Genetic Algorithm to Optimize the Design of Main Combustor and Gas Generator in Liquid Rocket Engines

作     者：Min Son Sangho Ko Jaye Koo 

作者机构：Graduate Student Korea Aerospace University School of Aerospace and Mechanical Engineering Korea Aerospace University 

出 版 物：《Journal of Thermal Science》 (热科学学报（英文版）)

年 卷 期：2014年第23卷第3期

页      面：259-268页

核心收录：

学科分类：0832[工学-食品科学与工程（可授工学、农学学位）] 080703[工学-动力机械及工程] 08[工学] 082502[工学-航空宇航推进理论与工程] 0807[工学-动力工程及工程热物理] 0805[工学-材料科学与工程（可授工学、理学学位）] 0825[工学-航空宇航科学与技术] 083204[工学-水产品加工及贮藏工程] 0702[理学-物理学] 

基　　金：supported by the National Research Foundation of Korea grant funded by the Korean Government(MSIP)NRF-2012M1A3A3A02033146 and NRF-2013M1A3A3A02042434 

主　　题：优化设计方法 液体火箭发动机 主燃烧室 遗传算法 气体发生器 气根 再生冷却 管壁温度 

摘      要：A genetic algorithm was used to develop optimal design methods for the regenerative cooled combustor and fuel-rich gas generator of a liquid rocket engine. For the combustor design, a chemical equilibrium analysis was applied, and the profile was calculated using Rao s method. One-dimensional heat transfer was assumed along the profile, and cooling channels were designed. For the gas-generator design, non-equilibrium properties were derived from a counterflow analysis, and a vaporization model for the fuel droplet was adopted to calculate residence time. Finally, a genetic algorithm was adopted to optimize the designs. The combustor and gas generator were optimally designed for 30-tonf, 75-tonf, and 150-tonf engines. The optimized combustors demonstrated superior design characteristics when compared with previous non-optimized results. Wall temperatures at the nozzle throat were optimized to satisfy the requirement of 800 K, and specific impulses were maximized. In addition, the target turbine power and a burned-gas temperature of 1000 K were obtained from the optimized gas-generator design.