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

A propulsive assembly for an aircraft comprising a nacelle and a turbojet positioned in the nacelle, wherein the nacelle includes an upstream air inlet section, wherein the turbojet includes a fan with removable blades positioned downstream from the upstream air inlet section, wherein the upstream air inlet section extends longitudinally over a length less than 0.6 times a diameter of the fan, wherein the fan includes a rotary disk including a roughly annular peripheral wall and a plurality of curvilinear recesses positioned circumferentially in the peripheral wall, wherein 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 an axis of rotation of the fan, wherein each blade root includes a curvilinear attachment housed in a respective recess of the rotary disk, the curvilinear attachment having a first face and a second face that is opposite the first face, wherein the recesses are of a shape complementary to that of the curvilinear attachments, wherein each curvilinear attachment has at least two support surfaces that each form an arc having a centre of curvature, wherein a function of the at least two support surfaces is to hold the curvilinear attachment in the recess, wherein each arc of the at least two support surfaces extends in or parallel to an attachment plane containing the blade axis or wherein each arc forms with the blade axis an angle of less than 15°, wherein each one of the at least two support surfaces forms a portion of a cylindrical surface that extends from the first face to the second face of the curvilinear attachment, and wherein an axis of the cylindrical surface is perpendicular to the attachment plane and passes through the centre of curvature of the arcs.