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터빈엔진시험을 통한 제트연료 변경에 따른 엔진성능 변화 연구
김유일(Youil Kim),민성기(Seongki Min) 한국추진공학회 2010 한국추진공학회 학술대회논문집 Vol.2010 No.11
제트연료변경에 따른 엔진 운용 특성 변화를 살펴보기 위해 JP-8 연료와 JP-S 연료를 사용하여 소형터보제트엔진의 지상시험 및 고도시험을 수행하였다. 비중이 18% 높은 JP-S 연료에 대한 연료조절 시스템 특성은 동일 연료공급명령에 대한 실 연료공급량이 JP-8 연료보다 8% 많이 공급되었다. 시동 특성은 연료조절시스템의 명령 대비 공급량의 차이로 인한 점화시점 및 엔진 회전수 가속율 등의 변화를 제외하고는 유사한 특성을 보였다. 정상상태 성능 특성은 순 추력의 일부 구간을 제외하고는 순추력과 공기유량, 배기가스온도 등 대부분의 엔진 성능 변수가 1% 이내로 유사하였으나 연료소모량만은 연료의 발열량 차이로 인해 최대 5 %이상 차이가 발생하였다. 이를 동일 추력 대비 비 연료소모율로 비교할 때 지상시험에서는 약 1.1~2.6 %, 고공환경시험에서는 5 % 이상 차이가 발생하였다. The engine ground and altitude tests were carried out to investigate the effect of jet fuel alteration on the performance of a small turbojet engine. JP-S was supplied 8% higher than JP-8 by fuel metering system at the same command. The employment of JP-S showed the similar starting characteristic to that of JP-8, however, difference in the ignition time and acceleration rate of engine speed due to the difference of fuel flow rate by fuel metering system was observed. In spite of jet fuel alteration, the test results yield the similar Steady-State engine performance in Net thrust, Air flow, Exhaust Gas Temperature, etc. On the other hand, the Fuel consumption of JP-S increased by 5 % compared with that of JP-8. In point of Specific Fuel Consumption (SFC), SFC of JP-S was approximately 1.1~2.6 %, 5 % higher than that of JP-8 in ground and altitude tests respectively at the same thrust.
유영준(Youngjoon Yoo),민성기(Seongki Min),최상민(Sangmin Choi) 한국연소학회 2012 KOSCOSYMPOSIUM논문집 Vol.- No.45
In order to estimate the efficiency of an evaporative heat exchanger having mini channel, the equations to calculate heat exchanger properties, those are air temperatures and water temperatures etc, are derived from the governing equations based on the Navier-Stokes equation, even though there are several assumptions to make problem simplify. There are three heat transfer zones at the mini channel heat exchanger depending on the water condition. So, there are three governing equations and solutions to calculate the properties. As a results of this study, the equations to calculate a saturation point and a dry point are derived to evaluate an evaporative heat exchanger having micro channel. It is supposed to predict the performance and evaluate a mini channel heat exchanger.
박정배(Jeongbae Park),민성기(Seongki Min),이세영(Seyoung Lee),김영신(Youngsin Kim),이종철(Jongchul Lee),장기원(Kiwon Jang) 한국추진공학회 2011 한국추진공학회 학술대회논문집 Vol.2011 No.5
연료탱크 내부에 존재하는 공기는 저장중 연료의 산화를 유발하고, 연료 이송성능을 저하시킬 수 있다. 따라서 항공기 연료탱크의 주유절차를 개선하기 위하여 연료탱크 내부에 존재하는 공기를 줄이는 방안으로 진공주유방식을 제안하였다. 본 논문에서는 진공주유 절차를 수립하여 실제 시험을 수행해 보았고, 이를 통해 진공주유중 발생하는 현상을 관찰할 수 있었다. 또한 탱크 내부의 기포 및 주유시간 절감을 위하여 다른 개선된 방안들을 제안하였다. The air remained in the fuel tank could cause oxidation of fuel during storage, and it also reduce the fuel transfer performance. To find better procedure for refueling of aircraft fuel tank, the vacuum refueling process was proposed to reduce air in the fuel tank. In this study, the vacuum refueling process established and tested, it could be helpful to find out what happened during vacuum refueling. Also the revised vacuum refueling processes were proposed to reduce the remained air and refueling time for aircraft fuel tank.
