Coolant-flow modeling in regeneratively cooled rocket engines fed with turbo-machinery is a challenging task because of the high wall temperature gradient, the high Reynolds number, the high aspect ratio of the channel cross section and the curved geometry. In the present study, to better comprehend the role of the thrust chamber shape of a rocket engine on the heat exchange, computations of supercritical hydrogen flow in single and doublecurvature channels are carried out. In particular, a parametric numerical analysis of the flow in asymmetrically heated rectangular channel with high aspect ratio and various radii of curvature is performed by means of a validated Reynolds Averaged Navier-Stokes solver for real fluids. Results permit to quantify the effect of curvature on global heat transfer coefficient, pressure loss and bulk temperature increase. Finally the results obtained for a straight channel with linear wall temperature distribution along the lateral wall are compared with straight channel flow-field characterized by a more realistic distribution of the lateral wall temperature.

CFD Analysis of Curved Cooling Channel Flow and Heat Transfer in Rocket Engines / Pizzarelli, Marco; Nasuti, Francesco; Onofri, Marcello. - ELETTRONICO. - (2010), pp. 1-14. ((Intervento presentato al convegno 46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit tenutosi a Nashville, Tennessee, USA nel 25-28 luglio 2010.

CFD Analysis of Curved Cooling Channel Flow and Heat Transfer in Rocket Engines

PIZZARELLI, MARCO;NASUTI, Francesco;ONOFRI, Marcello
2010

Abstract

Coolant-flow modeling in regeneratively cooled rocket engines fed with turbo-machinery is a challenging task because of the high wall temperature gradient, the high Reynolds number, the high aspect ratio of the channel cross section and the curved geometry. In the present study, to better comprehend the role of the thrust chamber shape of a rocket engine on the heat exchange, computations of supercritical hydrogen flow in single and doublecurvature channels are carried out. In particular, a parametric numerical analysis of the flow in asymmetrically heated rectangular channel with high aspect ratio and various radii of curvature is performed by means of a validated Reynolds Averaged Navier-Stokes solver for real fluids. Results permit to quantify the effect of curvature on global heat transfer coefficient, pressure loss and bulk temperature increase. Finally the results obtained for a straight channel with linear wall temperature distribution along the lateral wall are compared with straight channel flow-field characterized by a more realistic distribution of the lateral wall temperature.
46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit
04 Pubblicazione in atti di convegno::04b Atto di convegno in volume
CFD Analysis of Curved Cooling Channel Flow and Heat Transfer in Rocket Engines / Pizzarelli, Marco; Nasuti, Francesco; Onofri, Marcello. - ELETTRONICO. - (2010), pp. 1-14. ((Intervento presentato al convegno 46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit tenutosi a Nashville, Tennessee, USA nel 25-28 luglio 2010.
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Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11573/367001
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