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研究生:潘彥良
研究生(外文):Yen-Liang Pan
論文名稱:氣渦輪引擎壓縮器操作特徵與失速界限之理論研究
指導教授:夏筱明
指導教授(外文):Sheau-Ming Shiah
學位類別:碩士
校院名稱:國防大學中正理工學院
系所名稱:兵器系統工程研究所
學門:軍警國防安全學門
學類:軍事學類
論文種類:學術論文
論文出版年:2002
畢業學年度:90
語文別:日文
論文頁數:116
中文關鍵詞:齒輪式渦扇引擎壓縮器特徵圖失速界限
外文關鍵詞:geared turbofancompressorstall margin
相關次數:
  • 被引用被引用:14
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  • 下載下載:61
  • 收藏至我的研究室書目清單書目收藏:1
本論文旨以理論分析齒輪式渦扇引擎(geared turbofan)之模組操作特性,作為其設計點性能參數重建的基礎,再據此設計點參數重建結果,發展出一套建構氣渦輪引擎壓縮器圖(compressor map)的理論方法,並利用所獲壓縮器圖探討其失速現象與界限(stall margin)等議題。為說明此理論研究成果,本論文選擇TFE731-2型渦扇引擎為研究對象,經綜整廠家及公開文獻資料後進行其設計點性能參數重建與壓縮器圖建構等工作。在方法與步驟上:首先係根據熱氣動力理論與基本守恆定律,導出引擎模組之操作特性方程式。其次將各方程式予以整合求解,並據以發展一套系統模擬軟體CSJP-3(細節詳見附錄F),作為引擎設計點參數重建的計算工具。最後以此設計點為基準,應用參數尺度化原理(scaling laws)及已公開的壓縮器圖,將其轉換成所欲探討引擎之壓縮器圖。根據研究發現:以本論文尺度化方法配合適當壓縮器參考圖,建構所欲壓縮器圖是相當可行的,且可應用於渦輪壓縮器之研發設計與維修測評上。此外在TFE731-2設計點參數重建時,亦獲致相當豐富的參數調校心得(詳見附錄A至E)。至於在CSJP-3軟體驗證方面,經與使用GasTurb商用軟體所獲結果比對後,顯示出相當不錯的吻合度(相對誤差維持在2%以內),因而確立本論文研究成果之可行,當可作為後續探討引擎偏離設計點性能預測的參考。
This thesis presents a theoretical study of the module characteristics, the on-design system performance, and the compressor map of a typical geared turbofan engine. Focus has been centered on how to find the complete performance data set from inadequate engine information, how to use the data to generate the engine compressor map, and how to use the map to predict the stall, or surge, margin of the engine. For interpretation, a typical TFE731-2 turbofan engine is adopted, while basic information of the engine is extensively collected, from published material. In contents, a general engine module analysis is carried out based on fundamental conservation laws and aerothermodynamics to yield the governing equations of the engine system. It is then solved using the software CSJP-3 (see Appendix F for details) to give the complete data set of the engine design point, with many experiences in engine parameter adjustments (see Appendix A to E) obtained from the solution processes. Last, a practical method of map generation is derived using scaling techniques, the solved data, and a reference map. To justify the validity and accuracy of this method and CSJP-3, comparison with the results from using the commercial GasTurb were conducted, which shows a nice fit in between with a maximum relative error less than 2%. Although the present study may involve many approximations and assumptions, the method proposed and the results obtained still prepares a possible and simple way to the off-design performance study of turbo-engines, as an extension.
誌謝 ii
摘要 iii
ABSTRACT iv
目錄 v
表錄 viii
圖錄 ix
符號說明 xiii
1. 前言 1
1.1 研究目的 1
1.2 文獻探討 2
1.3 主題規劃 6
1.4 研究方法 7
1.5 論文架構 9
2. 典型氣渦輪引擎系統模組分析 11
2.1 進氣模組 13
2.2 旁通風扇 14
2.3 齒輪模組 15
2.4 壓縮模組 15
2.5 燃室模組 16
2.6 渦輪模組 17
2.7 噴口模組 19
3. 引擎模組整合與設計點參數重建 25
3.1 引擎基本資料蒐尋 25
3.2 模組關鍵參數辨識 30
3.3 設計點之數據重建 33
4. 設計點基準之壓縮器圖與失速界限 39
4.1 壓縮模組之變因分析 39
4.2 壓縮器圖之參數概要 41
4.3 典型壓縮器圖之建構 44
4.4 失速界限之計算探討 55
5. 結論 57
5.1 主要研究成果 57
5.2 後續研發展望 59
參考文獻 60
附錄A:進氣衝壓對TFE731-2設計點模擬之影響 65
附錄B:壓縮效率對TFE731-2設計點模擬之影響 69
附錄C:燃室性能對TFE731-2設計點模擬之影響 81
附錄D:渦輪效率對TFE731-2設計點模擬之影響 89
附錄E:傳動效率對TFE731-2設計點模擬之影響 97
附錄F:齒輪式渦扇引擎設計點模擬軟體(CSJP-3) 105
自傳 116
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