Numerical Study of Chemical Performance of 30 tonf -class LRE Nozzle of KARI

  • Kang, Ki-Ha (Pusan National University Dep. Aerospace Engineering) ;
  • Lee, Dae-Sung (Pusan National University Dep. Aerospace Engineering) ;
  • Cho, Deok-Rae (Pusan National University Dep. Aerospace Engineering) ;
  • Choi, H.S. (Korea Aerospace Research Institute) ;
  • Choi, J.Y. (Pusan National University Dep. Aerospace Engineering)
  • Published : 2008.03.30


Three methods of nozzle flow analysis, frozen-equilibrium, shifting-equilibrium and non-equilibrium approaches, were used to rocket nozzle flow, those were coupled with the methods of computational fluid dynamics code. For a design of high temperature rocket nozzle, chemical equilibrium analysis which shares the same numerical characteristics with frozen flow analysis can be an efficient design tool for predicting maximum thermodynamic performance of the nozzle. Frozen fluid analysis presents the minimum performance of the nozzle because of no consideration for the energy recovery. On the other hand, the case of chemical-equilibrium analysis is able to forecast the maximum performance of the nozzle due to consideration for the energy recovery that is produced for the fast reaction velocity compared with velocity of moving fluid. In this study, using the chemical equilibrium flow analysis code that is combined the modified frozen-equilibrium and the chemical-equilibrium. In order to understand the thermochemical characteristic components and the accompanying energy recovery, shifting-equilibrium flow analysis was carried out for the 30 $ton_f$-class KARI liquid rocket engine nozzle together with frozen flow. The performance evaluation based on the 30 $ton_f$-class KARI LRE nozzle flow analyses will provide an understanding of the thermochemical process in the nozzle and performances of nozzle.