發動機為飛機的心臟，其設計的方向將直接關係著飛機的用途與性能，軍用戰機更是對其發動機有著很高的設計要求，研究發動機的性能，必須對其參數有著完善的蒐集，然而越是近代發動機，參數越是難以取得，要利用少量的已知發動機參數，去推測剩餘的未知參數，將是研究近代發動機所需面臨的課題。
本研究主要研究如何在參數不足的情況下，模擬近代軍用航空發動機性能參數，並補足缺失參數，本研究以F119-PW-100、F135-PW-100此類軍用渦輪扇發動機作為模擬對象，並以早期的F100-PW-220發動機作為近代發動機模擬的參考對象進行先期模擬，因其性能參數取得較容易，模擬準確度較高，且模擬結果對其餘兩款發動機都具重要的參考價值。模擬方式以推力與比燃油消耗率參數做為模擬的最終設計點，利用模擬軟體GasTurb中的敏感性研究法、參數研究法與最佳化研究法，幫助進行各性能參數的研究，了解各參數對設計點的影響，並利用參數設計特性，進行參數的合理化修正，最終找到符合設計點的各項性能參數，且模擬結果與設計點誤差均在3%以內。利用設計點模擬結果，對F119-PW-100、F135-PW-100發動機進行離點推力研究，結果表明此模擬的性能可提供足夠推力，使其在10 kft高空擁有1.2馬赫以上的飛行動力，進一步驗證模擬結果的準確性。

The engine is the heart of an aircraft, and its design affects the purpose and performance of the aircraft directly. Especially for military aircraft, it needs engine of higher performance requirements for high altitude and speed than civil aircraft. To study engine performance, it is necessary to have a complete collection of its parameters. However, modern military engine parameters are difficult to obtain, therefore, deducing unknown parameters is the main task for modern engine studies nowadays.
The topic of this study is to simulate the performance parameters of modern aircraft by using the engine simulation software ‘GasTurb’ under the circumstance of insufficient parameters.
This research simulates the performance parameters of F119-PW-100 and F135-PW-100 engines. And also simulate F100-PW-220 engine as the reference of modern engine simulation for preliminary simulation. Since the F100-PW-220 engine performance parameters are easier design in history, and with the high accuracy simulation result, it provides important reference value for the other two engines. The simulation takes thrust and specific fuel consumption rate parameters as the design point, and uses the sensitivity study method, parameter study method and optimization method in the simulation software to study the performance of each parameter. Parameters are further modified for rationalization by using its designable characteristic. These methods help us to understand the influence of each parameter on the design point. Finally, the performance parameters are found to meet the design point, and the range of error between the simulation result and the design point is within 3%. By using the simulation results of the F119-PW-100 and F135-PW-100 engines to simulate the thrust parameters from the off-design point, the results show that the performance of this simulation can provide sufficient thrust to enable them flight above Mach 1.2 at an altitude of 10 kft.

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