• 한국추진공학회지
• /
• 제4권1호
• /
• pp.93-101
• /
• 2000

엔진 운용 중에 유로(flow Path)에 놓여 있는 팬 블레이드(blade)들은 많은 외부하중에 노출되어 있어서 고주기 피로(high cycle fatigue)에 의한 피로 파괴의 위험성이 크다. 그 중 가장 중요하게 평가되는 것이 주기적인 가진력에 의한 공진 현상과 그에 따른 피로파괴 가능성이다. 본 논문에서는 유동장 (flow field)이 지주(struts)에 의해 영향을 받게 되고, 이러한 유동장의 분포가 지주 후방에서 주기함수 형태로 팬 블레이드를 가진 할 때, 팬 블레이드에서의 진동 응답 특성과 구조적인 안정성을 평가하였다. 팬 블레이드의 피로강도를 시험적으로 평가하고, 팬 블레이드 전방 지주에 의한 공기 가진력을 가정하여 유한 요소 해석을 통한 구조적 안정성을 평가하였다. 그리고 엔진 시험에서 측정된 서지 압력 하중을 팬 블레이드의 유한요소 모델에 적용하여 구조적 영향을 평가함으로써 팬 블레이드의 구조적인 안정성을 확인하였다.

• Ocean Systems Engineering
• /
• 제1권1호
• /
• pp.17-28
• /
• 2011

The purpose of this paper is to demonstrate the efficacy of modeling a surface effect ship's air-cushion flexible seal utilizing a two-dimensional beam under steady state conditions. This effort is the initial phase of developing a more complex three-dimensional model of the air-seal-water fluid-structure interaction. The beam model incorporates the seal flexural rigidity and mass with large deformations while assuming linear elastic material response. The hydrodynamic pressure is derived utilizing the OpenFOAM computational fluid dynamic (CFD) solver for a given set of steady-state flow condition. The pressure distribution derived by the CFD solver is compared with the pressure required to deform the seal beam model. The air pressure, flow conditions and seal geometry are obtained from experimental analysis. The experimental data was derived from large-scale experimental tests utilizing a test apparatus of a canonical surface effect ship's flexible seal in a towing tank over a variety of test conditions.

• 한국추진공학회지
• /
• 제16권6호
• /
• pp.48-55
• /
• 2012

우주발사체 자세제어용 하이드라진 추력기의 지상연소시험을 수행하였다. 시험에 사용된 추력기는 추진제 주입압력 2.41 MPa (350 psia) 에서 정상상태 공칭추력 67 N (15 $lb_f$) 을 목표로 설계/제작 되었다. 개발모델 추력기의 성능특성 검토를 위해 정상상태 연소모드에서의 추력, 추진제 공급압력, 질량유량, 추력실 압력, 그리고 온도 등의 성능변수를 이용한다. 시험결과, 실제의 성능이 이론 요구규격 대비 89.1% 이상의 성능효율을 만족하는 것이 확인되었다.

• 한국추진공학회:학술대회논문집
• /
• 한국추진공학회 1997년도 제8회 학술강연회논문집
• /
• pp.43-51
• /
• 1997

Steady and unsteady numerical simulations are conducted for the experiments performed to investigate the ram accelerator flow field by using the expansion tube facility in Stanford University. Navier-Stokes equations for chemically reacting flows are analyzed by fully implicit and time accurate numerical methods with Jachimowski's detailed chemistry model for hydrogen-air combustion involving 9 species and 19 reaction steps. Although the steady state assumption shows a good agreement with the experimental schlieren and OH PLIF images for the case of $2H_2$+$O_2$+$17N_2$, it fails in reproducing the combustion region behind the shock intersection point shown in the case of $2H_2$+$O_2$+$12N_2$, mixture. Therefore, an unsteady numerical simulation is conducted for this case and the result shows all the detailed flow stabilization process. The experimental result is revealed to be an instantaneous result during the flow stabilization process. The combustion behind the shock intersection point is the result of a normal detonation formed by the intersection of strong oblique shocks that exist at early stage of the stabilization process. At final stage, the combustion region behind the shock intersection point disappears and the steady state result is retained. The time required for stabilization of the reacting flow in the model ram accelerator is found to be very long in comparison with the experimental test time.

• Nuclear Engineering and Technology
• /
• 제41권3호
• /
• pp.295-306
• /
• 2009

The subchannel grade void distributions in the NUPEC (Nuclear Power Engineering Corporation) BFBT (BWR Full-Size Fine-Mesh Bundle Tests) facility were evaluated with the subchannel analysis code MATRA and the system code MARS. Fifteen test series from five different test bundles were selected for an analysis of the steady-state subchannel void distributions. Two transient cases, a turbine trip without a bypass as a typical power transient and a re-circulation pump trip as a flow transient, were also chosen for this analysis. It was found that the steady-state void distributions calculated by both the MATRA and MARS codes coincided well with the measured data in the range of thermodynamic qualities from 5% to 25%. The results of the transient calculations were also similar and were highly feasible. However, the computational aspects of the two codes were clearly different.

• 한국전산유체공학회지
• /
• 제19권2호
• /
• pp.86-92
• /
• 2014

In this paper, prediction of separation trajectory for Two-stage-To-Orbit space launch vehicle has been numerically simulated by using an aerodynamic database based on steady state analysis. Aerodynamic database were obtained for matrix of longitudinal and vertical positions. The steady flow simulations around the launch vehicle have been made by using a 3-D RANS flow solver based on unstructured meshes. For this purpose, a vertex-centered finite-volume method was adopted to discretize inviscid and viscous fluxes. Roe's finite difference splitting was utilized to discretize the inviscid fluxes, and the viscous fluxes were computed based on central differencing. To validate this flow solver, calculations were made for the wind-tunnel experiment model of the LGBB TSTO vehicle configuration on steady state conditions. Aerodynamic database was constructed by using flow simulations based on test matrix from the wind-tunnel experiment. ANN(Artificial Neural Network) was applied to construct interpolation function among aerodynamic variables. Separation trajectory for TSTO launch vehicle was predicted from 6-DOF equation of motion based on the interpolated function. The result of present separation trajectory calculation was compared with the trajectory using experimental database. The predicted results for the separation trajectory shows fair agreement with reference[4] solution.

