Graduate Project
 

Cooling System Analysis of the Thrust Chamber

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https://ir.library.oregonstate.edu/concern/graduate_projects/2n49t8587

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  • The purpose of the study was to analyze the possible combination of cooling systems, which are film cooling and regenerative cooling, and obtain the initial estimates of possible temperature reduction. The analysis was conducted in Ansys Fluent. The methodology includes four main steps that are the following: flow simulation, combustion simulation, film cooling simulation and regenerative cooling simulation. The theoretical conditions for combustion chamber were 350 Psia for pressure and 3452 K for temperature and 5.207 for mach number. And the fuel flow for the entire system is 0.97 kg/s for kerosene and 2.23 kg/s for oxidizer. The study provided satisfactory results in temperature reduction near the walls of the thrust chamber. The film cooling system was able to reduce the temperature to an average of 1500 K and the regenerative system was able to lower it further down to the average temperature to 1050 K.
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