Modeling of Radiation Heat Transfer in Liquid Rocket Engines

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Concluding Remarks• For a LH2/LO2 engine it is shown that theradiation has a small effect on the walltemperature of the diverging section of thenozzle• the radiation results in a substantial increase inthe wall temperature of the thrust chamber andconverging section of the nozzle, such that thelocal peak temperature is the same order ofmagnitude as the throat temperature
Concluding Remarks• For the RP1/LO2 engine, radiative heattransfer resulted in a 30% increase in walltemperature. Additionally, it significantlyincreased the coolant pressure drop andMach number• neglecting radiation during the designphase may result in a faulty coolingsystem
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 and 12: Absorption Coefficient of SootWhen
Page 13 and 14: Results for a LH2-LO2 Engine(SSME)T
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: Concluding Remarks• The effects o

Modeling of Radiation Heat Transfer in Liquid Rocket Engines

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