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회전차의 축방향 변위가 펌프의 성능과 축추력에 미치는 영향
홍순삼,강신형,Hong, Sun-Sam,Gang, Sin-Hyeong,Orachelashvili, B. 대한기계학회 1997 大韓機械學會論文集B Vol.21 No.4
The axial position of an impeller is misaligned in the process of manufacturing and assembling. For a single suction centrifugal pump with balancing holes, the effect of axial displacement of impeller on the performance, leakage loss and axial thrust acting on the impeller is experimentally investigated. The axial displacement decreases the pump efficiency, increases the leakage through the clearance between wearing ring and impeller, and affects the characteristics of axial thrust.
홍순삼,김진선,최창호,김진한 한국유체기계학회 2006 한국유체기계학회 논문집 Vol.9 No.1
Experiments are carried out to investigate the effect of radial tip clearance on a turbopump inducer, which has two blades with inlet tip blade angle of 7.8 degree and tip solidity of 2.7. Hydraulic and cavitation tests are performed for three cases of tip clearance ratio, that is, 0.026, 0.053, and 0.079. With increase in the tip clearance, inducer head and pressure on the inducer tip decrease. Attached cavitation and cavitation surge are observed in the cavitation tests. In the attached cavitation one cell rotates at the same rotational speed as that of the inducer. Cavitation performance deteriorates with increase in the tip clearance. The level of casing vibration increases in the cavitation condition and the level is very high when the attached cavitation appears.1. 서 론* 한국항공우주연구원 터보펌프그룹
터보펌브 인듀서의 비정상 캐비테이션에 관한 실험적 연구
홍순삼,김진선,최창호,김진한 한국유체기계학회 2005 한국유체기계학회 논문집 Vol.8 No.1
Steady and unsteady cavitation characteristics of turbopump inducer were investigated in this paper. To investigate the effect of blade angle on the inducer performance, three inducers with inlet tip blade angle of 7.8°, 7.0°, 6.1°, respectively, were tested. For 7.8°, 7.0° inducers in the non-cavitating condition, head decreased linearly with flow rate, but head-flow rate curve had a dip at the flow coefficient φ=0.065 for 6.1° inducer. Attached cavitation and cavitation surge were found in the 7.8°, 7.0° inducers in the cavitation tests. During the attached cavitation one cell rotated at the same rotational speed as that of the inducer. The cavitation surge did not rotate and the oscillating frequency was 7~20 Hz. From the curve of the critical cavitation number versus flow rate, it was found that the steady cavitation performance of 6.1° inducer was much lower than that of 7.8°, 7.0° inducers.1. 서 론* 한국항공우주연구원 터보펌프개발그룹
홍순삼,김대진,김진한,Hong, Soonsam,Kim, Daejin,Kim, Jinhan 항공우주시스템공학회 2013 항공우주시스템공학회지 Vol.7 No.4
A turbopump for a 75 ton class liquid rocket engine was tested at full speed for 20 seconds using model fluid. Liquid nitrogen is used for the oxidizer pump, water for the fuel pump, and hot gas for the turbine. The non-cavitating head of pump from the turbopump assembly test showed a good agreement with that from the pump component test. The relative difference of turbine efficiency between the turbopump assembly test and the turbine component test was 0.3% only. Suction performance from the turbopump assembly test was higher than that of pump component test, which resulted from the thermodynamic effect of cavitation.
75톤급 액체로켓엔진용 터보펌프 조립체의 상사매질 성능시험
홍순삼(Soon-Sam Hong),김진선(Jin-Sun Kim),김대진(Dae-Jin Kim),김진한(Jinhan Kim) 한국추진공학회 2011 한국추진공학회지 Vol.15 No.2
Performance test of a full-scale turbopump assembly for a 75 ton class liquid rocket engine was carried out at full speed. Model fluid was used as a working medium: liquid nitrogen for the oxidizer pump, water for the fuel pump, and hot air for the turbine. The turbopump was operated stably, satisfying the performance requirements. Head coefficient and flow coefficient of the pumps remained constant at the speed-increasing period. In terms of performance characteristics of pumps and turbine, the results from the turbopump assembly test showed a good agreement with those from the turbopump component tests.