The Design and Discussion of a Micro Gas Turbine Engine

• Main Authors: Yau-Cheng Li, 李曜丞
• Other Authors: Chen, Shih-Hsiung
• Format: Others
• Language: en_US
• Published: 2003
• Online Access: http://ndltd.ncl.edu.tw/handle/02227925917156344683

碩士 === 國立成功大學 === 航空太空工程學系碩博士班 === 91 === The micro gas turbine engine has a good potential for UAV propulsion and power generation applications. Whereas the turbine engine with thrust level below 1 lbf is non-exist, except the MIT micro turbine made by MEMS technology. The objective of the present study is trying to design a 100g thrust level micro turbine engine. The approach of the design is similar to that used in 10 lbf thrust level micro turbine engines. The basic requirement is that the engine components can be made by traditional precision machining methods. The designed micro turbine engine has a overall dimension of 4.76 cm in length, and 2.40 cm in diameter. The thrust is 100 g at 300000 rpm. A test bed to measure basic performance parameters is built to verify the design for future design improvement.