2021/08/26 by Lei Zhan, Zhan, Lei, Tuan M. Nguyen +7
Chemical Engineering · Engineering · #Advanced Combustion Engine Technologies #Combustion and flame dynamics #FOS: Physical sciences #Fluid Dynamics (physics.flu-dyn) #Rocket and propulsion systems research
paper · pdf · doi:10.48550/arxiv.2108.12046
openalex publication_date 2021/08/26 · openalex created_date 2021/09/13 · openalex updated_date 2026/07/28
The combustion instability is investigated computationally for a multi-injector rocket engine using the flamelet progress variable (FPV) model. A C++ code is developed based on OpenFOAM 4.0 to apply the combustion model. Flamelet tables are generated for methane/oxygen combustion at the background pressure of 200 bar using a 12-species chemical mechanism. A power law is determined for rescaling the reaction rate for the progress variable to address the pressure effect. The combustion is also simulated by the one-step-kinetics (OSK) method for comparison with the FPV approach. A study of combustion instability shows that a longitudinal mode of 1500 Hz and a tangential standing wave of 2500 Hz are dominant for both approaches. While the amplitude of the longitudinal mode remains almost the same for both approaches, the tangential standing wave achieves a larger amplitude in the FPV simulation. A preliminary study of the resonance in the injectors, which is driven by the longitudinal-mode oscillation in the combustion chamber, is also presented.