Abstract: In a cryogenic engine thrust chamber, the fuel is passed through the regenerative channels in order to take care of high energy combustion. However cryogenic cooling results in wide range of temperature distribution in the cross section and along the axis of the thrust chamber with respect to time. In order to have an understanding of temperature distribution and stable combustion condition an accurate prediction of heat transfer characteristics for the complete spectrum of thrust chamber with respect to time is necessary. The objective of the paper includes the effects of regenerative cooling and the companion conjugate heat transfer. GAMBIT and FLUENT software programs are used as grid generator and solver respectively in the solution. Analysis is done three dimensionally and fluid flow is considered to be transient turbulent flow. The standard k-ε turbulence model is employed. Transient temperature prediction of coolant using CFD simulation is the main study related to this work. The study includes the analysis of regeneratively cooled thrust chamber with rectangular channels with aspect ratio 2:1.
Keywords: Cryogenic engine, Regenerative Cooling, k-ε turbulence model, GAMBIT and FLUENT, CFD, Aspect Ratio.
Title: Case Study of Regenerative Cooling in Rocket Combustors Using Rectangular Cooling Channels
Author: SARATH RAJ, SUJITH G
International Journal of Mechanical and Industrial Technology
ISSN 2348-7593 (Online)
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