Experimental of combustion instability in NTO/MMH impinging combustion chambers  

作　　者：Anlong YANG Bin LI Yu YAN Shuaijie XUE Lixin ZHOU 

机构地区：[1]Science and Technology on Liquid Rocket Engine Laboratory,Xi’an Aerospace Propulsion Institute,Xi’an 710100,China

出　　处：《Chinese Journal of Aeronautics》2020年第5期1476-1485,共10页中国航空学报（英文版）

基　　金：co-supported by the National Natural Science Foundation of China (Nos. 11502186 and 51506157);the National Key Basic Research Program of China

摘　　要：This paper presents an experimental study into dynamics of chamber pressure and heat release rate during self-excited spinning and standing azimuthal mode in NTO/MMH (nitrogen tetroxide/monomethylhydrazine) impinging combustion chambers.Nine cases including two combustion chamber configurations were conducted.The operating conditions of all unstable cases were located in the instability region according to Hewitt empirical correlation.The results show that chamber pressure oscillations keep pace with the corresponding OH*chemiluminescence intensity over the whole combustion region in the spinning and standing modes.It is indicated that the Rayleigh index is positive over the whole combustion area in all the unstable cases.A significant supersonic flame front structure of the first-order spinning mode was found in a cylindrical chamber,which means that a detonation wave could exist in the cylindrical chamber without a center body.The pressure and heat release rate oscillations at the pressure node are nonnegligible although their amplitudes are lower than those at the pressure antinode in the first-order standing mode with an annular chamber.Besides,the dominant frequency of pressure and heat release rate oscillations at the pressure node is twice as high as that at the pressure antinode.

关 键 词：ATOMIZATION Combustion stability Impinging jet injector Klystron effect Liquid rocket engine 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]