• Title/Summary/Keyword: Reactive Stream Separation

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Research Studies of Impingement Characteristics for Hypergolic Propellant (접촉 점화성 추진제의 충돌형 혼합 특성 연구 사례)

  • Kim, Kyu-Seop;Kim, Yehyun;Jung, Sangwoo;Jeong, Junyeong;Kwon, Sejin
    • Journal of the Korean Society of Propulsion Engineers
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    • v.23 no.5
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    • pp.90-100
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    • 2019
  • Hypergolic thrusters have been extensively researched and applied to spacecraft propulsion based on their simplicity and high reliability of ignition. Research on the impingement characteristics of $N_2O_4$/amine has been profoundly carried out since the 1960s in advanced countries, especially the United States. Recently, enhancements to advanced hypergolic thrusters using MON/MMH have been planned by NASA to improve compactness and high performance. In this work, technical studies were investigated on the mixing of hypergolic propellant and its combustion instabilities such as reactive separation flow and popping.

CFD simulation of a prefilming air blast fuel nozzle (Prefilming air blast 연료 노즐의 다상유동 및 반응 유동장 수치해석)

  • Jung, Seungchai;Kim, Shaun;Park, Heeho;Ryu, Shiyang
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2017.05a
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    • pp.251-253
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    • 2017
  • Numerical study of air-blast type injector for low emission aircraft engines was conducted. Volume-of-fluids approach was used to track interface of fuel and air. Primary atomization of fuel stream was visualized, and thickness and mean velocity at the injector exit was calculated. Liquid fuel injected from fuel slots joined together as a thin film on preflimer surface, and interacted with swirling air. As instability on the fuel surface increased, separation of fuel as ligaments and droplets occured. The film thickness and velocity were used to as fuel injection boundary condition for reactive flow simulation. Primary reaction zone was formed in vicinity of the fuel nozzle, creating a stable flame inside the combustor.

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