f ounded ▁Space X ▁with ▁El on ▁Mus k ▁and ▁became ▁the ▁V P ▁of ▁prop ulsion ▁after ▁can cellation ▁of ▁S LI ▁program . ▁ ▁Design ▁The ▁engine ▁used ▁du ct - co ol ing ▁of ▁the ▁main ▁comb ust ion ▁chamber ▁and ▁materials ▁that ▁would ▁not ▁interact ▁with ▁k eros ene ▁to ▁minim ize ▁c oking . ▁ ▁The ▁du ct ▁separated ▁the ▁fuel ▁from ▁the ▁chamber ▁wall ▁and ▁allowed ▁controlled ▁cool ing ▁of ▁the ▁chamber ▁to ▁keep ▁the ▁temperature ▁of ▁the ▁k eros ene ▁down . ▁This ▁approach ▁simplified ▁the ▁engine ▁in ▁comparison ▁with ▁compet ing ▁designs . ▁By ▁elimin ating ▁the ▁reg ener ative ▁cool ing ▁circuit , ▁many ▁large ▁manif olds ▁and ▁associated ▁pl umb ing ▁were ▁elimin ated ▁as ▁well , ▁reducing ▁potential ▁failure ▁modes ▁and ▁impro ving ▁engine ▁reli ability . ▁The ▁TR 1 0 7 ▁engine ▁used ▁o xygen - rich ▁comb ust ion ▁( OR SC ) ▁products ▁to ▁alle vi ate ▁so ot ▁build - up ▁when ▁running ▁the ▁tur bo ▁p umps . ▁The ▁goal ▁of ▁the ▁development ▁was ▁to ▁produce ▁a ▁large , ▁low - cost , ▁easy - to - man ufact ure ▁boost er ▁engine . ▁ ▁Status ▁North rop ▁Gr um man ▁development ▁of ▁the ▁TR - 1 0 7 ▁engine ▁permitted ▁consideration ▁for ▁potential ▁use ▁on ▁next - gener ation ▁launch ▁and ▁space ▁transport ation ▁system . ▁ ▁See ▁also ▁ ▁Mer lin ▁ 1 D ▁ ▁R apt or ▁ ▁S LI ▁Pro totype ▁engines ▁