| 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 |
| 相關次數: | 點閱:93 下載:0 |
| 分享至: |
| 查詢本校圖書館目錄 查詢臺灣博碩士論文知識加值系統 勘誤回報 |
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%.
[1]蒲冠志&楊金石,“借鏡歐盟/美國/中國大陸智慧電網開創低碳經濟”, 2010年。
[2]https://www.aidc.com.tw/tw/.
[3]W. G. Scott, “Micro-Turbine Generator for Distribution Systems,” IEEE Industry Applications Magazine, Vol.4, May-June, pp.57-62, 1998.
[4]Stephanie L. Hamilton “Project Title: Micro Turbine Generator Program,” Proceedings of the 33rd Hawaii International Conference on System Sciences, Jan.4-7, pp.1-4, 2000.
[5]E.M. Curtis, H.P. Hodson, M.R. Banieghbal, J.D. Denton, R.J. Howell, “Development of Blade Profiles for Low Pressure Turbine Applications,” Birmingham, UK, June 10-13, 1996.
[6]https://en.wikipedia.org/wiki/Turbocharger.
[7]https://www.capstoneturbine.com/products.
[8]A.H. Epstein, “Millimeter-scale, MEMS Gas Turbine Engines,” ASME Turbo Expo, Atlanta, Georgia, USA, pp.669-696, June, 2003.
[9]P.A. Pilavachi, “Power Generation with Gas Turbine Systems and Combined Heat and Power,” Applied Thermal Engineering, Vol.20, pp.1421-1429, 2000.
[10]M. Frister, “Directly Driven Dynamo Electric Machine-Gas Turbine Generator Structure,” U.S. Patents No. 4,253,031, 1981.
[11]J. Noe, and R. McKeirnan, “Gas Turbine Generator Set,” U.S. Patents No. 5,497,615, 1996.
[12]O. O. Badran, “Gas-Turbine Performance Improvements,” Applied Energy, Vol.64, pp.263-273, 1999.
[13]E. Bilgen, “Exergy and Engineering Analyses of Gas Turbine based Cogeneration Systems,” Energy, Vol.25, pp.1215-1229, 2000.
[14]C. Zwyssig, and J.W. Kolar, “Design of a 100 W, 500,000 rpm Permanent-magnet Generator for Mesoscale Gas Turbines,” Conference Record of the IEEE, Vol. 1, pp.253-260, 2005.
[15]李彥慶,微型渦輪引擎環狀燃燒式設計與實驗驗證之研究,國立成功大學航空太空工程所碩士論文,2003年6月。
[16]高嘉臨,八十磅級微型渦輪引擎性能分析及測試研究,國立成功大學航空太空工程所碩士論文,2009年6月。
[17]洪偉稜,高轉速渦輪發電系統之設計與驗證研究式,國立成功大學航空太空工程系碩士論文,2012年6月。
[18]Kyuho Sim, Bonjin Koo, Chang Ho Kim, Tae Ho Kim, “Development and Performance Measurement of Micro-Power Pack Using Micro-Gas Turbine Driven Automotive Alternators,” Applied Energy, Vol.102, pp.309-319, 2013.
[19]廖智群,“微型渦輪發電系統之設計與驗證研究”,國立成功大學航空太空工程系碩士論文,2013年6月。
[20]R. E. P. Silva and P. T. Lacava, “Preliminary Design of A Combustion Chamber for Microturbine Based in Automotive Turbocharger,” Proceedings of The 22nd COBEM, pp.412–422, 2013.
[21]黃仕丞,“微型渦輪摻氫發電系統之設計與驗證”,國立成功大學航空太空工程所碩士論文,2015年6月。
[22]張維庭,“微型渦輪發電系統之動力流路設計及分析研究”,國立成功大學航空太空工程系碩士論文,2018年7月。
[23]Valentyn Barannik, and Maksym Burlaka , and Leonid Moroz and Abdul Nassar, “Direct Off-Design Performance Prediction of Micro Gas Turbine Engine for Distributed Power Generation,’’ ASME 2017 Gas Turbine India Conference, December 7-8, 2017.
[24]C.F. McDonald, “Recuperator Considerations for Future Higher Efficiency Microturbines,” Applied Thermal Engineering, Vol.2, pp.1463-1487, 1998.
[25]J. Kurzke, “Gas Turbine Cycle Design Methodology: A Comparison of ameter Variation with Numerical Optimization,” International Gas Turbine & Aeroengine Congress & Exhibition, Stockholm, Sweden, June, 1998. ASME 98-GT-343,1998.
[26]陳建志,“微型渦輪發電系統之性能分析與模擬”,國立成功大學航空系碩士論文,2019年7月。
[27]https://aviation.stackexchange.com/questions/16177/what-are-the-differences-between-a-helicopter-engine-turboshaft-and-an-aircraf.
[28]http://www.mhiet.co.jp/en/products/turbocharger/technical/index.html
[29]G. Xiao, T.-F. Yang, H.-L. Liu, D. Ni, M. Ferrari, M. Li, Z. Luo, K. Cen, M. Ni, “Recuperator for Micro Gas Turbines: A Review,” Applied Energy, Vol.197, pp.83-89, 2017.
[30]http://www.proepowersystems.com/proe90.htm.