• Title/Summary/Keyword: 액체냉각

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A Study on the Cooling Mechanism in Liquid Rocket Engine of 10tf-thrust Level using Kerosene as a Fuel (케로신을 연료로 하는 10톤급 액체로켓엔진의 냉각 기구에 관한 연구)

  • 한풍규;조원국;조용호
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2003.10a
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    • pp.83-88
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    • 2003
  • An analytical study was carried out to evaluate the regenerative cooling characteristics in the liquid rocket engine of a 10tf-thrust level using kerosene as a fuel. As a supplementary cooling method, a radiative cooling was applied to the nozzle extension. It was found out from this work that the cooling system with the regenerative and radiation cooling only is not adaptable as a cooling method for the liquid rocket engine of a 10tf-thrust level using kerosene as a fuel for the 2nd stage of the space launch vehicle. So, additional cooling method, curtain cooling was introduced and analyzed. Curtain cooling was very effective to reduce the thermal and thermo-structural instability.

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Evaluation on the Regenerative Cooling Characteristics in Liquid Rocket Engine of 10tf-thrust using Kerosene and Liquid Oxygen as a Propellant (케로신과 액체산소를 추진제로 하는 10톤급 액체로켓엔진의 재생냉각 특성 평가)

  • Han, Poong-Gyoo;Cho, Won-Kook;Cho, Yong-Ho
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.32 no.4
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    • pp.111-117
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    • 2004
  • An analytical study was carried out to evaluate the regenerative cooling characteristics in the liquid rocket engine of a 10tf-thrust level using kerosene as a fuel. As a supplementary cooling method, a radiative cooling was applied to the nozzle extension. It was found out from this work that the cooling system with the regenerative and radiation cooling only is not adaptable for the liquid rocket engine of a 10tf-thrust level using kerosene as a fuel for the $2^{nd}$ stage of the space launch vehicle, with the viewpoint of the thermal and thermo-structural instability and the excessive pressure drop in the cooling channel.

A Case Study on the Design of Kerosene-LOx Liquid-Propellant Rocket Engines for Performance Enhancement (케로신-액체산소 액체로켓엔진의 성능향상 설계안 사례 조사)

  • Lee, Seon-Mi;Moon, In-Sang;Lee, Soo-Young
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.04a
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    • pp.12-15
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    • 2011
  • The most widely used kerosene-LOx liquid-propellant rocket engines in these days have a similar engine schematic to those of the past because of the development cost and the reliability. The efficiency of engines could be increased by the factors such as a cooling method, engine cycles, shape of cooling channels, additional coolant and so on. In this article, it is described that some design ideas for performance enhancement by exchange kerosene with LOx of a coolant.

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Development of Combustion Test Facility for Liquid Locket Engine (액체로켓엔진 성능 및 냉각특성 연구를 위한 연소시험 장치 개발)

  • Lee Sung-Woong;Kim Dong-Hwan;Kim Young-Soo
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2004.10a
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    • pp.189-192
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    • 2004
  • Test Facility for hot firing test of small size liquid rocket engine has been developed to research the cooing characteristics of kerosene for cylinder part especially. Propellants for the tests are kerosene and liquid oxygen as fuel and oxidizer respectively and they are fed by gaseous nitrogen. The engine components used hot firing test except for cylinder are cooled by tap-water. Valves for supply of propellants and coolants are controlled by pneumatically. System control and data recording are conducted automatically.

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Cool Down Characteristics of 7 Tonf-class Liquid Rocket Engine for KSLV-II (한국형발사체 7톤급 액체로켓엔진 냉각 특성)

  • Im, Ji-Hyuk;Yu, Byungil;Lee, Kwang-Jin;Han, Yeoung-Min
    • Journal of the Korean Society of Propulsion Engineers
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    • v.25 no.1
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    • pp.50-57
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    • 2021
  • Engine cool down process is necessary for the liquid rocket engines using cryogenic propellants in order to meet the requirement of engine inlet temperature. This paper evaluates the cool down characteristics of oxidizer supply pipeline and engine in prechill process prior to the engine firing tests, and calculate the quantity of liquid oxygen consumption.

A Study on Film Cooling Characteristics of Liner in Liquid Rocket Engine (액체로켓엔진에서의 상온 기체를 이용한 라이너 막냉각 특성 연구)

  • Jeon, Jun-Su;Lee, Yang-Suk;Lee, Dong-Hyeong;Kim, Yoo;Ko, Young-Sung;Chung, Hae-Seung
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2007.11a
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    • pp.170-173
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    • 2007
  • Cooling characteristics of a liner were investigated by a film cooling method using a gas nitrogen in a rocket engine. High temperature gas of this test was made by mixing liquid nitrogen with combustion gas of a liquid rocket. A supply system of gas nitrogen was additionally constructed to the existing test facility of liquid rocket engine, and a new test section consisted of a liner and a gas injection ring was manufactured. A 10 second firing test for finding cooling characteristics of the liner was successfully conducted and liner surface temperatures and hot gas temperature was obtained.

