以煤油與過氧化氫為推進劑組合的液態火箭引擎設計，使用兩階段衝擊式噴注盤可得到良好的噴霧混合效率及平均特徵速度。本研究應用理論計算、冷流光學觀察及實際開放空間點火實驗，進行兩階段衝擊噴注單元設計及噴霧混合特性分析，再以程式疊合設計為噴注盤。在以30組噴注單元組合為500磅推力噴注盤的條件下，各噴注單元推進劑總流量為25.52g/s，O/F為3.85。根據霧化影像觀察及PLIF噴霧質量分布之實驗結果，本研究選擇H2O2噴注孔徑0.6mm，以30度衝擊角置於內對；選擇煤油噴注孔徑0.4mm，以45度衝擊角置於外對；兩衝擊點之間垂直距離為5mm，預測可於第二衝擊點下游15mm處得最高平均特徵速度(1513.5m/s)。本研究亦以此設計進行開放空間點火實驗，量測得火焰長度約為107mm，而駐焰位置位於第二衝擊點下游30mm，平均特徵速度為1464.6m/s。並由此設計進行噴注單元排列，預測噴注盤整體之平均特徵速度為1582.2m/s。

For kerosene base fuel and H2O2 propellant system in liquid rocket engine design, two-stage impinging injection provides adequate mixing between propellants and excellent characteristic velocity after burning. In this thesis study, a two-stage impinging injector plate design of a 500lbf rocket engine has been researched. By assuming the Isp to be 280 seconds and 30 injection units on the injector plate, the propellant flow rate of each injection unit can be determined. Choosing an adequate O/F value and pressure drop across the injector orifices, the orifice size and impinging angle of the first stage like-double impinging of H2O2 is set at 0.6mm and 30, respectively. For the second stage impinging of kerosene base fuel, the corresponding orifice size and angle are 0.4mm and 45. Using optical methods, the characteristics of both like-doublet impinging sprays are determined. With hot firing experiments, the flame is around 107mm and is observed to station at 30mm below the second impinging point for various spatial two-stage arrangements. The distance between two impinging points is optimized to be 5mm, and the injection unit is estimated to provide the highest average characteristic velocity of 1464.6m/s. By fine adjustment of the arrangement of injection units on injector plate, the designed injector plate is estimate to have an average characteristic velocity of 1582.2m/s.

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