• 항공우주시스템공학회지
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• 제14권6호
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• pp.85-90
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• 2020

The infrared signature that is associated with an aircraft is mainly caused by heat released from the engine and the exhaust plume. In this study, a test-system was designed to observe the overall infrared signature characteristics of a turbofan engine during operation under ground running conditions and the infrared reduction features that result from different exhaust nozzle configurations. A test stand was designed for the 1400 lbf class turbofan engine that included a bell-mouth type intake, fuel supply system, a measurement system, and a data acquisition/control system. The design and verification of the test system were conducted so that the basic nozzle and various 2D nozzles could be applied to study the infrared signature produced by a turbofan engine exhaust.

• Journal of Advanced Marine Engineering and Technology
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• 제22권2호
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• pp.248-256
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• 1998

The effects of fuel injection system on the performance in a V8-type diesel engine was stuided in this paper. Fuel injection system is important factor which influence the engine performance and exhaust emission bcasuse the properties in the injected fuel depend on the atomization characteristics. In this study using diesel engine of 17.7:1 compression ration the engine performance and exhaust emission are measured experimentally according to 1000, 1400, 2200rpm in the full-load conditions. The chosen parameters for the major system are such diameter shape of combustion chamber and intake system. The results are as follows: As the nozzle hole diameter and injection angle become smaller and as the injection timing gets advanced the fuel consumption and concentration of smoke are decreasing whereas concentration of $NO_{x}$ is increasing. Andconcentration of $NO_{x}$ is increasing in accordance with the increase of injection pipe diameter and nozzle protrusion. Also it is shown that re-entrant type combustion chamber is more effective than that of toroidal type in the improvement of $NO_{x}$ reduction.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년 영문 학술대회
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• pp.671-679
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• 2008

The effect of Pre-cooled Turbojet Engine installation and nozzle exhaust jet on Hypersonic Turbojet EXperimental aircraft(HYTEX aircraft) were investigated by three-dimensional numerical analyses to obtain aerodynamic characteristics of the aircraft during its in-flight condition. First, simulations of wind tunnel experiment using small scale model of the aircraft with and without the rectangular duct reproducing engine was performed at M=5.1 condition in order to validate the calculation code. Here, good agreements with experimental data were obtained regarding centerline wall pressures on the aircraft and aerodynamic coefficients of forces and moments acting on the aircraft. Next, full scale integrated analysis of the aircraft and the engine were conducted for flight Mach numbers of M=5.0, 4.0, 3.5, 3.0, and 2.0. Increasing the angle of attack $\alpha$ of the aircraft in M=5.0 flight increased the mass flow rate of the air captured at the intake due to pre-compression effect of the nose shockwave, also increasing the thrust obtained at the engine plug nozzle. Sufficient thrust for acceleration were obtained at $\alpha=3$ and 5 degrees. Increase of flight Mach number at $\alpha=0$ degrees resulted in decrease of mass flow rate captured at the engine intake, and thus decrease in thrust at the nozzle. The thrust was sufficient for acceleration at M=3.5 and lower cases. Lift force on the aircraft was increased by the integration of engine on the aircraft for all varying angles of attack or flight Mach numbers. However, the slope of lift increase when increasing flight Mach number showed decrease as flight Mach number reach to M=5.0, due to the separation shockwave at the upper surface of the aircraft. Pitch moment of the aircraft was not affected by the installation of the engines for all angles of attack at M=5.0 condition. In low Mach number cases at $\alpha=0$ degrees, installation of the engines increased the pitch moment compared to no engine configuration. Installation of the engines increased the frictional drag on the aircraft, and its percentage to the total drag ranged between 30-50% for varying angle of attack in M=5.0 flight.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년도 제30회 춘계학술대회논문집
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• pp.299-302
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• 2008

램제트 추진체의 성능연구를 위하여 램제트 전 영역, 즉 흡입구에서부터 연소실과 노즐까지 통합하여 연소수치해석을 수행하였다. 램제트가 작동 시작하여 비행체가 상승하는 가속모드(Acceleration mode)와 고고도에서의 순항모드(Cruise mode)를 설정 하였으며, 각 모드에 대하여 분사되는 연료의 당량비 변화를 고려하였다. 각 모드에서 추진체 전 영역의 압력 분포, 흡입구의 종말충격파의 위치, 연소실에서의 온도분포, 노즐출구에서의 연료분포를 분석하였다.

