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

被引:0
作者
Won Kook Cho [1 ]
Woo Seok Seol [1 ]
Min Son [2 ]
Min Kyo Seo [2 ]
Jaye Koo [3 ]
机构
[1] Korea Aerospace Research Institute,Daejoen,Republic of Korea
[2] Graduate Student,Korea Aerospace University,Goyang,Republic of Korea
[3] School of Aerospace and Mechanical Engineering,Korea Aerospace University,Goyang,Republic of Korea
关键词
Liquid rocket engine; Preliminary design of Combustor; Regenerative cooling;
D O I
暂无
中图分类号
V434 [液体推进剂火箭发动机];
学科分类号
080703 ; 082502 ;
摘要
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.
引用
收藏
页码:467 / 473
页数:7
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