本研究主要目的為找尋出K60TP微型渦輪發動機的未知參數值；首先利用廠商提供之規格參數值進行初步模擬分析，為了能更準確的進行設計點參數模擬分析測試，本研究建置了K60TP微型渦輪之實驗系統，以藉此實驗運轉測試進而得知三個性能參數值，分別是發動機之入口質量流率(ṁ)為0.155 kg/s、渦輪出口溫度(T5)為939.0 K以及軸功率(Power)為7.0 kW，最終，再透過套裝軟體GasTurb11進行設計點參數模擬分析測試。

利用GasTurb11進行設計點參數模擬分析測試前，先行經由敏感性分析，得知壓縮比(γ)及燃燒室出口溫度(T4)此兩性能參數，為所有模擬輸入參數中對目標參數值的影響程度最大；故本研究將此兩性能參數之可能參數值細分成20個測試組合，分別於三種不同效率調整範圍，設計成60個測試組後，利用GasTurb11模擬軟體進行數值最佳化演算分析。將模擬結果比對實驗結果後發現，軸功率之模擬結果達到7.0 kW，並且渦輪出口溫度之模擬結果與實驗數據之間的誤差皆於3 %內之參數解共有10組，其中此最小誤差值為0.32 %的測試參數組合分別有γ =2及T4=1050 K、γ =2.6及T4=1100 K。

The main purpose of this study is to find the unknown parameter values of the K60TP micro-turbine engine. First, use the existing parameter values provided by the manufacturer for preliminary parameter simulation analysis. To improve the accuracy of simulation results, we construct the K60TP micro-turbine engine system and measure the performance parameters. Based on this experimental operation test, three performance parameter values are obtained, namely, the engine inlet mass flow rate (ṁ) is 0.155 kg/s, the turbine outlet temperature (T5) is 939.0 K, and the shaft power is 7.0 kW. Finally, carry on the design point parameter simulation analysis test by the package software GasTurb11.

Before starting the design point parameter simulation analysis test in GasTurb11, through sensitivity analysis, it is known that the pressure ratio (γ) and the combustion chamber outlet temperature (T4) are the greatest influence on the target parameters in all the simulation input parameters. So possible parameter values of the two performance parameters are divided into 20 parameter combinations, and combined three different efficiency adjustment ranges into total 60 test groups. Then the simulation results of the Numerical optimization calculation analysis compared with the experimental results has been revealed. The simulation result of the shaft power reaches 7.0 kW, and there are 10 sets of parameter solutions which the error between the simulation result and the experimental data of the turbine outlet temperature is within 3%. Among them, the test parameter combinations with the minimum error value (0.32 %) are γ =2 and T4=1050 K, γ=2.6 and T4=1100 K.

[1] https://zh.wikipedia.org/zh-tw/%E7%87%83%E6%B0%A3%E6%B8%A6%E8
%BC%AA%E7%99%BC%E5%8B%95%E6%A9%9F#/media/File:GasTurbine.svg
[2] J. Noe, R. McKeirnan, “Gas Turbine Generator Set,” U.S. Patents No.5, 497,615,
1996.
[3] J. Kurzke, “Gas Turbine Cycle Design Methodology: A Comparison of
Parameter Variation with Numerical Optimization,” International Gas Turbine &
Aeroengine Congress & Exhibition, Stockholm, Sweden, ASME 98-GT-343, June,
1998.
[4] P.A. Pilavachi, “Power Generation with Gas Turbine Systems and Combined
Heat and Power,” Applied Thermal Engineering, Vol.20, pp.1421-1429, 2000.
[5] Jian-Hua Gao, Ying-Yun Huang,“Modeling and Simulation of a Aero Turbojet
Engine with GasTurb,”International Conference on Intelligence Science and
Information Engineering, Wuhan China, pp.295-298, 2011.
[6] 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。
[7] 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.
[8] 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。
[9] 陳建志，“微型渦輪發電系統之性能分析與模擬”，國立成功大學航空太空工程系碩
士論文，2019 年 7 月。
[10] 田家榮，“微型渦輪發電系統性能分析與實驗驗證之研究”，國立成功大學航空太
空工程系碩士論文，2020 年 6 月。
[11] https://aviation.stackexchange.com/questions/16177/what-are-the-
differences-between-a-helicopter-engine-turboshaft-and-an-aircraf.
[12] Engine Manual Series2,KingTech Turbines , 01/29/2017.
[13] https://zh.wikipedia.org/zh-tw/%E7%83%AD%E7%94%B5%E5%81%B6
[14] https://www.hbm.com/cn/2384/t22-torque-transducer-for-simple-torque-
applications/
[15] http://www.tes.com.tw/product_detail.asp?seq=576
[16] https://zh.wikipedia.org/zh-hant/%E8%AE%A1%E7%AE%97%E6%B5%81%
E4%BD%93%E5%8A%9B%E5%AD%A6
[17] https://en.wikipedia.org/wiki/Turbulence_modeling
[18] 日本 KHK / 台 灣 昭 源 提 供，麗 台 國 際 有 限 公 司 整 理，“正齒輪的效率問
題”，2020年2月20日。
[19] Michael J. Vick, “High efficiency recuperated ceramic gas turbine engines for
small unmanned air vehicle propulsion,”PhD Thesis Department of
Mechanical Engineering Imperial College London, 01/31/2012.
[20]https://www.jetcat.de/en/products/produkte/jetcat/kategorien/hobby/SPT%2
0Series%20-Turboprop-Drives
[21] https://www.researchgate.net/figure/JetCat-SPT5-engine-compressor-map-
with-data-points-used-to-compute-P-and-operating-line_fig13_260872783