• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2006.11a
• /
• pp.289-292
• /
• 2006

In this paper, the hybrid algorithm of Support Vector Machine md Artificial Neural Network is used for the defect diagnostics algorithm for the aircraft turbo-shaft engine. The results of learning of ANN, especially, accuracy or speed of convergence are sensitive to the number of data, so a comparison between design point and off-design area, especially, Mach number and fuel flow variable area, is essential research. From application results for diagnostics of gas turbine engine, it was confirmed that the hybrid algorithm could detect well in the of-design area as well as design point.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.9 no.2
• /
• pp.17-24
• /
• 2005

In this study, the GSP and in-house numerical codes have been used for analyses of the on-design, static off-design and dynamic off-design performances. Through the various missions including altitude, velocity, and power variations the static engine performance have been investigated. The dynamic engine performances based on these complicated variations have been also analyzed. Especially, the power, engine rpm and heat overload characteristics of the turbine have been estimated with the response time through the control of the throttle setting rather than the power setting. It could be applied to the FADEC system as an engine control device.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.15 no.5
• /
• pp.54-59
• /
• 2011

Reliable starting capability of a gas turbine engine calls the engine industry's attention recently. So far the gas turbine engine performance researches have focused on the range between idle to Max rpm, but recent attention on the starting has brought interests in the range of "Sub-dile". As component characteristic maps are essential for the starting research, various kinds of studies have been doing and proposing ways to expand the existing maps toward sub-idle range. In this paper, previous studies were discussed and a new method suggested and validated.

• Proceedings of the Korean Vacuum Society Conference
• /
• 2014.02a
• /
• pp.261.1-261.1
• /
• 2014

지구상에 존재하는 모든 생물에 의해 배출되는 이산화탄소는 온실가스로써 산업혁명 이후 급격한 농도 증가로 인해 지구 온난화 등의 다양한 환경문제를 초래하고 있다. 지구 온난화의 가시화로 인한 각종 기후 협약 및 탄소배출권 등에 규제로 온실가스 감축의무부과가 확실해져 탈 석유기반 사회로 전환을 위한 이산화탄소를 처리하는 다양한 연구가 각국에서 활발히 진행 중이다. 본 연구에서 마이크로웨이브 플라즈마 토치를 이산화탄소 분해에 이용하게 되었고 그 목적은 이산화탄소가스를 마이크로웨이브로 가열하여 순수한 이산화탄소 플라즈마 토치를 발생함으로서 지구 온난화의 주범인 이산화탄소를 생산적으로 이용하기 위한 것으로 전자파를 발진하는 마그네트론으로는 3kW, 2.45GHz의 주파수를 사용한다. 마이크로웨이브 플라즈마 토치를 이용한 이산화탄소의 분해 시 생성되는 물질을 확인하기 위하여 이산화탄소의 열역학적 평형을 계산하였으며 또한 이산화탄소의 분해 반응의 준 평형상태에서의 속도상수를 이용하여 각 분해반응생성물들의 밀도비율을 계산하였고, 이를 일반화시켜 도시하였다. 위 과정을 통해 고온의 이산화탄소 토치는 탄화수소 연료를 1기압에서 개질할 수 있음을 알 수 있다. 예를 들어 메탄개질은 $CO_2+CH_4{\rightarrow}2CO+2H_2$의 반응식이 된다. 이때 엔탈피와 엔트로피 변화는 각 각 ${\Delta}H=247kJ/mole$과 ${\Delta}S=257J/mole/deg.$이며 이 반응에 대한 gibbs 자유에너지는 $G={\Delta}H-T{\Delta}S$로서 개질 자발반응이 일어나는 온도는 $T={\Delta}H/{\Delta}S=961K$가 된다. 그리고 탄화수소 개질에 참여하는 산소와 CO 라디칼의 밀도가 대단히 높다. 따라서 메탄개질은 이산화탄소 토치를 통하여 1기압에서 쉽게 이루어진다.

