本論文基於研究之宗旨，選用GSP 模擬軟體在氣渦輪引擎研究領域具備成熟模擬功能的特性，假設渦輪引擎處於穩態與暫態模式操作下，模擬其面臨失效因子時之性能衰退趨勢。研究時選用軸流式近似J85系列渦輪噴射引擎做為模擬對象，在不考慮使用可變幾何系統或放氣瓣等控制系統之原則下，假設引擎自最大燃油流量轉速減低轉速及流量，再加速回至原流量值，分別舉常見之外在不穩定因子的「壓縮器葉片損傷」與內在不穩定因子的「葉尖間隙增大」及「渦輪元件腐蝕」作為失效因子，分析該等因子構成性能衰退的關鍵參數，並將各參數值變率輸入GSP 模擬性能衰退平台，以獲得壓縮器效率、渦輪效率及淨推力等重要性能參數輸出值與趨勢圖，以及經過尺度化後之壓縮器特徵圖，據此量測性能衰退前後之操作線與失速線的壓縮比， 同時計算衰退前後之失速裕度。經研究發現：無論是內在或外在不穩定因子均使引擎在加速暫態其間，某些失效因子所出現的短暫提升現象，主要係引擎高轉速或高機械軸功效率而產生的慣性效應所致，惟當引擎回復至穩態運轉後，其整體性能即呈現全面衰退趨勢；此外本論文亦藉暫態失速裕度(Stall Margin)計算求解程序，可為後續探討各型渦輪引擎性能衰退預測之參考。

With regards to failure factors (compressor blade tip clearance increases, the compressor blade damage, turbine blade erosion), exploring their respective turbine engine may cause the extent of damages. With use of the Dutch National Skylab GSP simulation software (National Aerospace Laboratory, NLR) complete to develop as a performance analysis tool. After each failure simulation and factor analysis of research and found that in the acceleration transient meantime, part of the performance parameters of short lifting, does not represent the engine performance has been improved. It was found at an acceleration transient operating mode, failure factor due to the high engine speed / high mechanical axis inertial effects of power efficiency, resulting in net thrust each element efficiency or have short-term increase, which is not the overall performance of the engine can be identified has become Jia after the engine to respond to a steady operation mode, parameter variability observed increase due to continuous decline suddenly and showed a downward trend.

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