Author(s): S. Senthilkumar, Dr. P. Maniiarasan, Christy Oomman Jacob, T. Vinitha
Published in: International Journal of Engineering Research & Technology
License: This work is licensed under a Creative Commons Attribution 4.0 International License.
Volume/Issue: Vol.2 - Issue 8 (August - 2013)
The basic concept of a rocket engine relays on the release of the internal energy of the propellant molecules in the combustion chamber, the acceleration of the reaction product and finally the release of the hot gases at the highest possible velocity in the convergent/divergent nozzle. Liquid rocket engines burn propellants, which undergo chemical reactions to convert the stored chemical energy to thermal energy which results in the generation of thrust. Thrust chamber of cryogenic engine is modeled at a chamber pressure of 40 bar and thrust of 50KN to reduce the high temperature and pressure in the combustion chamber. CFD analysis is done to show the pressure and temperature variation in the thrust chamber modeled for 50KN thrust and chamber pressure of 40 bar. The design of rocket engine should be such that it should withstand the high pressure and high temperature of the combustion chamber.
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