• 한국자동차공학회논문집
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• 제18권1호
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• pp.131-138
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• 2010

Because real flow of engine exhaust is very hot and highly transient, it may cause thermal and inertial loads on catalyzed filters in DPF. Transient and detailed flow and thermal simulations are necessary in this field. To assess the importance of time dependent phenomena, typical cone-type configuration such as an underbody DPF is selected for steady and transient analysis. User defined functions of FLUENT by sinusoidal inlet velocities are written and integrated with main solver for realistic simulation. Also, 4-cylinder and 6-cylinder engines for 3,000 L class are considered for the dynamic exhaust effect of engine type. Key parameters to understanding of catalyst performance and durability issues such as flow uniformity index and peak velocity are investigated. Also, pressure drop for engine power are considered. From the simulation results for three different cases, proper approach is recommended.

• Journal of Astronomy and Space Sciences
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• 제26권4호
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• pp.693-702
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• 2009

액체로켓엔진의 구성품 중 하나인 산화제 라인 시스템의 3차원 모델과 유동해석을 수행하였다. 전체 시스템의 유동해석에 앞서 각 구성품들의 개별적인 유동해석과 단순화된 모델을 통해 최적의 위치를 결정하였다. 그 결과 가스발생기 라인의 입구는 압력보상이 필요하며 오리피스의 위치에 따라 출구 유동의 형태가 달라지는 것을 확인할 수 있었다. 전체적으로 해석된 라인 시스템은 주어진 요구조건을 만족하는 것으로 나타났으며 이는 실제 제품 제작과 시험을 통해 확인할 예정이다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2017년도 제48회 춘계학술대회논문집
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• pp.1093-1098
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• 2017

액체로켓엔진용 산화제펌프의 캐비테이션 시험 중 입출구 배관과 펌프 케이싱에서 계측된 고주파 신호를 분석하였다. 각각의 데이터의 RMS 값을 캐비테이션 수에 따라 표현하였다. 회전수 동기 주파수와 날개 개수 성분, 캐비테이션 불안정성 주파수의 RMS를 계산하였다. 입구 배관의 압력섭동은 캐비테이션 불안정성의 영향을 받았다. 출구 배관의 경우 3x 성분이 탁월하였는데, 인듀서에서 발생한 3x 성분이 임펠러에서 증폭된 결과로 해석된다. 케이싱에 부착된 가속도계에서도 캐비테이션 불안정성에 해당하는 주파수가 확인되었다.

• 한국자동차공학회논문집
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• 제24권2호
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• pp.232-241
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• 2016

The turbocharger, to decrease the harmful exhaust gas(CO, HC and etc.) and $CO_2$ emission as well as the increase of the engine output, would be an useful method for engine downsizing. Therefore the thermal endurance of turbine blade, the lubrication of turbine shaft and the engine knock according to the supercharge of the inlet air, had been studied. And there had been much progress in these research tasks to be achieved a breakthrough. But a study on the built-in WGV of a gasoline engine for a passenger car which may effect on the engine performance, is few. In this paper, the effect of the embedded WGV on the engine performance was performed through the endurance test, which was conducted more than 300 hrs using the 4 stroke, 1998 cc, water-cooled engine. To sum up the major results, there were an abrasion in the area of the WGV head edge and the thermal deformation on the WGV head face, These phenomena led to reducing the boost pressure which caused the reduction in the volumetric efficiency of the engine. It resulted in decreasing the engine power gradually during the life cycle of the embedded WGV.

• International Journal of Fluid Machinery and Systems
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• 제6권3호
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• pp.160-169
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• 2013

Two-stage turbocharging is an important way to raise engine power density, to realize energy saving and emission reducing. At present, turbine matching of two-stage turbocharger is based on MAP of turbine. The matching method does not take the effect of turbines' interaction into consideration, assuming that flow at high pressure turbine outlet and low pressure turbine inlet is uniform. Actually, there is swirl flow at outlet of high pressure turbine, and the swirl flow will influence performance of low pressure turbine which influencing performance of engine further. Three-dimension models of turbines with two-stage turbocharger were built in this paper. Based on the turbine models, mechanism of swirl flow at high pressure turbine outlet influencing low pressure turbine performance was studied and a two-stage radial counter-rotation turbine system was raised. Mechanisms of the influence of counter-rotation turbine system acting on low-pressure turbine were studied using simulation method. The research result proved that in condition of small turbine flow rate corresponding to engine low-speed working condition, counter-rotation turbine system can effectively decrease the influence of swirl flow at high pressure turbine outlet imposing on low pressure turbine and increases efficiency of the low-pressure turbine, furthermore increases the low-speed performance of the engine.