박정배(Jeongbae Park),민성기(Seongki Min),이세영(Seyoung Lee),김영신(Youngshin Kim),이종철(Jongchul Lee),장기원(Kiwon Jang) 한국추진공학회 2011 한국추진공학회지 Vol.15 No.3
The air in the fuel tank could cause oxidation of fuel during storage, and it also reduced the fuel transfer performance. To find better procedure for refueling of aircraft fuel tank, the vacuum refueling process was proposed to reduce the air in the fuel tank. In this study, the vacuum refueling process was established and tested, it could be helpful to find out what happened during vacuum refueling. Also the revised vacuum refueling process was proposed to reduce the air and refueling time.
유영준(Yungjun Yoo),민성기(Seongki Min) 한국추진공학회 2012 한국추진공학회지 Vol.16 No.1
While a conventional ECS mainly consisted of an air cycle machine and heat exchangers, a new concept of a phase change heat exchanger was added to improve the transient performance of the ECS. As a result, an ECS modeling program including the phase change heat exchanger is newly developed to estimate its effect in various flight conditions such as take-off, maneuver, cruise, and landing. The simulation result regarding a virtual flight profile has confirmed the new ECS fulfilled the requirement by showing the temperature of the cooling air returned from the bay was always kept below 80℃. Through this study, the new ECS concept with PCHE was verified successfully.
터빈엔진시험을 통한 제트연료 변경에 따른 엔진성능 변화 연구
김유일(Youil Kim),민성기(Seongki Min) 한국추진공학회 2011 한국추진공학회지 Vol.15 No.2
The engine ground and altitude tests were carried out to investigate the effect of jet fuel alteration on the performance of a small turbojet engine. JP-S was supplied 8% higher than JP-8 by fuel metering system at the same command. The employment of JP-S showed the similar starting characteristic to that of JP-8, however, difference in the ignition time and acceleration rate of engine speed due to the difference of fuel flow rate by fuel metering system was observed. In spite of jet fuel alteration, the test results yield the similar steady-state engine performance in net thrust, air flow, exhaust gas temperature, etc. On the other hand, the fuel consumption of JP-S increased by 5 % compared with that of JP-8. In point of specific fuel consumption (SFC), SFC of JP-S was approximately 1.1~2.6 %, 5 % higher than that of JP-8 in ground and altitude tests respectively at the same thrust.
진상욱(Sangwook Jin),이규준(Kyujoon Lee),민성기(Seongki Min) 한국추진공학회 2012 한국추진공학회 학술대회논문집 Vol.2012 No.11
고정된 자유제트 노즐에 대해 반-자유제트 시험이 가능한 항공기의 엔진의 크기를 전산유체해석을 통해 확인하였다. 엔진의 형상은 원뿔기둥 모양으로 단순화된 엔진 형상으로, 길이는 일정하게 두고 콘의 각도와 직경을 각각 4단계로 나누어 총 16가지의 경우에 대해 가상 시험을 진행 하였다. 시험물의 상대 위치는 유동을 만드는 자유제트 노즐의 출구면에서 발생된 경사충격파가 원뿔과 원기둥이 만나는 지점이 되도록 하였다. 시험이 가능한 유동의 판정은 시험 영역이 원뿔을 모두 감싸는 경우에 대해 반-자유제트 시험이 가능한 것으로 판단하였다. 시험 영역이 정상적으로 형상되는 시험물의 형상은 콘의 각과 시험물의 직경 사이에 반비례 관계를 알 수 있었으며 각각의 원뿔 각에 대해 최대 직경을 확인할 수 있었다. This paper described the capable maximum size of aircraft engine for a fixed free-jet nozzle in semi-free-jet test. The shape of engine was simplified as combination of a cone and cylinder. The relative position of engine in the test area was set as contacting region between cone bottom and the oblique shock derived by free-jet nozzle exit . The assessment of available test condition was regarded as the case which test area covered whole cone part. From these tests, it was found the maximum angle for each fixed cylinder diameter.