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Title: Flow Field and Heat Transfer Analysis of Oxygen/Methane Liquid Rocket Engine Thrust Chambers
Tutor: Nasuti, Francesco
Keywords: Heat transfer
Liquid rocket engine
Thrust Chamber
Film Cooling
Ribbed wall
Expander cycle
Numerical simulation
Issue Date: 28-Sep-2012
Abstract: This study is devoted to the characterization and analysis of the flow field and heat transfer in oxygen/methane liquid rocket engines. Attention is focused on the hot gas side of the thrust chamber, where highly energetic flows have to be managed en- suring the safe operation of the thrust chamber and of the entire engine. Different technological solutions to handle such flows are here investigated by means of CFD numerical simulations. As a compromise between details and computational cost, the attention is focused on capturing the basic phenomena involved which drive the main heat transfer processes, to allow full scale engine analysis as support to the engine design phase. The simplified approaches are defined, verified and validated against experimental data in different rocket engine conditions, such as film cooled and regeneratively cooled thrust chambers, and expander cycle engine thrust chambers with heat transfer enhancement devices. Hence, parametric analyses are finally carried out for each configuration. Finally, the simplified approaches are adopted in the thermal analysis of the LM-10 MIRA oxygen/methane expander cycle engine thrust chamber.
Research interests: numerical simulations of heat transfer in liquid rocket engine thrust chambers: active cooling techniques, coupled heat transfer problems, heat transfer enhancement devices.

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