• Journal of the KSME
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• v.33 no.1
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• pp.3-13
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• 1993

열에너지를 기계에너지로 변환하여 다시 전기에너지로 변환시켜 전기를 생산하는 발전설비로는 원자력발전, 석탄-석유 화력발전이 주종을 이루고 있으나 최근에는 원자력안전과 폐기물 처리 문제 및 화력발전의 엄격한 환경공해 규제의 제약 때문에 청전연료를 사용하는 가스터빈을 응 용한 고효율 복합 발전설비가 점차 각광을 받기 시작하고 있다. 최근에 국내에서도 국책 연구 과제로 고효율 가스터빈 연구개발이 진행되고 있고 가스터빈 제작에 대기업체의 참여와 관심이 증가되고 있는 것은 다행한 일이며 이러한 체제에 가스터빈 이해에 다소나마 도움이 되고자 그 현황과 전망에 대하여 살펴보고자 한다.

• Proceedings of the KIEE Conference
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• 2015.07a
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• pp.1054-1055
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• 2015

진동 수주형 파력발전 시스템(oscillating water column wave energy converter)의 효율을 증대할 수 있는 터빈의 최대 효율 추종 제어기를 제안한다. 진동 수주형 파력발전 시스템은 캡처 챔버(capture chamber)와 터빈, 발전기로 구성되어 있으며 발전기 말단에 연결된 저항의 값을 제어 입력으로 삼는다. 본 논문에서는 파력발전 시스템의 캡처 챔버와 터빈의 동역학 모델에 대해 소개하고, 터빈의 최대 효율 추종 제어기의 안정성을 증명하고 이를 JONSWAP 모델의 비규칙 파랑 조건하에서 시뮬레이션 하여 제어기 성능을 입증한다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.117-121
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• 2008

The effect of tip clearance on the performance of a supersonic impulse turbine was investigated experimentally. Test was performed using high pressure air in wide ranges of pressure ratio and rotational speeds. Test revealed that efficiency gradient of the subject turbine at a reference test point was a very low value of 0.05. Turbine efficiency was varied non-linearly with respect to tip clearance. It has been found that efficiency gradient is proportional to the cube of rotational speed at a fixed turbine pressure ratio. It also has been found that efficiency gradient shows its minimum at a reference test pressure ratio irrespective of rotational speeds.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.35 no.4
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• pp.399-407
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• 2011

This study analyzes the performance of hybrid power systems combining a solid oxide fuel cell (SOFC) and a gas turbine (GT). Research focus is given to the influence of the size-dependent gas turbine performance on hybrid system performance. Three hybrid systems adopting different gas turbines (kW, sub-MW, multi-MW classes) are designed. As the gas turbine power increases (i.e. as the gas turbine performance enhances), the gas turbine power portion increases and the hybrid system efficiency increases. The hybrid system shows efficiency improvement over the SOFC only system even in the case where the gas turbine net power is nearly zero. The increase of gas turbine pressure ratio contributes to the net hybrid system power output in all of the three cases, while system efficiency is almost independent on the pressure ratio.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.40 no.3
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• pp.139-148
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• 2016

Thermodynamic analysis is conducted on the first-order approximation model for turbines and compressors. It is shown that the adiabatic efficiency could be greater than unity, depending on the entropic mean temperature, entropy generation, thermal reservoir temperature, and heat transfer. Therefore, adiabatic efficiency applied to a diabatic control volume results in an error overestimating its performance. To resolve this overestimation, it is suggested that a reversible diabatic process be referred to as an ideal process to evaluate diabatic efficiency. The diabatic efficiency suggested in this work is proven to always be less than unity and it is smaller than the exergy efficiency in most cases. The diabatic efficiency could be used as a more general definition of efficiency, which would include adiabatic efficiency.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.4
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• pp.99-105
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• 2002

The performance test of an axial-type turbine is carried out with various axial gap distances between the stator and rotor. The turbine is operated at the low pressure and speed, and the degree of reaction is 0.373 at the mean radius. The axial-type turbine consists of ons-stage and 3-dimensional blades. The chord length of rotor is 28.2mm and mean diameter of turbine is 257.56mm. The power of turbo-blower for input power is 30kW and mass flow rate is $340m^3$/min at 290mmAq static-pressure. The RPM and output power are controlled by a dynamometer connected directly to the turbine shaft. The axial gap distances are changed from a quarter to three times of stator axial chord length, and performance curves are obtained with 9 different axial gaps. The efficiency varies about 8% of its peak value due to the variation of axial gap on the same non-dimensional mass flow rate and RPM, and experimental results show that the optimum axial gap is 1.6-1.9Cx.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.145-148
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• 2008

