高压补燃液体火箭发动机推力室冷却技术及结构优化  

Cooling Technology for Thrust Chamber of LM-5B LOX/kerosene Engine

作　　者：HOU Ruifeng LI Longfei LU Gang CHEN Jianhua 

机构地区：[1]Science and Technology on Liquid Rocket Engine Laboratory,Xi’an Aerospace Propulsion Institute,Xi’an 710100

出　　处：《Aerospace China》2023年第3期10-17,共8页中国航天（英文版）

摘　　要：The LM-5B launch vehicle has successfully completed four missions.Eight high-pressure staged combustion LOX/kerosene engines(YF-100)are equipped in the four boosters of the LM-5B,two in each booster.The YF-100 engine adopts various cooling techniques to ensure cooling,including a metal thermal barrier coating,multiple liquid film cooling slots,spiral milled regenerative cooling channels with high aspect ratio,a non-weld forming thrust chamber and an optimal cooling flow path design.In addition,the 480-ton LOX/kerosene engine for China’s future heavy-lift launch vehicle LM-9 will be larger in size,which makes it more difficult to be developed and will have more strict requirements in the cooling process.The main differences between the LM-5B and LM-5 are briefly described in this paper and the development process and working characteristics of YF-100 engines are introduced.The advantages and disadvantages of main cooling methods used in the thrust chambers of high-thrust liquid propellant engines are also described.Finally,the future challenges and countermeasures in cooling technology for China’s high-thrust LOX/kerosene engines and future reusable rocket engines are also presented.

关 键 词：LM-5B YF-100 staged combustion LOX/kerosene engine thrust chamber cooling technology 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]