonation wave in a radial-flow turbine engine combustor model
Investigation on propagation characteristics of rotating detonation wave in a radial-flow turbine engine combustor model
复制标题
径流式涡轮发动机燃烧室模型中旋转爆震波传播特性研究
DOI：
10.1016/j.actaastro.2019.04.022
复制
发表时间：
2019-07
影响因子：
3.5
通讯作者：
Zhou Changsheng
中科院分区：
文献类型：
--
作者：
Zhou Shengbing;Ma Hu;Yang Yuchen;Zhou Changsheng
本文研究了旋转爆震波在径向流涡轮机燃烧室模型中的传播特性。旋转爆轰燃烧室采用内径94 mm、外径106 mm的环形燃烧室，氢气和空气分别喷入燃烧室。分析了燃烧室出口有无导流片时爆轰波传播的稳定性。导叶试验的爆轰波速度比无导叶试验的爆轰波速度高，导叶对振荡压力有显着影响。对于无导流片的实验，在所有当量比下均得到爆轰波的两波碰撞模式，且存在碰撞点位移的不稳定现象。对于导叶试验，随着当量比的增大，爆轰波逐渐稳定，然后稳定性逐渐减弱。当当量比大于1时，出现低频压力波动现象，波动频率小于400 Hz。
In this experiment, the propagation characteristics of rotating detonation waves in a radial-flow turbine engine combustor model were investigated. An annular combustor, with an inner diameter of 94 mm and an outer diameter of 106 mm was used as the rotating detonation combustor, and the H2and air were separately injected into the combustor. The stability of the detonation wave propagation with and without a guide vane at the exit of the combustor was analyzed. The velocity of the detonation wave for the guide vane tests is higher than that of no guide vane tests, and the guide vane has a significant effect on the oscillating pressure. For the no guide vane tests, only the two-wave collision mode of detonation wave is obtained for all the equivalence ratios, and there is an unstable phenomenon of the collision point displacement. For the guide vane tests, the detonation-wave gradually stabilizes with the increase of the equivalence ratio, and then the stability gradually weakens. The phenomenon of the low-frequency pressure fluctuation occurs with the equivalence ratio larger than 1, and the fluctuation frequency is lower than 400 Hz.
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