• Journal of the Korean Society of Propulsion Engineers
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• v.14 no.3
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• pp.61-68
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• 2010

A small high altitude test facility has been developed to investigate ignition performance of a small gas-turbine combustor under high altitude conditions. Supersonic diffusers and a heat exchanger were used to perform a low pressure and a low temperature condition, respectively. Experimental results showed that the low pressure environment could be controlled by upstream pressure of primary nozzle flow and low temperature environment by mixture ratio of cooled air and ambient air. Ignition performance tests were performed to verify the performance of the facility under simulated high altitude conditions. Conclusively, it was proven that the test facility could be used for ignition performance test of a small gas-turbine combustor under high altitude condition of approximately 6,100m.

• Journal of the Korean Society of Propulsion Engineers
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• v.1 no.1
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• pp.24-32
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• 1997

A nonlinear dynamic simulation of a small gas turbine engine was performed by using DYNGEN program with various environmental conditions. It was observed that the effect of the bleed air flow rate changed to overall engine performance. The real time linear model which was a function of engine rotor speed was resulted to be close to nonlinear simulation results. For optimal LQR controller, it was considered only fuel flow rate or both fuel flow rate and bleed air rate as inputs. In the comparison of both results, the LQR controller with multi input had better performance than that with single input.

• Proceedings of the Korea Society for Energy Engineering kosee Conference
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• 2003.05a
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• pp.639-642
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• 2003

용융탄산염형 연료전지(MCFC)는 고효율의 환경친화성 발전시스템으로서, 더욱이 석탄가스를 연료로 사용할 수 있다는 점에서 전력사업용 발전시스템으로서 우리나라를 포함 각국에서 개발이 진행 중에 있다. 그러나 장래 이 MCFC는 하나의 발전시스템으로서 마이크로가스터빈 등의 소형 분산전원과의 경쟁관계에 놓이게 될 것이며, 따라서 적정규모의 경제성 및 신뢰성을 요구받게 될 것이다.(중략)

• Journal of the Korean Society of Propulsion Engineers
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• v.2 no.1
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• pp.13-20
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• 1998

A steady-state and dynamic simulation program for a small multi-purpose turboshaft engine with the free power turbine was developed. In order to reduce developing cost, time and risk, a turbojet engine whose performance was well-known was used for the gas generator, and life time was improved by replacing turbine material and by using Larson-Miller curves. The component characteristic of the power turbine was derived from scaling the gas generator turbine. Equilibrium equations of mass flow rate and work were used for the steady-state performance analysis, and the Constant Flow Method(CMF) was used for the dynamic performance simulation. The step fuel scheduling was carried out for acceleration in the dynamic simulation. Through this simulation, it was found that the overshoot of the turbine inlet temperature exceeded over the compressor turbine limit temperature.

• Journal of the Korean Society of Propulsion Engineers
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• v.25 no.4
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• pp.71-77
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• 2021

Several cooling techinques have been studied for protecting gas turbine blades from hot gas. In terms of film-cooling techniques, various shapes of film cooling holes have been studied including fan shaped holes, which are used on gas turbine blades. However, owing to increasing demands on smaller gas turbines, a research on film-cooling holes on thin walls is required. This study was conducted at blowing ratios of 1 and 2, using numerical analysis. Through the numerical analysis, the effect of geometrical parameters on the effectiveness of fan-shaped hole film cooling was studied. Moreover, optimization was performed on three geometrical parameters: metering length, lateral expansion angle and forward expansion angle. As a result, we realized that the optimal fan-shaped holes on each blowing ratio were found to have very similar geometry and cooling performance.

• The KSFM Journal of Fluid Machinery
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• v.12 no.3
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• pp.26-30
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• 2009

This paper predicts the critical speeds of a 5MW industrial gas turbine by using commercial rotordynamic tool, DYNAMICS 4.3. The gas turbine is operated at 12,975 rpm on squeeze film dampers. The stiffness of the squeeze film dampers are estimated. The critical speeds of the gas turbine rotor are calculated to have a sufficient separation margin (2%) from the 1st bending mode and pass over 2 rigid body modes below 4,000 cpm. This paper discussed the coupling effects on the dynamic response of the gas turbine.

