Abstract
AbstractSmall gas turbines have been used in many unmanned aerial vehicle (UAV) applications. For UAV, the design of gas turbine engine is driven by its simplicity, cost-effectiveness and reliability, and moderate fuel efficiency. This paper describes the aerodynamic design and salient features of a single-stage axial turbine designed for powerplant of UAV application. Profile, secondary and tip clearance losses are dominant due to reduced blade heights, Reynolds number, and manufacturing constraints. The transonic axial turbine is designed with low-aspect ratio and moderate stage loading. The design point pressure ratio is 2.3, and the target efficiency is 86%.
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