典型结构的层板发汗冷却推力室传热特性的推算方法  

CALCULATION METHOD OF HEAT TRANSFER IN PLATELET TRANSPIRATION COOLED THRUST WITH TYPICAL STRUCTURE

作　　者：刘伟强[1] 陈启智[1] 吴宝元[2] 

机构地区：[1]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6期15-19,共5页Journal of Propulsion Technology

摘　　要：针对典型的层板发汗冷却结构，提出了利用一个推力室的实验数据来计算另一推力室所需发汗流强的方法。在一种发动机推力室壁面发汗冷却实验数据测出以后，对同一发动机或另一发动机推力室壁采用不同的冷却剂、不同的壁面材料时的受热壁面工作温度与发汗流强的关系，由迭代计算完成。作为分析实例，利用氦气发汗冷却的试验数据对氢气发汗冷却流强进行了计算，其结果得到了实验的验证。A new calculation method was proposed for the typical structure of the platelet transpiration flux in the rocket thrust chamber based on the test data of another chamber.When the test data were obtained for one thrust chamber,the relationship between the temperature and the coolant flow rate on the hot surface for one thrust chamber or another using different platelet materials and different coolant can be got with iteration solution.The calculation for a thrust chamber using GH 2 as coolant was performed based on the test data using He as coolant.The results obtained were verified with test data

关 键 词：液体火箭发动机 发汗冷却 传热 数值计算 推力室 

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]