Numerical Investigation of an Integrated Ejector Nozzle with the Nozzle Pressure Ratio of 2.97

Abstract

The design of the integrated ejector nozzle system directly affects the secondary mass flow rate and the trust characteristics of the aero-engine. The numerical simulation was used to study the effects of longitudinal distance between engine nozzle exit and aircraft surface and radius of ejector nozzle exit on the performance of the integrated ejector nozzle system. Results indicates:(1) As NPRs increases, secondary mass flow rate and thrust coefficient of ejector nozzle system generally increase;(2) the effect of D2/D0 is not obvious but D3/D0 has great effect, and the value of D3/D0 designed between 1.1 and 1.25, which is beneficial to the secondary mass flow rate and thrust coefficient of ejector nozzle system;(3) the combination design of D2/D0 and D3/D0 can restrain the flow separation between the primary flow and have inhibitory effect on the over-expansion of low nozzle pressure rate.