Influence of Flow Rate Distribution on Combustion Instability of Hypergolic Propellant

Combustion instability is the biggest threat to reliability of liquid rocket engines, whose prediction and suppression are great significance for engineering applications. To predict stability a combustion chamber with hypergolic propellant, this work used method decoupling unsteady acoustic system. The turbulence described by Reynolds-averaged Navier–Stokes technique, interaction chemistry eddy-dissipation model. By extracting flame transfer function field, eigenvalues each mode were obtained solving Helmholtz equation, thereby predicting chamber. predictions different flow rate distributions, it was found that increasing inlet amplitude will improve or combustion. optimized when distribution oxidant set more uniform in radial direction. heterogeneity circumferential direction not recommended, considering homogeneous beneficial