由於航空發動機燃燒室內部燃燒反應的複雜性，早期的航空發動機燃燒室設計皆藉由過去成功的經驗與大量的一維計算及簡易燃燒室模型的試驗結果，逐步修正而得出最終成果。但這種藉由大量試錯來完成燃燒室設計的方法有成本高、耗時長及測試結果不完整等缺點。之後發展出CFD軟體能夠協助開發，然而實驗室實際進行燃燒研究時除了電腦模擬之外，還需要有實際的實驗結果來做驗證。但使用既有的航空發動機來做驗證是不切實際的想法，因為通常使用的簡易燃燒室觀察箱其外型與結構皆與實際差異甚大，時常需要反覆進行測試來改進其設計缺陷。

本論文藉由研究現有主流渦輪扇葉發動機燃燒室，嘗試自行開發設計出一款小型航空發動機燃燒室測試模型並使用自行設計之45度Swirler(旋流器)進行燃燒測試，本次自行設計的燃燒室模型使用Jet A-1當作燃料進行測試。根據測試結果發現，在當量比0.8時Jet A-1具有最佳的燃燒結果，其燃燒後廢棄物如CO、NO及HC對比於其他當量比組別，燃燒時於空氣中的濃度含量更低。在當量比0.8時，於可見光相機的拍攝下可以看到明亮且穩定的火焰核心，而當量比0.9到1.2時，火焰核心的形狀穩定性較差且好似充滿了懸浮物一般混濁，表示其渦流結構不足以形成穩定的回流區域。在OH*化學發光相機的拍攝下，可以看到當量比0.8時其火焰的OH*化學發光呈鐘罩形，CRZ 明顯，OH*分布均勻。

本測試模型成功實現燃燒觀察、成份採集分析與流場模擬驗證等功能，可應用於多種燃料類型與旋流器設計參數之實驗研究，進一步提升我國航空動力技術自主研發能力。期望在未來對於國內航空引擎燃燒室的研究及開發上做出一些貢獻，進而加強國內在軍民用航空引擎上的研發能力並達到縮短研發週期的效能。

Due to the complexity combustion reaction of combustion chamber. Early combustion chamber designs were slowly modified based on past successes experience to achieve results. However, this method of completing design through a lot of trial & error has the disadvantages of high cost, long time consumption and incomplete test results.

Later, CFD software was developed to assist in development. However, when conducting actual research in the laboratory, in addition to computer simulations, actual experimental results are also needed for verification. But it is impractical to use existing aircraft engines for verification. The appearance and structure of the common simple combustion chamber model are very different from the actual situation. Repeated testing is often required to improve the design defects.

This thesis studies the combustion chamber of existing mainstream turbofan engines, attempts to develop and design a small combustion chamber model, and uses a self-designed 45-degree swirler to conduct combustion tests. This self-designed combustion chamber model was tested by using Jet A-1 as the fuel. According to the experimental results, Jet A-1 has lower CO, NO and HC emissions when using a 45-degrees blade angle Swirler at equivalence ratio of 0.8. When photographed with a visible light camera, the flame shapes are clearer and brighter than other results.

The test model successfully integrates combustion, observation, emission sampling functions, and demonstrates potential for further applications involving alternative fuels and swirler configurations. This implementation is expected to contribute to the domestic development of advanced combustion technologies.

This implementation is expected to make some contribution to the research and development of future aviation engine combustion chambers, thereby enhancing the development capabilities in military and civil aviation engines and achieving the expectation of shortening the development cycle.

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