مدلسازي عددي فرايند احتراق HTPB/O2 در يك موتور موشك هيبريدي به منظور تعيين نرخ پسروي سطح سوخت جامد

Numerical Modeling of HTPB/02 Combustion Process in a Hybrid Rocket Motor to Determine Solid Fuel Surface Regression Rate

In this study, a two-dimensional, planar, numerical solution has been used to model the chemically reactive viscous flow in hybrid rocket motors for the purpose of determining the e solid fuel regression rate. The solution employs an implicit finite-volume, lower-upper Steger-Warming scheme (LU-SW) based on Van Leerʹs flux vector splitting method together with MUSCL technique, which includes minmod flux-limiter function. In agreement with other experimental studies, C4H6 species is considered as the main gaseous product of HTPB pyrolysis. The rate of pyrolysis is described by means of an Arrhenius-type relationship. In the present work, the chemical reactions between Oxygen and C4H6 are presented through an 11-species and 20-Step chemistry model. Also, turbulence is simulated using the Baldwin-Lomax algebraic eddy viscosity model. The characteristics of reactive flow in port and nozzle such as temperature distribution, Mach number, regression rate and surface temperature are calculated. Numerical simulation of a lab scale motor firing is presented, whereby comparison with other computational and experimental data shows good agreement between the predicted and measured regression rate.