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Development of Combustion Test Facility for Liquid Rocket Engine (액체로켓엔진 성능 및 냉각특성 연구를 위한 연소시험장치 개발)

  • Kim, Dong-Hwan;Lee, Seong-Ung;Yu, Byeong-Il
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.34 no.2
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    • pp.106-111
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    • 2006
  • Combustion test facility for liquid rocket engine using kerosene and liquid oxygen has been developed for the purpose of cooling and performance study. Test engine of thrust under 1.0 KN can be evaluated, and the real combustion test ensures a good operation of the combustion test facility. Combustion test facility will be modified to supply natural gas and liquefied natural gas as fuel and to give a regenerative cooling test.

Experimental study of Helium recondensing type superconducting magnet system with cryo-refrigerator (극저온 냉동기를 이용한 헬륨 재응축형 초전도 마그네트 시스템에 대한 실험적 연구)

  • Kim, H.J.;Sim, K.D.;Choi, S.J.;Han, H.H.;Kim, K.H.;Jin, H.B.;Lee, B.G.
    • Proceedings of the KIEE Conference
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    • 2002.07b
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    • pp.747-749
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    • 2002
  • 초전도 마그네트 시스템의 냉각방법 중, 액체 헬륨등의 극저온 유체를 이용한 액체냉각방식이 극저온 냉동기를 이용한 직접 전도냉각 방식에 비해 신뢰도가 높은 열적 안정성으로 인하여 현재도 많은 초전도 마그네트 시스템이 액체냉각방식을 이용하고 있다. 그러나, 고가의 극저온 액체의 재충전으로 인하여 경제성이 낮고 취급이 불편한 단점이 있다 이러한 액체냉각방식의 단점을 보완하고자 극저온 유체를 시스템 안에서 직접 응축하여 재충전을 하지 않는 재응축형 시스템을 개발하여 실험하였다. 실험에 사용한 초전도 마그네트 시스템은 상온보아 1270 mm. 최대자장 0.3 T로 설계되었고, 금속 전류도입선과 HTS 전류도입선을 복합적으로 사용하였으며, 복사차폐막 냉각용 극저온 냉동기와 헬륨 재응축용 극저온 냉동기를 사용하였다. 초전도 마그네트는 200 A에서 1600 gauss의 자장으로 운전하였고 극저온 용기에서는 0.05 bar의 압력으로 액체 헬륨이 증발하지 않고 유지되었다.

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A Numerical Study on the Combustion Characteristics in a Liquid Rocket Engine with Film Cooling Effect (막냉각 효과를 고려한 액체로켓 엔진의 연소 특성에 관한 연구)

  • Byeon,Do-Yeong;Kim,Man-Yeong;Baek,Seung-Uk
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.31 no.8
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    • pp.69-76
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    • 2003
  • For stable combustion and safety of a structure of the propulsion system, a cooling system to the liquid rocket engine should be incorporated. In this study, Eulerian-Lagrangian scheme for two phase combustion, nongray radiation and soot formation effect, and film-wall interaction have been introduced to study the effect of film cooling. After briefly introducing the governing equation, combustion characteristics with change of wall temperature has been investigated by varying such parameters as fuel mass fraction for film cooling, diameter of the fuel droplet, overall mixture fraction of oxygen to fuel. Also, radiative heat flux is compared with the conductive one at the combustor wall.

Investigation on Chilling Procedure for LOX Supply System for Liquid Rocket Engine (액체로켓엔진 산화제 공급부 냉각과정 고찰)

  • Cho, Nam-Kyung;Seo, Dae-Bahn;Yoo, Byung-Il;Kim, Seong-Han;Han, Yeoung-Min
    • Journal of the Korean Society of Propulsion Engineers
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    • v.23 no.3
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    • pp.119-126
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    • 2019
  • For rockets using cryogenic liquid hydrogen or liquid oxygen, chilling is required to avoid cavitation and surge problems. Chilling is categorized by the initial chilling/filling stage and the low-temperature maintenance stage. In addition, to improve satellite insertion capability, a multi-ignition capability is required and accordingly chilling to prepare for the next ignition during low-gravity coasting is also required. This paper describes the overall aspects of filling and low temperature maintain marinating for the booster and the upper stage engine including chilling for multi-ignition.