A computational study is presented of the nonlinear combustion instability of a multi-injector rocket engine. The study addresses a choked nozzle and a combustion chamber with 10 and 19 coaxial injector ports. Computations using a three-dimensional unsteady shear-stress transport delayed detached-eddy simulation method provide detailed time-resolved information about the combustion instability. The spontaneous longitudinal-mode instability is observed for the 10- and 19-injector geometries with a combustion-chamber diameter of 28 cm. The triggered tangential and longitudinal instability modes are obtained for the 19-injector geometry with a combustion-chamber diameter of 43 cm by pulsing the injector mass flux. It is shown that an oscillating combustion-chamber flow can be triggered to a new mode with a larger disturbance amplitude. The streamwise vorticity created by the instability impacts the heat release in a manner that supports the instability. A preliminary study of injector-size scaling effects is performed by comparison of the 10- and 19-injector combustors.
Nonlinear Combustion Instability in a Multi-Injector Rocket Engine
AIAA Journal ; 58 , 1 ; 219-235
2019-10-08
17 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Combustion Simulation of 82-Injector Rocket Engine
AIAA | 2022
|Liquid rocket engine combustion instability
TIBKAT | 1995
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