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75톤급 액체로켓엔진용 터보펌프 조립체의 상사매질 성능시험
홍순삼(Soon-Sam Hong),김진선(Jin-Sun Kim),김대진(Dae-Jin Kim),김진한(Jinhan Kim) 한국추진공학회 2010 한국추진공학회 학술대회논문집 Vol.2010 No.11
추력 75톤급 액체로켓엔진용 터보펌프 조립체 실물형에 대하여 정격 회전수에서 성능시험이 수행되었다. 실매질 대신 상사매질을 사용하였는데 산화제펌프에는 액체질소, 연료펌프에는 물, 터빈에는 고온 공기가 공급되었다. 시험 중 터보펌프는 안정적으로 운전되었으며 성능 요구조건을 만족시켰다. 운전 초기의 회전수 상승구간에서도 펌프의 양정계수와 유량계수는 일정하게 유지되었다. 터보펌프 단품 성능시험과 조립체 성능시험 결과를 비교할 때 펌프 양정계수와 터빈 효율이 두 종류의 성능시험에서 비교적 잘 일치하였다. 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.
홍순삼(Soon-Sam Hong),김진선(Jin-Sun Kim),김대진(Dae-Jin Kim),김진한(Jinhan Kim) 한국추진공학회 2009 한국추진공학회 학술대회논문집 Vol.2009 No.5
가스발생기 사이클의 추력 30톤급 액체로켓엔진용 터보펌프에 대하여 실매질 고온 시험이 이루어졌다. 산화제펌프와 연료펌프에는 각각 액체산소, 케로신이 공급되고 터빈에는 고온의 가스가 공급되며 이 가스는 펌프로부터 배출되는 추진제의 일부를 가스발생기에서 연소시켜 생성된다. 터보펌프는 시험 중에 설계점과 탈설계점의 전 영역에서 안정적으로 작동하였고 성능 요구 조건을 만족시켰다. 본 논문에서는 여러 차례의 시험 중에서 단일 운전으로 세 운용점에서 총 120초간 작동된 경우에 대하여 터보펌프에 관심을 두고 시험결과를 소개한다. 펌프와 터빈의 성능 특성 관점에서 터보펌프 조립체의 실매질 고온 시험 성능시험 결과와 터보펌프 구성품의 상사 성능 시험 결과가 양호하게 일치하였다. Hot-fire test of a turbopump for a gas generator cycle rocket engine of 30 ton class was carried out in real propellant environment. Liquid oxygen and kerosene were used for the oxidizer pump and the fuel pump, respectively, while hot gas produced by the gas generator was supplied to the turbine. A part of the propellant discharged from the pumps was provided to the gas generator. The turbopump was run stably at both on-design and off-design conditions, satisfying all the performance requirements. This paper describes one of the test cases, where the turbopump was run for 120 seconds at three different operating modes in one test. In terms of performance characteristics of pumps and turbine, the results from turbopump assembly test using real propellant showed a good agreement with those from the turbopump component tests using simulant working fluid.
홍순삼(Soon-Sam Hong),김대진(Dae-Jin Kim),김진선(Jin-Sun Kim),김진한(Jinhan Kim) 한국항공우주학회 2009 韓國航空宇宙學會誌 Vol.37 No.8
가스발생기 사이클의 추력 30톤급 엔진에 적용 가능한 터보펌프의 구성품인 산화제펌프에 대하여 실제 작동 유체인 액체산소를 이용한 시험이 이루어졌다. 본 시험에서 터빈은 상온 수소 가스로 구동되었다. 산화제펌프는 설계점 및 탈설계점에서 안정적으로 작동 되었고 성능 요구조건을 만족시켰다. 액체산소를 매질로 하는 경우의 산화제펌프 양정계수는 물을 매질로 하는 경우에 비하여 약 2~3% 더 낮은 값을 보였다. 산화제펌프 구동에 필요한 동력과 터빈에서 생성되는 동력이 서로 잘 일치하였다. An oxidizer pump of a turbopump for a 30-ton class gas generator cycle engine was tested in the medium of liquid oxygen. The turbine was driven by cold hydrogen gas in the test. The oxidizer pump was operated stably at both design and off-design conditions, satisfying the performance requirements. The pump head coefficient from the liquid oxygen test was 2~3% lower than that from the water test. The power required to run the oxidizer pump was well balanced with the power produced by the turbine.
