DETERMINATION OF THE FLOW FIELD IN THE PROPELLANT TANK OF A ROCKET ENGINE ON COMPLETION OF THE MISSION

In the present work, a method of mathematical simulation is employed to describe processes occurring in the specimens of new equipment and using the remaining propellant in rocket-engine tanks. Within the framework of certain turbulence models, the authors perform a calculation of the fl ow fi eld in the volume of the tank of the launch-vehicle stage when a hot gas jet is injected into it. A vortex fl ow structure is revealed; the characteristics of heat transfer for different angles of injection of the jet are determined. The obtained correlation Nu = Nu(Re) satisfactorily describes experimental data.
   
Author:  A. V. Fedorov, I. A. Bedarev, S. A. Lavruk, V. I. Trushlyakov, and V. Yu. Kudentsov
Keywords:  spent vehicle stages, physicomathematical simulation, heat transfer
Page:  324