Numerical Study on 3D Coupled Heat Transfer of Thrust Chamber with Regenerative Cooling

Abstract:

To obtain temperature distribution in regenerative-cooled liquid propellant rocket nozzle quickly and accurately, three-dimensional numerical simulation employed using empirical formulas. A reduced one-dimensional model is employed for the coolant flow and heat transfer, while three dimensional heat transfer model is used to calculate the coupling heat transfer through the wall. The geometrical model is subscale hot-firing chamber. The numerical results agree well with experimental data, while temperature field in nozzle obtained. In terms of computing time and accuracy of results, this method can provide a reference for optimization design and performance estimation.

• Periodical: Applied Mechanics and Materials (Volumes 52-54)
• Pages: 1057-1061
• DOI: https://doi.org/10.4028/www.scientific.net/AMM.52-54.1057
• Online since: March 2011
• Authors: Tao Nie, Wei Qiang Liu
• Keywords: Aerospace Propulsion System, Coupling, Numerical Simulation, Regenerative Cooling

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