Open AccessNumerical Investigation of an Integrated Ejector Nozzle with the Nozzle Pressure Ratio of 2.97
Author(s) -
Changjie Ge,
Lianghua Xiao,
Yinhui Shang
Publication year - 2021
Publication title -
journal of physics. conference series
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 0.21
H-Index - 85
eISSN - 1742-6596
pISSN - 1742-6588
DOI - 10.1088/1742-6596/1985/1/012022
Subject(s) - nozzle , injector , discharge coefficient , thrust , mass flow rate , radius , mass flow , mechanics , flow (mathematics) , materials science , expansion ratio , mechanical engineering , aerospace engineering , physics , engineering , computer science , composite material , computer security
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 D 2 /D 0 is not obvious but D 3 /D 0 has great effect, and the value of D 3 /D 0 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 D 2 /D 0 and D 3 /D 0 can restrain the flow separation between the primary flow and have inhibitory effect on the over-expansion of low nozzle pressure rate.