Coolant flowmodeling 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 heat transfer coupling with the hot-gas flow and the solid material. In this study the effect of wall heat conduction on the coolant flow is analyzed by means of coupled computations between a validated Reynolds-averaged Navier-Stokes equations solver for the coolant flowfield anda Fourier's equation solver for the thermal conduction in the solidmaterial. Computations of supercritical-hydrogen flowin a straight channelwith andwithout coupling with the solidmaterial are performed and compared to understand the role played by the coupling on the coolant flowevolution. Finally, thewhole cooling circuit of the space shuttlemain enginemain combustion chamber is analyzed in detail and discussed for the sake of comparison of results obtained with the present coupled procedure with available literature data.

Coupled wall heat conduction and coolant flow analysis for liquid rocket engines / Pizzarelli, Marco; Nasuti, Francesco; Onofri, Marcello. - In: JOURNAL OF PROPULSION AND POWER. - ISSN 0748-4658. - STAMPA. - 29:1(2013), pp. 34-41. [10.2514/1.b34533]

Coupled wall heat conduction and coolant flow analysis for liquid rocket engines

PIZZARELLI, MARCO;NASUTI, Francesco;ONOFRI, Marcello
2013

Abstract

Coolant flowmodeling 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 heat transfer coupling with the hot-gas flow and the solid material. In this study the effect of wall heat conduction on the coolant flow is analyzed by means of coupled computations between a validated Reynolds-averaged Navier-Stokes equations solver for the coolant flowfield anda Fourier's equation solver for the thermal conduction in the solidmaterial. Computations of supercritical-hydrogen flowin a straight channelwith andwithout coupling with the solidmaterial are performed and compared to understand the role played by the coupling on the coolant flowevolution. Finally, thewhole cooling circuit of the space shuttlemain enginemain combustion chamber is analyzed in detail and discussed for the sake of comparison of results obtained with the present coupled procedure with available literature data.
2013
01 Pubblicazione su rivista::01a Articolo in rivista
Coupled wall heat conduction and coolant flow analysis for liquid rocket engines / Pizzarelli, Marco; Nasuti, Francesco; Onofri, Marcello. - In: JOURNAL OF PROPULSION AND POWER. - ISSN 0748-4658. - STAMPA. - 29:1(2013), pp. 34-41. [10.2514/1.b34533]
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Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11573/453020
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