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 1998년도 유체기계 연구개발 발표회 논문집
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• pp.183-190
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• 1998

This paper introduces the part of efforts to develop a derivative type turbo-shaft engine from an existing baseline engine for multi-purpose helicopters targeting at 4000kg of take-off weight for 10-12 passengers. As a first step in meeting the development goal of increasing the output power to 840hp from 720hp with minimum modification, two stage axial compressor was redesigned to obtain the higher pressure ratio by removing the inlet guide vane and increasing the chord length. As a result, two stage axial compressors were designed to have the flow rate of 3.04 kg/s, the pressure ratio of 2.01 and the adiabatic efficiency of $85\%$. Its performance tests were carried out and verification of test results and redesign are under progress. Aerodynamic and structural analyses of the preliminary design are mainly described in this paper.

• 한국유체기계학회 논문집
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• 제2권1호
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• pp.88-95
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• 1999

This paper introduces the part of efforts to develop a derivative type turboshaft engine from an existing baseline engine for multi-purpose helicopters aiming at 4000 kg of take-off weight for 10-12 passengers. As a first step in meeting the development goal of increasing the output power from 720 hp to 840hp with minimum modification, a two stage axial compressor was redesigned to obtain the higher pressure ratio by removing the inlet guide vane and increasing the chord length. As a result, a two stage axial compressor was designed to facilitate a flow rate of 3.04 kg/s, a pressure ratio of 2.01 and an adiabatic efficiency of $85\%$. Its performance tests were carried out and verification of test results and redesign are under progress. Aerodynamic and structural analyses of the preliminary design are mainly described in this paper.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2010년도 제34회 춘계학술대회논문집
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• pp.411-414
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• 2010

초음속 엔진에서 흡입구의 buzz현상은 큰 압력진동과 연소 불안정성 그리고 추력 감소 등을 야기한다. 흡입구의 buzz현상과 액적 분사/연소의 동적인 상호관계를 이해하기 위하여 통합된 비정상 연소수치해석을 수행하였으며, 액적 모사를 위하여 TAB(Taylor Analogy Breakup) model을 적용하였다. 흡입구에서의 충격파거동과 주요 위치에서 압력거동을 분석하고 초음속 엔진 전영역에서의 음향모드를 분석하여 현 시스템의 동적거동을 파악하였다.

• Journal of Mechanical Science and Technology
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• 제16권6호
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• pp.839-850
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• 2002

A performance simulation program for the turboprop engine (PT6A-62), which is the power plant of the first Korean indigenous basic trainer KT-1, was developed for performance prediction, development of an EHMS (Engine Health Monitoring System) and the flight simulator. Characteristics of components including compressors, turbines, power turbines and the constant speed propeller were required for the steady state and transient performance analysis with on and off design point analysis. In most cases, these were substituted for what scaled from similar engine components'characteristics with the scaling law. The developed program was evaluated with the performance data provided by the engine manufacturer and with analysis results of GASTURB program, which is well known for the performance simulation of gas turbines. Performance parameters such as mass flow rate, compressor pressure ratio, fuel flow rate, specific fuel consumption and turbine inlet temperature were discussed to evaluate validity of the developed program at various cases. The first case was the sea level static standard condition and other cases were considered with various altitudes, flight velocities and part loads with the range between idle and 105% rotational speed of the gas generator. In the transient analysis, the Continuity of Mass Flow Method was utilized under the condition that mass stored between components is ignored and the flow compatibility is satisfied, and the Modified Euler Method was used for integration of the surplus torque. The transient performance analysis for various fuel schedules was performed. When the fuel step increase was considered, the overshoot of the turbine inlet temperature occurred. However, in case of ramp increase of the fuel longer than step increase of the fuel, the overshoot of the turbine inlet temperature was effectively reduced.

• 한국산학기술학회논문지
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• 제3권1호
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• pp.58-62
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• 2002

본 연구는 기관의 성능과 배출가스의 ECR 효과을 대한 것으로 기관은 6실린더 11리터의 대형터보디젤기관이며 ECR 방식은 저압루트시스템을 적용하였다. EGR 작동방식은 기계시이며 터빈 출구로부터 압축기 입구로 재순환시키는 방식이다. 또한 실험은 기관회전수와 부하별로 변경시켰으며 ECR율은 4%와 8%로 고정하여 실험하였고 그 결과를 기존 기관의 성능 및 배출가스결과와 비교 분석하였다. 따라서 본 연구의 목적은 대형터보디젤기관에 폭넓은 작동범위에서 ECR에 의한 기관 및 배출가스 성능에 미치는 영향을 고찰하고자 한다.