• Proceedings of the Korea Society for Energy Engineering kosee Conference
• /
• 1996.10b
• /
• pp.77-80
• /
• 1996

우리나라에서 피크부하용으로 사용하는 복합발전이 하계시에서 외기온도가 상승함에 따라 실제로는 정격출력을 내지 못하고 있다. 따라서 본 연구에서는 연료(LNG)의 냉열을 이용하여 가스터빈의 연소용공기를 냉각시킬 경우, 복합발전 시스템의 성능변화를 분석하기 위하여 시뮬레이션을 수행하였다. 그 결과 LNG의 냉열을 이용하여 연소용공기를 원하는 온도까지 냉각시킬 수 있음을 확인할 수 있었다. 또한 연소기로 연료를 투입하기전에 설계온도까지 예열시키는 열교환기를 통해 배기가스에 함유된 현열을 더욱 많이 회수하면서, 가스터빈 투입연료의 온도를 상승시킬 수 있어, 시스템효율이 더욱 상승함을 알 수 있었다. 결론적으로 외기온도가 변하는 경우에, 본 시스템의 도입을 위해서는 경제성분석과 더불어 열교환기 시스템의 최적합성이 추후 진행되어야 할 것이며, 이를 통해 최적의 발전시스템을 구성할 수 있으리라 생각된다.

• Journal of the Korean Society for Aviation and Aeronautics
• /
• v.14 no.1
• /
• pp.15-21
• /
• 2006

Parametric cycle analysis of a dual-spool, mixed exhaust turbofan engine with turbine blade cooling were described to investigate the effect of turbine blade cooling on the engine performance such as specific thrust and thrust specific fuel consumption. Coolant of low pressure turbine triggers high engine performance loss and cooling effect loss in high pressure turbine. Therefore low pressure turbine coolant should be much more considered for effective design.

• Transactions of the Korean Society of Mechanical Engineers
• /
• v.15 no.5
• /
• pp.1756-1762
• /
• 1991

본 연구에서는 막냉각되는 터빈블레이드에서의 열전달 계수를 측정하기 위하 여 열전달과 물질전달의 상사관계를 이용하였다.터빈블레이드의 선단을 다른 연구 에서와 마찬가지로 원봉으로 모사하였고, 원봉의 표면에 위치하고 있는 1열의 분사홀 로부터 제트가 분사될 때 분사홀 근처 및 그 하류에서의 물질 전달계수를 측정하기 위 해 나프탈렌승화법을 이용하였다. 분사홀 열의 위치를 정체점에서 하류방향으로 이 동시키면서, 물질전달계수의 변화를 연구하였고, 분사율(M=.rho.$_{j}$ U$_{j}$ /.rho.$_{\infty}$ U$_{\infty}$)의 영향도 고찰하였다.

• Proceedings of the Korea Society for Energy Engineering kosee Conference
• /
• 1997.10a
• /
• pp.3-8
• /
• 1997

본 연구에서는 복합발전시스템의 외기온도 변화로 인한 출력저하 문제를 극복할 수 있는 LNG 냉열 이용 복합발전 시스템을 제안하였다. 본 연구에 의해 제안된 LNG 냉열 이용 복합발전 시스템의 타당성을 검토하기 위해 ASPEN과 GateCycle을 이용한 시뮬레이션 모델을 구성하였고, 모델에 의해 예측한 결과를 실제 발전소 성능시험결과와 비교하여, 본 시뮬레이션 방법의 예측정확도를 검증하였다. 본 시뮬레이션 방법을 토대로 LNG 냉열을 이용하여 가스터빈의 유입공기를 냉각시켰을 경우의 복합발전 시스템 성능변화를 분석하였다. 그 결과 LNG 냉열을 이용하여 유입 공기를 원하는 온도까지 냉각시켜 하절기에도 출력을 일정하게 유지시킬 수 있음을 확인할 수 있었고, 이를 위한 기스터빈과 LNG 간의 열교환기 설계기준도 제시하였다.

• Transactions of the Korean Society of Mechanical Engineers A
• /
• v.29 no.7 s.238
• /
• pp.1013-1021
• /
• 2005

In this paper, we developed an automatic design optimization system for parametric shape optimization of cooling passages inside axial turbine blades. A parallel three-dimensional thermoelasticity finite element analysis code from an open source system was used to perform automatic thermal and stress analysis of different blade configuration. The developed code was connected to an evolutionary optimizer and built in a design optimization system. Using the optimization system, 279 feasible and optimal solutions were searched. It is provided not only one best solution of the searched solutions, but also information of variation structure and correlation of the 279 solutions in function, variable, and real design spaces. To explore design information, it is proposed a new interpretation approach based on evolutionary clustering and principal component analysis. The interpretation approach might be applicable to the increasing demands in the general area of design optimization.

