飞行过载对燃烧室化学反应流场影响  

Reaction flow field change in SRM under high flight acceleration load

作　　者：武渊[1] 何国强[1] 乐发仁[2] 

机构地区：[1]西北工业大学航天工程学院,陕西西安710072 [2]中国航天科技集团公司第四研究院,陕西西安710025

出　　处：《推进技术》2007年第4期342-345,共4页Journal of Propulsion Technology

摘　　要：为了研究飞行过载对固体火箭发动机燃烧室化学反应流场影响,以Liang模型模化铝滴燃烧,以有限化学反应速率模型模化湍流燃烧,对过载条件下发动机内流场进行了数值分析,数值结果与试验结果取得了趋势上的一致。研究表明,文中采用的数值计算方法可有效重现发动机热结构故障点;飞行过载改变了流场温度、粒子浓度、化学反应速率等参数分布;过载条件下燃烧室绝热结构表面铝滴积聚及剧烈的化学放热反应是导致其异常烧蚀的原因之一,铝滴局部积聚燃烧会导致温度场畸变;热结构设计必须与流动结构匹配。For studying the chemical reaction flow field of the aluminized solid rocket under high flight acceleration, the numerical simulation based on aluminium particle combustion model and turbulent no-premixed combustion model was performed. Contrast to the numerical simulation result of no-flight load, the distribution of flow field parameters such as temperature, concentration and reaction rate are changed by flight acceleration. Some obtained numerical results were tested by examination. The results show that, the numerical arithmetic recur the test malfunction of the solid rocket. Aluminum particle accumulation and intense exothermic reaction induces the high temperature region and insulator abnormal erosion of combustor under high overload. Designing of thermo protected structure must match flow spectrum.

关 键 词：固体推进剂火箭发动机 过载飞行 铝粒子燃烧 烧蚀 流动分布 

分 类 号：V435.14[航空宇航科学与技术—航空宇航推进理论与工程]