Kuisoon Kim

TRANSIENT ANALYSIS OF THERMO-FLUID PHENOMENA IN TWIN-ROLL CONTINUOUS CASTING

Abstract A computer programme has been developed for analyzing the two-dimensional, unsteady conservation equations for transport phenomena in the molten region of twin-roll continuous casting in order to describe the velocity, and temperature fields, and the solidifiaation process of the molten steel. The energy equation of the cooling roll is solved simultaneously with the conservation equations of molten steel in order to consider heat transfer through the cooling roll. The governing equations are expressed in the generalized coordinates to consider the characteristics of a rotating bank between twin-rollers. In the molten region, it is predicted that transient recirculating flows with small and large vortices are located in the vicinity of the middle of the twin-rollers. The temperature field is affected by the flow fields, showing the complete two-dimensional pattern. The solidification pattern in the molten steel and the temperature distribution in the cooling roll are also obtained as a function of time.

Numerical Studies of Supersonic Planar Mixing and Turbulent Combustion using a Detached Eddy Simulation (DES) Model

We present a simulation of a hybrid Reynolds-averaged Navier Stokes / Large Eddy Simulation (RANS/LES) based on detached eddy simulation (DES) for a Burrows and Kurkov supersonic planar mixing experiment. The preliminary simulation results are checked in order to validate the numerical computing capability of the current code. Mesh refinement studies are performed to identify the minimum grid size required to accurately capture the flow physics. A detailed investigation of the turbulence/chemistry interaction is carried out for a nine species 19-step hydrogen-air reaction mechanism. In contrast to the instantaneous value, the simulated time-averaged result inside the reactive shear layer underpredicts the maximum rise in H₂O concentration and total temperature relative to the experimental data. The reason for the discrepancy is described in detail. Combustion parameters such as OH mass fraction, flame index, scalar dissipation rate, and mixture fraction are analyzed in order to study the flame structure.

Performance Analysis and Optimal Design of Heat Exchangers Used in High Temperature and High Pressure System

A computational study for the optimal design of heat exchangers (HX) used in a high temperature and high pressure system is presented. Two types of air to air HX are considered in this study. One is a single-pass cross-flow type with straight plain tubes and the other is a twopass cross-counter flow type with plain U-tubes. These two types of HX have the staggered arrangement of tubes. The design models are formulated using the number of transfer units (e - NTU method) and optimized using a genetic algorithm. In order to design compact light weight HX with the minimum pressure loss and the maximum heat exchange rate, the weight of HX core is chosen as the object function. Dimensions and tube pitch ratio of a HX are used as design variables. Demanded performance such as the pressure loss (Δ P) and the temperature drop (Δ T) are used as constraints. The performance of HX is discussed and their optimal designs are presented with an investigation of the effect of design variables and constraints.

An Approach for the Integrated Performance Analysis of a Small Turbofan engine with Variable Inlet Guide and Variable Stator Vane

The present study is aimed to develop an integrated performance analysis approach for the application of a compressor with variable inlet guide vane (VIGV) and vairable stator vane (VSV) in a small turbofan engine. For the integrated analysis approach, an engine performance analysis program, NPSS and a computer program used for predicting of axial flow compressor performance based on stage stacking method, STGSTK were linked with an optimisation package, Isight. This enables off-design performance analysis for the turbofan engine with VIGV and VSV hence provides the capability to predict stable operation condition of the engine with acceptable surge margin.

A Preliminary Design of Flight Test Conditions for a Sub-scale RBCC Engine using a Sounding Rocket

Various R&D programs for rocket-based combined cycle (RBCC) engines have progressed worldwide for the space development and the defense applications. As a way toward indigenous domestic RBCC program, a preliminary design of flight test conditions was studied in this study for a sub-scale RBCC engine using a sounding rocket. Launch and flight profiles were calculated for several booster options and compared with that of HyShot II program. The result shows that the Korea Sounding Rocket-II (KSR-II) is a proper candidate to perform the flight test available in Korea. The recommend flight test conditions with KSR-II are Mach 6.0 with a test vehicle of 230 kg and Mach 7.4 with 50 kg. Present study will soon be followed by a design of sub-scale RBCC for a flight test using a sounding rocket.

Rotor Blade Sweep Effect on the Performance of a Small Axial Supersonic Impulse Turbine

In this paper, a computational study was conducted in order to investigate the rotor blade sweep effect on the aerodynamics of a small axial supersonic impulse turbine stage. For this purpose, three-dimensional unsteady RANS simulations have been performed with three different rotor blade sweep angles (-15°, 0°, +15°) and the results were compared with each other. Both NTG (No tip gap) and WTG (With tip gap) models were applied to examine the effect on tip leakage flow. As a result of the simulation, the positive sweep model (+15°) showed better performance in relative flow angle, Mach number distribution, entropy rise, and tip leakage mass flow rate compared with no sweep model. With the blade static pressure distribution result, the positive sweep model showed that hub and tip loading was increased and midspan loading was reduced compared with no sweep model while the negative sweep model (-15°) showed the opposite result. The positive sweep model also showed a good aerodynamic performance around the hub region compared with other models. Overall, the positive sweep angle enhanced the turbine efficiency.

