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김명국(Myeong-Kuk Kim),정용수(Yong-Soo Jung),박노길(No-gill Park) 한국유체기계학회 1998 유체기계 연구개발 발표회 논문집 Vol.- No.-
Bearing design of turbo type geared centrifugal air compressor for low vibration level has been studied. The Transfer Matrix Method was used in this paper to analyze the air-compressor consisting of impellers, multi-stage geared rotors, and oil-film bearings. We have to consider this air-compressor as multi-geared rotating system, because characteristics of rotor-bearing system are different from conventional characteristics of non-rotating system. From the view point of Rotordynamics, the stiffness and damping coefficient of oil-film bearing in case of compressor system are more sensitive than other design parameters such as shaft length, shaft diameter and the weight of impellers, etc. Therefore, the stiffness and damping coefficients on each bearing were considered as design parameters. As the result of this study, turbo type air compressor with low vibration level can be achieved.
무인기용 소형 가스터빈 엔진을 위한 고감속 기어박스 개발
허재성(Jae Sung Huh),이강희(Kang Hee Lee),박영준(Young Jun Park),김명국(Myeong Kuk Kim),김재환(Jae Hwan Kim) 대한기계학회 2021 大韓機械學會論文集A Vol.45 No.2
항공용 동력전달장치인 기어박스는 자동차, 건설기계, 농업용 기계와 다르게 AGMA 12 이상의 기어등급, 항공용 베어링 적용, 다양한 항공기 자세 및 환경에 따른 윤활 시스템의 안정성, 소형 경량화 설계, 높은 등급의 품질시스템 유지 등과 같은 높은 수준의 요구도를 만족하여야 하며, 국내에서는 이러한 설계/제작 기술의 고난이도와 제한된 수요로 인하여 2010년 이후에서야 제한된 범위에서 연구개발이 시작되었다. 본 연구에서는 무인기용 가스터빈 엔진의 출력단에 연결되어 1:10으로 감속하면서 95%이상의 동력효율을 가지는 고감속 기어박스 개발에 대해 기술하고자 한다. 즉, 기어박스 개발을 위한 요구도 도출, 기어박스의 설계/해석/제작과 시험평가를 위한 시험장치 개발과 성능, 내구성 시험 결과를 제시하고자 한다. A gearbox for the transmission of an aircraft propulsion system has complex requirements, such as a gear rating of AGMA 12 or higher, application of aviation bearings, stability of the lubrication system at various aircraft attitudes and environments, compact and lightweight design, and maintenance of a high-grade quality system. These characteristics distinguish it from general gearboxes for automobiles, construction machinery, and agricultural machinery. Research and development on aircraft gearboxes became popular domestically to a limited extent after 2010 because of difficulties associated with the design and fabrication technologies as well as limited demand. In this article, we describe the development of a gearbox with a high reduction ratio that is connected to the output of a turboshaft engine of an unmanned aerial vehicle and transmits power with over 95% efficiency while decelerating to 1:10. The requirements for gearbox development are first derived for design/analysis/manufacturing, and a test rig is developed to evaluate its performance and endurance; finally, the test results are described.