한국분무공학회지 (Journal of ILASS-Korea)

  • 제21권1호
  • /
  • Pages.13-19
  • /
  • 2016
  • /
  • 1226-2277(pISSN)
  • /
  • 2288-9051(eISSN)
한국분무공학회 (Institute for Liquid Atomization and Spray Systems-Korea)
권호 표지
DOI QR코드

DOI QR Code

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 (한국항공대학교 대학원, 현(주)스페이스솔루션) ;
  • 손민 (한국항공대학교 대학원) ;
  • ;
  • 김희동 (안동대학교 기계공학부) ;
  • 구자예 (한국항공대학교 항공우주 및 기계공학부)
  • 투고 : 2016.01.14
  • 심사 : 2016.02.23
  • 발행 : 2016.03.31
PDF 다운로드
⟨ 이전 논문 다음 논문 ⟩

초록

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.

키워드

참고문헌

  1. Robert, L. Sackheim, "An ultra low cost commercial launch vehicle that you can truly afford to throw away", 35th AIAA/ASME/SAE/ ASEE Joint Propulsion Conference and Exhibit, C.A., USA, 1999, AIAA 99-2621.
  2. Matthew, J. Casiano, James, R. Hulka and Vigor, Yang, "Liquid-propellant rocket engine throttling: a comprehensive review", Journal of propulsion and power, Vol. 26, No. 5, 2010, pp. 897-923. https://doi.org/10.2514/1.49791
  3. ChunGuo YUE, JInXian LI, Xiao HOU, XiPing FENG and ShuJun YANG, "Summarization on variable liquid thrust rocket engines", Science China Technological Sciences, Vol. 52, No. 10, 2009, pp. 2918-2923. https://doi.org/10.1007/s11431-009-0185-2
  4. Dressler, G. A. and Bauer, J. M., "TRW pintle Engine heritage and Performance Characteristics", 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, A.L., U.S.A, 2000, AIAA 2000-3871.
  5. Gilroy, R. and Sackheim, R., "The Lunar Module Descent engine-A Historical Summary", 25th AIAA/ ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, C.A., U.S.A, 1989, AIAA 89-2385.
  6. Mueller, T. and Dressler, G., "TRW 40 KLBf LOX/RP-1 Low Cost Pintle Engine Test Results", 36th AIAA/ ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, A.L., U.S.A, 2000, AIAA 2000-3863.
  7. Gromski, J. M., Majamaki, A. N., Chianese, S. G., Weinstock, V. D., and Kim, T. S., "Northrop Grumman TR202 LOX/LH2 Deep Throttling Engine Technology Project Status", 46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, T.N., U.S.A, 2010, AIAA 2010-6725.
  8. Seedhouse, E., "SpaceX Making Commercial Spaceflight a Reality", 2013.
  9. Min Son, Kijeong Yu, Jaye Koo, Oh Chae Kwon and Jeong Soo Kim, "Effects of Momentum Ratio and Weber number on Spray half Angles of Liquid Controlled Pintle Injector", Journal of Thermal Science, Vol. 24, No. 1, 2015, pp. 37-43. https://doi.org/10.1007/s11630-015-0753-7