Fabrication and Performance Evaluation of Temperature Sensor Matrix Using a Flexible Printed Circuit Board for the Visualization of Temperature Field

This paper presents the fabrication and performance measurement of a temperature sensor array on a flexible substrate attachable to a curved surface using MEMS technology. Specifically, the fabrication uses the well-developed printed circuit board fabrication technology for complex electrode definition. The temperature sensor array are lifted off with a matrix in a to visualize temperature distribution. Copper is used as temperature sensing material to measure the change in resistances with temperature increase. In a thermal oven with temperature control, the temperature sensor array is Characterized. The constant slope of resistance change is obtained and temperature distribution is measured from the relationship between resistance and temperature.

An Experimental Study on the Flow Characteristics ofa Supersonic Turbine Cascade as Pressure Ratio

In this paper, a small supersonic wind tunnel was designed and built to study the flow characteristics of a supersonic impulse turbine cascade by experiment. The flow was visualized by means of a single pass Schlieren system. The supersonic cascade with 3-dimensional supersonic nozzle was tested over a wide range of pressure ratio. Highly complicated flow patterns including shocks. nozzle-cascade interaction and shock boundary layer interactions were observed.

A Numerical Study on a Supersonic Turbine Performance Characteristics with Different Nozzle-Rotor Axial Gap Spacings

ABSTRACT In this study, 3-dimensional URANS simulation was performed t o analyze the effect of the nozzle-rotor axial gap spacing of a supersonic impulse turbine on turbine performance. The computations were conducted for four different axial gap cases corresponding to about 6%, 10%, 20% and 30% of the blade height, respectively. The results show a good agreement with previous studies and the turbine efficiency decreases drastically in certain range. It is examined that the turbine performance characteristics could change depending on the influ ence of leading edge shock to the nozzle outlet. It is also found that the entropy rise distribut ions along the span differ from each other. 초 록 본 연구에서는 초음속 충동형 터빈의 노즐과 1단 로터 사이 축 간극 거리를 달리하며 3차원 비정상 유동해석을 수행하고 초음속 터빈의 성능 특성을 분석하였다. 계산결과는 기존의 초음속 터빈 효율 경향과 잘 일치하였으며 특정 축 간극 구간에서 효율의 급격한 감소를 보이고 그 이후에는 큰 변화가 없는 구간이 존재함을 확인하였다. 로터 앞전에서 발생하는 충격파의 영향이 노즐 끝단에 전달이 되는 정도에 따라 터빈 내의 여러 성능 특성이 달라짐을 살펴보았고 터빈 스팬 별 손실 특성에서 축 간극이 커질수록 허브 영역에서의 손실이 증가하고 미드스팬 이상의 영역에서 손실이 감소함을 보였다.Key Words:Turbopump(터보펌프), Supersonic Turbine(초음속 터빈), Nozzle-rotor Axial Gap(노즐-로터 축 간극), Unsteady Flow(비정상 유동), Turbine Performance(터빈 성능)Received 13 March 2015 / Revised 11 May 2015 / Accepted 14 May 2015

A Comparative Study of Numerical Methods on Aerodynamic Characteristics of a Compressor Rotor at Near-stall Condition

The present work performs three-dimensional flow calculations based on Reynolds Averaged Navier-Stokes (RANS) and Delayed Detached Eddy Simulation (DDES) to investigate the flow field of a transonic rotor (NASA Rotor 37) at near-stall condition. It is found that the DES approach is likely to predict well the complex flow characteristics such as secondary vortex or turbulent flow phenomenon than RANS approach, which is useful to describe the flow mechanism of a transonic compressor. Especially, the DES results show improvement of predicting the flow field in the wake region and the model captures reasonably well separated regions compared to the RANS model. Besides, it is discovered that the three-dimensional vortical flows after the vortex breakdown from the rotor tip region are widely distributed and its vortex structures are clearly present. Near the rotor leading edge, a part of the tip leakage flows in DES solution spill over into next passage of the blade owing to the separation vortex flow and the backflow is clearly seen around the trailing edge of rotor tip. Furthermore, the DES solution shows strong turbulent eddies especially in the rotor hub, rotor tip section and the downstream of rotor trailing edge compared to the RANS solution.