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Propfan
A propfan is a type of aircraft engine related in concept to both the turboprop and turbofan, but distinct from both. The engine uses a gas turbine to drive an unshielded propeller like a turboprop, but the propeller itself is designed with a large number of short, highly twisted blades, similar to a turbofan's bypass compressor (the "fan" itself). For this reason, the propfan has been variously described as an "unducted fan" or an "ultra-high-bypass (UHB) turbofan". In technical papers it is described as "a small diameter, highly loaded multiple bladed variable pitch propulsor having swept blades with thin advanced airfoil sections, integrated with a nacelle contoured to retard the airflow through the blades thereby reducing compressibility losses and designed to operate with a turbine engine and using a single stage reduction gear resulting in high performance." The design is intended to offer the speed and performance of a turbofan, with the fuel economy of a turboprop. The propfan concept was first revealed by Carl Rohrbach and Bruce Metzger of the Hamilton Standard Division of United Technologies in 1975〔Rohrback, C. and Metzger, F.B., 'The Prop-Fan, a New Look at Propulsors', AIAA paper 75-1208, presented at the AIAA/SAE 11th Propulsion Conference, Anaheim California, September 1975.〕 and was patented by Robert Cornell and Carl Rohrbach of Hamilton Standard in 1979.〔(US Patent 4171183 ) Retrieved 28 June 2011.〕 Later work by General Electric on similar propulsors was done under the name unducted fan, which was a modified turbofan engine, with the fan placed outside the engine nacelle on the same axis as the compressor blades.
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抄文引用元・出典: フリー百科事典『 ウィキペディア（Wikipedia）』
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