本研究由燃燒室內外襯筒孔口設計理論出發，以市售KingTech K170-F微型渦輪噴射引擎規格為設計目標，進行燃燒室之設計。將設計之燃燒室加工後裝配至K170-F渦輪引擎上進行性能量測，以分析吾人設計之燃燒室燃燒情形。
研究分為三個階段：第一階段為量測K170-F渦輪引擎之性能參數，並利用渦輪分析軟體計算引擎各站位之條件，提供吾人設計燃燒室之條件及限制，並作為往後與吾人設計之燃燒室比較之依據。第二階段則利用上述之條件，從理論出發進行燃燒室設計，例如燃燒室幾何尺寸、燃燒室內外襯筒之孔口直徑及位置安排、各燃燒區空氣流量分配。第三階段將設計之燃燒室加工成型，裝配至K170-F渦輪引擎進行實際運轉量測，藉由量測所得之數據與原始數據進行比較，分析吾人設計之燃燒室燃燒情形。
實驗結果得知吾人設計之燃燒室可實際應用在渦輪引擎上，性能表現與原始燃燒室差異極小，提供一成功之燃燒室設計經驗。

This study starts from the design theory of the holes on the combustion chamber liners . I designed the combustion chamber to reach the standards of KingTech K170-F micro-turbojet engines. The designed chamber was then assembled onto the K170-F turbo-engine in order to test the performance and analyze the combustion in the chamber.
This study had three stages: (1) The performance of the K170-F turbo-engine was measured, and the turbine analysis program was used to calculate the conditions inside the turbo-engine, which in later stages would be referred to as the basics and restrictions; (2) Those conditions measured in last stage and the related theories were used to design a combustion chamber, in which details were all covered, including the geometrical chamber size, the positions and the diameters of the chamber liner holes, and the air flow rates of all combustion areas; (3) The chamber was assembled onto the K170-F turbo-engine, the performance of the running turbo-engine was measured, and then the testing results of the turbo-engine was compared with the designed chamber with the original ones in order to further analyze the combustion inside the chamber.
The experimental results show that the chamber I designed can be applied to real turbo-engines and that the performing difference between the designed chamber and the original one is not significant. This study serves as a successful attempt to design a combustion chamber for a micro turbo-engine.

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