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研究生: 田家榮
Tien, Chan-Rung
論文名稱: 微型渦輪發電系統性能分析與實驗驗證之研究
Performance Analysis and Experimental Verification of Micro Turbine Power Generation System
指導教授: 賴維祥
Lai, Wei-Hsiang
王振源
Wang, Chen-Yuan
學位類別: 碩士
Master
系所名稱: 工學院 - 航空太空工程學系
Department of Aeronautics & Astronautics
論文出版年: 2020
畢業學年度: 108
語文別: 中文
論文頁數: 111
中文關鍵詞: 渦輪增壓器氣體產生器微型渦輪發電系統熱回收系統
外文關鍵詞: Turbocharger, Gas Generator, Micro-Turbo Power Generation System, Heat Recovery System
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  • 本研究主要目的為建置一40 kW級之微型渦輪引擎發電系統,利用喬晟公司TD-08H渦輪增壓器來建置氣體產生器,分成模擬與實驗兩個部分進行,亦可拆成三個階段,第一個階段為建構氣體產生器,確認其性能;第二個階段將實驗數據匯入模擬軟體中,透過套裝軟體GasTurb11分析並驗證是否符合誤差範圍;最後階段將渦輪引擎延伸並應用於熱回收系統,並且利用敏感性分析探討其整體性能之優劣。
    實驗結果顯示,空氣質量流率0.53 kg/s、燃燒室入口溫度T3為436 K、渦輪出口溫度EGT為774 K、壓縮機等熵效率為0.767、渦輪等熵效率為0.837、布雷登循環系統淨功輸出(Wnet)為41.05 kW以及熱效率(ηth)為19.1%,與模擬值相比,僅燃燒室入口溫度的誤差值為5.65%,其餘參數誤差皆低於5%。
    當氣渦輪系統加入復熱器系統,系統輸出功率33.9kW減少至29.5kW,燃油消耗由0.6242下降至0.3159 kg/(kW*h),熱效率從11.49%提升至22.72%,因此系統配置復熱器後,其功率輸出雖下降了12.97%,但使熱效率提升11.23%。

    The main purpose of this research is to build a 40 kW micro-turbine engine power generation system. The TD-08H turbocharger is used to build a gas generator (is used as a gas generator to improve the engine’s efficiency). The project was divided into two parts: simulation and experiment. Three stages were conducted to obtain the final results. The first stage is to construct the gas generator and to confirm its performance. The second stage is to import the experimental data into the simulation software, then to analyze it, and to verify whether it meets the error tolerance according to the simulation tool GasTurb11; The last stage is to extend the turbine engine application to the heat recovery system and then using sensitivity analysis to discuss the advantages and disadvantages of its overall performance.
    The experimental results show that the air mass flow rate is 0.53 kg/s, the combustion chamber inlet temperature T3 is 436 K, the turbine outlet temperature EGT is 774 K, the compressor isentropic efficiency is 0.767, the turbine isentropic efficiency is 0.837, and the Braden cycle system net power output (Wnet) is 41.05 kW and the thermal efficiency (ηth) is 19.1%. Compared with the simulated value, the combustion chamber inlet temperature has an error value of 5.65%, and the error of the remaining parameter are all less than 5%.
    When the gas turbine system is added to the recuperator system, the system output power reduced from 33.9 kW to 29.5 kW, the fuel consumption dropped from 0.6242 to 0.3159 kg/(kW*h), and the thermal efficiency increased from 11.49% to 22.72%. Therefore, after the system was equipped with a recuperator, its power output decreased by 12.97%, which eventually improved the thermal efficiency by 11.23%.

    中文摘要 I Extended Abstract II 誌謝 V 目錄 VI 圖目錄 IX 表目錄 XIII 符號說明 XV 第 1 章 緒論 1 1-1 前言 1 1-2 文獻回顧 11 1-3 研究動機 22 1-4 研究目的 23 1-5 研究流程 24 第 2 章 基礎理論與系統設計 26 2-1 氣渦輪機理想熱循環原理 26 2-2 系統設計 35 2-2-1 系統設計概念 35 2-2-2 熱回收系統 39 2-3 氣渦輪模組建立 41 2-3-1 氣體產生器 42 2-3-2 動力渦輪 44 2-3-3 復熱器系統(Recuperator System) 46 2-4 系統規劃 48 第 3 章 模擬軟體 51 3-1 引擎性能模擬軟體 51 3-1-1 GasTurb模擬軟體介紹 51 3-1-2 引擎性能模擬方法 52 3-2 模擬參數初步設定(Initial System) 53 3-2-1 渦輪噴射引擎系統 53 3-2-2 渦輪軸引擎系統 55 3-2-3 復熱器系統 58 第 4 章 實驗設備與實驗步驟 59 4-1 測試平台 59 4-2 溫度量測系統 62 4-3 壓力量測系統 64 4-4 資料擷取系統 65 4-5 轉速量測系統 68 4-6 滑油供應系統 70 4-7 燃料供應系統 71 4-8 點火系統 72 4-9 實驗步驟(氣體產生器操作順序) 74 4-10 流速量測系統 76 4-11 氣體產生器故障排除 78 4-12 完整機台實體圖 79 第 5 章 結果與討論 80 5-1 GasTurb模擬數據分析 80 5-2 敏感性分析(Sensitivity Analysis) 90 5-3 實驗數據分析 92 第 6 章 結論與未來工作 100 6-1 結論 100 6-2 未來工作 102 參考文獻 103 附錄 106

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