• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.389-392
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• 2011

In this study, the engine performance data was extracted and analyzed through the flight test of Smart UAV which is tilt rotor aircraft. The flight test was conducted for the transition flight regime where the tilt angle of prop-rotor varies from 90 degree to 0 degree and vice versa. The engine performance data such as engine power and specific fuel consumption gathered from flight tests were compared well with the results of engine performance analysis program.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.11a
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• pp.382-386
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• 2006

Three dimensional numerical analysis of the supersonic turbines with different rotor tip clearances was conducted to analyze the effect of the tip gap clearance variations on the turbine performance. The result showed that the turbine performance deteriorates and the tip leakage increases by the effect of the rotor tip clearance and the tip leakage affects turbine performance degradation dominantly.

• Journal of the Korean Society of Propulsion Engineers
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• v.7 no.4
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• pp.19-26
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• 2003

In this paper, the result of the conceptual study of a tipjet driven propulsion system is presented. The concept of a tipjet driven propulsion system is to employ tipjet as power source to drive a rotor Because the vehicle is supposed to takeoff and land vertically, a rotor system, which has tipjet nozzles, is adopted to fly like a helicopter. Exhaust gas, which is generated by an engine, Passes through an internal duct system and divided into four blade ducts. The design code is consists of two parts, engine model and internal duct model. Inside a rotating duct, compressible flow is affected by two additional force terms, centrifugal force and coriolis force and they govern the performance in rotary mode, The intention of this paper is to address the issues associated with sizing and optimizing configurations of a tipjet driven propulsion system especially in rotary wing mode.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.413-422
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• 2005

In this paper, numerical results for 3-D supersonic turbine flow have been firstly compared with the experimental results to verify results computed by $Fine^{TM}/Turbo$. It was found that $Fine^{TM}/Turbo$ can accurately predict flow characteristics within supersonic turbine. Next, an grid system for 3D turbine flow was optimized selected through grid independency test. Finally the effect of axial gap between rotor and nozzle and chamfer angle of blade edge on the flow characteristics within 3-D supersonic turbine was analyzed with Frozen Rotor method.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.297-301
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• 2007

The blades of supersonic turbines with low aspect ratio are usually designed to have the same cross sectional shape in radial direction. The profile diameter definition of turbines may lead to produce unintended flow passage area variations resulting performance degradation. In this paper, the effects of profile diameter definition on the supersonic impulse turbine performance have been investigated. Computational results of three different profile diameters are compared. It has been found that flow passage area variation can be achieved according to designer's intention when blade profile is defined at rotor tip diameter. Furthermore, the turbine blade profile defined at rotor tip showed better performance than the others.

• Journal of the Korean Society of Propulsion Engineers
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• v.10 no.2
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• pp.78-86
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• 2006

This paper presents the performance test result of the 30-ton class turbopump turbine. Test has been conducted using high pressure cold air, The turbine overall performance has been measured for various pressure ratio and rotational speed settings. The nozzle-rotor clearance effect on turbine performance also has been tested for the four kinds of the nozzle-rotor clearance values. We found that turbine efficiency rated 51.1% at its design velocity ratio and pressure ratio of 13.5. We also found that turbine efficiency can be increased by 3.5% for approximately 1mm decrement of the nozzle-rotor clearance from its nominal value.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.1038-1044
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• 2017

We are working on improving the performance by applying the three-dimensional design element to the rotor blades of high pressure supersonic impulse turbine that drives turbo pump of liquid rocket engine. In this paper, based on the shape of a rotor blade of a turbopump turbine designed in the past, a three-dimensional shape is applied to a rotor blade through a stacking line change such as sweep and dihedral. After performing the flow analysis, the changes in the turbine performance characteristics for each design element were carefully examined and the results were summarized.

• Journal of the Korean Society of Propulsion Engineers
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• v.8 no.4
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• pp.76-83
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• 2004

A Propulsion System of the CRW(Canard Rotor Wing) type UAV(Unmanned Aerial Vehicle) was composed of the turbojet engine to generate the propulsive exhaust gas, and the duct system including main and rotary ducts, the nozzle subsystem including main and tip jet nozzle for three flight modes such as lift/landing mode, low speed transition flight mode and high speed forward flight mode. Transient simulation performance utilized the ICV (Inter-component volume) method and simulated using the SIMULINK. Transient performance analysis was performed on 3 cases. Fuel flow schedules to accelerate from Idle to maximum rotational speed were divided into the step increase of the most severe case and ramp increase cases to avoid the overshoot of turbine inlet temperature, and variations of thrust and the turbine inlet temperature were investigated in some transient analysis cases.

• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• 2017.11a
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• pp.143-144
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• 2017

에어보트(Air boat)는, 판옥선처럼 선체 밑바닥이 편평한 형태로 되어있어 물위는 물론 일반 선박이 갈 수 없는 얕은 수면, 늪지수풀 위를 달릴 수 있는 모터보트의 한 종류로서, 팬 보트(Fan boat) 혹은 덕 보트(Duck boat)라고 불리기도 한다. 선체상부 뒤쪽에 장착된 로터의 회전에 의한 풍력으로 추진되며, 로터 바로 뒤에 방향키가 있다. 선체 재질로는 스틸, FRP 등이 사용되고 있으나 최근 고부가선박을 대상으로 알루미늄, 탄소섬유 사용이 늘어나고 있다. 주로 수상 크루징, 낚시, 스쿠버 등에 활용되며, 특히 선저의 독특한 형상으로 인해 군사용, 인명구조용, 수산물수송용 등 특수 목적으로도 사용된다. 이 연구에서는 에어보트 국산화 개발을 위해 주요 개발항목을 도출하고, 12인승 보트를 제조하고자 한다.

• Journal of Advanced Marine Engineering and Technology
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• v.18 no.2
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• pp.1-17
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• 1994

잠수함추진방식은 크게 원자력 추진과 재래식 추진으로 나눌수 있다. 최근에는 재래식 추진방식과 하이브리드 개념으로 운용될 수 있는 AIP(Air Independent Propulsion)방식도 활발히 연구되고 있다. AIP추진으로는 폐회로 디젤기관추진(Closed Cycle Diesel Engine Propulsion), 연료전지추진(Fuel Cell Propulsion), 스터링기관추진(Stirling Engine Propulsion) 및 폐회로터빈추진(Closed Cycle Turbin Propulsion) 등이 있다. 이러한 잠수함 추진체계에 대해 앞으로 크게 세부분으로 나누어 그 현황과 발전추세를 살펴보고자 한다. 즉, 초기의 순수전기추진방식으로 불리는 재래식 추진체계, 재래식 추진방식의 한계를 극복하기 위해 최근 활발히 연구되고 있는 외기와 무관한 추진장치인 폐회로 추진체계, 그리고 궁극적으로는 에너지의 문제로 귀착되어 거의 무한대의 에너지원을 가지고 있는 원자력 추진체계로 구분하여 그 현황과 발전내용을 살펴 봄으로써 잠수함추진체계의 국내연구 개발방향정립에 조금이나마 보탬이 되었으면 합니다. 또한 차세대 추진장치로 불리는 전자유체 추진방식에 대해서는 한국박용기관 학회지 1993년 4월호 "박용전자유체(MHD) 추진장치"를 참조하시기 바랍니다.조하시기 바랍니다.