• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.1
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• pp.73-79
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• 2010

Propellant tank pressurizing gas injector is used in the pressurization system of liquid propellant rocket to reduce incoming gas velocity and distribute the gas in the tank. Temperature distribution in the propellant tank ullage is varied according to the gas injector shape, and it has influence on the required pressurant gas and thermal phenomena in the tank. In this paper, diffuser type gas injector was studied to make the ullage have stratified temperature distribution. Injected gas flow at the outlet of prototype diffuser was visulized using particle image velocimetry method and it was compared with the results of calculation. Calculation was well agreed with measurement and was used as an inlet condition of propellant tank ullage calculation.

• Proceedings of the KAIS Fall Conference
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• 2012.05a
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• pp.436-439
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• 2012

본 연구는 오존수 제조장치에 인젝터를 이용한 오존 주입방식을 도입하여 소형화, 저전력화를 실현하고자 하였다. 오존발생기, 물-오존 혼합기(인젝터), 오존용해조, 배오존 처리기로 구성된 시스템을 제작하여 인젝터 주입방식에 의한 오존수 제조장치의 오존 용해특성과 그 적용성을 검토하였다. 오존 용해 특성으로 물-공기량에 따른 인젝터 성능, 용해조에서의 오존 용해능 등을 검토하였다. 인젝터 방식은 기존의 가압용해방식에 비하여 저농도 용해능을 보였으나, 인젝터 내부의 물-오존 접촉효율이 높아 평형농도에 도달되는 시간이 단축됨을 확인하였다. 제조된 오존수의 적용 효용성은 용존오존의 잔류시간과 미생물 살균능 검사를 통하여 실시하였다. 횡형식 인젝터 시스템에 의해 용해된 용존오존의 잔류시간이 기존의 가압용해방식에 비하여 다소 짧았으나 미생물의 살균능에는 크게 차이가 나지 않았다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.05a
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• pp.61-65
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• 2010

To research and develop a liquid rocket engine injector, it needs empirical studies about the hydrodynamic and spray characteristics such as pressure drop, mixing and atomization. In this study, the design and implementation of lab-scale cold-flow/hot fire test stand which can supply cryogenic propellant and be controlled by time-critical LabVIEW cyclogram logic has been done. In order to visualize the spray of a liquid-centered swirl coaxial injector in cryogenic condition, LN2-GN2 cold-flow test has been done, and combustor assembly and thrust bed for LOX-$GCH_4$ hot-fire test have been fabricated.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.72-76
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• 2010

To research and develop a high performance injector for LRE, it needs not only cold flow test, but also investigations of combustion performance, optimization of cyclogram and thermo-fluid dynamical characteristics of combustion flow field through hot-fire test. In this study, hot-fire test of LOX-CH4 coaxial swirl injector has been carried out using lab-scale hot fire test stand which can supply and control cryogenic propellant. Ignition and continuous combustion for LOX-$GCH_4$ propellant of 0.19 kg/s total mass flowrate and 2.80 O/F Ratio was achieved through cyclogram optimization. The mean combustion chamber pressure and thrust were measured as approximately 1.43 MPa and 38.7 kgf respectively.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.05a
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• pp.49-52
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• 2009

The response times of monopropellant thrusters at a pulse mode were investigated experimentally as design parameters and feed pressure conditions. Five different model thrusters as injection direction/uniformity, aspect ratio of reactor, volumes of manifold and chamber were designed. As a results, two parameters, aspect ratio and manifold volume, were directly related to response characteristics. Additionally, chugging instability at reaction chamber was observed when pressure drop across the catalyst bed was increased due to high aspect ratio or when low pressure was built at reaction chamber.