Abstract：A numerical simulation method based on finite element is proposed for the active cooling research of liquid rocket engine. The method includes numerical simulation of atomization combustion and fluidsolid coupling and mechanical analysis of the cooling structure. The paper takes a watercooling gasoxygen/kerosene rocket engine thrust chamber as an example to study its inner flow field and the temperature of chamber wall. The cooling structure of thrust chamber adopts copper alloy lining and stainless steel housing. The analysis shows that this cooling structure has sufficient structural strength and the internal temperature of chamber wall is controlled within 600K.The method proposed in this paper is validated by calculation and can be widely used in active cooling research of liquid rocket engine.
安国琛, 李仁俊, 臧月进, 李凌黎. 基于有限元方法的液体火箭发动机主动冷却技术研究[J]. 空天防御, 2018, 1(3): 56-60.
An Guochen, Li Renjun, Zang Yuejin, Li Lingli. Active Cooling Technology of Liquid Rocket Engine Based on Finite Element. Air & Space Defense, 2018, 1(3): 56-60.
