层板发汗冷却推力室传热分析  

Heat transfer analysis of platelet transpiration cooling thrust chamber

作　　者：黄春桃[1] 孙冰[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《火箭推进》2011年第1期17-21,39,共6页Journal of Rocket Propulsion

摘　　要：对于采用层板发汗冷却的推力室,为了最大限度地减少冷却剂流量,理想情况是,应根据不同轴向位置的受热情况来分配冷却剂流量,以使各处的壁面温度都控制在材料的许用温度内。本文运用有限体积法,对层板发汗冷却推力室内的燃气流动和壁面内的传热进行了数值模拟,同时通过调节冷却剂吹风比,使各处的壁面温度都控制在材料的许用温度之内。为综合考虑发汗冷却效果,将发汗冷却的两个方面,即推力室壁面内的传热和发汗流对传热的阻隔进行了耦合求解。数值研究结果表明:推力室内壁温度越低,所需的冷却剂的吹风比越大。For a platelet transpiration cooled thrust chamber,in order to achieve the maximum reduction of the coolant flow rate,the ideal means is to distribute the coolant according to different axial heating positions to keep overall wall temperature under material permissible limit.The numerical simulation for the internal gas flow and wall heat transfer in a platelet transpiration cooled thrust chamber were performed by using finite volume method.The two aspects of transpiration cooling,the heat transfer in the wall and the obstructing effect of blowing ratio on the surface temperature,were solved in a coupled solution to consider the transpiration cooling effect synthetically.The numerical results show that blowing ratio increases with the decrease of the wall temperature.

关 键 词：层板推力室 发汗冷却 耦合传热 数值模拟 

分 类 号：V434-34[航空宇航科学与技术—航空宇航推进理论与工程]