Development of a micro turboprop to extend altitude capabilities of small UAVs
At the moment there are no relatively small unmanned aircraft for flights above 15000 ft, due to the lack of an appropriate propulsion system. If a reasonable thermal efficiency can be attained, small turboprop engines could fill this gap. A careful design and optimization of components is however a must to counteract the drop in efficiency encountered when reducing the size of gas turbines. The current paper describes results from reverse engineering of the KJ66 micro gas turbine. It is shown that the efficiencies of each of the components can be improved by several percent by minor modifications, which results in a considerable reduction in fuel consumption. An improved combustion chamber design proves to be of primary importance to obtain a reasonable fuel consumption at high altitude.
micro gas turbines micro turboprop unmanned aerial vehicles component optimisation engine performance
Dries Verstraete Jack Ling KC Wong Steve Armfield
School of Aerospace, Mechanical and Mechatronic Engineering, The University of Sydney,Aeronautical Engineering Building J11, Sydney, NSW, 2006, Australia
国际会议
2011年亚太航空航天技术学术会议(APISAT 2011)
澳大利亚
英文
1-10
2011-02-28（万方平台首次上网日期，不代表论文的发表时间）