• Title/Summary/Keyword: 실매질시험

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Development Test of Alcohol Burner for Turbopump Real-propellant Test Facility (터보펌프 실매질 시험설비를 위한 알코올버너 개발시험)

  • Kim, Jin-Sun;Han, Yeoung-Min;Ko, Youngsung
    • Journal of the Korean Society of Propulsion Engineers
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    • v.18 no.5
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    • pp.79-86
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    • 2014
  • A turbopump real-propellant test facility(TPTF) is to verify the performance of a turbopump unit(TPU) based on liquid oxygen and kerosene. One of the most important sub-facilities is a hot-gas generation system which makes the driving force of the TPU with an alcohol burner. The alcohol burner generates the required flow rates and temperature at the facility using high pressure air and ethanol. In the study, the verification tests of the alcohol burner which was manufactured entirely with domestic technology were performed and fabrication technique and operation skill for the burner could be obtained ahead of the construction of the facility. Two burners will be operated simultaneously for the real-propellant test of 75tf class turbopump and satisfy the power requirement from the turbine of the TPU.

Introduction to Construction of a Turbopump Real-Propellant Test Facility (터보펌프 실매질 시험설비 구축에 대한 소개)

  • Kim, Jin-Sun;Ko, Young-Sung
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.11a
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    • pp.835-840
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    • 2011
  • The development of a turbopump is fundamental to have an independent LRE(liquid rocket engine) for KSLV-II. Recently, the detail design of a turbopump real-propellant test facility based on liquid oxygen and kerosene has been performed to structure the test facility for the experimental validation of the turbopump. In this paper, the design requirements of the turbopump and the specifications of the test facility was presented and the representative sub-facilities were explained on the basis of the design results. Also, the uncertainty of the sub-facilities which could be appeared during the operation was removed in advance through the simulation method and the experimental verification.

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Real-Propellant Test of a Turbopump for a 30-Ton Thrust Level of Liquid Rocket Engine (30톤급 액체로켓엔진용 터보펌프 실매질시험)

  • Hong, Soon-Sam;Kim, Dae-Jin;Kim, Jin-Sun;Kim, Jin-Han
    • 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.

Real-Propellant Test of a Turbopump for a 30-Ton Thrust Level of Liquid Rocket Engine (30톤급 액체로켓엔진용 터보펌프 실매질시험)

  • Hong, Soon-Sam;Kim, Dae-Jin;Kim, Jin-Sun;Kim, Jin-Han
    • 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.

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Water tests of pumps for real-propellent tests of turbopump (실매질 시험용 터보펌프의 단품 수류시험)

  • Kim, Dae-Jin;Hong, Soon-Sam;Kim, Jin-Sun;Kim, Jin-Han
    • Aerospace Engineering and Technology
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    • v.8 no.1
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    • pp.26-31
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    • 2009
  • Three Lox pumps and one fuel pump are manufactured for turbopump real-propellent tests and water tests of the pumps are performed in order to estimate the performance characteristics of the pumps. According to the test results, the test region(flow ratio, cavitation number) of the pumps at the water tests cover the operating region at the real-propellent tests and also all the pumps satisfy the design requirement. The head of the Lox pumps shows a 2% difference among them due to the internal geometry, but the efficiency and overall cavitation performance are almost same. It is found that the fuel pump has a similar head and efficiency compared with the previous model of the same internal geometry, while it has a little inferior cavitation performance.

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Construction and Validation Test of Turbopump Real-propellant Test Facility (터보펌프 실매질 시험설비 구축 및 인증시험)

  • Kim, Jin-Sun;Han, Yeoung-Min;Ko, Youngsung
    • Journal of the Korean Society of Propulsion Engineers
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    • v.19 no.4
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    • pp.85-93
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    • 2015
  • Liquid rocket engines of KSLV-II employ a turbopump feed system for propellants. A turbopump real-propellant test facility based on liquid oxygen and kerosene has been constructed for the experimental verification of the turbopump performance using the real media of propellants(i.e., LOX/Kerosene). The verification tests of sub-systems were performed such as LOX/kerosene feed system and alcohol burner system. Finally, the performance of the whole system was executed and verified through a sets of validation tests with the development model of the KSLV-II turbopumps. It has been confirmed that the test facility satisfies the operating conditions and time of the turbopump at the design and off-design performance test using real-propellant.

Hot-Fire Test of a Turbopump for a 30 Ton Class Engine in Real Propellant Environment (30톤급 엔진용 터보펌프 실매질 고온시험)

  • Hong, Soon-Sam;Kim, Jin-Sun;Kim, Dae-Jin;Kim, Jin-Han
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2009.05a
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    • pp.11-17
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    • 2009
  • 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.

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Design Review of Combustion Chamber/Turbo-pump Test Facility of Liquid Rocket Engine for KSLV-II (한국형발사체 액체엔진 연소기 및 터보펌프 시험설비 배치 및 설계에 대한 검토)

  • Han, Yeoung-Min;Cho, Nam-Kyung;Chung, Young-Gahp;Kim, Seung-Han;Yu, Byung-Il;Lee, Kwang-Jin;Kim, Jin-Sun;Kim, Ji-Hoon
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.04a
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    • pp.109-112
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    • 2011
  • The result of design review and arrangement of a combustion chamber test facility(CTF) and a turbo-pump real propellant test facility(TPTF) is briefly described. The development/qualification tests of combustion chamber and turbo-pump for 75ton-class liquid rocket engine will be performed in CTF and TPTF. The critical design of hydraulic-pneumatic system, control and data acquisition system, test stand cell, and auxiliary facilities in CTF and TPTF was performed.

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Performance Test of Turbopump Assembly for 75 Ton Liquid Rocket Engine Using Model Fluid (75톤급 액체로켓엔진용 터보펌프 조립체의 상사매질 성능시험)

  • Hong, Soon-Sam;Kim, Jin-Sun;Kim, Dae-Jin;Kim, Jin-Han
    • 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.

Performance Test of Turbopump Assembly for 75 Ton Liquid Rocket Engine Using Model Fluid (75톤급 액체로켓엔진용 터보펌프 조립체의 상사매질 성능시험)

  • Hong, Soon-Sam;Kim, Jin-Sun;Kim, Dae-Jin;Kim, Jin-Han
    • 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.

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