• 한국추진공학회지
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• 제19권3호
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• pp.89-95
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• 2015

7톤급 로켓엔진용 산화제펌프와 연료펌프에 대하여 물을 매질로 하는 성능시험을 수행하였다. 펌프는 전기모터로 구동되었고 설계 및 탈설계 유량비 조건에서 펌프의 수력성능과 흡입성능이 측정되었다. 양정-유량 곡선, 효율-유량 곡선, 양정-캐비테이션수 곡선을 얻었다. 개발된 펌프는 펌프 양정과 효율의 수력성능에 관한 설계요구조건을 만족시킬 수 있음을 확인하였다. 또한 흡입성능에 관한 설계요구조건을 만족시킨다.

• Tribology and Lubricants
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• 제28권4호
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• pp.167-172
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• 2012

The turbo pump of a liquid rocket engine is composed of three main parts: the oxidizer pump, fuel pump, and turbine. Liquid oxygen ($LO_X$) is the working fluid in the cryogenic environment in the oxidizer pump, but tests are usually performed using liquid nitrogen ($LN_2$), which has a boiling point similar to that of $LO_X$ but is comparatively safer and easier to use for the test. In this study, a bearing test rig is developed and its performance is evaluated using a cryogenic ball bearing with $LN_2$ as the working fluid. Verifying the performance of the bearing test rig is crucial for ensuring correct working of the turbo pump unit in the liquid rocket engine. A stable test rig for the bearing in a cryogenic environment makes the bearing technology enhance its reliability. The test results show that the system operates stably and the requirement of performance time of 500 s is met. The test results of temperature, motor speed, and torque are discussed. The developed cryogenic bearing test rig is expected to help in widening knowledge and expanding research on ball bearings in the future.

• 대한기계학회논문집B
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• 제32권4호
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• pp.249-254
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• 2008

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.

• 한국추진공학회지
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• 제13권3호
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• pp.20-26
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• 2009

30톤급 액체로켓엔진용 터보펌프에 대하여 실매질을 사용하여 성능시험이 이루어졌다. 산화제펌프와 연료펌프에는 각각 액체산소, 케로신의 실매질을 사용하고 터빈에는 고압의 상온 수소가스가 사용되었다. 터보펌프는 설계점과 탈설계점의 전 영역에서 안정적으로 작동하였고 요구되는 성능 조건을 만족 시켰으며 이로써 엔진 서브시스템 수준의 터보펌프 개발이 성능 측면에서 검증되었다고 볼 수 있다. 본 논문에서는 단일 운전으로 세 운용점에서 총 75초간 작동된 경우의 시험결과를 소개하였다. 펌프와 터빈의 성능 특성 관점에서 터보펌프 조립체의 실매질 성능시험 결과와 터보펌프 구성품의 상사 성능시험 결과가 양호하게 일치하였다.

• 한국추진공학회지
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• 제14권5호
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• pp.57-64
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• 2010

75톤급 터보펌프용 추진제 혼합 방지 실의 누설 성능 및 내구 성능을 평가하기 위한 수류환경 성능 시험을 수행하였다. 추진제 혼합 방지 실 시제품은 연료펌프 부와 산화제펌프 부 각각 누적 시험 시간 2,100초 동안 수류환경에서 내구 성능 시험이 이루어 졌다. 1단의 카본 플로팅 링 실로 구성된 연료펌프 부는 성능 시험 동안 평균 실 차압 9.4 bar에서 평균 누설 유량 13.7 gram/sec의 결과를 얻었다. 반면, 2단의 카본 플로팅 링 실로 구성된 산화제펌프 부는 성능 시험 동안 평균 실 차압 9.5 bar에서 평균 누설 유량 7.3 gram/sec의 결과를 얻었다. 내구 성능 시험 후, 추진제 혼합 방지 실은 양호한 상태를 보였다. 향후 액체 질소를 시험 매질로 하는 극저온 환경에서 추진제 혼합 방지 실 누설 성능 시험이 수행될 예정이다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년도 제31회 추계학술대회논문집
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• pp.359-365
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• 2008

