27_Comparison.pdf - ISSN(Online 2319-8753 ISSN(Print 2347-6710 International Journal of Innovative Research in Science Engineering and Technology(A High

27_Comparison.pdf - ISSN(Online 2319-8753 ISSN(Print...

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ISSN(Online): 2319-8753 ISSN (Print): 2347-6710 I nternational J ournal of I nnovative R esearch in S cience, E ngineering and T echnology (A High Impact Factor, Monthly Peer Reviewed Journal) Vol. 5, Issue 1, Januray 2016 Copyright to IJIRSET DOI:10.15680/IJIRSET.2015.0501027 203 Comparison on the Effect Of Regenerative and Sub Cooling in the Heat Transfer Characteristics of Semi Cryogenic Thrust Chamber Having Rectangular Cooling Channels by Using CFD and Numerical Analysis Sarath Raj 1 , AswaniRajan 2 Assistant Professor, Dept. of Mechanical Engineering, Sree Narayana Institute of Technology, Kerala India 1 Assistant Professor, Dept. of Electrical and Electronics Engineering, Sree Narayana Institute of Technology, Kerala, India 2 ABSTRACT :In this paper, Computational Fluid Dynamics and Numerical Analysis is used to investigate the rocket thrust chamber cooling characteristics. The scope of the investigation involves the study of effect of regenerative and sub cooling on the heat transfer characteristics of coolant channel. Steady state pressure based analysis is carried out in this work. The temperature distributions of coolant along the rectangular cooling channel, temperature distributions of copper and stainless steel walls are the main focus of the study. In this study the, the coolant (kerosene), which is the fuel) enters at the aft end of the thrust chamber and passes through the rectangular cooling channels before it is fed to the injectors. KEYWORDS :Computational Fluid Dynamics, Numerical Analysis, Thrust Chamber, Rectangular Cooling Channel. I. I NTRODUCTION All rocket engines have one problem in common; high energy released by combusted gases. This problem results in high combustion temperatures in the order of 2400K to 3600 K, high heat transfer rates (0.8 to160 MW/m 2 ) in thrust chamber and therefore requires special cooling techniques for the engine. Cooling techniques developed to cope with this problem, either singly or in combination, include regenerative, radiation, sub cooling, film cooling or transpiration cooling, ablation, arid inert or endothermic heat sinks. To choose the proper cooling technique mission requirements, environmental requirements and operational requirements should be considered. Regenerative cooling is one of the most widely applied cooling techniques used in liquid propellant rocket engines. In this paper CFD modelling and analysis is used for predicting the heat transfer characteristics, considering a rectangular channel of aspect ratio 5.Numerical analysis is also carried along with the CFD analysis. Regenerative cooling of a liquid propellant rocket engine consists of a balance between the energy rejected by the combustion of gases and the heat energy absorbed by the coolant. The energy absorbed by the coolant is not wasted; it increases the initial energy content of the propellant prior to injection, increasing the exhaust velocity slightly (0.1 to 1.5%).
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  • Heat Transfer, ISSN, Computational fluid dynamics, International Journal of Innovative Research in Science, high impact factor

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