• The KSFM Journal of Fluid Machinery
• /
• v.2 no.1 s.2
• /
• pp.7-14
• /
• 1999

This simulation method is developed by using GateCycle code for the performance evaluation of the gas turbine in IGCC(Integrated Gasification Combined Cycle) power plant that uses clean coal gas fuel derived from coal gasification and gas clean-up processes and it is integrated with ASU(Air Separation Unit). In the present simulation method, thermodynamic calculation procedure is incorporated with compressor performance map and expander choking models for considering the off-design effects due to coal gas firing and ASU integration. With the clean coal gases produced through commercially available chemical processes, their compatibility as IGCC gas turbine fuel is investigated in the aspects the overall performance of the gas turbine system. The predictions by the present method show that the reduction of the air extraction from gas turbine to ASU results in a remarkable increase in the efficiency and net power of gas turbines, but it is accompanied with a shift of compressor operation point toward to surge limit. In addition, the present analysis results reveal the influence of compressor performance characteristics of gas turbine have to be carefully examined in designing the ASU integration process and evaluating the overall performance parameters of the gas turbine in IGCC Power plant.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.13 no.6
• /
• pp.1-7
• /
• 2009

The gas turbine engine performance is greatly relied on its component performance characteristics. Generally, acquisition of component maps is not easy for engine purchasers because it is an expensive intellectual property of gas turbine engine supplier. In the previous work, the maps were inversely generated from engine performance deck data, but this method is limited to obtain the realistic maps due to calculated performance deck data. Therefore this work proposes newly to generate more realistic compressor map from experimental performance test data. And then a realistic compressor map can be generated form those processed data using the proposed extended scaling method at each rotational speed. Evaluation can be made through comparison between performance analysis results using the performance simulation program including the generated compressor map and on-condition monitoring performance data.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2010.11a
• /
• pp.694-699
• /
• 2010

Reliable starting capability of a gas turbine engine calls the engine industry's attention recently. So far the gas turbine engine performance researches have focused on the range between idle to Max rpm, but recent attention on the starting has brought interests in the range of "Sub-dile". As component characteristic maps are essential for the starting research, various kinds of studies have been doing and proposing ways to expand the existing maps toward sub-idle range. In this paper, previous studies were discussed and a new method suggested and validated.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.33 no.6
• /
• pp.64-70
• /
• 2005

The overall results of hot firing tests of fuel-rich gas generator with impinging injector at design and off-design points are described. The gas generator consists of an injector head with impinging injector, a water cooled combustor wall, a turbulence ring to enhance mixing, an instrument ring measuring temperature and pressure and a nozzle. The combustion tests were successfully performed without damage of gas generator. Test results show that the outlet temperature is not dependent on residence time of hot gas within 4～6msec but dependent on chamber pressure. The relation between outlet temperature and combustion efficiency resulting from measured pressure, mass flow rate and area of nozzle throat is shown. The overall O/F ratio is the critical parameter to determine the outlet temperature and the linear correlation between two parameters is established.

• Journal of the Korean Institute of Gas
• /
• v.22 no.6
• /
• pp.34-39
• /
• 2018

Natural gas is attracting attention as an alternative to existing fossil fuels. Natural gas has a high octane number. Therefore, knocking does not occur even if the compression ratio is increased, so that the thermal efficiency and the output can be improved. And it is relatively easy to apply the natural gas supply system to the internal combustion engine hardware system. In this study, a gasoline direct injection turbo engine was converted into a natural gas port injection type turbo engine. Therefore, the combustion and performance of the engine are measured and compared comprehensively in the region where the turbo operates.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2009.05a
• /
• pp.11-17
• /
• 2009

Hot-fire test of a turbopump for a gas generator cycle rocket engine of 30 ton class was carried out in real propellant environment. Liquid oxygen and kerosene were used for the oxidizer pump and the fuel pump, respectively, while hot gas produced by the gas generator was supplied to the turbine. A part of the propellant discharged from the pumps was provided to the gas generator. The turbopump was run stably at both on-design and off-design conditions, satisfying all the performance requirements. This paper describes one of the test cases, where the turbopump was run for 120 seconds at three different operating modes in one test. In terms of performance characteristics of pumps and turbine, the results from turbopump assembly test using real propellant showed a good agreement with those from the turbopump component tests using simulant working fluid.