• 한국지반공학회:학술대회논문집
• /
• 한국지반공학회 1999년도 가을 학술발표회 논문집
• /
• pp.193-200
• /
• 1999

Since Broms and Bennermark(1967) suggested the face stability criterion based on laboratory extrusion tests and field observations, the face stability of a tunnel driven in cohesive material has been studied by several authors. And recently, more general solution for the tunnel front is given by Leca and Panet(1988). They adopted a limit state design concept to evaluate the face stability of a shallow tunnel driven into cohesionless material and showed that the calculated upper bound solution represented the actual behavior reasonably well. In this study, two factors are simultaneously considered for assessing tunnel face stability: One is the effective stress acting on the tunnel front calculated by upper bound solution; and the other is the seepage force calculated by numerical analysis under the condition of steady state ground water flow. The model tests were performed to evaluate the seepage force acting on the tunnel front and these results were compared with results of numerical analysis. Consequently, the methodology to evaluate the stability of a tunnel face including limit analysis and seepage analysis is suggested under the condition of steady state ground water flow.

• 한국소성가공학회:학술대회논문집
• /
• 한국소성가공학회 2001년도 춘계학술대회 논문집
• /
• pp.143-146
• /
• 2001

The evolution of dynamic recrystallization (DRX) was studied with torsion test for AISI 304 stainless steel in the temperature range of $900-1000^{\circ}C$ and strain rate range of 0.05-5/sec. The evolution of DRX was investigated with microstructural analysis and change of flow stress curve slope. The investigation of serrated grain boundaries using electron back scattered diffraction (EBSD) analysis indicated that the nucleated new DRX grain size was similar to the size of bulging part. Before the steady state, the dynamically recrystallizing grains do not remain a constant size and gradually grow to the size of fully DRX grain at steady state. The calculation of grain size was based on $X_{DRX}$ and the assumption, which the nucleated DRX grains are growing to the steady state, continuously. It was found that the calculated results agreed with the microstructure of the alloy.

• Archives of Pharmacal Research
• /
• 제21권4호
• /
• pp.411-417
• /
• 1998

In order to investigate the effect of the pretreatment with various doses of diltiazem (DTZ) on the pharmacokinetics of indocyanine green (ICG) at steady state, especially the hepatic blood clearance due to the change of hepatic blood flow, the following experiments were carried out with ICG, a hepatic function test marker, not metabolized in liver and only excreted in bile. The intravenous bolus injection ($3,780\mu\textrm{g}$/kg) and the constant-rate infusion ($10,100\mu\textrm{g}$/kg/hr) of ICG into the left femoral vein were made in order to check the steady-state plasma concentration ($C_{ss} of $10\mu\textrm{g}$/ml) of ICG at 20, 25 and 30 min. Following a 90-min washout period, the intravenous bolus injection (108, 430, 860 and $1,720\mu\textrm{g}$/kg) and the constant-rate infusion (108, 433, 866 and $1,730\mu\textrm{g}$/kg/hr) of DTZ into the right femoral vein were made and the achievement of the steady-state plasma levels ($C_{ss} of 50, 200, 400 and 800 ng/ml) of DTZ were conformed at 60, 70 and 80 min. During the steady state of DTZ, the intravenous bolus injection ($3,780\mu\textrm{g}$/kg) and the constant-rate infusion ($10,200\mu\textrm{g}$/kg/hr) of ICG into the left femoral vein were made and also the steady-state plasma concentration of ICG was checked at 20, 25 and 30 min. The plasma concentrations of DTZ and ICG were determined using a high performance liquid chromatographic technique. At the steady state, the hepatic blood clearance of ICG was obtained from the plasma concentration and blood-to-plasma concentration ratio ($R_B$) of ICG. The pretreatment with various doses of DTZ did not influence the plasma concentrations, $R_B$ and plasma free fraction ($f_p$) of ICG. So the hepatic blood clearance of ICG was independent of concentration of DTZ. The hepatic blood clearance of ICG could be affected by both hepatic bood flow and hepatic intrinsic clearance. But there was no change of the hepatic blood clearance of ICG between the control and the DTZ-pretreated rats in this study. So it may be suggested that DTZ does not influence hepatic blood flow.

• International Journal of Fluid Machinery and Systems
• /
• 제8권3호
• /
• pp.155-168
• /
• 2015

No-load speed is an important performance factor for the safe operation of hydropower systems. In turbine design, the manufacturers must conduct several model tests to calculate the accurate value of no-load speed for the complete range of operating conditions, which are expensive and time-consuming. The present study presents steady and unsteady methods for calculating no-load speed of a Francis turbine. The steady simulations are implemented using a commercial flow solver and an iterative algorithm that relies on a smooth relation between turbine torque and speed factor. The unsteady method uses unsteady RANS simulations that have been integrated with a user subroutine to compute and return the value of runner speed, time step and friction torque. The main goal of this research is to evaluate and compare the two methods by calculating turbine dynamic parameters for three test cases consisting of high and medium head Francis turbines. Overall, the numerical results agreed well with experimental data. The unsteady method provided more accurate results in the opening angle range from 20 to 26 degrees. Nevertheless, the steady results showed more consistency than unsteady results for the three different test cases at different operating conditions.