期刊
PROCEEDINGS OF THE COMBUSTION INSTITUTE
卷 37, 期 3, 页码 3685-3692出版社
ELSEVIER SCIENCE INC
DOI: 10.1016/j.proci.2018.07.097
关键词
Supersonic combustion; Flame stabilization mode; DLR Strut injection scheme; Stagnation Temperature; Overall equivalence ratio
资金
- Training Program of the Major Research Plan of the National Natural Science Foundation of China [91641110]
- National Natural Science Foundation of China [11502270]
- RGC/GRF [PolyU 152217/14E, PolyU 152651/16E]
- NSFC [91641105]
Inspired by the existence of multiple flame stabilization modes in cavity-assisted supersonic combustor, multiple flame stabilization modes of DLR hydrogen-fueled strut injection supersonic combustor were numerically realized and analyzed for a wide ranges of inflow stagnation temperature from 607 to 2141 K and overall equivalence ratio from 0.022 to 0.110. Finite-rate chemistry large eddy simulation with detailed hydrogen mechanism was employed to capture unsteady flow characteristics and the effects of chemical kinetics. Two typical flame stabilization modes were identified and presented in a regime nomogram, which shows the dominant influence of the stagnation temperature and the secondary influence of overall equivalence ratio. At relatively low stagnation temperatures, the flame is stabilized in an attached flame mode, which requires a low-speed recirculation zone behind the strut for radical production and a high-speed intense combustion zone for heat release. At relatively high stagnation temperatures, the flame is stabilized in a lifted flame mode, in which the effect of the low-speed recirculation zone is negligible, rendering most reactions take place in supersonic flow. At intermediate stagnation temperatures, blow-out was always observed and flame cannot be stabilized in the combustor even with initially forced ignition. (C) 2018 The Combustion Institute. Published by Elsevier Inc. All rights reserved.
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