홍순삼(Soon-Sam Hong),김진선(Jin-Sun Kim),최창호(Chang-Ho Choi),김진한(Jinhan Kim) 한국유체기계학회 2004 유체기계 연구개발 발표회 논문집 Vol.- No.-
Experiments were performed to see 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 were done 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 decreased. Attached cavitation and cavitation surge were found in the cavitation tests. In the attached cavitation one cell rotated at the same rotational speed as that of the inducer. Cavitation performance deteriorated with increase in the tip clearance. The level of casing vibration increased in the cavitation condition and the level was very high when the attached cavitation appeared.
터보펌프 인듀서의 비정상 캐비테이션에 관한 실험적 연구
홍순삼(Soon-Sam Hong),김진선(Jin-Sun Kim),최창호(Chang-Ho Choi),김진한(Jinhan Kim) 한국유체기계학회 2003 유체기계 연구개발 발표회 논문집 Vol.- No.-
Steady and unsteady cavitation characteristics of turbopump inducer were investigated in this paper. To see 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. Rotating cavitation and cavitation surge were found in the 7.8°, 7.0° inducers in the cavitation tests. During the rotating 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 ㎐. 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.
홍순삼(Soon-Sam Hong),강신형(Shin-Hyoung Kang) 한국유체기계학회 2000 유체기계 연구개발 발표회 논문집 Vol.- No.-
비교적 낮은 비속도 원심펌프의 회전차 출구 및 깃없는 디퓨저 내부에서 열필름 프로브와 고응답 압력센서를 이용하여 비정상 유동장을 측정했는데 다음의 결과를 얻었다.<br/> 평균유동의 경우 미끄럼계수는 유량에 대해 거의 일정한 분포를 보였으며 경험식들로부터 구한 값보다 약간 작았다. 평균 유동의 반경방향 변화를 보면 깃없는 디퓨저에서 표면 마찰을 고려하는 경험 계수를 이용했을 때 측정값을 잘 예측하였다.<br/> 순간유동의 경우 쉬라우드가 없는 압축기 회전차와는 다르게 낮은 반경속도 영역이 피치방향으로 넓게 분포되었다. 회전차 출구에서 하류로 가면서 피치방향 비균일성은 감소하는데 본 실험의 경우 반경비가 1.18일 때 이 비균일성은 거의 없어졌다. The flow at the impeller exit is important to validate engineering design and numerical analysis of pumps. We installed axisymmetric collector instead of the volute casing, so there is no interaction between the impeller and casing. A hot-film probe and a high response pressure transducer are used to investigate the flow at impeller exit and vaneless diffuser region for design and off design flow rate. For a single suction centrifugal pump of low specific speed, the flow field such as velocity, flow angle, and total pressure are measured by traversing the probe across the vaneless diffuser. These data can be used for performance prediction, design, and numerical analysis of pumps.
홍순삼(Soon-Sam Hong),김대진(Dae-Jin Kim),김진선(Jin-Sun Kim),김진한(Jinhan Kim) 대한기계학회 2008 大韓機械學會論文集B Vol.32 No.4
Hydrodynamic performance test of a turbopump for a liquid rocket engine is carried out. The turbopump is composed of an oxidizer pump, a fuel pump and a turbine, and the two pumps are driven by the turbine. In the test, water is used for the pumps as working media and air is used for the turbine. Performance parameters of pumps and a turbine are drawn, and a power balance between the pumps and the turbine are calculated. The calculation shows a good power balance, which implies that the pump component tests, the turbine component test and the assembly test are reliably performed. At the starting period of the test, pressure rise-flow rate curve of a pump gradually approaches the ideal curve which could be obtained by very slow starting.