臺灣博碩士論文加值系統

由於飛行安全對確保民航旅運生命財產的重要性，世界各國莫不將其相關工作，諸如：飛行事故的通報與調查、肇因分析與統計、案例宣教與人員訓練等，納入政府的專責部門，期能累積經驗防患於未然。然而在軍用飛行器方面，因事涉國家安全，故各國在相關工作的處理上，均明訂依權責分層執行，並在資料公開方面作某種程度的區隔。有鑒於飛安研究及現代化科技對提昇空軍戰力的重要，本論文乃構思從系統工程的觀點，應用模擬與分析方法，探討有關戰機引擎熄火事故(Engine Flameout)的預警與防制，並規劃以下三項研究重點：(1)引擎熄火的肇因分析與歸類，(2)渦扇引擎穩態平衡運轉模式的分析，(3)典型戰機引擎因高壓軸轉速(N2)降低而造成性能衰降的趨勢探討。至於在成果方面，根據本論文以德國學者Joachim Kurzke教授發展的GasTurb軟體，針對美軍F-16戰機之F100-PW-220渦扇引擎所作個案研究(Case Study)，發現當N2低於60%，即無法再以穩態平衡運轉模式預測引擎性能，此恰與Childre及McCoy針對F-16所作
飛行測試研究時(詳參考文獻[17])，採用N2=60%作為F100-PW-220空中再啟動
(Air Restart)須達成的目標轉速要求相當吻合，因而確立本論文模擬結果的適用性，並據以導出下列兩項成果：(1)獲得七項具指標性的引擎性能參數隨N2變化之迴歸分析算式(文中以7Ω命名)，可作為後續探討熄火徵兆預警機制的參考，(2)辨識出三種不同油氣比」定義及其比值隨N2變化的定量趨勢，可作為後續探討引擎燃室熄火防制的理論基礎。由於本論文旨在建立一架構作為探討戰機飛安的論述參考，故在引擎參數的選取，係以網際網路公開文獻的資料為主，如後續因特殊目的及需求，則應視「實情實況」而作必要的調校與驗證。

Flight safety is a long been concerned worldwide subject, for its role in assuring the life and property in aviation. Administration of relevant works thus is hosted by government agency or authorized committee, with the ultimate goal of zero accident. As to the military aviation, however, it is restricted to different levels of authorization,forming a source of difficulty for academic study. In viewing the importance of flight safety and the need of modern fighter technology to support a superior air force, this thesis proposes a simulation study on the flameout problem of a
turbofan-powered fighter airplane. Particular concern has been centered on the symptom warning, while in approach the GasTurb software developed by Professor J. Kurzke is adopted for doing engine performance calculations. In contents, major effort has been dedicated on: (i) a general survey of the Internet literatures for the flameout cause analysis, (ii)deriving a mathematical model for the stable, equilibrium running of a mixed-flow type turbofan system, (iii) a case study of the F100-PW-220 turbofan of F-16 as an
example for the symptom analysis subject to the effect of a decaying high pressure shaft speed, N2 . According to the case study, it was found that when 60% ≤ N2 , the engine seems no longer operating in a stable and equilibrium mode, informed by the automatic stop of GasTurb and the final trace on the compressor map. This was then
validated using the flight test data published by Childre and McCoy [17], who suggested the 60% = N2 criterion as the goal for the air restart of F100-PW-220. In addition, two typical achievements based on the case study results are as follows: (i)identifications of seven regression formula(7Ω) for computing the performance
deterioration subject to a decaying N2, and (ii) the variation trend of fuel/air ratio with N2 based on three popular definition. Since this thesis is an academic study of a typical fighter airplane, it is thus noted that the results presented here only provide a trend of references, and may subject to change for a real case with special purpose.

