连续式高焓超声速预混加热器设计与分析  

Design and analysis of continuous high-enthalpy supersonic premixed heater

作　　者：林志勇[1] 李大鹏[1] 周进[1] 黄玉辉[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《推进技术》2007年第6期616-619,共4页Journal of Propulsion Technology

基　　金：国家自然科学基金(10272111)

摘　　要：为研究超声速燃烧和爆轰相关的机理问题,提出了一种结合燃烧型加热器和阵列喷管的超声速预混加热器设计思想。通过预热燃烧室来提供总温可变的高焓富氧气流,经过特征线型面喷管膨胀降温后,在喷管扩张段的适当位置以一定角度喷入燃料,经过混合段后形成所需的连续高焓总温和当量比可调的预混气流。通过对混合过程的数值模拟和预混气体的着火延迟时间分析了当前的预混高焓加热器的混合和自燃问题。在超声速气流中加入斜劈采用纹影技术进行激波点火实验,并验证了当前的预混加热器设计是成功。A new method integrating the mirror nozzles into combustion heater is presented, aiming at experimental study for fundamental problem of supersonic combustion and detonation. The high-enthalpy fuel-lean flow with variable stagnation temperature is produced in preheated combustor, and fuel is injected into the flow with a special angle in the appropriate position where the temperature descends after expanding along the mirror nozzle. After the flow mixed in the mixing segment, the continuous supersonic premixed mixture with variable stagnation temperature and equivalence ratio is produced. Some preliminary numerical simulation and analysis are performed for the mixing process and ignition delay. Some shock-induced combustion wedge experiments with the high speed schlieren technology are conducted and the premixed heater is validated.

关 键 词：超声速燃烧 预混加热器设计^+ 点火延迟 激波诱导燃烧^+ 

分 类 号：V231.26[航空宇航科学与技术—航空宇航推进理论与工程]