30톤급 액체로켓엔진용 터보펌프에 대하여 실매질을 사용하여 성능시험이 이루어졌다. 산화제펌프와 연료펌프에는 각각 액체산소, 케로신의 실매질을 사용하고 터빈에는 고압의 상온 수소가스가 사용되었다. 터보펌프는 설계점과 탈설계점의 전 영역에서 안정적으로 작동하였고 요구되는 성능 조건을 만족시켰으며 이로써 엔진 서브시스템 수준의 터보펌프 개발이 성능 측면에서 검증되었다고 볼 수 있다. 본 논문에서는 단일 운전으로 세 운용점에서 총 75초간 작동된 경우의 시험결과를 소개하였다. 펌프와 터빈의 성능 특성 관점에서 터보펌프 조립체의 실매질 성능시험 결과와 터보펌프 구성품의 상사 성능 시험 결과가 양호하게 일치하였다.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2006년도 춘계학술대회논문집
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• pp.1142-1148
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• 2006

The floating ring seal which is used in the high pressure turbo pump is frequently used in the oxidizer pump and the fuel pump of the turbo pump of the liquid propulsion rocket, because it is able to minimize clearance to decrease the leakage flow rate. But, floating ring seal has a tendency to increase the force which caused instability of system as the eccentricity ratio increases. In this paper, we devised design of floating ring seal which decrease contact area between floating and supporting ring. Modified floating ring seal has a tendency to decrease the eccentricity ratio compare with original floating ring seal. The whirl frequency ratio which is able to distinguish stability of system decrease compare with original floating ring seal

• Tribology and Lubricants
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• 제20권4호
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• pp.183-189
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• 2004

The floating ring seal is used in an oxidizer and a fuel pump of the turbo pump unit in the liquid rocket engine to optimize a leakage without rubbing phenomenon. The damper floating ring seal, one of the floating ring seals, is with round hole pattern surfaces. It can reduce the leakage by increased friction factor that obtained from experimental data. In this paper, the leakage test about floating ring seal and damper floating ring seal was conducted. The test result showed the leakage performance of damper floating ring seal was better than the leakage performance of floating ring seal. With the leakage test the lock-up and rotation test about seal was conducted and that position is measured. The relatively large lock-up eccentric ratio was obtained from the test result of damping floating ring seal. The attitude angle of seal increases with increasing of shaft rotation.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2004년도 춘계학술대회논문집
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• pp.820-825
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• 2004

The floating ring seal is used in an oxidizer and a fuel pump of the turbo pump unit in the liquid rocket engine to optimize a leakage without rubbing phenomenon. The damper floating ring seal, one of the floating ring seals, is with round hole pattern surfaces. It can reduce the leakage by increased friction factor that obtained from experimental data. In this paper, the leakage test about floating ring seal and damper floating ring seal was conducted. The test result showed the leakage performance of damper floating ring seal was better than the leakage performance of floating ring seal. With the leakage test the lock-up and rotation test about seal was conducted and that position is measured. The relatively large lock-up eccentric ratio was obtained from the test result of damping floating ring seal. The attitude angle of seal increases with increasing of shaft rotation

• Tribology and Lubricants
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• 제24권3호
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• pp.140-146
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• 2008

The floating ring seal which is used in the high pressure turbo pump is frequently used in the oxidizer pump and the fuel pump of the turbo pump of the liquid propulsion rocket, because it is able to minimize clearance to decrease the leakage flow rate. But, the floating ring seal has a tendency to increase instability in decreasing eccentricity ratio. To complement this weakness, it is devised bump floating ring seal which is inserted bump in the outer surface. It has various experiment results. But the theoretical study of the bump floating ring seal didn't investigated yet. In this paper, we analyse about static characteristics of bump floating ring seal, compared previous experimental results. To analyze the characteristic of bump floating ring seal, we coupled perturbation method of floating ring seal and FEM of bump foil.