| 摘要 |
The purpose of the present invention is to provide a blade of a propeller for a turboprop aircraft, which can provide a weight lightening structure and safety by applying a composite to the blade of a turboprop aircraft propeller. To achieve the above purpose, the blade of a propeller for a turboprop aircraft has a skin-spar-foam sandwich structure by comprising: a skin portion which forms the outer circumferential surface of a blade; a spar portion which is in surface contact with a lower surface of the skin portion and has a structure of covering a fixed area of the skin portion; and a foam portion which fills an internal space formed by the skin portion and is sandwiched by the spar portion. The skin portion and spar portion have a structure where carbon fiber composites are laminated. A fixed area (station 5) at a wind tip side of the blade is formed only of the skin portion without the spar portion. The spar portion has a structure where the number of laminated carbon fiber composites is reduced toward the longitudinal direction (Z direction) of the blade. |
