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초음속난류유동장에서 후향계단 후류의 측면제트분사에 대한 수치적연구
김종록(J.R. Kim),김재수(J.S. Kim) 한국전산유체공학회 2002 한국전산유체공학회 학술대회논문집 Vol.2002 No.-
This paper describes numerical research on transverse jet behind rearward-facing step in turbulent supersonic flowfields without chemical reaction. The purpose of transverse jet behind rearward-facing step is to improve mixing of the fuel in the combustor. Two-dimensional unsteady flowfields generated by slot injection into supersonic flow are numerically simulated by integration of Navier-Stokes equation. Final-scale turbulence effects are modeled with two-equation k- E model. Numerical methods are modeled high-order upwind TVDschemes. A total of 4 cases are computed, comprising slot momentum flux ratios at four step heights downstream of the step. These numerical results are represented periodic phenomenon in unsteady flowfields.
적응 격자계를 이용한 초음속 난류유동장의 측면제트분사에 대한 수치적연구
김종록(J.R. Kim),김익태(I.T. Kim),김재수(J.S. Kim) 한국전산유체공학회 2001 한국전산유체공학회지 Vol.6 No.2
Two-dimensional steady flowfields generated by slot injection into supersonic flow are numerically simulated by the integration of Navier-stokes equation with two-equation k-turbulence model. High-order upwind scheme is used on unstructured adaptive meshes. The numerical results are compared with experimental data in terms of surface static pressure distributions, the length of the upstream separation region, and the height of the Mach surface for steady flowfields with a Mach number of 3.71 and a unit Reynolds number of 5.83×10^6/m.
역류제트를 이용한 센터바디 디퓨져의 열차폐 특성에 관한 연구
김종록(J.R. Kim),이경환(K.H. Lee),김재수(J.S. Kim) 한국전산유체공학회 2017 한국전산유체공학회지 Vol.22 No.2
In the development of liquid-propellant rocket engines, it is important to simulate high-altitude environments and verify the performance of the engines in these environments. Supersonic diffusers are the most important technology in high-altitude simulation facilities. Using the thermal protection system based on the counter-flow jet, as proposed in this study, the cooling efficiency of the CBD(center-body diffusers) can realize an efficient high-altitude simulation facility for the liquid-propellant rocket engine. The analysis for the supersonic flow with a counter-flow jet was performed by experimental and numerical methods. The thermal protection effect by the counter-flow jet in the center body diffuser was analyzed by a numerical method. When the pressure ratio of counter-flow jet injection is less than 0.5, the cooling effect is insignificant, but when the pressure ratio is 1.0 or more, the cooling effect is more than 1000K.
스피닝 공정을 이용한 스터브엔드의 제조방법에 대한 연구
전종원(J. W. Jeon),조종래(J. R. Cho),홍린표(L. P. Hong),김재수(J. S. Kim),최진영(J. Y. Choi) 한국소성가공학회 2013 한국소성가공학회 학술대회 논문집 Vol.2013 No.5
The spinning method was used for developing the connection component of pipe flanges. Generally lab joint is manufactured by welding that pipe is jointed with flange plate. However, this method requires large amounts of time and money due to the pipe and the thick-plate production of individual through the process; cutting, welding and finishing. The defects in the process may occur due to thermal deformation and mistake of operator. In order to solve this problem, the manufacturing method using spinning process of integrated stub-end is developed. The objective of this paper is to study how to manufacturing the stub-end from initial pipe by spinning process. ALE finite element method is used to solve the element rotation problem. FE simulation was performed by the commercial code Forge 2011. The key technology is that flange thickness is not thinner than initial pipe. In addition, it also form a rectangular part and round part.