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26th National Symposium on Cryogenics and Superconductivity

22-24 February 2017
VECC
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Preliminary design and analysis of tripropellant rocket engine
 
Content: Tripropellant rocket can be designed in two ways- either by adding a metallic fuel like Al or Be to the bipropellant system or can be a semi-cryogenic. Here, the mode used is semi-cryogenic, where we use liquid oxygen as oxidizer, liquid hydrogen and kerosene based RP-1 as fuels. The main advantage of semi-cryogenic system is that it combines high thrust of a hydrocarbon fuel and high specific impulse of cryogenic propellants. The preliminary analysis is done in RPA (Rocket Performance Analysis) where we get the thermodynamic and transport properties along with performance parameters variation with altitude. The results are validated using CEA (Chemical Equilibrium and Applications). Using the results obtained from the analysis, the thrust chamber and 80% bell nozzle is designed using the parabolic approximation method. Thrust chamber cooling analysis is done using the regenerative cooling method where LH2 is used as the coolant which takes up the heat released by the combustion gases and thus raises enthalpy of the fuel before entering the combustion chamber. CFD analysis is done using the designed geometry by considering rectangular cooling channels.
Id: 83
Place: VECC
Room: Hall B(Annex Auditorium)
Starting date:
23-Feb-2017   12:30 (Asia/Kolkata)
Duration: 15'
Contribution type: Contributory Talk
Primary Authors: Mr. K, AZHAR (NIT CALICUT)
Co-Authors: Dr. KUZHIVELI, BIJU T (NIT CALICUT)
Presenters: Mr. K, AZHAR
 
Included in session: Technical Session 5
Included in track: Cryogenics Storage and transfer lines / Space Research / Cryogenic Test & Test Facilities