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

Journal of Thermal Science 2014年第3期23卷 259-268页

作者： min.son.sangho ko Jaye koo Graduate Student Korea Aerospace University School of Aerospace and Mechanical Engineering Korea Aerospace University

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.

关键词： Liquid Rocket Engine Main Combustor Gas Generator Optimization Genetic Algorithm

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