Numerical simulation of HTPB combustion in a 2D hybrid slab combustor

Abstract

A code for the numerical simulation of combustion processes in hybrid rockets, developed at the Space Propulsion Laboratory of Politecnico di Milano (SPLab), is presented. The code deals with Navier–Stokes equations solved with RANS approach, blowing effect, combustion kinetics and radiation. The equations are closed with k–epsilon turbulence model and well stirred reactor model. The P1 model, a simplification of the PN radiation model, is adopted. Specific simulation tools were developed using OpenFOAM®open source technology. The computational domain is 2D and split in two subdomains, simulating the reacting gas mixture on one side and the solid fuel grain on the other. The interface between the two regions plays a key role as the solid grain pyrolysis comes from a straight solution of the model without shortcuts. A propellant combination with polybutadiene and gaseous oxygen has been chosen and a reduced kinetic model for combustion of butadiene, considered as the major gaseous constituent coming from polybutadiene pyrolysis, has been developed for reactions occurring in oxygen atmosphere. The computational domain tries to replicate the real experimental setup and is split into three areas: pre-chamber, slab zone and post-chamber. High speed camera visualizations of the combustion processes allow to compare the flame height, obtained by the code and by experimental tests, along the grain for given boundary conditions.