• 유체기계공업학회:학술대회논문집
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• 2000.12a
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• pp.211-218
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• 2000

Off-design experimental performance was investigated for a small centrifugal compressor, whose impeller diameter is about 125mm, used in an industrial gas turbine. Test rig was designed and manufactured with a radial inflow turbine and a combustor to supply driving power to the compressor. Static pressure was measured on the casing of the impeller, vaneless diffuser, vaned diffuser and volute. Total pressure was obtained using specially fabricated rakes at the vaned diffuser throat and exit. Circumferential nonuniformity was found, near surge, in the Impeller, vaned diffuser and volute region. Spanwise nonuniform flow from the impeller affected the total pressure defects in the vaned diffuser region. Static pressure distortion in the circumferential direction in the volute was found near surge, where the minimum occurred near 140 degree position.

• The KSFM Journal of Fluid Machinery
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• v.13 no.3
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• pp.18-23
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• 2010

This paper predicts the unbalance and transient (start-up) response of a 5MW industrial gas turbine by using commercial rotordynamic tool, DYNAMICS 4.3. The gas turbine is operated at 12,975rpm on squeeze film dampers or tilting pad bearings. The stiffness and damping coefficients of the squeeze film dampers and tilting pad bearings are estimated. It is seen that the vibration amplitude of the gas turbine rotor is sufficiently small around the critical speeds and at the rated speed.

• The KSFM Journal of Fluid Machinery
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• v.14 no.4
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• pp.52-56
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• 2011

Small-sized gas turbine engine could be applied to various fields such as propulsion, power generation, machine driving, etc., and Doosan has been developing 5MW class gas turbine engine for power generation since 2005. To verify its design performance and operating characteristics, a gas turbine engine test facility was constructed, and control system was also established to satisfy rapid and reliable control performance. In this paper, the hardware specification and structure of control system for gas turbine engine are introduced, and test result for starting characteristics analysis and loading is also presented.

• 한국신재생에너지학회:학술대회논문집
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• 2011.05a
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• pp.174.2-174.2
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• 2011

최근 유가상승과 석유, 천연가스의 가채 매장량의 한계등과 함께 온실가스에 의한 지구온난화 방지를 위하여 미국, 유럽국가 및 캐나다 등에서는 바이오매스를 이용한 에너지 회수 기술개발에 많은 관심과 연구를 수행하고 있다. 바이오 매스는 에너지 밀도 대비 존재하는 지역이 광범위하여 발생, 수집, 수송에 따른 비용이 많이 소요되는 특성이 있어 산지에서 직접처리하거나 수집하여 대규모처리등과 같이 여러 가지 현장상황에 따라 적정한 플랜트 운용의 유연성을 갖추고 있어야 한다. 일반적으로 바이오매스로부터 중소형으로 분산형 발전이나 수소제조를 위해서는 직접 연소법 보다는 가스화 방식을 이용하고 있는데, 연소에 의해 열을 생산하여 전기를 생산하는 방식은 스팀터빈을 이용하는 것이며, 스팀터빈은 소형 운용이 어렵기 때문이다. 본 연구에서는 폐목재로부터 합성가스제조를 위하여 5톤/일 규모 가스화기를 제작하였으며, 타르 및 수트와 같은 미반응 물질을 제거할 수 있는 집진, 세정장치를 설계 및 제작하였다. 또한 합성가스에 함유된 현열로부터 열회수를 위하여 열교환기를 설치하였으며, 정제된 합성가스를 이용하는 가스엔진을 통하여 열병합 발전시스템 연계운전을 수행하였다. 운전 실험을 폐목재 가스화 3톤/일 규모로 수행하였으며, 평균 1,500kcal/$Nm^3$의 발열량을 갖는 합성가스를 생성시킬 수 있었다. 사이클론, 스크러버 및 기수분리 장치를 이용하여 정제된 합성가스는 합성가스 엔진을 통하여 72kW 이상의 전력생산이 가능하였다. 열교환기를 통하여 평균 15,000kcal/h의 배열 회수가 가능하였으며, 바이오매스 가스화 합성가스를 이용한 열병합 발전이 가능함을 입증하였다.