The objectives of this paper are to develop a multidisciplinary, computational methodology to predict the hot-gas-side and coolant-side heat transfer, and to use it in parametric studies to recommended optimized design of the coolant channels for a regeneratively cooled liquid rockets engine combustor. An integrated numerical model which incorporates computational fluid dynamics (CFD) for the hot-gas thermal environment, and thermal analysis for the liner and coolant channels, was developed. This integrated CFD/thermal model was validated by comparing predicted heat fluxes with those of hot-firing test and industrial design methods for a 40 k calorimeter thrust chamber and the Space Shuttle Main Engine (SSME) Main Combustion Chamber (MCC). Parametric studies were performed for the advanced Main Combustion Chamber (AMMCC) to find a strategy for a proposed combustion chamber coolant channel design.
Numerical analysis of the hot-gas-side and coolant-side heat transfer in liquid rocket engine combustors
Numerische Untersuchung des Wärmetransports im Heißgas-seitigem und kühlseitigem Bereich der Brennkammer im Flüssigkeitsraketenantrieb
AIAA-Papers ; 1-11
1992
11 Seiten, 12 Bilder, 3 Tabellen, 20 Quellen
Aufsatz (Konferenz)
Englisch