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냉각 팬 형상을 고려한 저압전동기 냉각시스템의 수치해석 및 실험적 연구
성민규(Minkyu Sung),이종인(Jongin Lee),장충만(Chungman Jang),정준영(Junyeong Jung) 대한기계학회 2019 대한기계학회 춘추학술대회 Vol.2019 No.11
Cooling systems in industrial motors directly and indirectly affect motor performance and efficiency. TEFC (Totally Enclosed Fan Cooled) motor is a form in which internal heat is discharged through fins attached to the frame. Flow generated from an external cooling fan is discharged to the motor frame to pass between the frame and the fin to cool the motor.In this paper, in order to investigate the effect of flow according to the cooling fan shape on the motor performance, the results were compared and analyzed by numerical analysis and experiment on 180Fr. 4P 30㎾ TEFC motor. Numerical analysis is performed with a commercial CFD Software Star-CCM+ and experiments are performed with a cooling fans manufactured using 3D print technology.
김규섭(Kyu-Seop Kim),김예현(Yehyun Kim),정상우(Sangwoo Jung),정준영(Junyeong Jeong),권세진(Sejin Kwon) 한국추진공학회 2019 한국추진공학회지 Vol.23 No.5
Hypergolic thrusters have been extensively researched and applied to spacecraft propulsion based on their simplicity and high reliability of ignition. Research on the impingement characteristics of N2O4/amine has been profoundly carried out since the 1960s in advanced countries, especially the United States. Recently, enhancements to advanced hypergolic thrusters using MON/MMH have been planned by NASA to improve compactness and high performance. In this work, technical studies were investigated on the mixing of hypergolic propellant and its combustion instabilities such as reactive separation flow and popping.
접촉 점화성 추진제의 충돌형 혼합 특성 연구 동향 조사
김규섭(Kyu-Seop, Kim),김예현(Yehyun Kim),정상우(Sangwoo Jung),정준영(Junyeong Jeong),권세진(Sejin Kwon) 한국추진공학회 2019 한국추진공학회 학술대회논문집 Vol.2019 No.5
접촉 점화 추진제 특성을 활용한 추력기는 간단한 시스템 구조와 점화의 높은 신뢰성을 기반으로 고고도, 우주 환경에서의 적용되어 왔다. 미국을 위시한 선진국의 경우 사산화질소/아민 계열의 추진제의 충돌 혼합 특성을 1960년대 이후로 심도 깊은 연구를 진행하고 있으며 최근 차세대 접촉 점화 추력기 역시 고성능화, 경량화 측면에서 활발한 연구개발을 수행하고 있다. 본 논문에서는 접촉 점화성 추진제의 충돌형 혼합 특성과 반응성 유동 분리(Reactive Separation Flow), 간헐적 폭발(Popping)의 충돌 혼합 시 발생할 수 있는 연소 불안정성에 대한 연구 동향을 조사하고 요약하였다. The hypergolic thruster has been extensively researched and applied on spacecraft propulsion based on simple system and high reliability of ignition. Research on impingement characteristics of N2O4/Amine has been profoundly carried out since the 1960s in advanced countries, especially the US. Recently enhancement of advanced hypergolic thruster using MON/MMH is currently planned by NASA in terms of improving compactness and high performance. In this work, technical trends of mixing of hypergolic propellant and its combustion instabilities such as reactive separation flow and poping were investigated.