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遠心 임펠러의 相對 渦流 크기 모델에 根據한 이론적인 미끄럼 係數
팽기석,정명균,Paeng, Kee-Seok,Chung, Myung-Kyoon 대한기계학회 2000 大韓機械學會論文集B Vol.24 No.3
By calculating the location and size of the relative eddy formed in the rotating impellers with the logarithmic spiral vanes, a new simple but accurate slip factor is analytically derived. The proposed slip factor depends on only one parameter that is a function of the number of vanes and the vane exit angle. Predicted slip factor for various cases are compared with those estimated by a number of previous slip factors as well as a recent theoretical calculation by Visser et al. ( JFM, Vol. 268, pp. 107-141, 1994). It is found that the present slip factor yields almost similar results to Wiesner's which has been empirically formulated based on the theoretical calculation of Busemann.
팽기석(Kiseok Paeng),안철주(Chulju Ahn),민성기(Seongki Min),김유일(Yuil Kim) 한국추진공학회 2010 한국추진공학회 학술대회논문집 Vol.2010 No.11
추력 150 lbf 급의 초소형 터보제트 엔진이 개발되었다. 본 엔진은 소형 무인항공기(UAV), 기만기, 대공망 제압용 유도무기 등 다양한 무기체계에 적용이 될 수 있도록 고성능, 소형, 저가로 설계되었으며, 시제엔진을 제작하여 지상 성능 시험 및 고도 시험을 수행하였다. 본 논문에서는 소형, 저가, 고효율 터보제트 엔진을 구성하는 각 엔진 구성품의 특징, 구조, 구성품 및 엔진 시험 결과 등에 대하여 기술하였다. A 150 lbf-thrust class micro turbojet engine has been developed. The engine could be applied to power plant for small aviation vehicle such as UAV, decoy and anti-radar missile and was designed with concepts that has small size, low-cost and high performance. A prototype was manufactured and performed the ground static test and high altitude test. This paper outlines the features and layout of 150 lbf turbojet engine and also describes the design characteristics and test results of the engine and components.
정명균,오재민,팽기석,송재욱,Jeong, Myeong-Gyun,O, Jae-Min,Paeng, Gi-Seok,Song, Jae-Uk 대한기계학회 2002 大韓機械學會論文集B Vol.26 No.3
In order to design and analyze the performance of an axial-flow pump it is necessary to know the flow deviation, deflection angle and pressure loss coefficient as a function of the angle of incidence for the hydrofoil section in use. Because such functions are unique to the particular section, however, general correlation formulae are not available for the multitude of hydrofoil profiles, and such functions must be generated by either experiment or numerical simulation for the given or selected hydrofoil section. The purpose of present study is to generate design correlations for hydrofoils with double circular arc (DCA) camber by numerical analysis using a commercial code, FLUENT. The cascade configuration is determined by a combination of the inlet blade angle, blade thickness, camber angle, and cascade solidity, and a total of 90 cascade configurations are analyzed in this study. The inlet Reynolds number based on the chord and the inlet absolute velocity is fixed at 5${\times}$10$\^$5/. Design correlations are formulated, based on the data at the incidence angle of minimum total pressure loss. The correlations obtained in this way show good agreement with the experiment data collected at NASA with DCA hydrofoils.
UAV 추진기관의 현황 및 차세대 UAV 추진기관의 개발 전망
이동훈(Donghun Lee),팽기석(Kisuk Paeng),김유일(Yuil Kim),박부민(Poomin Par),최성만(Seongman Choi),허환일(Hwanil Huh) 한국추진공학회 2009 한국추진공학회 학술대회논문집 Vol.2009 No.11
현재 운용중인 UAV(Unmanned Aerial Vehicle) 추진기관의 현황 및 추진기관 종류에 따른 장, 단점을 분석하였으며, 차세대 UAV 추진기관의 개발 전망 및 UAV 추진기관에 적용될 가스터빈 엔진의 특성 및 요구조건을 제시하였다. The characteristics and present state of UAV engine which is operating currently were studied and advantages/disadvantages of UAV engines were also analyzed. Forecast of next generation UAV engine development trend was presented and the performance demand of gas turbine engine for UAV were suggested.
이동훈(Donghun Lee),팽기석(Kisuk Paeng),김유일(Yuil Kim),박부민(Boomin Park),최성만(Seongman Choi),허환일(Hwanil Huh) 한국추진공학회 2010 한국추진공학회지 Vol.14 No.3
The characteristics and classification of UAV power plants were studied. The energy source for electric generation and power source for internal combustion engine for UAVs were compared. The advantage and drawbacks of power plants were analyzed respectively and the performance demand condition was suggested for next generation UAV power plant finally.
초소형 터보제트엔진 연소기의 리그시험 및 고고도 점화시험
이동훈(Donghun Lee),김형모(Hyungmo Kim),박부민(Poomin Park),유경원(Gyungwon You),팽기석(Kisuk Paeng) 한국추진공학회 2009 한국추진공학회 학술대회논문집 Vol.2009 No.5
초소형 터보제트엔진에 적용되는 반경형 연소기에 대한 전부하 연소리그시험과 고고도 점화시험을 수행하였다. 지상정지, 표준대기 조건에서 엔진의 최대운용점에서 연소리그시험과 기본 점화시험을 수행한 결과, 11.2%의 압력손실과 99.85%의 최종 성능을 도출하였으며, 주 시동영역에서 공기과잉율 2~6의 점화영역이 측정되었다. 30,000 ft 고고도 점화시험을 실시하여 고공환경에서의 점화영역을 측정하였고, 이러한 결과를 통해 개발된 연소기의 설계가 타당함을 입증하였다. A full rig combustor test and altitude ignition test were carried out for radial-annular combustor of micro turbojet engine. 11.2% total pressure loss and 99.85% of combustion efficiency were measured at design point of engine under sea level standard condition and 2~6 of air excess ratio for ignition envelope was achieved on engine starting regime. Finally, A 30,000 ft high altitude ignition test was also performed and finally we found out that the developed radial-annular combustor is appropriate to micro turbojet engine.