• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.375-383
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• 2005

The present paper describes the first development of a LOX/kerosene type turbopump in Korea. The liquid rocket engine, that the turbopump can be applied to, has a 30-ton(metric) level of vacuum thrust and employs a gas generator cycle. The turbopump consists of two single-stage centrifugal pumps, that is, LOX and kerosene pumps, and one single-stage impulse turbine. Inter-propellant seal(IPS) is located between the LOX pump and the kerosene pump to avoid any interaction between the propellants. A series of component and TPU(Turbopump Unit) test has been completed in the level of simulant propellants and ready for hot firing tests.

• Journal of the Korean Society of Propulsion Engineers
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• v.15 no.2
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• pp.56-61
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• 2011

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.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.27-32
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• 2010

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.

• Journal of the Korean Society of Propulsion Engineers
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• v.13 no.3
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• pp.20-26
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• 2009

Turbopump test for a 30-ton-thrust liquid rocket engine was carried out using real-propellant. Liquid oxygen, kerosene, cold hydrogen gas were used for the oxidizer pump, the fuel pump, and the turbine, respectively. The turbopump was reliably operated at the design and off-design conditions and the performance requirements were satisfied, which implies that the turbopump development at the engine subsystem level is successfully accomplished in the point of performance validation. This paper presents the results of a test where the turbopump was run for 75 seconds at three operating modes. In terms of performance characteristics of pumps and turbine, the results of turbopump assembly test using real-propellant showed a good agreement with those of the turbopump component tests using simulant working fluid.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.359-365
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• 2008

Turbopump test for a 30-ton-thrust liquid rocket engine was carried out using real-propellant. Liquid oxygen, kerosene, cold hydrogen gas were used for the oxidizer pump, the fuel pump, the turbine, respectively. The turbopump was run stably at the design and off-design conditions and the performance requirements were satisfied, which implies that the turbopump development at the engine subsystem level is successfully accomplished in the point of performance validation. This paper presents the results of a test where the turbopump was run for 75 seconds at three operating modes. 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.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.243-247
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• 2005

Hydraulic performance test was conducted for a fuel pump of a liquid rocket engine turbopump. The pump driven by an electric motor was tested in water environment. It is experimentally shown that the inducer had very small effect on the pimp's head and efficiency but great effect on the pump's cavitation performance. Additionally, inducer test was carried out to investigate the effect of the inducer on the pump in detail, and it was found that the pump had a critical cavitation number when the inducer head dropped by $55\%$.

• Journal of the Korean Society of Propulsion Engineers
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• v.10 no.1
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• pp.18-22
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• 2006

Hydrodynamic performance test was conducted for a fuel pump of a liquid rocket engine turbopump. The pump driven by an electric motor was tested using water. It is experimentally shown that the inducer had very small effect on the pump's head and efficiency but great effect on the pump's cavitation performance. Additionally, inducer test was carried out to investigate the effect of the inducer on the pump in detail, and it was found that the pump reached a critical cavitation number when the inducer head dropped by 55%.

• Aerospace Engineering and Technology
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• v.10 no.1
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• pp.122-128
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• 2011

A series of water tests of a Lox pump for liquid rocket engines are performed at a room temperature. According to the hydraulic test results, the head coefficient is slightly decreased when the rotational speed of the pump is increased. However the efficiency is high at the high-speed test. Also, according to the cavitation test results, the cavitation performance of the pump is found to be decreased when the flow ratio is less than 92%. Furthermore, the vibration characteristic is analyzed using measured high frequency data.

• Journal of the Korean Society of Propulsion Engineers
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• v.12 no.5
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• pp.73-78
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• 2008

The development of turbopump in Korea has been practically started from 1999. Recently, the turbopump for a LRE with 30-ton level thrust has been successfully developed, which is able to work for all the required LRE regimes. This success is considered as a breakthrough in development of LRE because the turbopump, a core component of LREs, has been considered as a critical barrier in domestic technology point of view. In this paper, status of the turbopump development in Korea is provided and some suggestions are made for the prospective future.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.62-65
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• 2011

액체로켓엔진용 극저온 산화제 고압 배관 기술 개발을 위해 시제품을 제작하였다. 기술 개발 시제품은 체결용 플랜지, 직관, 곡관, 벨로우즈, 분기구로 구성하였다. 액체로켓엔진용 극저온 산화제 고압 배관은 터보펌프에서 토출된 고압의 극저온 산화제를 연소기로 공급하는 경로이므로 극저온, 고압의 작동환경에서 구조적 안정성을 가져야 한다. 따라서 본 제작공정 개발에서는 극저온을 고려한 구조해석을 수행하여 적합한 소재를 선정하였으며, 공정개발과 특수공정을 적용하여 시제품을 제작한 후 구조강도 시험을 수행하였다. 본 개발을 통해 액체로켓엔진에 적용되는 극저온 산화재 고압배관을 위한 기술적 기반과 소재 응용기술, 향후 고성능 대형 액체로켓엔진에 적용하기 위한 공정개발을 완료하였다.