Influence of curvature in regenerative cooling system of rocket engine

Abstract

Thermomechanical loads in rocket engines can be drastically reduced by a reliable cooling system. The regenerative cooling system uses propellants as coolant which flows through milled cooling channels in the chamber walls. Due to centrifugal forces, dynamic secondary motions appear in cooling-channel curvatures, which strongly modify heat transfer. Three-dimensional (3D) numerical calculations have been performed in order to compare this heat flux modification with empirical correlations. Different turbulence models and wall treatments have been tested to develop a complete numerical data base about asymmetrical (concave side) heat transfer in curved cooling channels of rocket engine.