• 오토저널
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• 제13권6호
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• pp.48-56
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• 1991

This paper describes the experimental investigations on the pressure variations of intake and exhaust manifold and mass flow rate through exhaust turbine of turbocharged 6-cylinder diesel engine. The turbocharger of experimental diesel engine is constructed with the radial ty pe exhaust turbine and blower driven by exhaust gases. The pressure variations were measur ed by pressure transducer at the points such as turbine inlet and outlet, compressor inlet and outlet, and inlet pipe and exhaust manifolds for normal and combined charging engines with the change of engine speed. The experimental results of this study show that the mass flow rate of exhaust turbine and the variations of pressure in intake and exhaust manifold are all increased with the increase of engine speed.

• Journal of Astronomy and Space Sciences
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• 제2권2호
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• pp.153-174
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• 1985

The one of critical factor in gas turbine engine performance is high turbine inlet gas temperature. Therefore, the turbine rotor has so many problems which must be considered such as the turbine blade cooling, thermal stress of turbine disk due to severe temperature gradient, turbine rotor tip clearance, under the high operating temperature. The purpose of this study is to provider the temperature distribution and heat flux in turbine disk which is required to considered premensioned problem by the Finite Difference Method and the Finite Element Methods on the steady state condition. In this study, the optimum aspect ratio of turbine disk was analysed for various heat conductivity of turbine disk material by Finite Difference Method, and the effect of laminating method with high conductivity materials to disk thickness direction by Finite Element Methods in order to cool the disk. The laminating method with high conductivity material on the side of the disk is effective.

• 제어로봇시스템학회논문지
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• 제14권1호
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• pp.49-53
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• 2008

A fuzzy inference logic system is proposed for gas turbine engine fault isolation. The gas path measurements used for fault isolation are exhaust gas temperature, low and high rotor speed, and fuel flow. The fuzzy inference logic uses rules developed from a model of performance influence coefficients to isolate engine faults while accounting for uncertainty in gas path measurements. Inputs to the fuzzy inference logic system are measurement deviations of gas path parameters which are transferred directly from the ECM(Engine Control Monitoring) program and outputs are engine module faults. The proposed fuzzy inference logic system is tested using simulated data developed from the ECM trend plot reports and the results show that the proposed fuzzy inference logic system isolates module faults with high accuracy rate in the environment of high level of uncertainty.

• Journal of Advanced Marine Engineering and Technology
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• 제21권4호
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• pp.421-429
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• 1997

This study is theoretically examined the influences on the performance of diesel engine super¬charged by exhaust gas turbine with the change of excess air factor, admission ratio, total efficien¬cy of turbine and compressor, scavenging pressure ratio, and scavenging temperature. In this study, all calculations are carried out by computer, and the theoretical engine performance is com¬pared with the actual engine performance which is offered from engine manufacturer. Following results are acquired by this study. The mean effective pressure is increased with decrease of excess air factor or increase of scavenging pressure ratio. As the admission ratio or total efficiency of tur¬bine is increased, the mean effective pressure is increased but the specific fuel consumption is decreased. Mean calculation error compared with the actual engine performance is under 5 per¬cents, therefore, this calculation method can be used in the design of diesel engine.

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 2002년도 유체기계 연구개발 발표회 논문집
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• pp.314-319
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• 2002

Performance analysis and test of a 50kW micro gas turbine is carried out. The present study was initiated in 1996 by KIMM researchers to develope a 50kW class turbogenerator gas turbine engine for hybrid vehicle propulsion system. but with its low emission and compactness, it seemed that it can also be applied as a source of distributed power generation. In this study, general description of the KIMM's efforts to acquire performance test skills of the self-made 50kW micro gas turbine engine. At present, non-load performance test up to 615000 rpm was accomplished and is expected to make through 80,000 rpm by the end of year. Several revisions in design and manufacture were made during the course of experiments. The resulting outputs is thought to be valuable for the further refinement of the system for eventual commercialization of the product.

• Tribology and Lubricants
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• 제27권2호
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• pp.77-87
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• 2011

In this study, using the governing equation for thermohydrodyamic lubrication involving the homogeneous mixture of incompressible fluid derived by based on the principle of continuum mechanics, it is discussed the effects of water within turbine oil on the performance of high speed journal bearing of a steam turbine shipping engine. The governing equation is the general equation being able to be applied on the mixture of Newtonian fluid and non-Newtonian fluid. Here, the fluid viscosity index, n of power-law non-Newtonian fluid is supposed to be 1 for the application of the journal bearing in a steam turbine shipping engine lubricated with the mixture of two Newtonian fluid, for example, water within turbine oil. The results related with the bearing performance are showed.

• 한국추진공학회지
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• 제22권6호
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• pp.64-71
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• 2018

가스터빈엔진의 탈설계점 운전 성능해석을 수행하기 위해서는 구성품의 성능 특성을 파악하는 것이 필수적이다. 본 연구에서는 가스터빈의 성능특성을 이해하기 위하여 마이크로 가스터빈엔진 성능시험 장치를 구축하였다. 구축된 마이크로 가스터빈 시험 장치를 이용하여 엔진의 회전수에 따른 유동장내의 온도와 압력 데이터를 수집하였으며, 수집된 실험 데이터를 이용하여 압축기 성능선도를 구성하였다. 터빈 출구부에서 배기가스를 포집하여 연소효율을 계산하였다. 구성된 압축기 성능선도와 연소효율을 GasTurb 성능해석 소프트웨어에 적용하여 지상 정지시의 탈설계점 성능해석을 수행하였고, 측정된 엔진성능데이터와 비교분석을 수행하였다.

• 한국추진공학회지
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• 제25권5호
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• pp.1-9
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• 2021

국내 소형 가스터빈엔진 상용화 시장의 저변화를 위하여 상용 소형 가스터빈엔진의 시동 및 정상운용구간에서의 제어로직을 파악하고자 하였다. 이를 통하여 시동 및 정상운용구간에서 엔진의 점화 및 정상작동을 위하여 엔진의 점화기, 시동모터, 연료펌프 및 연료밸브가 어떻게 제어되는지 파악하였고, 확보된 제어로직을 실제 상용화 연구가 진행되고 있는 소형 가스터빈엔진의 지상용 제어기에 활용하였다. 해당 엔진은 비행용 엔진 제어기를 제작 중이며, 제작 완료 후 항우연에서 보유하고 있는 고도시험설비를 활용한 고도시험을 통해 비행시험 전에 고도에서의 운용성능을 확인할 예정이다.

• 한국정밀공학회:학술대회논문집
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• 한국정밀공학회 2011년도 춘계학술대회 논문집
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• pp.879-880
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• 2011

• 한국유체기계학회 논문집
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• 제17권5호
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• pp.78-82
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• 2014

This paper describes a brief aerodynamic design procedure of multi-stage axial turbine. The design procedure was established including one dimensional scratch design, through flow analysis with empirical correlations, two dimensional airfoil design and three dimensional airfoil stacking. Detailed aerodynamic performance assessment was done with full three dimensional CFD method at the design and off design conditions to construct turbine performance map. With the present method, aerodynamic design procedure of 1st and 2nd stages of high pressure turbine for 10,000lbf class turbofan engine was introduced.