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액체로켓 엔진 연소장치 개발에 있어서의 전산유체역학 적용 사례
조미옥(M. Joh),김성구(S.-K. Kim),한상훈(S.H. Han),최환석(H.-S. Choi) 한국전산유체공학회 2013 한국전산유체공학회 학술대회논문집 Vol.2013 No.5
This paper provides a brief introduction to application examples of the computational fluid dynamics to development of combustion devices for domestic liquid-propellant rocket engines. It is demonstrated that multi-dimensional flow analysis and multi-disciplinary combustion/cooling performance analysis can be effectively applied to provide key information on some performance-related design issues for thrust chambers and gas generators. Efforts are being made to understand complex physical phenomena inside these combustion devices, especially near the injection plate, by resolving mixing/combustion characteristics of LOX/kerosene with taking the geometry of liquid-liquid coaxial swirl injectors into consideration.
평형화학반응과 복사열전달을 고려한 로켓 플룸 유동 해석
신재렬(J.-R. Shin),최정열(J.-Y. Choi),최환석(H.-S. Choi) 한국전산유체공학회 2004 한국전산유체공학회 학술대회논문집 Vol.2004 No.-
The Numerical study has been carried out to investigate the effects of chemical reaction and thermal radiation on the rocket plume flow-field at various altitudes. The theoretical formulation is based on the Navier-Stokes equations for compressible flows along with the infinitely fast chemistry and thermal radiation. The governing equations were solved by a finite volume fully-implicit TVD(Total Variation Diminishing) code which uses Roe's approximate Riemann solver and MUSCL(Monotone Upstream-centered Schemes for Conservation Laws) scheme. LU-SGS (Lower Upper Symmetric Gauss Seidel) method is used for the implicit solution strategy. An equilibrium chemistry module for hydrocarbon mixture with detailed thenno-chemical properties and a thermal radiation module for optically thin media were incorporated with the fluid dynamics code.<br/> n this study, kerosene-fueled rocket was assumed operating at O/F ratio of 2.34 with a nozzle expansion ratio of 6.14. Flight conditions considered were Mach number zero at ground level, Mach number 1.16 at altitude 5.06km and Mach number 2.9 at altitude 17.34km. Numerical results gave the understandings on the detailed plume structures at different altitude conditions. The diffusive effect of the thermal radiation on temperature field and the effect of chemical recombination during the expansion process could be also understood. By comparing the results from frozen flow and infinitely fast chemistry assumptions, the excess temperature of the exhaust gas resulting from the chemical recombination seems to be significant and cannot be neglected in the view point of performance, thermal protection and flow physics.
KARI 30톤급 액체 로켓 엔진 노즐 유동 화학 평형 해석
이대성(Dae-Sung Lee),강기하(Ki-Ha Kang),조덕래(D. -R. Cho),최정열(Jeong-Yeol Choi),최환석(H. -S. Choi) 한국추진공학회 2008 한국추진공학회지 Vol.12 No.3
Nozzle flow analyses of 30 ton<SUB>f</SUB>-class KARI liquid rocket engine for high altitude propulsion are carried out using a chemically frozen and equilibrium flow analysis code developed previously. It is considered that the combined frozen- and shifting- equilibrium analysis is cost-effective regarding the convergence characteristics and modeling uncertainties, though the non-equilibrium analysis is most reliable approach. A dependable performance prediction could be attainable through the present analyses that account for the recombination process and thermal and kinetic energy recovery during the expansion process with viscous effects.