本研究利用熱力學及空氣動力學的理論公式，以似一維流場方法來分析一具推力H-80八十磅級微型渦輪引擎性能，並詳細探討其理論分析方法與站位計算流程，並以八十磅微型渦輪引擎實體測試數據，驗證性能分析之有效性。引擎全程控制由電子控制單元(ECU)操作，透過ECU數據顯示器，控制不同轉速，並分別量測引擎基本性能參數，如引擎推力(lb)、壓縮比、油耗、燃燒室溫度T4、排氣溫度EGT(℃)、尾管壓力等。在引擎分析方面，首先分析渦輪引擎在設計點轉速及離點轉速下的對應空氣質流量、各站位組件的工作參數及流道數據，進一步計算各站位的流體工作馬赫數，並求得各站位的流體熱力性質。在引擎量測方面，根據分析計算的站位結果比照實體站位所量測的數據，驗證引擎理論分析架構及各站位估計的組件工作效率。八十磅級微型渦輪引擎量測實驗證明，推力在93000rpm設計點下可達80磅足推力，壓縮比為3.49，壓縮器及渦輪的效率分別是67%跟80%，燃燒室的壓力降在設計點為2.3%，TSFC值為1.5。

The purpose of this research is to analyze the performance of an eighty-pound micro gas turbine engine. With FADEC electrical control, it shows the basic engine test data, such as thrust, exhaust temperature and rpm were examined also. The turbine engine type is H-80. With quasi-one-dimensional, aerothermodynamics theory analysis, the station Mach number of turbine engine can be calculated. The experiment of this research is to measure the engine mass flow, station fluid property, combustion T4, engine fuel consumption at design point and off-design point. According to the measurement, verify the theoretical property of each station, Mach number and turbine engine efficiency. The engine design point is 93000rpm ,thrust 81.42lb ,compressor pressure ratio 3.49 ,efficiency 67% ,combustor pressure drop 2.3% , turbine efficiency 80% and TSFC 1.5.

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