FLUENT MODELLING OF COMBUSTION IN A DUCTED ROCKET英文电子书.pdfVIP

FLUENT MODELLING OF COMBUSTION IN A DUCTED ROCKET R.A. Stowe Defence RD Canada – Valcartier A. deChamplain, Department of Mechanical Engineering, Université Laval, Canada OUTLINE • Introduction • Combustor configurations • Direct-connect combustion tests • CFD modelling • Boundary conditions • Two phase flow • Results – Effect of twostream model on temperatures – Comparison of modelling and experiments – Time-dependency • Conclusions Defence RD Canada – Valcartier INTRODUCTION • solid propellant rocket motors around for hundreds of years, evolved into highly reliable and powerful systems • simpler than liquid fuel rockets – performance improvement limited since oxidizer onboard • up to 88% by mass of the propellant • how do we drastically improve the performance but maintain the simplicity? • use an airbreathing system: solid fuel ducted rocket – also called a ramrocket or integral rocket ramjet – increased range, higher average speed than solid rocket Defence RD Canada – Valcartier SOLID FUEL DUCTED ROCKET • not as widely used as other airbreathing propulsion systems – gas turbines, liquid fuel ramjets – but less complex (no pumps, compressors, etc.) – uses a gas generator to provide “fuel” for the ramjet combustor Defence RD Canada – Valcartier OPERATION OF A DUCTED ROCKET • Ducted rocket launched Defence RD Canada – Valcartier OPERATION OF A DUCTED ROCKET • Ducted rocket launched • Booster ignites, accelerates to Mach 1.2-1.4 Defenc