Numerical investigations on direct contact condensation (DCC) of oxygen vapour in a staged combustion cycle based rocket engine

Numerical simulations are performed for 60%, 100% and 105% thrust conditions at the inlet duct to the main LOX pump in SCE-200, a staged combustion cycle based semi-cryogenic rocket engine, indigenously being developed in India. A two-fluid Eulerian multiphase model has been implemented for investigating the direct contact condensation of oxygen vapor jets in subcooled flowing liquid oxygen. For predicting the condensation effects, thermal phase change model has been applied with two resistance model to capture the heat transfer effects on the liquid and vapor side. The governing equations along with the constitutive relations are solved using the unsteady coupled solver available in the commercial CFD package ANSYS CFX®. Plume shapes and heat transfer coefficients are plotted for different thrust conditions for a time period of 50 ms and the results are analyzed.