Propulsive assembly for aircraft comprising a turbojet fitted with a fan with removable blades

摘要

A propulsive assembly for an aircraft includes a nacelle and a turbojet. The nacelle includes an upstream air inlet section. The turbojet includes a fan with removable blades. The air inlet section extends longitudinally. The fan includes a rotary disk including an annular peripheral wall and a plurality of curvilinear recesses positioned circumferentially in the wall. Each blade includes a blade body extending between a blade root and a blade head in a blade axis which is roughly radial relative to a fan rotation axis. Each blade root includes a curvilinear attachment housed in a respective recess of the rotary disk. Each attachment has a support surface forming an arc. The function of the support surface is to hold the attachment in the recess. The arc extends in or parallel to an attachment plane containing the blade axis or forming with the blade axis an angle of less than 15°.