A numerical solver able to describe a rocket engine cooling channel fed with supercritical methane is validated against experimental data coming from a test article conceived and tested by the Italian Aerospace Research Center. The multi-dimensional numerical solver is based on a conjugate model for the coolant flow, modeled by the Reynolds-Averaged Navier-Stokes equations, and the heat transfer within the wall, modeled by the Fourier’s law of conduction. In this study a typical experimental test case is reproduced in detail in order to evaluate the influence of partially unknown parameters, as surface roughness and wall thermal conductivity, and of operative parameters uncertainty, as coolant mass flow rate and entering heat transfer rate. The comparison made with respect to the wall temperature and coolant pressure drop of the whole set of experimental data allows to discuss the reliability of the experimental data and to identify the test cases with significant heat loss.

Assessment of a conjugate heat transfer model for rocket engine cooling channels fed with supercritical methane / Pizzarelli, Marco; Nasuti, Francesco; Votta, Raffaele; Battista, Francesco. - ELETTRONICO. - 2:(2015), pp. 1809-1822. (Intervento presentato al convegno 51st AIAA/SAE/ASEE Joint Propulsion Conference, 2015 tenutosi a Orlando, FL, USA nel July 27-29, 2015) [10.2514/6.2015-3852].

Assessment of a conjugate heat transfer model for rocket engine cooling channels fed with supercritical methane

PIZZARELLI, MARCO
;
NASUTI, Francesco
;
2015

Abstract

A numerical solver able to describe a rocket engine cooling channel fed with supercritical methane is validated against experimental data coming from a test article conceived and tested by the Italian Aerospace Research Center. The multi-dimensional numerical solver is based on a conjugate model for the coolant flow, modeled by the Reynolds-Averaged Navier-Stokes equations, and the heat transfer within the wall, modeled by the Fourier’s law of conduction. In this study a typical experimental test case is reproduced in detail in order to evaluate the influence of partially unknown parameters, as surface roughness and wall thermal conductivity, and of operative parameters uncertainty, as coolant mass flow rate and entering heat transfer rate. The comparison made with respect to the wall temperature and coolant pressure drop of the whole set of experimental data allows to discuss the reliability of the experimental data and to identify the test cases with significant heat loss.
2015
51st AIAA/SAE/ASEE Joint Propulsion Conference, 2015
coolants; engines; methane; Navier stokes equations; propulsion; rocket engines; rockets; surface roughness; thermal conductivity
04 Pubblicazione in atti di convegno::04b Atto di convegno in volume
Assessment of a conjugate heat transfer model for rocket engine cooling channels fed with supercritical methane / Pizzarelli, Marco; Nasuti, Francesco; Votta, Raffaele; Battista, Francesco. - ELETTRONICO. - 2:(2015), pp. 1809-1822. (Intervento presentato al convegno 51st AIAA/SAE/ASEE Joint Propulsion Conference, 2015 tenutosi a Orlando, FL, USA nel July 27-29, 2015) [10.2514/6.2015-3852].
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Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11573/961762
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