TY - GEN
T1 - Investigation on fluidic throat control of fixed geometric nozzle and coupling performance with aero-engine
AU - Wang, Z. X.
AU - Shi, J. W.
AU - Zhou, L.
AU - Zhang, X. B.
AU - Sun, X. L.
AU - Yan, H.
N1 - Publisher Copyright:
Copyright © 2015 by ASME.
PY - 2015
Y1 - 2015
N2 - Fluidic throat control is one key technology of fixed geometry thrust vectoring nozzle. Based on CFD numerical simulation, the flow characteristics of fluidic throat control by high pressure secondary flow injected into throat of nozzle, and performance of nozzle were investigated. The coupling method of nozzle with fluidic throat control and aero-engine was proposed. Firstly, the approximate model of nozzle with fluidic throat control was established by combining the design of experiment and response surface methodology. Then the aero-engine simulation model with air extraction was established. And by mass flow balance and pressure balance relationship, the approximate model of fluidic throat control nozzle and aero-engine simulation model with air extraction were combined into coupling model. Simulation results show that, due to the high pressure secondary flow injected into nozzle throat, there exist obvious high and low speed layers near nozzle throat, and the secondary injection made the nozzle flow over expand. Through the check of validation of approximate model, it shows good precision and can be used for the coupling model. For coupling performance, under different air extraction ratios from fan, the operating point on compressor map did not move obviously, the change of throat area affects the fan operating points greatly, and made it move to the surge boundary. And in the simulation, at the air extraction ratio of 12%, the throat control ratio of 17.8% was achieved.
AB - Fluidic throat control is one key technology of fixed geometry thrust vectoring nozzle. Based on CFD numerical simulation, the flow characteristics of fluidic throat control by high pressure secondary flow injected into throat of nozzle, and performance of nozzle were investigated. The coupling method of nozzle with fluidic throat control and aero-engine was proposed. Firstly, the approximate model of nozzle with fluidic throat control was established by combining the design of experiment and response surface methodology. Then the aero-engine simulation model with air extraction was established. And by mass flow balance and pressure balance relationship, the approximate model of fluidic throat control nozzle and aero-engine simulation model with air extraction were combined into coupling model. Simulation results show that, due to the high pressure secondary flow injected into nozzle throat, there exist obvious high and low speed layers near nozzle throat, and the secondary injection made the nozzle flow over expand. Through the check of validation of approximate model, it shows good precision and can be used for the coupling model. For coupling performance, under different air extraction ratios from fan, the operating point on compressor map did not move obviously, the change of throat area affects the fan operating points greatly, and made it move to the surge boundary. And in the simulation, at the air extraction ratio of 12%, the throat control ratio of 17.8% was achieved.
UR - https://www.scopus.com/pages/publications/84954306546
U2 - 10.1115/GT2015-43162
DO - 10.1115/GT2015-43162
M3 - 会议稿件
AN - SCOPUS:84954306546
T3 - Proceedings of the ASME Turbo Expo
BT - Aircraft Engine; Fans and Blowers; Marine
PB - American Society of Mechanical Engineers (ASME)
T2 - ASME Turbo Expo 2015: Turbine Technical Conference and Exposition, GT 2015
Y2 - 15 June 2015 through 19 June 2015
ER -