誌謝 ii
摘要 iii
ABSTRACT iv
目錄 v
表目錄 viii
圖目錄 ix
符號說明 xi
1. 前言 1
1.1 主題構思緣起 1
1.2 相關研究回顧 4
1.3 工作重點規劃 7
1.4 論文架構說明 10
2. 渦輪引擎熄火事故之肇因分析與文獻探討 12
2.1 從美軍戰機1999飛安統計看引擎事故的類型 13
2.2 從典型戰機飛行測試看引擎熄火與空中再啟動 16
2.3 從網路資蒐看渦輪引擎熄火肇因的分析與研究 18
2.3.1 網路文獻的蒐集與綜整 19
2.3.2 概括說明類的文獻探討 20
2.3.3 肇因分析類的文獻探討 21
2.4 文獻探討心得與選擇N2為控制變因的構思 24
3. 典型戰機引擎穩態平衡運轉理論模式建構 31
3.1 引擎系統概述 32
3.2 主要模組之特性分析與數學方程式 35
3.2.1 風扇模組 35
3.2.2 壓縮器模組 39
3.2.3 燃燒室模組 43
3.2.4 高壓渦輪模組 45
3.2.5 低壓渦輪模組 47
3.2.6 燃氣與旁通氣流混合區 47
3.2.7 排氣尾管 49
3.2.8 推進噴嘴 51
3.2.9 引擎系統性能 53
3.3 引擎設計點性能規範之模擬算則 54
3.4 偏離設計點操作條件之引擎性能算則 59
4. 應用穩態運轉模式探討熄火徵兆實例評估 66
4.1 目標引擎性能諸元與設計點模擬 66
4.2 以N2減速為控制變因之目標引擎離點性能的模式模擬 72
4.3 根據進氣與燃油流量模擬結果探討引擎燃室熄火 78
4.3.1 目標引擎燃油之可燃極限計算 78
4.3.2 以燃氣比隨N2變化之燃室熄火評估 85
4.4 從週邊模組性能衰降評估引擎熄火之關鍵預警參數 91
5. 結論 100
5.1 主要成果說明 100
5.2 後續研究展望 102
參考文獻 103
附錄A：引擎熄火概括說明類文獻之網路資蒐結果一覽表 106
附錄B：引擎熄火概括說明類文獻之網路資蒐結果一覽表 109
自傳 114

[1]Chappell, M. A. and Blevins, E. G., “Advanced Turbine Engine Simulation Technique Development and Applications to Testing,” AIAA–1986–1731, pp.1, 1986.
[2]Gronstedt T., “Development of methods for analysis and optimization of complex jet engine systems,” Ph.D. Dissertation, Department of Thermo and Fluid Dynamics, Chalmers University of Technology, Sweden , pp.1–5, 2000.
[3]http://www.gasturb.de/index.html
[4]茹承斌， “單軸渦輪噴射引擎系統之熱氣動力模擬研究”，碩士論文，國防大學中正理工學院兵器系統工程研究所，桃園大溪，1998。
[5]林豪傑，“雙軸燃氣渦輪機操作循環與性能之模擬研究”，碩士論文，中正理工學院兵器系統工程研究所，桃園大溪，2000。
[6]高廣權， “分流式渦扇發動機操作循環與性能模擬研究”，碩士論文，國防大學中正理工學院兵器系統工程研究所，桃園大溪，2001。
[7]潘彥良， “氣渦輪引擎壓縮器操作特徵與失速界限之理論研究”，碩士論文，國防大學中正理工學院兵器系統工程研究所，桃園大溪，2002。
[8]許勝雄， “單軸傳動之渦扇引擎飛行包絡線預測研究”，碩士論文，國防大學中正理工學院兵器系統工程研究所，桃園大溪，2003。
[9]王立杰， “新一代戰機推進系統性能提昇之模擬研究”，碩士論文，國防大學中正理工學院兵器系統工程研究所，桃園大溪，2003。
[10]吳宏佑， “巡航用小型氣渦輪引擎之系統規範與壓縮器流場之性能解析模擬研究” ，碩士論文，中正理工學院兵器系統工程研究所，桃園大溪，2004。
[11]文宏達， “雙渦軸T700–GE–401發動機壓縮性能與渦輪冷卻效應之解析模擬研究” ，碩士論文，中正理工學院兵器系統工程研究所，桃園大溪，2004。
[12]張顧寶， “燃油特性對戰機引擎加速過程與暫態性能之影響研究”，碩士論文，國防大學中正理工學院兵器系統工程研究所，桃園大溪，2005。
[13]中華民國飛行安全基金會，《2003年國籍航空飛安回顧》，2005。
[14]USAF, Safety Investigations and Reports, Air Force Instruction 91–204, pp.1–2, Apr. 2004.
