• Title/Summary/Keyword: 파이로시동기

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Design and Hot Fire Tests of the Pyrostarter for Liquid Rocket Engines (액체로켓엔진용 파이로시동기의 설계 및 연소시험연구)

  • Kang, Sang Hun;Jang, Jesun
    • Journal of the Korean Society of Propulsion Engineers
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    • v.18 no.3
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    • pp.48-55
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    • 2014
  • In present study, design and hot fire tests of the pryostarter are conducted. To prevent the turbopump RPM overshoot, regressive mass flow rate profile is applied. Sudden decrease of the mass flow rate at the end of the propellant burning is realized as well. Firing test results show good agreements with the design requirements. Through the study with ignition substance variations, combustion products and ignition performances are improved.

Estimation of the operating characteristics of a turbopump driven by a pyro-starter (파이로시동기로 작동되는 터보펌프의 구동특성 예측)

  • Kim Cheul-Woong;Seol Woo-Seok
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2006.05a
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    • pp.167-170
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    • 2006
  • For a short time a pyre-starter should turn the blades of a turbine to the adequate rotational speed by a single operation. Through this process the pressures of the components of a propellant rise rapidly up to the operating point, and the components enter into a gas-generator. Combustion in the gas-generator occurs to keep the turbopumps working. In this research characteristic parameters of a pyre-starter which correspond to the required performance of the turbopump before the gas-generator starts to work were selected

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Turbine Rotor-Pyrostarter Coupled Test for the Verification of Thermo-Structural Suitability of a Turbopump Turbine (터보펌프 터빈의 열구조적 적합성 검증을 위한 터빈로터-파이로시동기 연계시험)

  • Jeong, Eunhwan;Kang, Sang Hun;Hong, Moongeun;Lee, Hanggi;Lee, Soo Yong;Kim, Jinhan
    • Journal of the Korean Society of Propulsion Engineers
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    • v.18 no.1
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    • pp.65-72
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    • 2014
  • Turbine rotor-pyrostarter coupled test was performed for the verification of thermo-structural suitability of a turbopump turbine. Newly developed solid propellant and design concept were used in pyrostarter development. In case of turbine rotor, rotor configuration modification and post EDM machining process are adopted in rotor manufacturing respectively for the thermal stress relief and the surface integrity improvement on the blade surfaces. In the test, combustion gas of pyrostarter was directly ejected from the nozzles and impinged on the stationary turbine rotor specimen through the identically shaped flow passage of turbopump. Three kind of thermal load - design to extreme condition - test were performed and no damages were found on the turbine rotor specimens.

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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Liquid Rocket Engine System of Korean Launch Vehicle (한국형발사체 액체로켓엔진 시스템)

  • Cho, Won-Kook;Park, Soon-Young;Moon, Yoon-Wan;Nam, Chang-Ho;Kim, Chul-Woong;Seol, Woo-Seok
    • Journal of the Korean Society of Propulsion Engineers
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    • v.14 no.1
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    • pp.56-64
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    • 2010
  • A system design has been conducted of the liquid rocket engine for Korean launch vehicle (KSLV-II, Korea Space Launch Vehicle II). The present turbopump-fed liquid rocket engine of vacuum thrust 76 ton and vacuum specific impulse 297 sec adopts gas generator cycle. The combustion pressure of the regeneratively cooled combustor is 60 bar. The propellant is LOx/kerosene. The engine is started by pyrostarter and the combustor is ignited by TEA (TriEthylAluminium). The engine system performance and the subsystems performance requirements are given through energy balance analysis. The combustion pressure, specific impulse and the engine mass are analyzed to be reasonable comparing with the published data. The startup analysis method which will be used in the future has been validated against the turbopump-gas generator coupled test. The tuning method for performance variation of the engine which is not actively controled has been prepared by mode analysis and performance deviation analysis.

Numerical Analysis on the Startup of a Rocket Engine (로켓 엔진의 시동에 관한 해석적 연구)

  • Park, Soon-Young;Seol, Woo-Seok
    • Journal of the Korean Society of Propulsion Engineers
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    • v.11 no.5
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    • pp.60-71
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    • 2007
  • The startup characteristic of liquid propellant rocket engine should be focused on the stable ignition of combustion chamber and gas generator. Also, to lessen the propellants consumption during this period which doesn't contribute to the flight thrust, the engine has to be transferred to the nominal mode quickly. Because of the risk of test, it is impossible to develop all the startup cyclogram or the specifications of engine by test, so the precedent numerical approach is quite necessary. In this study we developed a mathematical model for the startup phenomena in a liquid rocket engine driven by gas generator-turbopump system based on the commercial 1-D flow system analysis program, Flowmaster. Using this program we proposed a methodology to obtain the specifications of turbine starter and the opening time of shutoff valves for the stable startup of the engine. To verify this methodology we qualitatively compared the analysis results to the typical startup curve of the published engine, then found it is quite well matched.

Current Status of Development Test of 75 tonf Engine System for KSLV-II (한국형발사체 75톤급 엔진 개발 시험 현황)

  • Kim, SeungHan;Kim, SeungRyong;Kim, SungHyuk;Kim, ChaeHyung;Seo, DaeBan;Woo, SeongPil;Yu, ByungIl;So, YoonSeok;Lee, KwangJin;Lee, SeungJae;Lee, JungHo;Lim, JiHyuk;Jeon, JunSoo;Cho, NamKyung;Hwang, ChangHwan;Park, Jea-Young;Han, YeongMin
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2017.05a
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    • pp.99-103
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    • 2017
  • As a development test of the 75-tonf LOx/Kerosene liquid rocket engine for KSLV-II first Stage Engine, hot firing test of 75-tonf engine are performed. The current status of development test on first stage 75-tonf engine system including combustion chamber, turbopump, gas generator, propellant supply system are presented. During the 75tonf engine test campaign, the development of startup sequence of LOx-Kerosene engine system, engine startup using pyrostarter, ignition of gas generator, steady operation and engine shutdown is successfully performed. As a passenger test during engine hot firing tests, Thrust Vector Control system (TVC) of the engine are also evaluated during engine hot firing test. The results of hot firing test of 75-tonf thrust engine system will be used for the design confirmation and performance evaluation of 75 tonf engine system for KSLV-II first Stage.

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