| 摘要 |
A composite turbomachine blade comprises a preform of yarns or fibers woven in three dimensions and a binder between the yarns of the perform. The preform comprises first and second portions that are united by a transition zone, thus obtaining a reduction at least in the thickness of the blade between the second portion and the first portion. A composite turbomachine blade comprises a preform of yarns or fibers woven in three dimensions and a binder maintaining the relative disposition between the yarns of the perform. The preform is made up of warp yarns and weft yarns. The direction of the warp yarns forms the longitudinal direction of the perform. The preform comprises at least a first portion made with a first weave and forming the airfoil of the blade, and a second portion made using a second weave and forming the root of the blade. The first portion and the second portion are united by a transition zone in which the first weave is progressively modified to end up with the second weave, thus obtaining a reduction at least in the thickness of the blade between the second portion and the first portion. An independent claim is also included for a method of manufacturing a fan blade for a turbojet, comprising: (1) weaving warp yarns and weft yarns so as to form a preform of yarns or fibers that is woven in three dimensions, being made up of warp yarns and weft yarns; (2) cutting the preform to the shape and dimensions of the component portions of the blade; (3) providing a mold in which the preform is placed; (4) injecting a binder into the mold in order to impregnate the entire preform, the binder comprising a thermosetting resin; (5) heating the mold; and (6) extracting a molded part from the mold. |
