液体火箭发动机层板式预燃室液氧发汗冷却热控制  

THERMAL CONTROL FOR PLATELET TRANSPIRATION COOLED PREBURNER OF LIQUID ROCKET ENGINE USING LIQUID OXYGEN

作　　者：刘伟强[1] 陈启智[1] 吴宝元[2] 

机构地区：[1]长沙国防科技大学航天技术系 [2]陕西动力机械设计研究所

出　　处：《推进技术》1998年第5期10-14,共5页Journal of Propulsion Technology

摘　　要：讨论了富氧预燃室液氧发汗冷却的分析计算方法。发汗流对燃气热流的阻隔分析采用Ｂａｒｔｌｅ－Ｌｅａｄｏｎ修正方法来完成，室壁温度分布和热穿透深度应用结构层板与发汗流存在温差的传热模型获得。讨论了发汗流压降和控制流道长度对预燃室壁温的控制作用。The study on thermal control of platelet transpiration cooling with liquid oxygen was made for preburner of liquid rocket engine.The analysis of heat transfer was performed by using the Bartle and Leadon correlation to determine the heat flux blockage for transpiration cooled wall.A heat transfer model for platelet and liquid oxygen in different temperatures was used to obtain the thermal penetration depth and the temperature profiles of the platelet and the coolant.The effects of the coolant pressure drop and the controlled channel length on the temperature of the preburner wall were discussed in detail.

关 键 词：液体火箭发动机 预燃室 发汗冷却 热控制 

分 类 号：V434.14[航空宇航科学与技术—航空宇航推进理论与工程]