LIQUID PROPELLANT ROCKET ENGINE WITH AFTERBURNER COMBUSTOR

摘要

A liquid propellant rocket engine includes a combustion chamber that has a throat. A nozzle diverges from the throat. The nozzle includes an afterburner combustor section that has a fuel injector orifice. A gas generator includes an exhaust duct and there is at least one turbine that has a turbine inlet and a turbine outlet. The turbine inlet is fluidly coupled with the exhaust duct, and a turbine outlet is fluidly coupled with the fuel injector orifice.