Modeling of Radiation Heat Transfer in Liquid Rocket Engines

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Computer ModelThe properties and computational models(RAD2005) discussed were incorporated inthe TDK-RTE.Naraghi, M.H.N., Dunn, S., and Coats, D., “A Model forDesign and Analysis of Regeneratively Cooled RocketEngines,” AIAA paper 2005-3852, present at the JointPropulsion Conference, Fort Lauderdale, July 2004.
Results for a LH2-LO2 Engine(SSME)The specifications of this engine are:Chamber pressure3027 psiaO/F 6.0Contraction ratio 3.0Expansion ratio 77.5Throat diameter10.3 inchesPropellantLH2-LO2CoolantLH2Total coolant flow rate29.06 lb/sCoolant inlet temperature95RCoolant inlet stagnation pressure 6452 psiaNumber of cooling channels 430
Page 1 and 2: Modeling of Radiation HeatTransfer
Page 3 and 4: Previous Works• Hammad, K.J., and
Page 5 and 6: Exchange Factors betweengas and sur
Page 7 and 8: Total Exchange FactorsAccount for w
Page 9 and 10: Plank-Mean Properties for CO 20.40.
Page 11: Absorption Coefficient of SootWhen
Page 15 and 16: Effects of radiation on the walltem
Page 17 and 18: Effects of radiation on coolantstag
Page 19 and 20: Contour of the RP1-LOX engine108Lin
Page 21 and 22: Effects of radiation on the walltem
Page 23 and 24: Effects of radiation on the coolant
Page 25 and 26: Concluding Remarks• The effects o
Page 27 and 28: Concluding Remarks• For the RP1/L

Modeling of Radiation Heat Transfer in Liquid Rocket Engines

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