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로켓 엔진의 연소 성능 예측 및 시험

박정;김용욱;김영한;정용갑;조남경;오승협
Park, Jeong;Kim, Yong-Wook;Kim, Young-Han;Chung, Yong-Gahp;Cho, Nam-Kyung;Oh, Seung-Hyub

  • 발행 : 2000.05.01

초록

A model for depicting the rocket engine combustion process is presented and several experiments near a design point are provided with a FOOF type of unlike impinging injector for a propellant combination of Jet A-1 fuel and liquid-oxygen. The model is based on the assumption that the vaporization is the rate-controlling combustion process. The effects of initial drop size and initial drop velocity are systematically shown and discussed. It is seen that in the midst of considered parameters the change of initial drop size is more sensitive to the performance. The proposed model describes qualitative trends of combustion process well despite of its simplicity

키워드

비동류형 충돌 인젝터;공기역학적 항력;증발;특성 속도

참고문헌

  1. Richard, J. P. and Marcus, F.H., 1960, 'Propellant Vaporization As A Design Criterion For Rocket Engine Combustion Chamber,' NASA TR R-67
  2. Hougen, O.A. and Watson, K.M., 1943, Chemical Process Principles, John Wiley & Sons, Inc.
  3. Sherwood, T.K. and Pigford, R.I., 1952, Absorption and Extraction, 2nd. ed., Mc-Graw-Hill Book Co., Inc.
  4. Ranz, W.E. and Marshall, W.R., 1952, 'Evaporation from Drops, pt. I,' Eng. Prog., Vol. 48, No. 4, Apr. p. 141
  5. Ingeb, R.D., 1954, 'Vaporization Rates and Drag Coefficients for Isooctane Sprays in Turbulent Air Streams,' NASA TN 3265
  6. Dunn, G, 1990, Pressure Fed Thrust Chamber Technology, Aerojet Report, Contact NAS 8-37365