• Journal of the Korean Society for Precision Engineering
• /
• v.15 no.9
• /
• pp.25-32
• /
• 1998

The forced cooling system is designed to shorten the overhaul time of steam turbine, which is important in view of economic concern of utility companies, Forced cooling of the hot turbine is achieved by suction of air flow into the turbine after the turbine shuts down. The heat transfer process by suction of air flow can cause thermal stress due to the thermal gradients. In this paper, the analysis of heat transfer is performed to calculate the air flow rate. Based on the prediction of cyclic fatigue damage and the experience, the cooling equipment is designed for shortening the cooling time of steam turbine.

• Transactions of the Korean Society of Mechanical Engineers B
• /
• v.26 no.9
• /
• pp.1249-1259
• /
• 2002

The present study investigates the convective heat/mass transfer inside a cooling passage of rotating gas-turbine blades. The rotating duct has various configurations made of ribs with 70。 attack angle, which are attached on leading and trailing surfaces. A naphthalene sublimation technique is employed to determine detailed local heat transfer coefficients using the heat and mass transfer analogy. The present experiments employ two-surface heating conditions in the rotating duct because the surfaces, exposed to hot gas stream, are pressure and suction side surfaces in the middle passages of an actual gas-turbine blade. In the stationary conditions, the parallel rib arrangement presents higher heat/mass transfer characteristics in the first pass, however, these characteristics disappear in the second pass due to the turning effects. In the rotating conditions, the cross rib present less heat/mass transfer discrepancy between the leading and the trailing surfaces in the first pass. In the second pass, the heat/mass transfer characteristics are much more complex due to the combined effects of the angled ribs, the sharp fuming and the rotation.

• Journal of computational fluids engineering
• /
• v.19 no.4
• /
• pp.14-19
• /
• 2014

This study conducts shape optimization of rib turbulator on the internal cooling passage that has triangular cross-section of high pressure turbine nozzle. During optimization, various types of rib turbulator including angled, V-shaped, A-shaped and angled rib with intersecting rib are considered. Each type of rib turbulator is parameterized with attack angle(s), rib height, spacing ratio and bending/intersecting location. For optimization, Design of Experiment (DOE) and Kriging surrogate model are used to utilize computational resource more efficiently and Genetic Algorithm (GA) is used to search the optimum points. As a result, Pareto front of each type of rib turbulator with friction factor that relates to pressure drop in cooling passage and spatially averaged Nusselt number that relates to heat transfer on the wall is drawn and optimum points on the Pareto front are suggested.

• Journal of Advanced Marine Engineering and Technology
• /
• v.36 no.8
• /
• pp.1050-1060
• /
• 2012

As an approach to high-efficiency of SOFC system, SOFC/GT Hybrid system is effective. However, if the output size of the system belongs to the marine class of dozens MWs, the introduction of the cooling system of GT system, which is used as sub-system, makes its related devices complicated and also makes its control difficult. Accordingly, for the marine use, SOFC/GT (non-cooling)Hybrid system looks more suitable than SOFC/GT(cooling)Hybrid system. This study established the SOFC/GT (non-cooling)Hybrid system, and examined the operating temperature & current density of the stack for the system, pressure ratio of the gas turbine, the influence of TIT(Turbine Inlet Temperature) on system performance, etc. through the simulation process. Through this research process, this study was able to confirm that electrical efficiency rises in spite of the increase in the required power for the air compressor, and there exists a limited range of temperatures for operation in TIT.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2010.05a
• /
• pp.304-310
• /
• 2010

Heat transfer coefficients in a dimpled channel, a ribbed channel, and a rip-dimple compound channel were measured by the transient liquid crystal technique. The channel aspect ratio, the rib height, the rip pitch, and the rib angle were 4:1, 6 mm, 60 mm and $60^{\circ}$, respectively. The dimple diameter and the center-to-center distance were 6mm and 7.2 mm, respectively, and the Reynolds number range was 30,000-50,000. Results showed that the heat transfer coefficients were increased by the angled rib. For the dimple-rib compound cooling cases, the heat transfer coefficients were further augmented and the thermal performance factor for the case was the highest.