ZURUECK HOCH VOR INHALT SUCHEN

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Proposing Institution

Lehrstuhl für Aerodynamik, TU München
Project Manager

Dipl.-Ing. (Univ.) Thomas Kaller
Boltzmannstr. 15
85748 Garching
Abstract
Current high performance space launchers use liquid combustion rocket engines for themain stage. These are fueled with liquid hydrogen and oxygen, which leads to extremelyhigh temperatures of up to 3600 K and heat fluxes of up to 160 MW/m 2 . To ensure safeoperating conditions and structural integrity of the launcher system an efficient coolingof the propulsion system is vital. For the structure cooling the cryogenic liquid propel-lants are used. It has been shown, that high aspect cooling channels (HARCC) provide asignificant increase in cooling effectiveness. With future rocket technologies focusing onoptimal weight systems, improving the cooling efficiency is one of the key factors. There-fore a deep understanding of the principles and mechanisms of turbulent heat transfer inHARCCs leading to a more precise prediction accuracy becomes increasingly significant.Within the collaborative research program ”Transregio 40” of the DFG one objective is2to develop high-fidelity numerical tools for an integrated interdisciplinary design process.For our studies we have developed a high-fidelity LES-code, which we will apply fora well-resolved simulation of a generic cooling duct using subcritical liquid water as acoolant. We want to validate our approach with the experimental investigation results,at the same time conducted by our project partners from the Institute of Fluid Mechanicsof TU Braunschweig.The three dimensional velocity field of high aspect ratio duct flows is characterized bythe existence of secondary flow structures, which cannot be represented by state of theart low-order turbulence models. Therefore we want to investigate in detail velocity fieldand secondary flow phenomena and their influence on turbulent heat transfer. The mainfocus lies on understanding the interaction of secondary flow structures and asymmetricwall heating at high Reynolds numbers.Finally, the results of this well-resolved simulation will serve as a high quality databasefor the development of wall-modelled LES (WMLES) of high aspect ratio cooling ductsunder realistic operating conditions of current launcher systems.

Impressum, Conny Wendler