本研究的主要目的為根據八十磅級微型渦輪引擎實際實驗數據，以此為核心引擎，並藉由GasTurb來模擬引擎在增加一級不同類型之壓縮器，包括假設一單軸雙壓縮器之噴射引擎(Two compressor turbojet)與一渦輪風扇引擎(Turbofan)來模擬整體性能；單軸雙壓縮器之形式，又可再細分一為加裝離心式壓縮器、一為加裝軸流式壓縮器；所對應之淨推力(Fn)、每單位時間單位推力耗油率(Tsfc)、淨推力(Fs)來做比較。並利用最佳化趨勢來推算引擎最低之耗油率與最大淨推力，由模擬測試結果發現，在前端增加一級風扇效果最佳，在風扇壓縮比為1.15，旁通比為5時，本引擎可得到淨推力增加67.5%，耗油率減少43.3%之模擬結果，有助於未來微型渦輪引擎製作設計做為可靠之參考數據。

The purpose of this research is based on eighty-pound micro gas turbine engine’s actual experimental data to simulate it for increase different types of compressor by GasTurb ; Including the assumption of two-stage single-shift compressor and turbofan jet engine to simulate the overall performance; Two-stage single-shift compressor can be divided into a centrifugal compressor, and an axial compressor. To compare specific fuel consumption (Tsfc) , thrust(Fn), and net thrust (Fs) for this engine, and optimize specific fuel consumption (Tsfc), thrust, and net thrust (Fs). According the simulation test results show that increase a fan in front of this engine is the best, the compression ratio is 1.15 and the fan bypass ratio is 5, and the engine net thrust increases 67.5%, the fuel consumption decreases 43.3%. It will help engine production design as a reliable reference by this simulation results in the future.

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