Performance estimation for fluidic thrust vectoring nozzle coupled with aero-engine

Shock vector controlling (SVC) nozzle has simpler working principle, lower weight, and quicker vector response, and is more suitable for exhausting system with high nozzle pressure ratio. In the paper, the working mechanism and flow characteristics of SVC nozzle, which based on transverse injection in confined space, were investigated by solving 3D RANS equations. Then the performance estimation model for SVC nozzle coupled with aeroengine was established by combining design of experiment (DOE), response surface methodology (RSM) and aero-engine simulation program based on component characters. In coupling model six aerodynamic and geometric parameters were involved in the model, e.g. nozzle pressure ratio, secondary pressure ratio, injection angle et. al. and different air extraction positions and mass ratio of secondary flow were taken into consideration. Results show that the interaction effects between different parameters are evident; air extraction from fan exit behaves better, and thrust vector angle of 19°is obtained at mass ratio of 0.15 with total thrust decrease of 17%.