Air Force Research Laboratory (AFMC)

14. ABSTRACT A new rocket engine design concept has been proposed that combusts a portion of the propellant flow in the nozzle section. This concept which is called Thrust Augmented Nozzle (TAN) allows for higher thrust at takeoff and a more optimum nozzle design that avoids flow separation at sea level conditions. The TAN injector is a cooled nozzle section downstream of the throat that injects propellants that combust and provides additional thrust. The TAN injector has similar design issues associated with conventional rocket engine injectors with the additional design challenge of combustion products flowing over the TAN injector. In order to demonstrate this new engine design concept, Aerojet designed, manufactured, and hot fire tested a subscale version of this engine. The thermal design process and results are presented herein. The derivation of gas side boundary conditions are based on test data and CFD analysis. The coolant side boundary conditions are based on conventional correlations for the propellants. Test data are also presented.