Numerical Simulation Study of Effects of Precooling on Flow Characteristics of Engine Inlets

被引：0
|
作者：
Xue L.-B. [1 ]
Sun B. [1 ]
Zhuo C.-F. [1 ]
Man Y.-J. [2 ]
Li H.-D. [2 ]
机构：
[1] School of Mechanical Engineering, Nanjing University of Science and Technology, Nanjing
[2] Beijing Power Machinery Institute, Beijing
来源：
Tuijin Jishu/Journal of Propulsion Technology | 2020年 / 41卷 / 06期
关键词：
Numerical simulation; Porous media; Precooling; Pressure drop; SABRE inlet; Source term;
D O I：
10.13675/j.cnki.tjjs.190368
中图分类号：
学科分类号：
摘要：
To study the precooling effect and flow field performance of synergetic air-breathing rocket engine (SABRE) inlet, the SABRE engine inlet without precooling under critical state of each working condition was adopted, and a numerical simulation study of the effects of precooling on the flow characteristics of inlet was carried out in combination with porous media coupling source term. The change of aerodynamic performance of inlet before and after precooling was compared, and the effect of airflow on inlet performance after precooling was explored. Studies indicate that porous media coupled source term method could commendably simulate the cooling effect and pressure drop effect of precooler and the terminal shock wave moves forward a distance after precooling. The total temperature of turbine channel outlet under each working condition decreases by 48%~77%, among which the total temperature at Ma2~4 reduces to around 210K. After precooling the incoming air, the exit Mach number of turbine channel is reduced, and its mass flow ratio also decreases accordingly. The inlet total pressure recovery coefficient tends to decrease, and it is better at low speed condition. The change of total pressure recovery coefficient of the two channels before and after precooling is not obvious. Mass flow ratio of turbine channel is approximately 15% lower than that without precooling. © 2020, Editorial Department of Journal of Propulsion Technology. All right reserved.
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页码：1227 / 1236
页数：9
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