本研究目的在於設計一具微型渦輪引擎環狀燃燒室並測試之。燃料為丙烷並選用喬晟公司的TD08渦輪增壓器之軸件來搭配設計。

　　研究步驟分二階段；第一階段為燃燒室設計，主要於推算出渦輪引擎各站位性能參考數據，依此來設計環狀燃燒室，例如：孔口位置安排、孔口面積大小與各燃燒區流量分配。第二階段則針對設計完成之燃燒室進行冷流與燃燒測試實驗。冷流實驗用來驗證與修改燃燒室設計。燃燒測試則探討燃料注入方向與渦漩產生機制對燃燒室的影響，吾人預期採用與氣流反向的燃料注入方式能更有助於提升燃料和空氣的混合度，使得燃燒過程在燃燒室長度被限制下可以於燃燒室內完成。

　　由冷流實驗結果可推得氣流通過孔口之壓降，可以提高孔口面積理論計算之正確性，將燃燒室孔口面積修改後並完成燃燒室襯筒加工。點火測試實驗則從渦旋產生機制個數及燃料注入方向來測試。結果可以發現渦旋產生機制的個數為8個時對於燃料與空氣的混合度獲得有效提昇。改變燃料注入方向結果亦顯示當燃料注入方向與氣流方向相反時，確實可以降低渦輪出口的高溫，顯示逆流注入燃料方式比順流注入能有效地提昇燃料與空氣混合度。

　　The study is to design and test the annular combustor of the miniature gas turbine engine and to set up the testing equipment. In this thesis, the miniature gas turbine engine is designed based on the performance of the centrifugal compressor and the turbine blades of a turbo-charger.

　　First, the author roughly decided the distribution of the compressed air in each combustion zone and then calculated the total area of the holes on the chamber liners and the numbers of holes. After the theoretical design, performing some cold-flow tests and ignition tests on this annular chamber.

　　In the cold-flow tests, manufacturing the model chamber which is geometrically identical to prototype chamber. And it is found that the pressure loss of flow through the liner hole is about 3% of the total pressure. And it is also found the information about the flow rate of the holes. These are helpful to modify the chamber design. In the firing tests, discussing the mixing effect by changing the fuel injection direction and by control the numbers of swirl holes. The results show that upstream fuel injection mode dose play well in the short chamber length compared with the side fuel injection mode.

[1] K. S. Kaddah,“Discharge Coefficients and Jet Deflection Angles for Combustor Liner Air Entry Holes,”College of Aeronautics MSc thesis, Cranfield, England, 1964.

[2] B. C. Freeman,“Discharge Coefficients of Combustion Chamber Dilution Holes,” College of Aeronautics MSc thesis, Cranfield, England, 1965.

[3] Howard S. Bean,“Fluid Meters,”sixth edition, pp.47-58, 1971.

[4] Ralph T. Dittrich, “Discharge Coefficients for Combustor-liner Air-entry Holes II – flush rectangular holes, step louvers,”Technical Note 3924, National Advisory Committee for Aeronautics, 1975.

[5] Arthur H. Lefebvre,“Gas turbine combustion,”Hemisphere Pub.Corp., 1983.

[6] James E. A. John, “Gas Dynamics,”Second Edition, pp.372-375, 1984.

[7] 賴維祥,“燃燒室冷流試驗計劃,”中山科學研究院第一研究所研究報告, 1986年4月.

[8] Jack D. Mattingly,“Elements of Gas Turbine Propulsion,”McGraw-Hill International Edition, 1996.

[9] W.C. Ho, Y.C. Chao and D.B. Shiung, “Annular Combustor for Miniature Jet Engines,” International Journal of Turbo and Jet Engines, vol.14, pp.105-115, 1997.

[10] 趙怡欽、袁曉峰、賴維祥等,“氣渦輪引擎燃燒室研發期
末報告,”財團法人成大研究發展基金會, 1997.

[11] Yunus A. Gengel & Michael A. Boles,“Thermodynamics,”Mc GRAW-HILL, 3rd ed, 1998.

[12] 盧衍良,“燃氣渦輪引擎燃燒室進氣孔之進氣特性研究,” 國立成功大學碩士論文, 1999年6月.

[13] Christopher A. Fannin,“Thermoacoustic Stability Analysis for Multi-port Fuel Injection in a Lean Premixed Combustor,”AIAA 2000-0711, January 10-13, 2000.

[14] C. Stone and S. Menon,“Combustion Instabilities in Swirling Flows”AIAA 2001-3846, July 8-11,2001.

[15] 蔡禹擎、陳菁菘、李皓傑、李又儒, “國立成功大學航空太空工程學系航太實作總報告,” 2001年11月。

[16] Kyung J. Choi and Giyoung Tak,“Experimental Studies of Mixing Effects on LDI Combustion,”AIAA-2002-0334, 2002.

[17] 謝維昇,“觸媒氣渦輪引擎原型之發展,”國立成功大學航空太空工程學系所碩士論文, 2002年.

[18] 經濟部能源委員會,“氣化暨微型發電應用技術研討會論文集,” 2003.