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 Stella
Secondo
Writing – Original Draft Preparation
;
Enrico Cavallini
Writing – Original Draft Preparation
;
Andrea Di Mascio
Writing – Original Draft Preparation
;
Emanuele Martelli
Penultimo
Writing – Original Draft Preparation
;
Matteo Bernardini
Ultimo
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.
2022
9ᵀᴴ EUROPEAN CONFERENCE FOR AERONAUTICS AND SPACE SCIENCES (EUCASS)
CFD; turbulence flows; compressible flows; aeroacoustic; SRM;
04 Pubblicazione in atti di convegno::04b Atto di convegno in volume
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].
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Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11573/1666394
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