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이진근,이경재,고성희,곽재수,Lee, Jinkun,Lee, Kyungjae,Kho, Sunghee,Kwak, Jae Su 항공우주시스템공학회 2007 항공우주시스템공학회지 Vol.1 No.1
Inlet distortion test was performed at Korea Aerospace Research Institute in order to evaluate the degradation of engine performance under the distorted inlet condition. In this paper, only the inlet pressure distortion was taken into consideration. During the development process of the inlet distortion test technique, variable distortion screen was designed and evaluated under various test conditions to establish the experimental database of distortion for engine test. The result of inlet distortion test for engine shows that the operating point was changed toward the worse direction and the degradation of engine performance by inlet distortion was verified.
이진근(Jinkun Lee),김진한(Jinhan Kim) 한국항공우주학회 2004 韓國航空宇宙學會誌 Vol.32 No.5
액체산소와 등유를 추진제로 사용하는 액체로켓엔진 터보펌프의 기본설계 사양을 도출하기 위한 1차원 시스템 설계 프로그램을 개발하였다. 터보펌프식 액체로켓엔진 시스템으로는 가스발생기 사이클과 단계식 연소 사이클 두 가지 사양을 고려하였다. 시스템 해석을 통하여 엔진 시스템의 유량 밸런스, 추력, 비추력, 혼합비, 터보펌프의 출력, 터빈 팽창비에 대한 분석이 수행되었으며 가스발생기를 제외한 대부분의 설계변수들이 실제 엔진과 잘 일치하는 결과를 얻었다. 본 논문에서는 개발된 1차원 시스템 설계 프로그램을 사용하여 임의의 액체로켓엔진 추력에 대한 터보펌프 기본 사양을 도출할 수 있음을 확인하였다. A 1D system design program has been developed for the preliminary design of the turbopump system in liquid rocket engines, which use LOx and kerosene as propellants. Gasgenerator cycle and staged combustion cycle were considered as turbopump type liquid rocket engine systems. In the system analysis, mass flow balances, thrust, specific impulse, mixture ratios, turbopump power, and turbine expansion ratio of engine system were analyzed. Results show that most of the parameters agree well with real engine parameters except gasgenerator. Therefore, the 1D system design program developed in this study can be used to derive the preliminary design parameters of a turbopump with any thrust level liquid rocket engine.
가스 터빈 엔진의 서지마진 측정을 위한 연료 돌출 시험
이진근(Jinkun Lee),김춘택(Chuntaek Kim),이경재(Kyungjae Lee),하만호(Manho Ha),안동찬(Dongchan An),양수석(Sooseok Yang),이대성(Daesung Lee) 한국유체기계학회 2003 유체기계 연구개발 발표회 논문집 Vol.- No.-
A fuel spiking test was performed to measure the surge margin of gas turbine engines. The surge marin was mainly determined by the compressors and fuel spiking was used to change the operating point in the compressor characteristic map while speed remained constant. To access the surge margin region different spiking signals were applied by modulations of time(frequency) and fuel flow rate(amplitude). The test results showed good agreements with expected fuel spiking patterns and possibility of further studies.
고공환경 엔진시험의 신뢰성 평가를 위한 불확도 분석 및 분산 분석 기법의 적용
이진근(Jinkun Lee),양인영(Inyoung Yang),양수석(Sooseok Yang),곽재수(Jaesu Kwak) 한국유체기계학회 2006 유체기계 연구개발 발표회 논문집 Vol.- No.-
The altitude engine test is a sort of engine performance tests, carried out to measure the performance of a engine at the high altitude circumstance prior to that at the flight test. The measured values in the test are the pressures and temperatures at various positions, air flow rate, fuel flow rate, and thrust. These measured values are used to derive the representative performance values such as the net thrust and the specific fuel consumption through a momentum equation hence each of the measured values has certain effects on the total uncertainty of the performance values. In this paper, the combined standard uncertainties of the net thrust and the specific fuel consumption were estimated from the uncertainties of the various measured values and the confidence level of the altitude engine test for the repeatability and the reproducibility was validated by the analysis of variation on the repeated test data of the different tester groups.
박태춘(Tae Choon Park),강영석(Young-Seok Kang),양수석(Soo Seok Yang),이진근(Jinkun Lee) 한국항공우주연구원 2009 항공우주기술 Vol.8 No.1
5㎿급 발전용 가스터빈을 개발하기 위해 주요 구성품 중의 하나인 압축기의 성능을 시험 평가하고자 하며, 이를 위한 사전 작업으로 압축기 시험 리그의 진동 특성을 분석하여 압축기 운전시 구동 방법에 대한 정보를 확보하였다. 압축기 시험 설비는 입?출구 배관과 시험부 및 구동부로 구성되어 있고, 특히 구동부와 시험부에서 가속도계를 이용하여 진동 특성을 계측하였다. 압축기 주 하우징과 콜렉터, 베어링캐리어, 토크미터, 기어박스, 전동 모터 등에 가속도계를 장착하여 진동 속도 및 주파수 분석을 수행하였다. Vibration analysis of a turbo compressor test rig was carried out in order to investigate the vibrational characteristics of the compressor facility in KARI before conducting the compressor performance test of 5㎿-class gas turbine engine for generation. The overall compressor test facility consists largely of inlet and exit ducts, a test section and a driving part. Vibration was measured with accelerometers at the test section and the driving part, especially at a main housing, a collector, a bearing carrier, a torquemeter, a gearbox, and an electric motor. Gap sensors are also installed to measure the rotordynamic characteristics of compressor shaft.