Effect of fuel impingement cooling on the combustion flow field in a bipropellant liquid rocket combustor

• Main Authors: Ting-Hao Lan, 藍庭豪
• Other Authors: Tsung-Leo Jiang
• Format: Others
• Language: zh-TW
• Published: 2003
• Online Access: http://ndltd.ncl.edu.tw/handle/13930665941411461830

碩士 === 國立成功大學 === 航空太空工程學系碩博士班 === 91 === In this thesis, the combustion flow in a small bipropellant liquid rocket combustor is numerically simulated. Effects of injecting partial fuel on the chamber wall for cooling are investigated. The parameters investigated include the ratio of the cooling fuel to the total injected fuel, the spray angle of the cooling fuel and the injection angle of the cooling fuel. The results obtained from the simulation show that the 30% ratio of the cooling fuel reduces the flow rate of MMH impinging with NTO, resulting in uneven mixing and lower combustion efficiency. The 10% ratio of the cooling fuel makes the combustion area concentrate in the center region of the combustor, increasing the combustion efficiency. Increasing the spray angle of the cooling fuel leads to a larger cover area of the cooling fuel on the chamber wall. The fore-end of the chamber wall is thus cooled more effectively. Additionally, a larger injection angle reduces the peak temperature of the fore-end wall of the combustor. Compared to the cases with a 60o atomization spray angle, the cases with a 90o atomization spray angle cause more droplets in the outer region of the spray flowing towards the chamber wall, resulting in higher temperature in the fore-end wall of the chamber.