Abstract
Regenerative and curtain cooling methods were studied for a cooling mechani ;m for the liquid rocket engine which will be used ir the second stage of a space launch vehicle. In case tE at a regenerative cooling system is used only, the liqu d rocket engine has no thermal stability because of hi ;h wall temperature. So, curtain coohng mechanism shc uld be introduced to get the thermal stability of the liqu d rocket engine. Curtai~ cooling section means the annl~lus area between a core circle and the inner wall, and it; concept is based on the concept of a highly-stratified gas flow in the thrust chamber. Additional fuel is i ~jected into the curtain cooling section and gas tempe ature can be reduced in this section because of the low OF mixture ratio. Consequently, the heat flux from hot combustion gas into the coolant through the ir ner wall is reduced and the thermal stability of a liqu d rocket engine can be improved.
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