Analysis of the Heat Transfer in Liquid Rocket Engine Cooling Channels

被引：5
|
作者：
Calvo, J. Bartolome [1 ]
Hannemann, K. [2 ]
机构：
[1] DLR, Inst Aerodynam & Flow Technol, Lilienthalpl 7, D-38114 Braunschweig, Germany
[2] DLR, Inst Aerodynam & Flow Technol, D-37073 Gottingen, Germany
来源：
NEW RESULTS IN NUMERICAL AND EXPERIMENTAL FLUID MECHANICS VII | 2010年 / 112卷
关键词：
FLUID-FLOW; OPTIMIZATION; NITROGEN; MODEL;
D O I：
10.1007/978-3-642-14243-7_54
中图分类号：
O29 [应用数学];
学科分类号：
070104 ;
摘要：
Simulations of supercritical nitrogen flow in cooling channels are compared with experimental results provided by EADS-Astrium Ottobrunn. The objective is to extend and validate the DLR-Tau code to compute and predict the heat transfer in cooling channels of liquid rocket engines. To simulate the flow accurately, the roughness of the surface, the thermophysical properties of the supercritical fluid, as well as the conduction in the structure are modeled.
引用
收藏
页码：441 / +
页数：3
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