A multi-dimensional approach for low order modeling of combustion instability in a rocket combustor

The present paper reports on the status of development of a new multi-dimensional approach for modeling combustion instability in liquid propellant rocket engines. The aim is to study the transverse thermo-acoustic instability by a low-order model based on suitable response functions. The flow is considered as one-dimensional within the injector, whereas the combustion chamber flow is modeled by a simplified approach able to preserve the needed multi-dimensional features of wave propagation. Preliminary results are reported, showing numerical validations for some well-known gas dynamic problems and the capability to resolve transverse wave-propagation.