|
參 考 文 獻 [1] 張希誠譯,RS-232界面研究,第三波文化事業股份有限公司,1987。 [2] 白中和編譯,RS-232介面技術應用,全華科技圖書公司,1986。 [3] 夏筱明、茹承斌,“單軸渦噴發動機設計點熱動力循環建構之研究” , 第七屆國防科技研討會,桃園大溪中正理工學院,1998。 [4] 賴正權、夏筱明、潘彥良、陳光宏,”燃氣渦輪引擎壓縮器特徵分析與實驗模組建置之研究”,2001 中華民國「燃燒學會/民航學會/航太學會」學術聯合會議論文集,元智大學,桃園中壢,第61-68頁,2001。 [5] 陳光宏、賴正權、夏筱明,”燃氣渦輪引擎壓縮器特徵分析實驗測試設備之建置”,2002 中華民國「民航學會/航太學會/燃燒學會」學術聯合會議論文集,高雄餐旅學院,高雄市,第389-396頁,2002。 [6] CNS(中國國家標準)總號7779(送風機檢驗方法)。 [7] 東元變頻馬達(EVEFYH)使用說明書。 [8] 富士變頻器(5000G11S)使用說明書。 [9] LEADER 6520使用說明書。 [10] TES 1307數位溫度錶使用說明書。 [11] PASCO CI-6532A 壓力感測器說明書。 [12] TES 2730 記錄式數位電錶使用說明書。 [13] KAZ 8205 差壓計使用說明說明書。 [14] LUTRON AM-4202 數位熱線式風速計使用說明說明書。 [15] Hesse, W. J. and Mumford, N. V. S. Jr., “Jet Propulsion for Aerospace Application,” 2nd. Edition, 1964。 [16] Hünecke, Klause, “Jet Engines,” Motorbooks International Publisher Wholesalers, 4th edition, 1997。 [17] Cumpsty, N., “Jet Propulsion,” Cambridge University Press, 1997. [18] Bathie, W. W., “Fundamentals of gas turbines,” 2nd edition, John Wiley & Sons Inc., 1996. [19] Cohen, H., Rogers, G. F. C. and Saravanamuttoo, H. I. H., “Gas Turbine Theory,” Longmam Group Limited, 1997. [20] Langhaar, H.L., “Steady Flow in the Transition Length of a Straight Tube,” J. Appl. Mech., vol 9,1942. [21] Boylestad,R., “Introductory Circuit Analysis,”9th edition, Prentice-Hall ,Inc., 2000. [22] Saravanamutto, H. I. H. and Maclsaac, B. D., ”Thermodynamic Models for Pipeline Gas Turbine Diagnostics,” Journal of Engineering for Power, Vol. 105, 1983. [23] Zhu, Ping, “Simulation of an Advanced Twin-spool Industrial Gas Turbine,” Journal of Engineering for Gas Turbine and Power, ASME,Vol. 114, 1992. [24] Robbins,W.H.,and Dugan,J.F., “Prediction of Off-Design Performance of Multistage Compressor”,NASA SP-36,Chapter x,pp297-310,1965. [25] Kurzke, J., “How to Get Compressor Map for Aircraft Gas Turbine Performance Calculations,” ASME paper, 96-GT-48, 1997. [26] Wittenberg, H., “Prediction of Off-Design Performance of Turbojet and Turbofan Engine Based on Gasdynamic Relationships,” Deflt University of Techno, The Netherlands, 1976. [27] Peng, Z. Y., and Jeng, D.R., “A Comment on Approaches for Compressor Performance Map Improvement,” the American Institute of Aeronautics and Astronautics, Inc. AIAA, 1995. [28] Schulze, G., Blaha, C., Hennecke, D. K., and Henne, J.M.,“ The Performance of a New Axial Single Stage Transonic Compressort,” the American Institute of Aeronautics and Astronautics, Inc. AIAA, 1995. [29] Sieros, G., Stamatis, A., and Mathioudakis,K.,“Jet Engine Component Maps for Performance Modeling and Diagnosis,” the AmericanInstitute of Aeronautics and Astronautics, Inc. AIAA, 1997. [30] Kobor, A., “Multistage Axial Compressor Map Generation,”Department of Heat Engines Technical University of Budapest,1987. [31] Johnson, M., “One-Dimensional, Stage-By-Stage, Axial Compressor Performance Model,” Gas Turbine and Aeroengine Congress and Exposition, Orlando,FL, June 3-6,1991. [32] Attia M., and Taher Schobeiri M., “a New Method for the Prediction of Compressor Performance Maps Using One-Dimensional Row-By-Row Analysis,” Gas Turbine and Aeroengine Congress and Exposition, Houston,Texas, June 5-8,1995. [33] ISO3966。 [34] BS1042 part2.1。
|