TY - GEN
T1 - Performance estimation for fluidic thrust vectoring nozzle coupled with aero-engine
AU - Shi, Jing Wei
AU - Wang, Zhan Xue
AU - Zhang, Xiao Bo
AU - Zhou, Li
AU - Sun, Xiao Lin
N1 - Publisher Copyright:
© 2014 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
PY - 2014
Y1 - 2014
N2 - 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%.
AB - 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%.
UR - http://www.scopus.com/inward/record.url?scp=84913582660&partnerID=8YFLogxK
U2 - 10.2514/6.2014-3771
DO - 10.2514/6.2014-3771
M3 - 会议稿件
AN - SCOPUS:84913582660
T3 - 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014
BT - 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014
PB - American Institute of Aeronautics and Astronautics Inc.
T2 - 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and exhibit 2014
Y2 - 28 July 2014 through 30 July 2014
ER -