TY - GEN
T1 - Numerical simulations of flame propagation and DDT in obstructed detonation tubes filled with fluidic obstacles
AU - Wang, Yongjia
AU - Fan, Wei
AU - Li, Shuxin
AU - Zhang, Qibin
AU - Li, Hongbin
N1 - Publisher Copyright:
© 2017, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2017
Y1 - 2017
N2 - In order to investigate the impact of hot fluidic obstacles on the flame acceleration and deflagration-to-detonation transition (DDT) process, 2D numerical simulations were conducted in 6 mm channels, using ethylene and air as fuel and oxidizer, respectively. Computations show that the DDT time can be reduced by 37.5% with hot fluidic obstacles, compared to that of the smooth tube. The flame in the detonation chamber can be accelerated either by turbulence occurred around the jet hole, or by the retonation wave ejected from the jet cavity which attributes to the shock-flame interaction. Compared to the typical physical obstacles, the fluidic obstacles can decrease the total pressure loss significantly, which indicates its potential to be applied in the propulsion system.
AB - In order to investigate the impact of hot fluidic obstacles on the flame acceleration and deflagration-to-detonation transition (DDT) process, 2D numerical simulations were conducted in 6 mm channels, using ethylene and air as fuel and oxidizer, respectively. Computations show that the DDT time can be reduced by 37.5% with hot fluidic obstacles, compared to that of the smooth tube. The flame in the detonation chamber can be accelerated either by turbulence occurred around the jet hole, or by the retonation wave ejected from the jet cavity which attributes to the shock-flame interaction. Compared to the typical physical obstacles, the fluidic obstacles can decrease the total pressure loss significantly, which indicates its potential to be applied in the propulsion system.
UR - http://www.scopus.com/inward/record.url?scp=85085406936&partnerID=8YFLogxK
U2 - 10.2514/6.2017-2382
DO - 10.2514/6.2017-2382
M3 - 会议稿件
AN - SCOPUS:85085406936
SN - 9781624104633
T3 - 21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017
BT - 21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - 21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017
Y2 - 6 March 2017 through 9 March 2017
ER -