摘要
引射火箭能够为火箭基组合循环(RBCC)发动机提供大推力,但是其喉部面临着极高的热载荷。本文提出使用冲击冷却的方式对引射火箭进行局部热防护,建立了射流冲击冷却的三维数值模型,研究了喉部曲率半径和冲击孔数量对冷却性能的影响,结果表明在设计半径R=(1~2)R_(t)范围内,R的取值对射流冲击换热无明显影响;靶面平均对流换热系数随冲击孔数量n的增大而减小,分布均匀程度随n先增大后减小,冲击孔数量n=6时换热效率最高。
Ejector rockets are capable of providing large thrust for rocket-based combined cycle(RBCC)engines,but face extremely high thermal loads at the throat.In this paper,the impingement cooling method is proposed to provide local thermal protection of the ejector rocket.A threedimensional numerical model of jet impingement cooling is established.The effects of throat radius and the number of impingement holes on the cooling performance are studied.The results show that in the range of design radius R=(12)Rt,the value of R has no obvious effect on jet impingement heat transfer.The average convective heat transfer coefficient of the target surface decreases with the increase of the number of impingement holes n,and the distribution uniformity increases first and then decreases with the increase of n.The heat transfer efficiency is the highest when the number of impingement holes n=6.
作者
万昊
李文强
秦飞
魏祥庚
袁彪
WAN Hao;LI Wen-Qiang;QIN Fei;WEI Xiang-Geng;YUAN Biao(Science and Technology on Combustion,Internal Flow and Thermo-structure Laboratory,School of Astronautics,Northwestern Poly technical University,Xifan 710072,China;China Gas Turbine Establishment,Chengdu 610500,China)
出处
《工程热物理学报》
EI
CAS
CSCD
北大核心
2021年第8期2141-2149,共9页
Journal of Engineering Thermophysics
基金
国家自然科学基金(No.51506180)。
关键词
冲击冷却
RBCC
引射火箭
数值模拟
impingement cooling
RBCC
ejector rocket
numerical simulation
