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김춘택(Chun Taek Kim),양인영(Inyoung Yang),이경재(Kyungjae Lee),이양지(Yangji Lee) 한국항공우주학회 2016 韓國航空宇宙學會誌 Vol.44 No.8
과거 냉전시절의 우주개발은 성능이라는 목표에 초점이 맞추어져 있었다. 하지만 냉전 이후 경제성이 우주개발에 있어서 중요한 목표가 되었으며, 이러한 경제성을 확보하기 위한 중요한 수단으로 재사용 발사체에 대한 관심과 연구가 지속적으로 증가하고 있는 실정이다. 본 논문에서는 이와 같이 진행되고 있는 현재 세계 각국의 재사용 발사체 및 미래추진기관에 대한 기술발전 전망과 방향에 대하여 소개하고자 한다. During the Cold War, all space developments were focused on the performance only. However economy becomes more important for space development after the Cold War. There is a growing interest in reusable launch vehicle to secure the economic feasibility. In this paper, technology development prospects and direction of reusable launch vehicles and future propulsion systems of various countries are presented.
김진한,김춘택,이대성,Kim, Jin-Han,Kim, Chun-Taek,Lee, Dae-Sung 한국유체기계학회 1999 한국유체기계학회 논문집 Vol.2 No.1
This paper introduces the part of efforts to develop a derivative type turboshaft engine from an existing baseline engine for multi-purpose helicopters aiming at 4000 kg of take-off weight for 10-12 passengers. As a first step in meeting the development goal of increasing the output power from 720 hp to 840hp with minimum modification, a two stage axial compressor was redesigned to obtain the higher pressure ratio by removing the inlet guide vane and increasing the chord length. As a result, a two stage axial compressor was designed to facilitate a flow rate of 3.04 kg/s, a pressure ratio of 2.01 and an adiabatic efficiency of $85\%$. Its performance tests were carried out and verification of test results and redesign are under progress. Aerodynamic and structural analyses of the preliminary design are mainly described in this paper.
기체 유량 측정에서 몬테 카를로 모사를 이용한 측정불확도 평가
이대성,양인영,김춘택,양수석,Lee, Dae-Sung,Yang, In-Young,Kim, Chun-Taek,Yang, Soo-Seok 대한기계학회 2003 大韓機械學會論文集B Vol.27 No.12
Monte Carlo simulation(MC) method was used as an uncertainty assessment tool for gas flow measurement in this paper. Uncertainty sources for gas flow measurement were analyzed, and probability distribution characteristics of each source were discussed. Detailed MC methodology was described including the effect of the number of simulation. The uncertainty result was compared with that of the conventional sensitivity coefficient method, and it was revealed that the results were different from each other for this particular gas flow measurement case of which the modelling equation was nonlinear. The MC was comparatively simple, convenient and accurate as an uncertainty assessment method, especially in cases of complex, nonlinear measurement modelling equations. It was noted that the uncertainty assessment method should be selected carefully according to the mathematical characteristics of the measurement.
터빈 노즐의 Fillet 설치에 따른 가스터빈 엔진의 성능 특성에 관한 연구
김재민(Jaemin Kim),진상욱(Sangwook Jin),김귀순(Kuisoon Kim),최정열(Jeong-Yeol Choi),김춘택(Chun-Taek Kim) 한국추진공학회 2009 한국추진공학회 학술대회논문집 Vol.2009 No.11
터빈 형상에 따른 가스터빈 엔진의 성능을 전산유체역학을 기반으로 하여 개발된 프로그램을 통하여 예측하여 보았다. 압축기, 연소기, 터빈의 상호작용을 고려하여 엔진의 성능을 예측하였다. 압축기와 터빈의 해석은 각각 2차원과 3차원의 Navier-Stokes 방정식을 사용하였다. 연소기에서는 화학평형방정식을 적용하여 온도변화를 계산하였다. 계산은 터빈 노즐의 fillet 설치의 유무에 따라 두 가지 형상을 적용하여 비교하였다. In this study, the effect of turbine geometry on the overall performance of a gas turbine was investigated by computational fluid dynamics. Overall engine performance was predicted through a full engine simulation program which can predict the interactions of the compressor, the combustor and the turbine. The compressor and the turbine analysis code solves 2D and 3D Navier-Stokes equations respectively. The chemical equilibrium code was applied to simulate the combustor. The computations were performed for two different shapes of turbine nozzle. The nozzle shapes adopted a baseline blade and a blade with fillet.