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Heat and mass transfers in curved cooling channels of rocket engines

Abstract : The materials of the combustion chamber wall of rocket engines have to withstand extreme thermal and mechanical loadings, which are managed by efficient cooling. For an optimal design of the cooling system, with minimal hydrodynamic losses, a precise knowledge of the heat transfer is required. The combustion chamber profile imposes some curvatures to the cooling channel, because they follow the nozzle profile of the combustion chamber. These curvatures create dynamical secondary flows inside the channel and bring heat flux modifications through the chamber walls. The experimental project EH3C (Electrical Heated Curved Cooling Channels) has been supported by the german space propulsion center (DLR) in the frame of this PhD. Two test specimens have been designed, manufactured and tested. The first specimen is a single straight cooling channel, presenting a high aspect ratio and the second one is curved, in order to enlighten the curvature effects on the heat transfer and the pressure losses. Numerical simulations have been provided to model the experiments
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Submitted on : Tuesday, November 17, 2020 - 3:05:50 PM
Last modification on : Tuesday, November 23, 2021 - 9:44:23 AM
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  • HAL Id : tel-03009976, version 1


Yohann Torres. Heat and mass transfers in curved cooling channels of rocket engines. Mechanics [physics]. Université de Valenciennes et du Hainaut-Cambrésis, 2008. English. ⟨NNT : 2008VALE0021⟩. ⟨tel-03009976⟩



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