• 한국분무공학회지
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• 제16권3호
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• pp.146-151
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• 2011

LPG(Liquified Petroleum Gas) fuel for vehicles has lots of advantages such as low emission level, cheaper fuel cost and enough infrastructure. Therefore it arouses interest as an alternative engine to reduce emission of diesel engines. Especially MPI(Multi Point Injection) type LPLi(Liquid Phase LPG injection) system could have overcome the disadvantages of mixer types such as low engine performance, decreased charging efficiency and cold starting difficulty. However ice formation on the nozzle tip and intake port due to the freezing of moisture around the components is often observed in LPLi systems. This icing phenomenon is the direct cause of unstable engine combustion, resulting in engine emissions. Therefore in this research, a spray visualization test for LPG injection was carried out to obtain the basic information of an LPLi injector, then the effects of butane and propane mixing rates on ice formation at the intake port and nozzle tip was investigated. As a result, the icing characteristics of them showed contrary results according to the mixing rates.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2003년도 추계학술대회
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• pp.390-395
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• 2003

The effect of recirculated exhaust gas on exhaust emissions under four kinds of nozzle tip with the different fuel consumption rate are experimentally investigated by using an once-through boiler with FGR system. The purpose of this study is to develop the FGR control system for reducing NOx in a boiler. Intake and exhaust oxygen concentrations, and equivalence ratio are applied to discuss the effect of FGR rate on exhaust emissions at various fuel consumption rates. It is found that NOx emissions are decreased, while soot emissions are increased owing to the drop of intake and exhaust oxygen concentrations, and the rise of equivalence ratio as FGR rates are elevated.

• 에너지공학
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• 제13권2호
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• pp.118-127
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• 2004

본 연구는 배기량이 16.7ι인 V8형 터보차져 인터쿨러 직접분사식 디젤기관에서 흡기포트의 선회유동과 연료분사계 및 과급기가 기관성능 및 배출가스특성에 미치는 영향을 실험적으로 고찰하며 성능을 개선하는데 있다. 일반적으로 기관의 출력을 높이기 위하여 과급기 및 인터쿨러를 장착하여 과급공기를 냉각시켜 과급효율을 더욱 높인 TCI디젤기관이 보편화되고 있다 본 연구의 결과로서 흡기포트의 선회비가 2.25인 경우에서 압축비 17.5, re-entrant 8.5$^{\circ}$ 형 연소실, 노즐분공경 $\Phi$0.33*3+$\Phi$0.35*2, 노즐돌출량 3.18mm, 분사시기 BTDC 12$^{\circ}$CA, 과급기 T042(압축기 0.6A/R+46Trim, 터빈 1.0A/R+57Trim)경우가 기관성능 및 NO$_{x}$ 농도의 배출특성을 고려할 때 운전영역에서 가장 우수하여 흡기포트, 분사계 및 과급기에 대한 각 인자를 적정화할 수 있었다.

• 대한조선학회논문집
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• 제34권4호
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• pp.42-52
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• 1997

수중램제트(underwater ram-jet)는 램흡입부(ram intake), 혼합실(mixing chamber) 및 노즐(nozzle)로 구성되어 있으며, 램흡입부로 유입된 작동유체는 압력이 증가되며 이 증압된 작동유체에 혼합실로부터 고압공기를 분사하여 기 액이상류를 형성하여 노즐을 통과하면서 대기압까지 팽창을 하여 작동유체를 고속으로 가속시켜 노즐출구로부터 추력을 얻는 방식으로 차세대 초고속 선박추진장치이다. 본 연구에서는 80노트를 낼 수 있는 선내관통형(buried type vessel) 램제트의 최적 노즐형상데이터를 이용하여 제반변수(벽마찰계수, 가스속도, 기포반경, 대기온도, 질량유량비, 디퓨저면적비, 작동유체의 속도구배)의 변화가 추진특성에 미치는 영향을 파악하였다.

• 한국분무공학회지
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• 제17권2호
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• pp.94-99
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• 2012

The characteristics of spray behavior and injected amount were studied with two types of nozzles for using in a compression ignition engine with dual fuel technology for construction machines. A penetration length of spray tends to shorten due to a decrease of injected amount of a diesel fuel with dual fuel engine application. In order to ignite the gaseous fuel premixed with air during intake process, a diesel fuel, which was compression ignited, needs to penetrate somehow similar depth compared with the case of a diesel fuel-only-injection. In this work, a nozzle with reduced hole diameter and increased number of holes was tested and demonstrated that, compared to diesel 100% case, its penetration lengths are comparable to 74% and 79%, respectively, of those of 100% and 50% supply of a diesel fuel with the baseline nozzle that has four holes and 30.4% increased diameter. This will presumably enhancement the combustion in a dual fuel engine. A design suggestion was also made in this work to achieve similar penetration length of spray with diesel 100% case to prevent combustion from being deteriorated in a dual fuel engine.

• 대한조선학회논문집
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• 제45권6호
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• pp.569-578
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• 2008

The Coanda effects demonstrate that a jet stream applied tangential to a curved surface can generate lift force by increasing the circulation. Many experimental and numerical studies have been performed on the Coanda effect and it is found to be useful in various fields of aerodynamics. The Coanda effect may have practical application to marine hydrodynamics since various control surfaces are being used to control behaviors of ships and offshore structures. In the present study, numerical computations are performed to find the applicability of the Coanda effect to the marine control surfaces. For the purpose, changes in flow characteristics around a flapped foil due to the Coanda effect have been simulated by RANS equations discretized with a cell-centered finite volume method (FVM). In the process, special attention has been given to the influence of jet nozzle arrangement on the lift characteristics of the Coanda foil. It is found that the shape as well as the location of the jet intake and jet exit affects the lift performance of the foil significantly.