CFD simulation of turbulent convective heat transfer in rectangular mini-channels for rocket cooling applications

Beg, OA ORCID:, Zubair, A, Kuharat, S and Babaie, M ORCID: 2018, CFD simulation of turbulent convective heat transfer in rectangular mini-channels for rocket cooling applications , in: ICHTFM 2018 : 20th International Conference on Heat Transfer and Fluid Mechanics, 16-17 August 2018, Istanbul, Turkey.

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Heat transfer is one of the most critical aspects of the rocket propulsion design process. According to released heat, thermal loads are extremely large, and thermal insulation is frequently necessary in the motor combustion chambers and nozzles. In high temperature conditions, large thermal dilatations are present, and also the motor’s parts mechanical characteristics decreases. These occurrences are very important in the motor design process, and they are directly dependent from them temperature field. This is the reason why precise heat transfer calculation is necessary. Non-eroding metallic throat inserts made with pure tungsten, tungsten-rhenium alloys, and tungsten-rhenium alloys doped with hafnium carbide are now common. Combustion gas temperatures can rise up to 3,000 Celsius. Very high heat transfer rates from hot gases to the chamber wall must be designed for. Important research areas related to heat transfer of rocket nozzle include the internal and external heat transfer coefficient predictions, metal temperature distribution, wall cooling methods, and ceramic coatings among others. Life extension of the nozzle, which consists of an expensive super alloy, is very effective for reduction of the running costs of a power generation plant. Accordingly, it is very important for the life assessment of the nozzle to predict the operating conditions and to establish a basis for the criteria of repair. In order to assess the life of the nozzle accurately, it is necessary to estimate its temperature distribution by prediction of the thermal environment. A cooling system is essential therefore in order to maintain engine integrity. To elucidate aspect ratio effects in rocket channel cooling, we present ANSYS FLUENT CFD single-phase, two-dimensional turbulent forced convection simulations. We have used the data provided by Forrest of MIT. Extensive visuals of temperature, pressure and velocity contours are given. Mesh independence is included. Interesting thermal fluid dynamics characteristics are elucidated.

Item Type: Conference or Workshop Item (Poster)
Schools: Schools > School of Computing, Science and Engineering
Publisher: WASET
Depositing User: OA Beg
Date Deposited: 23 Jul 2018 11:16
Last Modified: 15 Feb 2022 23:33

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