• 한국연소학회:학술대회논문집
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• 2013.06a
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• pp.133-134
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• 2013

Gas turbine technology has steadily advanced since its inception and continues to evolve. Development is active in producing both smaller gas turbines and more powerful and efficient engines. However, it is shown that our state-of-the-art technologies for gas turbine developments remain at a basic level by comparisons with advanced technology countries. This paper shows that development process and preliminary design tools for gas turbine combustor were introduced as a first results of source technology secure researches for the gas turbine combustors.

• Proceedings of the Korean Society of Precision Engineering Conference
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• 2006.10a
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• pp.83-84
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• 2006

• Proceedings of the KIEE Conference
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• 1993.07b
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• pp.899-901
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• 1993

LARGE SYNCHRONOUS GENERATORS USED IN CONNECTION WITH COMPRESSOR, TURBINE, IN MOST CASE, NEED THE HELP OF AN ELECTRICAL DRIVES FOR STARTING IN GAS TURBINES. NOWDAYS, THE STATIC FREQUENCE CONVERTER STARTING SYSTEM is EMPLOYED IN POWER PLANT. THIS PAPER DESCRIBES TORQUE CONVERTER, STATIC FREQUENCY CONVERTER AND COMPARSION OF TWO SYSTEMS.

• Journal of Mechanical Science and Technology
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• v.17 no.6
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• pp.906-913
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• 2003

Lean premixed combustion has been considered as one of the promising solutions for the reduction of NOx emissions from gas turbines. However, unstable combustion of lean premixed flow becomes a real challenge on the way to design a reliable, highly efficient dry low NOx gas turbine combustor. Contrary to a conventional diffusion type combustion system, characteristics of premixed combustion significantly depend on a premixing degree of combusting flow. Combustion behavior in terms of stability has been studied in a model gas turbine combustor burning natural gas and air. Incompleteness of premixing is identified as significant perturbation source for inducing unstable combustion. Application of a simple convection time lag theory can only predict instability modes but cannot determine whether instability occurs or not. Low frequency perturbations are observed at the onset of instability and believed to initiate the coupling between heat release rate and pressure fluctuations.

• Proceedings of the Korean Institute of Intelligent Systems Conference
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• 1998.03a
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• pp.61-66
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• 1998

Since a gas turbine is made use of generating electricity for peak time, it is a very important to operate a peak time load with safety. The main components of a gas turbine are the compressor, the combustion chamber and the turbine. So, there also must be modeled a component of gas turbines for the control with safety but it is not easy. In this paper we acquire a transfer function based on the operations data of Gun-san gas turbine and study to apply Neural-Network 2-DOF PID controler to control loop of gas turbine to reduce phenomena caused by integral and derivative actions through simulation. We obtained satisfactory results to disturbances of subcontrol loop such as, fuel flow, air flow, turbine extraction temperature.

• 한국연소학회:학술대회논문집
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• 2013.06a
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• pp.113-116
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• 2013

The Samsung Techwin has been developed the various types of combustor and fuel nozzle frontal devices for the aero engine and small scale industrial gas turbines. Currently, we have been developed the highly heat capacity and long-lived gas turbine combustor based on the short-lived combustor and fuel injector technologies. In this paper, the market trends and the information on the survey of an advanced gas turbine combustor were introduced for the development of large scale gas turbine combustor and fuel nozzle assembly.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.30 no.5 s.248
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• pp.472-479
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• 2006

Recently, various methods have been developed to improve the performance of gas turbines for combined cycle power plants. This paper especially focused on the gas turbine with a reheat process. The purpose of this study is to analyze performance characteristics of a reheat-cycle gas turbine on both a design point and off-design operations. Results of the parametric study of this model show how operating and design parameters influence on the performance of the gas turbine. Moreover, possibilities for the analysis of off-design performance based on a self-generated compressor performance characteristic map are presented.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2010.10a
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• pp.507-508
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• 2010

• Proceedings of the Korean Institute of Surface Engineering Conference
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• 2006.04a
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• pp.101-102
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• 2006

• Journal of Mechanical Science and Technology
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• v.16 no.6
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• pp.839-850
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• 2002

A performance simulation program for the turboprop engine (PT6A-62), which is the power plant of the first Korean indigenous basic trainer KT-1, was developed for performance prediction, development of an EHMS (Engine Health Monitoring System) and the flight simulator. Characteristics of components including compressors, turbines, power turbines and the constant speed propeller were required for the steady state and transient performance analysis with on and off design point analysis. In most cases, these were substituted for what scaled from similar engine components'characteristics with the scaling law. The developed program was evaluated with the performance data provided by the engine manufacturer and with analysis results of GASTURB program, which is well known for the performance simulation of gas turbines. Performance parameters such as mass flow rate, compressor pressure ratio, fuel flow rate, specific fuel consumption and turbine inlet temperature were discussed to evaluate validity of the developed program at various cases. The first case was the sea level static standard condition and other cases were considered with various altitudes, flight velocities and part loads with the range between idle and 105% rotational speed of the gas generator. In the transient analysis, the Continuity of Mass Flow Method was utilized under the condition that mass stored between components is ignored and the flow compatibility is satisfied, and the Modified Euler Method was used for integration of the surplus torque. The transient performance analysis for various fuel schedules was performed. When the fuel step increase was considered, the overshoot of the turbine inlet temperature occurred. However, in case of ramp increase of the fuel longer than step increase of the fuel, the overshoot of the turbine inlet temperature was effectively reduced.