http://chineseinput.net/에서 pinyin(병음)방식으로 중국어를 변환할 수 있습니다.
변환된 중국어를 복사하여 사용하시면 됩니다.
박부민(Poo-Min Park),양인영(In-Young Yang),김형모(Hyung-Mo Kim),김재환(Jae-Hwan Kim),양수석(Soo-Seok Yang),이대성(Dae-Sung Lee) 한국항공우주연구원 2006 항공우주기술 Vol.5 No.1
본 논문은 항우연에 설치된 가스터빈,연료전지 혼합형 고효율 발전시스템의 실증 유닛의 운전에 대한 것이다. 시스템의 연료전지는 SOFC이고, 가스터빈은 마이크로 가스터빈을 사용하였다. 마이크로 가스터빈 및 연료전지 시스템은 손상되기 쉬운 관계로, 이의 운전은 아주 섬세한 주의가 요구된다. 실증 유닛의 성공적인 운전을 통하여 가스터빈,연료전지 혼합형 발전시스템의 개념이 검증되었으며, 이의 운전에서 쌓은 경험은 향후 혼합형 발전 시스템의 연구에 밑바탕이 될 것이다. High efficiency gas turbine (GT),fuel cell (FC) hybrid power generation system demonstration unit is constructed in KARI. SOFC and micro gas turbine were used as the fuel cell and the gas turbine of the system. Operation of the hybrid system is very difficult because both component are easily damaged from a wrong operation. Thus delicate operation technique is required. Most of all, safety is the first concern in operating the hybrid system due to the hydrogen which is supplied to the fuel cell. The concept of the GT,FC hybrid generation system is proved by the successful operation of the demonstration unit. The experience we obtain from this study will be very helpful for future hybrid power generation system research.
박부민(Poo-Min Park),양인영(In-Young Yang),김재환(Jae-Hwan Kim),양수석(Soo-Seok Yang),이대성(Dae-Sung Lee) 대한기계학회 2006 대한기계학회 춘추학술대회 Vol.2006 No.6
Demonstration unit for the gas turbine-fuel cell hybrid power generation system is developed and the system performance was tested. SOFC and micro gas turbine were used as the fuel cell and the gas turbine of the system. As the result of the experiment, concept of the GT-FC hybrid generation system is proved. The demonstration unit was constructed as the 1st stage of 200㎾ grade high efficiency GT-FC hybrid power generation system development which is divided into 3 stages.
박부민(Poo-Min Park) 한국항공우주연구원 2013 항공우주기술 Vol.12 No.2
프로펠러는 인간동력 항공기 추진시스템의 중요한 구성품이다. 높은 프로펠러 효율을 얻기 위하여 프로펠러는 큰 지름을 가지고 느리게 구동된다. 프로펠러는 인간동력 항공기용 프로펠러 설계 프로그램을 사용하여 설계되었다. 프로펠러의 피치는 지상에서 조정이 가능하다. 본 논문에서는 여러 가지 변수에 대하여 설계에 사용된 동일한 프로그램을 통하여 프로펠러의 성능 해석을 수행하였다. 또한, 파일롯의 체력이나 비행속도의 변화에 따른 탈설계점 해석도 수행하였다. 설계된 프로펠러는 카본 복합재의 초경량 구조로 제작되어 총950g의 무게로 제작되었다. 제작된 프로펠러는 아이언 버드에서의 지상 성능 시험을 통하여 속도 및 동력을 측정하고 튜닝을 수행하여 실기에 장착되어 최종적으로 291 m 비행에 성공하였다. Propeller is an important component of Human Powered Aircraft (HPA) propulsion system. HPA uses large diameter low rotational speed propeller to get high propeller efficiency. The propeller was designed by HPA propeller designing program. The propeller pitch is adjustable by rotating the blade axis angle at ground. Performance of the propeller for various parameters are analysed by the same program used for design. Off-design condition performance was also checked including pilot power change and flight speed change. The propeller was manufactured in ultra-light structure using carbon composite material down to 950g. The propeller was ground tested on ironbird and installed on KARI HPA. Finally the HPA flew 291m with this propeller.
박부민(Poo Min Park),김형모(Hyung Mo Kim),최영호(Young Ho Choi),양수석(Soo Seok Yang),천무환(Mu Hwan Chon) 한국연소학회 2008 한국연소학회지 Vol.13 No.4
Performance test of 5MW class gasturbine combustor was carried out at combustor test facility of KARI(Korea Aerospace Research Institute). The combustor is dry low NOx type premixed combustor and fuel is natural gas. The characteristics of combustor were measured including emission, pressure pulsation and exit temperature distribution. Optimum operation point of combustor was found by changing parameters like fuel ratio between pilot and main burner. The test result showed that the combustor performance is sufficient to satisfy the gasturbinc system requirement.
김재환(Kim, Jae Hwan),박부민(Park, Poo Min),양수석(Yang, Soo Seok),이대성(Lee, Dae Sung) 한국신재생에너지학회 2005 한국신재생에너지학회 학술대회논문집 Vol.2005 No.06
This paper describes an on-going national R&D program for the development of a gas turbine/fuel cell hybrid power generation system and related R&D activities. The final goal of this program is to develop a 200kW-c1ass gas turbine/fuel cell hybrid power generation system and achieve high efficiency over 60% (AC/LHV). In the first phase of the development, a sub-scaled 60kW-class hybrid system based on the 50kW-class microturbine and the 5kW SOFC will be developed for the purpose of concept proof of the hybrid system. Core components such as the microturbine and the SOFC system are being developed and parallel preparation for system integration is being carried out. Before the core components are assembled in the final system. operating characteristics of a hybrid system are investigated from a simulated system where a turbocharger (microturbine simulator) and a modified fuel cell burner test facility (fuel cell simulator) are employed. The 60kW demonstration unit will be built up and operated to provide the valuable information for the preparation of the final full scale 200kW hybrid system.