Korea Aeronautics Research Institute (KARI) is developing a turbo pump that has 1-stage impulse turbine and relatively high tip clearance for safety. The objective of this research is to investigate the effect of reaction on tip clearance loss in axial turbines. Both cascades were tested in a subsonic wind tunnel. In each cascade, total pressure was measured for tip clearance ranging from 1% to 20% of chord. In results, increasing tip clearance, total pressure loss in reaction turbines is continually increased but impulse turbines keep almost same level of mass averaged total pressure loss. When tip clearance becomes more than 10% of chord, mass-averaged total pressure loss in impulse turbines is less than in reaction. This means that when tip clearance is more than 10% of chord, impulse turbines have better efficiency than reaction turbines.

• Journal of Energy Engineering
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• v.9 no.3
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• pp.157-162
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• 2000

기존의 IGCC의 장점인 고효율 플랜트의 특성을 살리기 위해 고온정제를 적용하는 경우 조건변화에 따른 플랜트 성능의 영향을 관찰하고자 본 연구를 수행하였다. IGCC에 고온정제 공정을 적용하여 구성한 모델은 연구 목적에 알맞은 범위의 건전성을 가진 것으로 나타났으며 기타 조건을 동일하게 설정한 경우 저온 정제 공정(MDEA amine) 적용에 비해 플랜트 효율이 약 2.7% 가량 상승하였다. 한편 동일한 고온정제 공정이라도 적용하는 흡수제를 zinc titanate에서 zinc ferrite로 달리 하는 경우 탈황제의 화학 반응상 특성 및 차이점으로 인해 연료가스의 발열량 변화를 유발하므로 결과적으로 약 0.5%의 플랜트 효율 손실이 발생함을 알 수 있었다. 또한 탈황 온도 350~$650^{\circ}C$ 사이의 온도범위에 대해 민감도 분석을 실행하였으며 민감도 분석 결과 전제 온도의 증가와 플랜트 효율은 정비례하지 않으며 50$0^{\circ}C$ 이상의 정제 온도를 적용한 경우는 거의 비슷한 효율을 나타내었다. 이와 같은 결과는 정제 온도를 증가시킴으로 인해 가스터빈에 공급되는 연료가스의 온도는 높아지지만 적용한 가스터빈의 출력 및 연소 온도가 제한되어 있어 고온정제를 적용함으로써 얻어지는 이득을 가스터빈에서 충분히 보상하지 못하고 한편으로 고온정제를 채택함으로써 저온정제 적용시 보다 syngas cooler에서 회수할 수 있는 헌열이 줄어듦으로 인한 증기 터빈 출력의 감소가 커지기 때문으로 분석되었다.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.36 no.4
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• pp.439-447
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• 2012

Solid oxide fuel cell/gas turbine hybrid systems that use three gas turbines having different power outputs were devised and their performance was compared. The power shares of the gas turbine and fuel cell and the net system efficiency were compared among the three systems, and their variations with the design fuel cell temperature were investigated. The system efficiency was predicted to be insensitive to the fuel cell temperature in the sub-MW system, but it increased with increasing fuel cell temperature in both the multi-MW and hundred-MW systems. The influence of air bypass around the fuel cell on the system performance was also investigated.

• Journal of Advanced Marine Engineering and Technology
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• v.39 no.7
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• pp.735-743
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• 2015

The major component with a significant impact on the thermodynamic efficiency of the organic Rankine cycle is the turbine. Many difficulties occur in the turbine design of an organic Rankine cycle because the expansion process in an organic Rankine cycle is generally accompanied by a dramatic change in the working fluid properties. A precise preliminary design for a radial inflow turbine is hard to obtain using the classic method for selecting the loading and flow coefficients from the existing performance chart. Therefore, this study proposed a method to calculate the loading and flow coefficient based on the number of rotor vanes and thermodynamic design requirements. Preliminary design results using the proposed models were in fairly good agreement with the credible results using the commercial preliminary design software. Furthermore, a numerical analysis of the preliminary design results was carried out to verify the accuracy of the proposed preliminary design models, and most of the dependent variables, with the exception of the efficiency, were analyzed to meet the preliminary design conditions.