• Title/Summary/Keyword: 동축 스월형 분사기

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Modeling of Breakup and Spray of Co-axial Swirl Injector's Outer Orifice Installed LRE combustor (액체로켓엔진에 장착되는 동축 스월형 분사기의 외측 오리피스에서의 분무 및 분열 모사)

  • Moon, Yoon-Wan;Seol, Woo-Seok;Yoon, Young-Bin
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2006.11a
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    • pp.186-190
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    • 2006
  • This study was performed to investigate the characteristics of a co-axial swirl injector. Especially to predict the initial liquid sheet thickness and spray cone angle of an outer orifice a concept of effective area was introduced from hydraulic analysis. In addition, the parameters determining the characteristics of a co-axial swirl injector were re-defined around outer orifice. The calculated results-SMD, spray cone angle, and spray thickness agreed well with the test results qualitatively.

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A Numerical Study of the Spray Characteristics of Co-axial Swirl Injector in Liquid Propellant Rocket Engine (액체로켓엔진에서 동축 스월형 분사기의 분무특성에 대한 수치적 고찰)

  • Moon Yoon-Wan;Seol Woo-Seok;Yoon Young-Bin
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2006.05a
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    • pp.156-160
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    • 2006
  • This study investigated the characteristics of spray generated by a liquid-liquid co-axial swirl injector used in a combustor of the liquid rocket engine. The linear stability analysis[1] was introduced In liquid sheet breakup and Post[2]'s collision model which considers shattering was adopted on the collision model after breakup. Every model was implemented to KIVA[3], which was adopted as solve. To validate the implemented models the cases of high and low injection velocity were calculated respectively and each result agreed well with test results.

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A Study of Collision Model in Coaxial Swirl Injector (동축 스월형 분사기에서 충돌 모델 연구)

  • Moon, Yoon-Wan;Seol, Woo-Seok;Yoon, Young-Bin
    • 한국전산유체공학회:학술대회논문집
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    • 2008.03b
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    • pp.320-323
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    • 2008
  • In this study the effect of collision model was evaluated in spray field by CFD. A collision is basically the interaction between droplets and criteria of collision is determined by drop Weber number, impact parameter, and drop-size ratio. Early developed collision model considered coalescence and grazing collision with the exchange of momentum. However in experimental research there were bouncing, coalescence, reflexive separating and stretching separating in interaction between droplets. In this study the collision considering such complex phenomena is modeled and was compared with the basic collision model.

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Development and Validation of Spray Model of Coaxial Swirl Injector Installed in Liquid Propellant Rocket Engine (액체로켓엔진에 장착되는 스월 분사기의 분무 모델 개발 및 검증)

  • Moon, Yoon-Wan;Seol, Woo-Seok
    • Journal of the Korean Society of Propulsion Engineers
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    • v.11 no.5
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    • pp.37-50
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    • 2007
  • This study investigated the characteristics of spray generated by a liquid coaxial swirl injector used in a combustor of the liquid rocket engine. The linear stability analysis considered long and short wave was introduced in liquid sheet breakup. Through the hydrodynamic analysis the initial liquid sheet thickness spray angle and injection velocity were predicted. To evaluate the effect of turbulence model standard $k-{\varepsilon}$ and RNC $k-{\varepsilon}$ model were applied to numerical calculation and it was known that RNC $k-{\varepsilon}$ model was more applicable to predict spray characteristics. On the basis of this evaluation validation of the developed model was performed with swirl injector installed in LPRE and the predicted results of breakup length, spray angle, and SMD agreed well with experiments qualitatively and quantitatively.

Numerical Analysis for Characteristics of Coaxial Swirl Injector in High-Pressure Environment (고압환경에서 동축 스월 분사기 분무 특성에 대한 수치적 해석)

  • Moon, Yoon-Wan;Seol, Woo-Seok;Kim, Dong-Jun;Yoon, Young-Bin
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2007.11a
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    • pp.131-134
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    • 2007
  • This numerical analysis was performed in order to validate adoption of the sheet breakup model in high-pressure environment, which were used for prediction of spray characteristics in atmosphere environment. In experiments the higher environment pressure the shorter breakup length; the results of new sheet breakup model predicted the breakup length in good agreement with experimental results qualitatively and quantitatively. Also the shape of spray calculated by numerical analysis were agreed well with experiments quantitatively.

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Study on Combustion Characteristics of Unielement Thrust Chambers with Various Injectors (다종의 동축 스월형 단일 분사기 연소 특성에 관한 실험적 연구)

  • Seonghyeon Seo;Lee, Kwang-Jin;Han, Yeoung-Min;Kim, Seung-Han;Kim, Jong-Gyu;Moon, Il-Yoon;Seol, Woo-Seok
    • Journal of the Korean Society of Propulsion Engineers
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    • v.8 no.2
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    • pp.85-94
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    • 2004
  • Experimental study on combustion characteristics of double swirl coaxial injectors has been conducted for the assessment of critical injector design parameters. A reusable, unielement thrust chamber has been fabricated with a water-cooled copper nozzle. Two principal design parameters. a swirl angle and a recess length, have been investigated through hot firing tests for the understanding of their effects on high pressure combustion. Clearly, both parameters considerably affect the combustion efficiency, dynamics and hydraulic characteristics of an injector. Internal mixing of propellants in a recess region increases combustion efficiency along with the increase of a pressure drop required for flowing the same amount of mass flow rates. It is concluded that pressure buildup due to flame can be released by the increase of LOx flow axial momentum or the reduction of a recess length. Dynamic pressure measurements of the thrust chamber show varied dynamic behaviors depending on injector configurations.

Ignition and Extinction Characteristics of a Low Thrust Combustion Chamber using Green Propellant according to Sequence of the Combustion Test (친환경 추진제를 사용하는 저추력 액체로켓엔진의 연소시험 시퀀스에 따른 점화 및 소염 특성)

  • Kim, Young-Mun;Jeon, Jun-Su;Choi, Yu-Ri;Ko, Young-Sung;Kim, Yoo;Kim, Sun-Jin
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2009.11a
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    • pp.130-133
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    • 2009
  • The sequence of the propellant supply is very important for the reliable and safe operation of a LRE combustion test. So combustion performance tests were performed to find an optimum test sequence by changing supply time of propellants and purge gas in the moment of ignition and extinction. The liquid rocket engine consisted of a catalytic ignitor and six swirl-coaxial injectors which used hydrogen peroxide and kerosene. Conclusively, an optimum sequence was found for stable combustion in the moment of ignition and extinction.

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