• Title/Summary/Keyword: Turbopump(터보펌프)

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Structural Analysis and Measurement of Turbopump Casings (터보펌프 케이징의 구조해석 및 측정)

  • Yun, Seok-Hwan;Jeon, Seong-Min;Kim, Jin-Han
    • Aerospace Engineering and Technology
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    • v.5 no.2
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    • pp.174-180
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    • 2006
  • The present paper describes transient thermal and mechanical analyses of a lox/kerosene type turbopump in a LRE(Liquid Rocket Engine). Turbopumps are used to pressurize propellants to achieve higher specific impulse of LRE. The turbopump under development has been designed and verified by structural analyses using finite element methods. Some parts of the turbopump operate under cryogenic environments, while the others work under ambient and high temperature environments. Therefore, numerical analysis at a turbopump system level is essential. In this study, casing assemblies of lox pump and fuel pump were analyzed to determine strength test and air-tightness test conditions. Also, some operational stress and strains of fuel pump casings were measured and analyzed. Based on these results, stress concentration of fuel pump casings during the operation could be successfully predicted.

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Experimental Study on Fluid Viscosity Effects for Centrifugal Turbopump Efficiency (유체점성에 따른 원심형 터보펌프 효율에 관한 실험적 연구)

  • Kim, Jin-Sun;Choi, Chang-Ho;Ko, Youngsung
    • Journal of the Korean Society of Propulsion Engineers
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    • v.20 no.6
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    • pp.91-100
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    • 2016
  • Efficiency characteristics of centrifugal turbopumps for a liquid rocket engine were investigated. Predicting the performance of pumps for a turbopump assembly test, the variation on pump efficiency by working fluids was analyzed from pump component tests. Water and liquid nitrogen (LN2) were used for the component test, kerosene (Jet A-1) and liquid oxygen (LOX) were adapted for the turbopump assembly (TPU) test as working fluids. Overall performance of the pumps was investigated covering design/off-design operating points and the pump efficiency on the environment of real media (LOX/kerosene) could be modified from the pump component tests.

Characteristics and prediction of the cavitation inception in a turbopump inducer (터보펌프 인듀서에서 캐비테이션 시작점의 특성 및 예측에 관한 연구)

  • Kang, Byung Yun;Kim, Dae-Jin;Choi, Chang-Ho
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2017.05a
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    • pp.1077-1079
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    • 2017
  • The cavitation in the turbopump inducer progresses from the inception to the critical point, and finally develops to a breakdown which sharply declined in head. In this paper, we evaluated characteristics and predicted empirical equations about the cavitation inception of a turbopump inducer. The empirical equation of the cavitation inception for the elliptical plate was relatively well predicted to the turbopump inducer. However, in case of the marine propeller, it showed a big difference due to Reynolds number under the operating point.

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Research on the Torque and Starting Characteristics of a Turbopump Turbine (터보펌프 터빈의 토크 및 시동특성 연구)

  • Jeong, Eunhwan;Lee, Hang-Gi;Park, Pyun-Goo;Hong, Moongeun;Kim, Jinhan
    • Journal of the Korean Society of Propulsion Engineers
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    • v.17 no.1
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    • pp.35-41
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    • 2013
  • Torque characteristics of a turbopump turbine was analyzed using the turbine performance test result. Specific torque of the subject turbine could be expressed as a linear function of corrected rotor speed at a fixed pressure ratio and it has been confirmed by the test result. It also found that corrected rotor speed-specific torque characteristics does not change anymore if the turbine pressure ratio is set bigger than a certain value. Using the turbine torque characteristics and pyro-starter performance test results, rotational speed development behavior of the turbopump was predicted. Prediction revealed that the lap time reaching 50% of turbopump design speed is less than 0.7 second. Effect of the thermal loss between pyro-starter and turbopump was negligible.

Research on the Torque and Starting Characteristics of a Turbopump Turbine (터보펌프 터빈의 토크 및 시동특성 연구)

  • Jeong, Eun-Hwan;Lee, Hang-Gi;Park, Pyun-Goo;Hong, Moon-Geun;Kim, Jin-Han
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2012.05a
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    • pp.4-10
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    • 2012
  • Torque characteristics of a 75-tonf turbopump turbine was analyzed using the turbine performance test result. Specific torque of the subject turbine could be expressed as a linear function of corrected rotor speed at a fixed pressure ratio and it has been confirmed by the test result. It also found that corrected rotor speed-specific torque characteristics does not change anymore if the turbine pressure ratio is set bigger than a certain value. Using the turbine torque characteristics and pyro-starter performance test results, rotational speed development behavior of the turbopump was predicted. Prediction revealed that the lap time reaching 50% of turbopump design speed is less than 0.7 second. Effect of the thermal loss between pyro-starter and turbopump was negligible.

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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.

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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Study on Turbopump and Gas Generator Coupled Tests (터보펌프+가스발생기 연계시험 연구)

  • Kim, Seung-Han;Nam, Chang-Ho;Seol, Woo-Seok
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2007.11a
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    • pp.155-158
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    • 2007
  • As a secondary stage of the liquid rocket engine development test, turbopump-gas generator powerpack tests are being performed. The schematics of the test hardware and the test facility for the TP+GG coupled test are presented. The results of a preliminary test results for the verification of the propellant supply system of the test facility are also presented. Based on the preliminary tests results, the verification of the propellants supply systems of the facility system was performed.

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Study on Structural Characteristic for Durability Insurance of Turbopump Turbine (터보펌프 터빈의 내구성 확보를 위한 구조적 특성 연구)

  • Lee, Mu-Hyoung;Jang, Byung-Wook;Kwon, Jeong-Sik;Kim, Jin-Han;Jeong, Eun-Hwan;Jeon, Seong-Min;Lee, Soo-Yong;Park, Jung-Sun
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2009.11a
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    • pp.382-386
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    • 2009
  • The life of a component decreases when it was exposed at the extreme condition. A turbine blade of a turbopump used for a liquid rocket engine is operated under the environment of high temperature and pressure, and experienced high centrifugal force. Thus the durability of the turbopump operated under the these conditions become lower than expected because of the severe fatigue and creep influence. The damage of the turbine being considered the fatigue and the creep influence is estimated to ensure the durability of turbopump turbine. ABAQUS/CAE and MSC.Fatigue are used for the fatigue analysis, and Larson-Miller parameter and robinson's rule are used for the creep analysis. In this paper, comparison and analysis of the fatigue and the creep influence were performed to ensure the life expectancy of turbopump turbine.

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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.