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증기 터빈 노즐에서의 익단 간극에 의한 3차원 유동장의 수치 해석적 연구
조수용,오군섭,김수용,윤의수,Jo, Su-Yong,O, Gun-Seop,Kim, Su-Yong,Yun, Ui-Su 한국기계연구원 1995 硏究論文集 Vol.25 No.-
Three-dimensional incompressible turbulent flow fields within the passage of the steam turbine nozzle with/without tip clearance have been simulated by solving the Navier-Stokes equations with SIMPLE scheme. The extended k-e model is applied to modeling the Reynolds stresses. Grids in the computational domain are generated by solving the Poisson's equations to improve the smoothness and orthogonality. Flow losses, secondary flow, velocity profiles, and deviation angles are obtained. The computated results without tip clearance show good agreement with the experimental data.
Circular-to-Rectangular Transition Duct 내부의 3차원 유동장에 관한 연구
조수용,정희택,손호재,Jo, Su-Yong,Jeong, Hui-Taek,Son, Ho-Jae 한국전산유체공학회 1998 한국전산유체공학회지 Vol.3 No.2
Predictive behaviors by the extended k-${\varepsilon}$ turbulence model and the standard k-${\varepsilon}$ turbulence model are compared. Grid dependency is tested with the H-type grid as well as the O-type grid. Computations have been performed on a circular-to-rectangular transition duct. The Reynolds number is 390,000 based on the bulk velocity at the inlet. The computed axial velocity contours, transverse velocity profiles, static pressure contours, peripheral skin friction coefficient, peripheral wall static pressure distributions and turbulence kinetic energy have been compared with experimental results. The computed results than those obtained with the standard k-${\varepsilon}$ turbulence model. Comparing to the computed results obtained with the H-type grid and O-type grid, those with H-type grid seem to agree well with experimental results.
50KW 터보제너레이터용 가스터빈 엔진의 설계점/ 탈설계/과도성능해석
김수용,박무룡,조수용,Kim, Su-Yong,Park, Mu-Ryong,Jo, Su-Yong 한국기계연구원 1997 硏究論文集 Vol.27 No.-
Present paper describes on/off design performance of a 50KW turbogenerator gas turbine engine for hybrid vehicle application. For optimum design point selection, relevant parameter study is carried out. The turbogenerator gas turbine engine for a hybrid vehicle is expected to be designed for maximum fuel economy, ultra low emissions, and very low cost. Compressor, combustor, turbine, and permanent-magnet generator will be mounted on a single high speed (82,000 rpm) shaft that will be supported on air bearings. As the generator is built into the shaft, gearbox and other moving parts become unnecessary and thus will increase the system's reliability and reduce the manufacturing cost. The engine has a radial compressor and turbine with design point pressure ratio of 4.0. This pressure ratio was set based on calculation of specific fuel consumption and specific power variation with pressure ratio. For the given turbine inlet temperature, a rather conservative value of $1100^\circK$ was selected. Designed mass flow rate was 0.5 kg/sec. Parametric study of the cycle indicates that specific work and efficiency increase at a given pressure ratio and turbine inlet temperature. Off design analysis shows that the gas turbine system reaches self operating condition at N/$N_{DP}$ = 0.53. Bleeding air for turbine stator cooling is omitted considering low TIT and for a simple geometric structure. Various engine performance simulations including, ambient temperature influence, surging at part load condition. Transient analysis were performed to secure the optimum engine operating characteristics. Surge margin throughout the performance analysis were maintained to be over 80% approximately. Validation of present results are yet to be seen as the performance tests are scheduled by the end of 1998 for comparison.
74 KW급 터보축 싸이클 산업용 가스터빈 엔진의 성능 예측
김수용,윤의수,조수용,오군섭,Kim, Su-Yong,Yun, Ui-Su,Jo, Su-Yong,O, Gun-Seop 한국기계연구원 1996 硏究論文集 Vol.26 No.-
Present paper describes on/off design performance analysis of an 74KW industrial turboshaft gasturbine engine. Procedures to match between the compressor, combustor and turbine have been incorporated into the developed program satisfying compatibility requirement of flow and work and ratational speed. The validity of the performance results from the developed program are yet to be proved through performance experiments of the resultant engine, but comparison of the present results with those from "GASCAN(Thermoflow:America) under similar mass inlet flow, pressure ratio, and speed condition show good agreement despite present results underpredict 6-10% for power and up to 3% in efficiency, respectively.