• 제목/요약/키워드: Propellent phase

검색결과 3건 처리시간 0.018초

액체로켓 동축인젝터(CH4/LOx)의 고압 연소실 내 연소 유동장에 대한 수치적 연구 (Numerical Study of CH4/LOx Combustion of Shear-coaxial Injector in High Pressure Combustion Chamber of Liquid Rocket)

  • 김정은;정인석
    • 한국연소학회:학술대회논문집
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    • 한국연소학회 2014년도 제49회 KOSCO SYMPOSIUM 초록집
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    • pp.311-313
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    • 2014
  • High pressure combustion with multiphase--liquid, gas, and supercritical phase--mixtures are widely used technology in the high efficiency liquid propellent rocket engine. This is the typical characteristics differentiate from the combustor of conventional air-breathing engines. Therefore, successful research of high pressure combustion at supercritical condition is essential to develope a high efficiency liquid rocket engine. Numerical studies have been carried out to explore capabilities of numerical method for LOx-CH4 non-premixed flames at high pressure. In this paper, corresponding numerical results are presented and compared with experimental result of MASCOTTE facility.

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가변 추력용 핀틀 분사기에서 추진제 상에 따른 상압분무 특성 (Effects of Propellant Phases on Atmospheric Spray Characteristics of a Pintle Injector for Throttleable Rocket Engines)

  • 유기정;손민;;김희동;구자예
    • 한국분무공학회지
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    • 제21권1호
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    • pp.13-19
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    • 2016
  • Atmospheric spray characteristics were experimentally compared between liquid-gas and liquid-liquid sprays of a pintle injector. In order to study spray characteristics, water and air were used as the simulants and the visualization technic was adopted. Spray images were acquired by using a backlight method by a high-resolution CMOS camera. As a result, when the pintle opening distance increased, liquid sheets became unstabled and fluttering droplets increased. In the liquid-gas case, the breakup performance increased as the pressure of gas injected from the annular orifice increased. In the liquid-liquid case, atomization efficiency decreased as the pressure of liquid injected from the annular orifice increased. Spray angles presented a similar trend between two cases. At the same momentum ratio, the spray angle of liquid-liquid case was lower than the angle of liquid-gas case.

액체추진제 로켓 엔진 연소장치 개발에 있어서의 전산유체역학 응용 (Application of Computational Fluid Dynamics to Development of Combustion Devices for Liquid-Propellant Rocket Engines)

  • 조미옥;김성구;한상훈;최환석
    • 항공우주기술
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    • 제13권2호
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    • pp.150-159
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    • 2014
  • 본 연구에서는 액체산소/케로신 추진 로켓 엔진 연소장치의 국내 개발에 있어서의 전산유체역학 응용 사례를 간략히 소개하였다. 추진제 공급부에 대한 다차원 유동 해석을 통해 유동 균일성을 확인하고 및 압력 손실을 예측할 수 있으며, 개념 설계 단계에서 추진제 매니폴드 형상 설계안을 비교/선택할 수 있다. 다분야 연소/냉각 성능 통합 해석을 통해 로켓 엔진 연소기의 연료 막냉각 및 열차폐 코팅 조건 등 연소/냉각 성능 관련 설계 문제 해결에 필요한 주요 정보를 도출할 수 있다. 향후 분사면 근처에서의 추진제 혼합 및 연소특성을 파악할 수 있는 해석 모델/기법을 개발할 필요가 있다.