Purpose of this thesis is to conduct a thermo-fluid dynamic study of a two-phase chemical reagent flow during the expansion in a supersonic nozzle. The presence of unburned particulate, particularly appreciable in solid-propellant rockets, significantly influence the performance of the rocket. First of all, we want to understand what are the most important variables in play and to estabilish what is the mass fraction of particles that can burn during the expansion and what is the remaining part, fully ejected from the nozzle, that is unable to complete the reaction and is therefore not used for propulsion. After analyzing these issues, we will try to investigate whether and how the burning of particulates during the nozzle expansion provides benefits in terms of propulsive performance. In particular, we will use the informations obtained for the study of Z9, the third stage of the VEGA launcher, currently being developed by Avio.
Lo scopo di questa tesi è quello di effettuare uno studio termo-fuidodinamico di un flusso bi-fase chimicamente reagente in espansione in un ugello supersonico. La presenza di particolato incombusto, sensibile soprattutto negli endoreattori a propellente solido, influenza infatti in maniera significativa le prestazioni del motore. Si vuole innanzitutto capire quali sono le grandezze importanti in gioco e fornire qual è la frazione di massa degli agglomerati che riesce a bruciare durante l'espansione e qual è la restante parte che, espulsa completamente dall'ugello, non riesce a completare la reazione ed è quindi non utilizzabile ai fini propulsivi. Una volta analizzati tali aspetti, si cercherà di studiare se e quanto la combustione del particolato durante l'espansione in ugello fornisca benefici in termini di prestazioni propulsive, applicando in particolare le informazioni ottenute allo studio del motore Z9, terzo stadio del lanciatore VEGA, attualmente in fase di sviluppo presso Avio.
Espansione di flussi bifase in ugelli supersonici con combustione del particolato
COSTANTINI, MASSIMILIANO
2010/2011
Abstract
Purpose of this thesis is to conduct a thermo-fluid dynamic study of a two-phase chemical reagent flow during the expansion in a supersonic nozzle. The presence of unburned particulate, particularly appreciable in solid-propellant rockets, significantly influence the performance of the rocket. First of all, we want to understand what are the most important variables in play and to estabilish what is the mass fraction of particles that can burn during the expansion and what is the remaining part, fully ejected from the nozzle, that is unable to complete the reaction and is therefore not used for propulsion. After analyzing these issues, we will try to investigate whether and how the burning of particulates during the nozzle expansion provides benefits in terms of propulsive performance. In particular, we will use the informations obtained for the study of Z9, the third stage of the VEGA launcher, currently being developed by Avio.File | Dimensione | Formato | |
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https://hdl.handle.net/10589/31621