• Journal of Biosystems Engineering
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• 제28권4호
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• pp.285-294
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• 2003

This study was carried out to propose a new-concept internal combustion engine which has great potential advantages to the conventional engines. Proposed new-concept engine is a kind of rotary engine. A rotor is rotating concentrically in a cylinder which is divided into two partitioning valves, and it makes four compartments in the cylinder. The volumes of each of four compartments are changing continuously with the rotor movement and performs the functions of intake, compression. expansion and exhaust simultaneously. Expected thermal efficiency for the real cycle is 26 percent at conditions of 1,000 rpm and compression ratio of 8.0, which is 3 to 4 percent higher than that of the conventional engines such as the piston engine, gas turbine and Wankel rotary engine. A simulation procedure proved that the new concept engine is functional, and has many potential advantages compared to the existing conventional engines.

• Journal of Biosystems Engineering
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• 제28권1호
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• pp.27-34
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• 2003

Present combustion engines have reached almost at the limit of development due to the fundamental structural problems. This study was carried out to propose a new concept internal combustion engine which has great potential advantages to the conventional engines. Proposed new concept engine is a kind of rotary engine. A rotor is rotating concentrically in a cylinder which is divided into two partitioning valves. and it makes four compartments in the cylinder. The volumes of each of four compartments are changing continuously with the rotor movement, and performs the functions of intake, compression. expansion and exhaust simultaneously. The results of this study can be summarized as follows. 1. Expected theoretical thermal efficiency is 44.9 percent at the condition of 1000rpm and compression ratio of 8.0. which is almost the same as that of the conventional engines. i.e., piston and Wankel rotary engine. 2. The new concept engine has 2. working strokes in every revolution. Therefore. the new concept engine can reduce the specific weight and volume than four-stroke piston engine. 3. The torque variation is very small. therefore minimal noise and vibration are expectable. 4. The new concept engine can reduce mechanical energy loss than piston engine because neither crank mechanism nor eccentrical motion exists.

• 한국추진공학회지
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• 제21권4호
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• pp.71-78
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• 2017

새로운 개념의 로터리엔진 초기 프로토타입을 제작하고 작동성 확인을 위한 모터링, 압축기 압력 및 연료 연소시험을 수행하였다. 기존 피스톤 엔진 및 반켈 로터리엔진과의 비교 분석을 통해 이 신개념 로터리엔진의 장 단점과 활용분야를 조사한 결과 이 엔진은 소형 항공기에 가장 적합하고, 이륜차와 휴대용 및 하이브리드 자동차용 Genset에도 기존 엔진보다 적용성이 더 좋을 것으로 파악되었다.

• 한국추진공학회지
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• 제23권3호
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• pp.104-111
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• 2019

압축기와 팽창기로 구성된 새로운 개념의 로터리엔진이 개발 중에 있다. 초기 프로토타입을 제작하고 작동성 확인을 위한 모터링, 압축기 압력 및 연료 연소시험을 수행하였다. 본 논문은 이 새로운 엔진에 적합하게 개발된 사이클 해석 방법에 대한 것이다. 본 엔진 고유의 작동 메커니즘에 대한 분석과 공기의 열역학적 해석을 공기 흡입, 압축, 연소실 진입, 연소, 팽창 그리고 배기에 이르는 각 과정에서 수행하였다. 본 논문에서 제시된 해석 방법으로 압축기와 팽창기 사이의 압축공기 냉각효과는 물론 엔진의 여러 설계 변수가 엔진 성능에 주는 영향을 파악할 수 있으며 이 논문에 몇 가지 경우에 대한 계산 결과를 기술하였다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2004년도 제22회 춘계학술대회논문집
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• pp.513-520
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• 2004

A steady-state/transient performance simulation model was newly developed for the propulsion system of the CRW (Canard Rotor Wing) type UAV (Unmanned Aerial Vehicle) during flight mode transition. The CRW type UAV has a new concept RPV (Remotely Piloted Vehicle) which can fly at two flight modes such as the take-off/landing and low speed forward flight mode using the rotary wing driven by engine bypass exhaust gas and the high speed forward flight mode using the stopped wing and main engine thrust. The propulsion system of the CRW type UAV consists of the main engine system and the duct system. The flight vehicle may generally select a proper type and specific engine with acceptable thrust level to meet the flight mission in the propulsion system design phase. In this study, a turbojet engine with one spool was selected by decision of the vehicle system designer, and the duct system is composed of main duct, rotor duct, master valve, rotor tip-jet nozzles, and variable area main nozzle. In order to establish the safe flight mode transition region of the propulsion system, steady-state and transient performance simulation should be needed. Using this simulation model, the optimal fuel flow schedules were obtained to keep the proper surge margin and the turbine inlet temperature limitation through steady-state and transient performance estimation. Furthermore, these analysis results will be used to the control optimization of the propulsion system, later. In the transient performance model, ICV (Inter-Component Volume) model was used. The performance analysis using the developed models was performed at various flight conditions and fuel flow schedules, and these results could set the safe flight mode transition region to satisfy the turbine inlet temperature overshoot limitation as well as the compressor surge margin. Because the engine performance simulation results without the duct system were well agreed with the engine manufacturer's data and the analysis results using a commercial program, it was confirmed that the validity of the proposed performance model was verified. However, the propulsion system performance model including the duct system will be compared with experimental measuring data, later.

• 한국항공우주학회지
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• 제33권2호
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• pp.22-31
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• 2005

본 연구에서는 회전익 항공기의 수직 이/착륙 성능과 고정익 항공기의 고속/고효율 순항 비행 성능을 모두 가지는 Canard Rotor/Wing 항공기 최적 형상설계를 수행하였다. CRW 항공기의 특징인 로터/날개 가변 방식과 로터 회전 시 팁 제트를 통하여 회전력을 얻는 점 때문에 기존의 회전익 또는 고정익 사이징 프로그램만으로는 바로 적용이 어렵고 Reaction Driven 로터에 대한 해석 모듈의 추가와 회전익/고정익 비행 모드 해석이 혼합되어야 한다. 따라서 기존의 사이징 프로그램을 바탕으로 로터 성능, 덕트 유동, 엔진 유동 해석 코드를 연결하여 Reaction Driven 로터 성능 해석이 가능하게 하였으며, 비행체 외형상 특징과 임무별 비행특징이 반영되도록 사이징 프로그램을 개발하였다. 1500 lbs급 소형 무인기에 대하여 비행체 사이징을 수행하고 성능에 크게 영향을 미치는 설계변수를 파악하여 최적화 문제를 구성하였고 전역적 최적화 기법을 이용하여 최소 중량을 가지는 CRW 항공기의 최적형상을 도출하였다.