scholarly journals Exploration of combustion instability triggering using Large Eddy Simulation of a multiple injector liquid rocket engine

2016 ◽  
Vol 169 ◽  
pp. 129-140 ◽  
Author(s):  
A. Urbano ◽  
L. Selle ◽  
G. Staffelbach ◽  
B. Cuenot ◽  
T. Schmitt ◽  
...  
Keyword(s):  
Large Eddy Simulation ◽  
Rocket Engine ◽  
Combustion Instability ◽  
Liquid Rocket Engine ◽  
Eddy Simulation ◽  
Large Eddy ◽  
Liquid Rocket

scholarly journals Analysis of Tangential Combustion Instability Modes in a LOX/Kerosene Liquid Rocket Engine Based on OpenFOAM

2022 ◽  
Vol 9 ◽  
Author(s):  
Kangkang Guo ◽  
Boqi Xu ◽  
Yongjie Ren ◽  
Yiheng Tong ◽  
Wansheng Nie
Keyword(s):  
Heat Release ◽  
Standing Wave ◽  
Rocket Engine ◽  
Combustion Instability ◽  
Wave Mode ◽  
Acoustic Mode ◽  
Chamber Pressure ◽  
Liquid Rocket Engine ◽  
Operation Condition ◽  
Liquid Rocket

Self-excited high frequency combustion instability (HFCI) of first-order tangential (1T) mode was observed in a staged-combustion LOX/Kerosene liquid rocket engine numerically. Two different kinds of 1T patterns, standing wave mode and traveling wave mode, were captured in the present work. In the nominal operation condition, the ratio of oxygen-to-fuel (O/F) was 2.5. Propellant was evenly distributed in all injectors and no HFCI occurred. The chamber pressure obtained from the numerical simulation and experiment showed a good agreement, which validated the numerical model. When the mass flow of fuel for two injectors was modified, severe HFCI occurred. The pressure wave node was located at a fixed diameter, showing a 1T standing wave mode. As the O/F was set 4.4 and the propellant distribution was completely uniform, the numerical result yielded a 1T wave node featured a spinning behavior, which was a traveling 1T wave mode. Once the HFCI arose, no matter what standing mode or spinning mode, the pressure and heat release oscillated totally in phase temporally and coupled spatially. The heat release from combustion was fed into the resonant acoustic mode. This was the thermoacoustic coupling process that maintained the HFCI.

Effects of self-pulsation on combustion instability in a liquid rocket engine

2020 ◽  
Vol 114 ◽  
pp. 110038 ◽  
Author(s):  
Xiao Bai ◽  
Peng Cheng ◽  
Qinglian Li ◽  
Liyong Sheng ◽  
Zhongtao Kang
Keyword(s):  
Rocket Engine ◽  
Combustion Instability ◽  
Liquid Rocket Engine ◽  
Liquid Rocket

Large Eddy Simulation of Combustion Instability of Low-Swirl Flames in a Multi-Nozzle Combustor

2017 ◽  
Author(s):  
Weijie Liu ◽  
Bing Ge ◽  
Shusheng Zang ◽  
Mingjia Li ◽  
Wenyan Xu
Keyword(s):  
Large Eddy Simulation ◽  
Heat Release ◽  
Pressure Fluctuation ◽  
Combustion Instability ◽  
Eddy Simulation ◽  
Numerical Result ◽  
Large Eddy ◽  
Reversal Flow ◽  
Flame Flashback ◽  
Flow Vortex

Large eddy simulation of self-induced combustion instability of low-swirl flames in a multi-nozzle combustor is carried out. The unsteady behaviors in the multi-nozzle burner including pressure fluctuation, velocity oscillation, PVC and triggering mechanism are studied in detail. Numerical result is compared with experimental measurement in terms of frequency and amplitude of pressure fluctuation. Results show LES successfully predicts the longitudinal instability mode in the multi-nozzle combustor with a reasonable agreement with experimental data. Flow parameters in the burner, such as pressure, axial velocity and CH4 mass fraction oscillate with the same frequency but different phases. Combustion instability leads to flame flashback into the burner due to the reversal flow. Vortex generation and shedding off in the outer shear layer result in unsteady heat release at the tail edge of the outer flame near combustor wall. Meanwhile, the unsteady heat release feedback to the pressure and flowfield, which is the main reason for inducing combustion instability.

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