渦輪噴射引擎為航空器常見的推進系統，其結構上主要由壓縮器、燃燒室、渦輪與排氣噴嘴等元件所組成，各元件間必須遵守流量與動量守恆的原則，方得以穩定運轉。但引擎操作時並非隨時保持恆定狀態，而是在不同油門角度下，有不同的操作性能，全域操作性能可由壓縮器性能圖中之平衡操作線予以呈現。而上述之引擎全域操作性能必須透過大量實驗獲得，因此對於製造廠家而言均視為機密不願釋出，故於公開文獻中，通常僅能獲得引擎設計點性能規範，而對於全域操作性能相關資訊卻是付之闕如。鑒此，本論文根據渦輪機械原理進行引擎元件操作特性分析，並以Microsoft Visual Basic 6.0程式語言自行開發渦輪噴射引擎平衡操作性能預測模擬程式：AFSP。至於實例模擬部分，則是以J85-21B引擎為例，首先採用商用軟體GasTurb 12(網路試用版)完成壓縮器性能圖製作，再以AFSP模擬程式進行平衡操作線預測與驗證。本論文主要成果在於根據基本學理完成渦輪噴射引擎之平衡操作性能推論，並自行發展模擬程式AFSP，在有限資訊（引擎設計點性能）的條件下，可完成平衡操作線預測，對於掌握渦輪噴射引擎全域操作性能上提供一可行的途徑。

The aircraft ordinary propulsion system is turbojet engine, which consists of compressor, combustor, turbine and exhaust nozzle. When engine is in stably working situation, each unit should follow the principle of flow and momentum conservation. When turbojet engine is working, it is not always maintain in steady operation. However there are different kinds of operation performance depends on various angle of throttle and all operating areas performance is showed via the Equilibrium Running Line in the Compressor Performance Map. The aforementioned all operating areas performance requires plenty of experiments to research so that it has been classified and covered by manufactures. In general, the archives, uncovering document, only show the specifications of engine designed performance, but the information of all operating areas is seldom refer in researches. Above all, the research which analyzes the specifications of engine unit operation is based on mechanical principle of turbo. By using the Microsoft Visual Basic 6.0 program design a simulator – AFSP, which can predict equilibrium running performance of turbojet engine. The sample of simulator is using J85-21B engine. First, using GasTurb 12(online test version) program complete the compressor performance map. Then using AFSP simulator predicts and proves the Equilibrium Running Line. The major result of the research is to complete the equilibrium running performance of turbojet engine prediction by using fundamental theories and design a simulator – AFSP, and therefore it accomplish the prediction of Equilibrium Running Line in limited circumstance (engine design point performance). It offers a usable method on controlling all operating areas performance of turbojet engine.

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