• 한국정밀공학회지
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• 제31권8호
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• pp.671-675
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• 2014

Nozzle ring is an important part of turbocharger which is applied to today's most diesel engines. Turbo charger nozzle ring is difficult to process and takes a high cost and a long time relatively. For this reason, it is largely produced by using a precision casting. Investment method, the representative technology of precision casting, has excellent dimensional accuracy and can produce complex shapes relatively easily. However, it is difficult to avoid the casting defects such as shrinkage cavity and short shot. This study is to predict the casting defects which could be occurred during the investment method by use of finite element analysis software and to design the process and mold of the marine turbocharger nozzle ring.

• 한국추진공학회지
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• 제8권2호
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• pp.10-17
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• 2004

본 논문에서는 액체로켓엔진용 160 kW급 터보펌프의 터빈을 구동하고, 액체산소와 케로신을 추진제로 사용하는 연료 과잉 가스발생기의 설계점 연소성능시험 결과에 대해 논의하였다. 충돌형 F-O-F 분사기로 구성된 헤드부, 물냉각 채널 연소실, torch igniter, turbulence ring 그리고 측정 링을 갖는 가스발생기에 대해 기술하였고, 설계점에서의 연소시험 및 turbulence ring 장착여부. 연소실 길이 변화에 따른 연소시험의 결과들에 대해 기술하였다. 연소시험 결과 가스발생기는 설계점에서 안정된 작동성을 보여주었고. 연소압력 및 온도 등의 성능은 예측치에 근접하는 결과였다. Turbulence ring은 출구에서의 가스온도를 균일하게 분포시켜 효과적인 혼합 장치임을 보여 주었고, 4∼6msec 정도에서의 연소가스 잔류시간은 연소효율에 큰 영향을 주지 않았다. 가스발생기 출구에서의 온도는 공급되는 추진제의 O/F ratio에 따라 매우 민감하게 변화하였다.

• 한국유체기계학회 논문집
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• 제7권5호
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• pp.43-49
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• 2004

A turbo blower, driven by a high-speed blushless DC motor, was designed as a efficient substitute of a ring blower or a roots blower. Computational analysis and performance tests have been performed to investigate performance characteristics of the blower. Experimental measurements showed that the blower has a good stability margin. This paper gives an outline of design, computational flow analysis and performance test for aerodynamic evaluation of the variable speed turboblower.

• 한국자동차공학회논문집
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• 제23권1호
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• pp.97-104
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• 2015

This study is a part of the high pressure injection system development on the Turbo GDI engine in order to reduce smoke emission in case of using the low volatile(high DI) fuel which is used as normal gasoline fuel in the US market. Firstly, theoretical approach was done regarding gasoline fuel property, performance, definition of particle matters and its creation as well as problems of the high DI fuel. In this experimental study, 2L Turbo GDI engine was selected and optimized system parameter was inspected by changing fuel, fuel injection mode (single/multiple), fuel pressure, distance between injector tip and combustion chamber, start of injection, intake valve timing in engine dyno at all engine speed range with full load. In case of normal gasoline fuel, opacity was contained within 2% in all conditions. On the other hands, in case of low volatile fuel (high DI fuel), it was confirmed that the opacity was rapidly increased above 5,000 rpm at 14.5 ~ 20 MPa of fuel pressure and there were almost no differences on the opacity(smoke) between 17 MPa and 20 MPa fuel pressure. According to the SOI retard, smoke decrease tendency was observed but intake valve close timing change has almost no impact on the smoke level in this area. Consequently, smoke decrease was observed and 16% at 6000rpm respectively with injector washer ring installed. By removing injector washer to make injector tip closer to the combustion chamber, smoke decrease was observed by 46% at 5,500 rpm, 42% at 6,000 rpm. It is assumed that the fuel injection interaction with cylinder head, piston head, intake and exhaust valve is reduced so that impingement is reduced in local area.

• 한국산림과학회지
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• 제79권1호
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• pp.1-15
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• 1990

본 연구에서는 수간석해의 분석시간과 경비를 줄이고 정확도를 높히기 위하여 P.C용 수간석해 프로그램을 제작하였으며, 본 프로그램에 이용된 수간석해 방법과 기존방법을 비교하여 다음과 같은 결과를 얻었다. 연륜측정기로 부터 1/100mm단위로 연륜 1개씩 측정된 data가 컴퓨터에 자동입력되도록 Turbo pascal을 이용하여 프로그램 하였다. 또한 각 단판의 직경이 단면적 평균법에 의해 계산되며, Spline function에 의해 재적 및 수고가 계산되도록 Fortran 77을 이용하여 수간석해 계산프로그램을 제작하였다. 이와같이 계산된 각종 생장량은 1년, 5년 단위로 각각 출력되며 수간석해도 및 각종 생장량도가 personal computer용 dot printer로 출력가능하여 수간 석해의 결과를 보다 쉽게 이용할 수 있게 되었다. 본 프로그램에서 이용된 수간석해 계산방법과 기존방법을 비교한 결과 단면적평균법이 편심에 의한 오차를 줄일 수 있었고, 수고 및 재적계산에서 Spline함수에 의한 간곡선 추정을 이용할 경우에는 다른 함수식에 의한 생장량 계산값보다 더욱 정확히 계산 가능하였다.

• 대한기계학회논문집B
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• 제23권8호
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• pp.1048-1062
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• 1999

A numerical method and experiments for the aerodynamic design of high performance two-stage axial flow fans was carried out. A vortex ring element method used for the aerodynamic analysis of the propellers was extended to the fan-duct system. Fan Performance and velocity profiles at the fan inlet and outlet are compared with experimental data for the validations of numerical method. Performance test was done based on KS B 6311(testing methods for turbo-fans and blowers). The velocity profile was obtained using a 5-hole pitot tube by the non-nulling method. The two stage axial flow fan configurations for the optimal operation conditions were set by using the experimental results for the single rotating axial flow fan and the single stage axial flow fan. The single rotating axial flow fan showed relatively low efficiency due to the swirl velocities behind rotor exit which produced pressure losses. In contrast, the single stage and the two-stage axial flow fans showed performance improvements due to the swirl velocity reduction by the stator. The peak efficiency of the two stage axial flow fan was improved by 21% and 6%, compared to the single rotating axial flow fan and the single stage axial flow fan, respectively.