[15]USAF, Flight Safety magazine, Vol. 56, No. 1&2, pp.36, Jan/Feb, 2000.
[16]USAF, Flight Safety magazine, Vol. 59, No. 1&2, pp.46–47, Jan/Feb, 2003.
[17]Childre, M. T. and McCoy, K. D., “Flight Test of the F100-PW-220 Engine in the F–16,” J. of Propulsion and Power, Vol. 5, No 5, pp.620–625, 1989.
[18]http://www.pratt-whitney.com/prod_mil_f100.asp
[19]http://www.answers.com/, Online Encyclopedia, Answers Corporation.
[20]Hesse, W. J. and Mumford, N. V. S., Jet Propulsion for Aerospace Applications, 2nd ed., Texas, pp.177–220, 1970.
[21]Cohen, H., Rogers, G. F. C. and Saravonamuttoo, H. I. H., Gas Turbine Theory, 4th ed., Longman Group Limited, pp.61–406, 1995.
[22]Bathie, W. W., Fundamental of Gas Turbines, 2nd ed., John Wiley & Sons Ine., New York, pp.362–365, 1996.
[23]Mattingly, J. D., Elements of Gas Turbine Propulsion, McGraw–Hill Book Co., pp.363, 1996.
[24]Pratt & Whitney, F100–PW–220 Turbofan Engine Study Guide, 2000.
[25]Younossi, O., Arena M. V., Moore, R. M., Lorell M., Mason J., and Graser, J. C, “Military Jet Engine Acquisition,” Technology Basics and Cost–Estimating Methodology, USAF, pp.67, 2002.
[26]http://www.cpckor.com.tw/talin/talin-22-11.doc
[27]Holman, J.P., Experimental methods for Engineers, McGraw–Hill Ine, 4th ed., Singapore, pp.85–86, 1989.
[28]http://www.csgnetwork.com/jetfuel.html
[29] http://etda.libraries.psu.edu/theses/approved/WorldWideFiles/ETD-671/dissertation_juntaowu.pdf
[30]http://www.atsdr.cdc.gov/toxprofiles/tp121-c3.pdf
[31]McDougal, J. N., Pollard, D. L., Weisman, W., Garrett, C. M., and Miller, T. E., “Assessment of Skin Absorption and Penetration of JP–8 Jet Fuel and Its Components,” Toxicological Sciences, Vol. 55, pp.247–255, 2000.
[32]http://www.nhrc.wpafb.af.mil/download/reports/01jp8.pdf
[33]http://darwin.nap.edu/openbook/0309087155/html/13.html
[34]Edwards, T., and Maurice, L. Q., “Surrogate Mixtures to Represent Complex Aviation and Rocket Fuels ,” Journal of Propulsion and Power, Vol. 17, No. 2, pp.461, 2001.
[35]Visser, W. P. J. and Kluiters, S. C. A., “Modeling the effects of operating conditions and alternative fuels on gas turbine performance and emissions”, NLR–TP–98629, pp.24–25, 1998.
[36]The Jet Engine, 3rd ed, Rolls–Royce, pp.31, 1969.
[37]http://www.mech.kuleuven.be/tme/museum/engines/jet/
[38]http://www.enginehistory.org/G&jJBrossett/Coventry/RR Derwent 8 can.JPG