| 摘要 |
FIELD: engines.SUBSTANCE: fan rotor blade of an aircraft jet engine fitted in a fitting groove formed in a fan disk comprises a blade body and sheath. Blade body is made from a composite material of a resin and fibers and has a pressure surface facing one side in a rotation direction and a suction surface facing the other side in the rotation direction as well as a back edge. At the end side of the blade body there is a fitting portion fitted in a fitting groove formed in a fan disk. Sheath is more rigid than the blade body, and fixed to the blade body, the sheath covers a leading edge portion of the blade body. Sheath extends in the longitudinal direction of the blade body and comprises a base end portion of, which is located closer to the end side of the blade body than blade platform surface limiting the passage formed in the engine case. Sheath includes a tip end portion covering a tip end portion of the blade body from the leading edge portion of the blade body to the back edge of the blade body.EFFECT: invention allows reducing the weight of the blade and increasing its impact resistance.5 cl, 9 dwg |
