戰機引擎熄火徵兆與預警之模式模擬研究

• Main Authors: Chun-An Chen, 陳俊安
• Other Authors: S. M. Shiah
• Format: Others
• Language: zh-TW
• Published: 2006
• Online Access: http://ndltd.ncl.edu.tw/handle/92618579556415603071

碩士 === 國防大學中正理工學院 === 兵器系統工程研究所 === 94 === 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.