The combustion of heterogeneous solid propellants is characterized by velocity fluctuations which have a fundamental effect on the turbulence development and on the onset of aeroacoustic instabilities. In this work, following open literature, we propose a parametric study to develop a specific mass-injection boundary condition able to account for such fluctuations. This new propellant boundary condition is implemented in an advanced flow solver which adopts the immersed boundary methodology to deal with complex geometries and is applied to a real rocket motor inspired by the second stage of the European VEGA launcher. The numerical results show that it is possible to tune the model in order to correctly reproduce the amplitude and the main frequency of the pressure oscillations which develop inside the combustion chamber.
Immersed boundary simulations of aeroacoustics phenomena in solid rocket motors / Cimini, Matteo; Stella, Fulvio; Cavallini, Enrico; DI MASCIO, Andrea; Neri, Agostino; Martelli, Emanuele; Bernardini, Matteo. - (2022). (Intervento presentato al convegno 9ᵀᴴ EUROPEAN CONFERENCE FOR AERONAUTICS AND SPACE SCIENCES (EUCASS) tenutosi a Lille; France) [10.13009/eucass2022-4744].
Immersed boundary simulations of aeroacoustics phenomena in solid rocket motors
Matteo Cimini
Primo
Writing – Original Draft Preparation
;Fulvio StellaSecondo
Writing – Original Draft Preparation
;Enrico CavalliniWriting – Original Draft Preparation
;Andrea Di MascioWriting – Original Draft Preparation
;Emanuele MartelliPenultimo
Writing – Original Draft Preparation
;Matteo BernardiniUltimo
Writing – Original Draft Preparation
2022
Abstract
The combustion of heterogeneous solid propellants is characterized by velocity fluctuations which have a fundamental effect on the turbulence development and on the onset of aeroacoustic instabilities. In this work, following open literature, we propose a parametric study to develop a specific mass-injection boundary condition able to account for such fluctuations. This new propellant boundary condition is implemented in an advanced flow solver which adopts the immersed boundary methodology to deal with complex geometries and is applied to a real rocket motor inspired by the second stage of the European VEGA launcher. The numerical results show that it is possible to tune the model in order to correctly reproduce the amplitude and the main frequency of the pressure oscillations which develop inside the combustion chamber.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.