The prediction of wall heat flux at the nozzle throat is of paramount importance in liquid rocket engine (LRE) design both for sizing and safety purposes. Computational fluid dynamics (CFD) simulations can aid in the prediction provided that they can be effectively used during the design phase and that suitable modeling is employed. In this framework, this study aims at evaluating the suitability of a RANS-based CFD approach to predict in affordable times the nozzle wall heat flux of LREs employing the oxygen/methane propellant combination, which is nowadays attracting the attention of many developers. The interest to study the throat heat flux estimation for oxygen/methane engines comes from the known greater role played by the near-wall recombination reactions, as compared to the oxygen/hydrogen propellant pair. Nevertheless, only few indirect experimental measurements are available in the open literature for the validation of numerical tools. Recently published experimental data are used here as benchmark for the comparison of numerical simulations obtained with different assumptions. Results confirm that, for a well-designed engine, the details of injection and combustion processes have only a secondary effect on the prediction of throat heat flux.

Modeling of wall heat flux in oxygen-methane liquid rocket thrust chambers / Concio, Pierluigi; Migliorino, MARIO TINDARO; Bianchi, Daniele; Nasuti, Francesco. - (2022). (Intervento presentato al convegno AIAA AVIATION 2022 Forum tenutosi a Chicago) [10.2514/6.2022-3275].

Modeling of wall heat flux in oxygen-methane liquid rocket thrust chambers

Pierluigi concio
Primo
;
Mario Tindaro Migliorino
Secondo
;
Daniele Bianchi
Penultimo
;
Francesco Nasuti
Ultimo
2022

Abstract

The prediction of wall heat flux at the nozzle throat is of paramount importance in liquid rocket engine (LRE) design both for sizing and safety purposes. Computational fluid dynamics (CFD) simulations can aid in the prediction provided that they can be effectively used during the design phase and that suitable modeling is employed. In this framework, this study aims at evaluating the suitability of a RANS-based CFD approach to predict in affordable times the nozzle wall heat flux of LREs employing the oxygen/methane propellant combination, which is nowadays attracting the attention of many developers. The interest to study the throat heat flux estimation for oxygen/methane engines comes from the known greater role played by the near-wall recombination reactions, as compared to the oxygen/hydrogen propellant pair. Nevertheless, only few indirect experimental measurements are available in the open literature for the validation of numerical tools. Recently published experimental data are used here as benchmark for the comparison of numerical simulations obtained with different assumptions. Results confirm that, for a well-designed engine, the details of injection and combustion processes have only a secondary effect on the prediction of throat heat flux.
2022
AIAA AVIATION 2022 Forum
liquid rocket engines; throat heat flux; CFD
04 Pubblicazione in atti di convegno::04b Atto di convegno in volume
Modeling of wall heat flux in oxygen-methane liquid rocket thrust chambers / Concio, Pierluigi; Migliorino, MARIO TINDARO; Bianchi, Daniele; Nasuti, Francesco. - (2022). (Intervento presentato al convegno AIAA AVIATION 2022 Forum tenutosi a Chicago) [10.2514/6.2022-3275].
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Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11573/1650441
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