本研究首先利用冷流實驗觀察超音速流場在不同噴注方式、質量流率下燃料分佈情形。冷流實驗結果顯示槽內三股斜噴相較於槽內單股斜噴能使燃料更平均分佈於凹槽內且霧化效果佳；槽內質量流率大小會影響燃油於槽內之霧化效果。增加上游單垂直噴注之質量流量會使燃油穿透高度提高、消散長度變長、抬升高度變高；固定動量通量比、增加上游噴注孔徑會使燃油噴出變高，增加穿透高度、消散長度變長、抬升高度不變；上游雙垂直噴注能增加震波作用及流場震盪，使得穿透高度提高、消散長度變短、抬升高度減少。
接著利用點火器作為母火，點燃槽內燃料，找出最佳槽內穩定駐焰配置。結果顯示槽內三股斜噴3g/s為本凹槽最佳配置，能穩定駐焰時間長達48秒直到燃油關閉。接著加入於距離前壁面處15mm處加入上游噴注，發現上游噴注點燃後槽底溫度幾乎沒有改變、斜壁面溫度下降。推測是上游噴注點燃後會改變槽內燃燒範圍，使得鞋壁面溫度下降，溫度下降大小會因上游之質量流率大小而改變。最後加入上游雙垂直噴注，發現點燃後槽底溫度會上升，斜壁面溫度下降，推測是上游B燃油噴注碎裂霧化後加強槽內燃燒效果，使得槽底溫度上升。

In this study on supersonic combustion ramjets, an open-type cavity flamefolder is chosen to generate a low-speed recirculation zone for proper fuel combustion due to the extremely short residence time in the combustion chamber. The experiment involved fixed 45° inclined fuel injection inside the cavity and an igniter as the pilot flame. Different mass flow rates and injection patterns were tested to achieve stable flameholding in Mach 2 supersonic flow. Cold flow results showed that three inclined jets inside the cavity distributed fuel more evenly and atomized better than a single inclined jet. Mass flow rate inside the cavity affected fuel atomization. Increasing the upstream single vertical injection's mass flow rate resulted in higher penetration height, longer dissipation length, and higher lift-off height. Increasing the orifice size of the upstream injection resulted in higher fuel jet height and increased penetration height and dissipation length. The upstream double vertical injection enhanced shock effects and flow oscillation, leading to increased penetration height and shortened dissipation length. The ignition experiment found the best configuration to be three inclined jets with a flow rate of 3g/s, providing stable flameholding for up to 48 seconds. Adding an upstream injection had minimal impact on cavity temperature, while the inclined wall temperature decreased. The addition of an upstream double vertical injection increased cavity temperature, hypothesized to be due to enhanced combustion inside the cavity.

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