Design and testing of a reversed intake for a turboprop engine on a subsonic pusher aircraft

Le résumé fourni par la source

The objective of this paper is to design a new reversed intake for a pusher aircraft having dimension restriction of the nacelle and establish a testing platform to verify the results. For a pusher aircraft, the turboprop engine is mounted on the tail of the aircraft, and hence a reversed intake with U-elbow to guide airflow flowing through a 180˚ bend, maintaining excellent flow quality, prior to entering the engine is required. The U-elbow channel has a twisted angle to connect the throat and the inlet mouth of the engine. In the design and analysis, the ANSYS CFX was employed to examine the influence produced by the variation of intake geometry on two crucial performance parameters: total pressure recovery and flow distortion coefficient. In the experiment, the TPE331-10 engine was employed and a testing platform was built to carry out the test.

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