脉冲爆震发动机模型机爆震室壁温分布试验研究  

Experimental Investigation on Outer Wall Temperature Distribution of a Pulse Detonation Engine Model

作　　者：郑龙席[1] 严传俊[1] 范玮[1] 张群[1] 黄希桥[1] 雷恒仁[1] 

机构地区：[1]西北工业大学航空动力与热力工程系,西安710072

出　　处：《燃烧科学与技术》2003年第4期344-347,共4页Journal of Combustion Science and Technology

基　　金：八六三"高技术基金资助项目(863 2 1 4).

摘　　要：利用TVS2000 MKⅡ热成像仪,在脉冲爆震发动机原理性试验模型上,对爆震燃烧室在多循环工作状态下的外壁面温度分布进行了实验研究.发现爆震室外壁面温度分布呈现从前到后逐渐升高的趋势,距推力壁近的区域上升斜率大,距推力壁远的区域上升斜率趋缓,并在爆燃转变为爆震后的区域内温度梯度较小.壁温分布热平衡时间随爆震频率的升高而减小,且基本上呈线性关系.同一轴向位置处,壁温随爆震频率的升高而升高,并呈线性关系.同一爆震频率下,不同轴向位置处,壁温随时间的变化规律基本相同.Experimental investigation on detonation combustion chamber outer wall temperature distribution of a pulse detonation engine model was carried out by using TVS2000-MK II thermal video system. It is found that from the thrust wall of the detonation chamber, the outer wall temperature is increasing along the axial direction and the increasing slope is decreasing. On the whole, the increasing speed is faster in the zone near the thrust wall than in the zone far from the thrust wall and the temperature slope decreases in the zone where deflagration transformed to detonation. The thermal equilibrium time of wall temperature decreases linearly with the detonation frequency increasing. At the same axial location, wall temperature increases linearly as the engine frequency increases. At the same detonation frequency, the temperature variation trends of different axial locations on detonation chamber wall are almost the same.

关 键 词：脉冲爆震发动机 多循环 爆震燃烧室 温度分布 热成像仪 

分 类 号：V231.22[航空宇航科学与技术—航空宇航推进理论与工程]