本研究之目的是探討一具微型渦輪引擎以直接噴油啟動方式作為點火機制。微型渦輪引擎啟動點火主要分為兩種，氣態燃料和液態燃料作為點火方式的來源，其中氣態燃料主要是使用天然氣，然而液態燃料吾人則使用航空煤油JP-8。研究中發現若以氣態啟動方式，其優點是氣態分子碰撞快速且易擴散至整個燃燒室，使用天然氣點火成功率相當地高，然而現今航空器或飛行載具對於整體空間運用及可靠性相當講究，故使用煤油霧化點火方式可省去裝置天然氣氣瓶的使用空間，點火方面也可重複點火以降低啟動失敗的風險。但液態點火方式霧化器與火星塞的相對位置也比氣態點火重要許多，吾人對霧化器錐角、霧化粒徑、霧化器位置以及預熱絲在燃燒室所放置在不同位置的實驗，嘗試探討出最佳啟動點火的範圍。從實驗中發現，60度錐角的霧化器與80度錐角的霧化器，在不同情況下，點火成功率的趨勢都是類似的，只有在較淺的深度，因60度錐角的霧化器無法涵蓋到較大的範圍，故在霧化器與預熱絲的夾角過大時，60度錐角的霧化器比80度錐角的霧化器點火成功率相較之下會比較低，研究中發現霧化器所噴出來的霧化夾角，與霧化器與火星塞的相對夾角對於點火試驗的成功率有顯著的影響。希望藉由本次點火試驗的研究結果，作為未來發展與研究的參考。

The goal of this study is to investigate how the gas turbine ignites by direct injection. Two fuel types were applied on conventional micro gas turbine. In this study, natural gas is adopted for gas-fuel ignition, while JP8 is applied for liquid-fuel. If the gas turbine is ignited with gas, the possibility for operation is high and the collision diffusion is fast. The gas molecules easily fill the whole combustion chamber. However, aircrafts or flight vehicles nowadays use kerosene and achieved optimal special arrangement. The diameter of atomized kerosene droplet, the cone angle of spray, the flow rate and operation pressure variation versus the percentage of successful ignition. Analysis of the influence of the relative position of the atomizer to the glow plug also performed to find out the optimal operation range for ignition. Along the observation, the results are similar in different ignition parameters, when 60° and 80° atomizer is individually applied. When the glow plug moved closer to the atomizer, the coverage of is apparently smaller than. It is concluded that the possibility of successful ignition will decrease in 60° atomizer when the angle is large between the atomizer and glow plug. It will also be affected by the angle of the atomizer and the relative position of the atomizer and the glow plug.

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