Experimental study on flow excursion instability of supercritical hydrocarbon fuel in scramjet regenerative cooling parallel channels  

作　　者：Xiaoyong LIU Zhuqiang YANG Ruipu MIAO Feng LIU Shujun ZHAO Qincheng BI 

机构地区：[1]Beijing Power Machinery Research Institute,Beijing 100074,China [2]Liaoning Key Laboratory of Complex Energy Conversion and Utilization,School of Energy and Power Engineering,Dalian University of Technology,Dalian 116024,China [3]State Key Laboratory of Multiphase Flow in Power Engineering,Xi’an Jiaotong University,Xi’an 710049,China

出　　处：《Chinese Journal of Aeronautics》2023年第1期201-215,共15页中国航空学报（英文版）

基　　金：co-supported by the Open Fund of Key Laboratory of Power Research of China(No.2017-Ⅲ-0005-0029);the National Natural Science Foundation of China(No.51776167).

摘　　要：Flow instability of supercritical hydrocarbon fuel is a crucial issue in scramjet regenerative cooling structure. In this study, flow excursion instability and flow distribution in parallel tubes were experimentally studied for supercritical fluids. Two types of flow excursion occur in a single tube. Type Ⅰ and Type Ⅱ excursions, and they are corresponding to decreasing and increasing flow rate respectively. They can trigger flow maldistribution between parallel tubes and the hysteresis phenomenon of flow distribution. The effects of system parameters, including inlet temperature,system pressure, and heat flux, on flow distribution were analyzed. In addition, the relationship between flow excursion and the pseudo-critical interval proposed in the literature was established according to the heated tube outlet temperature at the onset of flow instability. Finally, the flow excursion instability boundary was obtained using two dimensionless parameters. These experimental results can provide helpful insight on the mechanism of Scramjet regenerative cooling.

关 键 词：Flow distribution Ledinegg instability Onset of flow excursion Parallel channels Regenerative cooling SCRAMJET Supercritical flow 

分 类 号：V236[航空宇航科学与技术—航空宇航推进理论与工程]