Development of Preliminary Design Program for Combustor of Regenerative Cooled Liquid Rocket Engine

• Published in: Journal of thermal science 2011-10, Vol.20 (5), p.467-473
• Main Authors: Cho, Won Kook, Seol, Woo Seok, Son, Min, Seo, Min Kyo, Koo, Jaye
• Format: Article
• Language: English
• Subjects: Classical and Continuum Physics; Engineering Fluid Dynamics; Engineering Thermodynamics; Heat and Mass Transfer; Physics; Physics and Astronomy; 再生冷却; 压降计算; 发动机燃烧室; 液体火箭发动机; 燃烧室设计; 蓄热式燃烧器; 设计水平; 过冷
• ISSN: 1003-2169; 1993-033X
• DOI: 10.1007/s11630-011-0497-y

An integrated program was established to design a combustor for a liquid rocket engine and to analyze regenerative cooling results on a preliminary design level. Properties of burnt gas from a kerosene-LOx mixture in the combustor and rocket performance were calculated from CEA which is the code for the calculation of chemical equilibrium. The heat transfer of regenerative cooling was analyzed by using SUPERTRAPP code for coolant properties and by one-dimensional correlations of the heat transfer coefficient from the combustor liner to the coolant. Profiles of the combustors of F-1 and RS-27A engines were designed from similar input data and the present results were compared to actual data for validation. Finally, the combustors of 30 tonf class, 75 tonf class and 150 tonf class were designed from the required thrust, combustion chamber, exit pressure and mixture ratio of propellants. The wall temperature, heat flux and pressure drop were calculated for heat transfer analysis of regenerative cooling using the profiles.