Abstract: The invention relates to a fan blink (28) for an aircraft turbomachine, comprising a hub, an annular platform (42) and fan blades (44) arranged projecting from the annual platform. It also comprises a mechanical discharge slit (52) from a trailing edge (49) of the fan blade, associated with at least one of the fan blades (44), for the case of ingestion of a bird, the slit being made on the annular platform (42) going around the trailing edge (49).

Abstract: A turbine engine rotor blade including a plurality of blade cross sections stacked along an axis Z between a blade root and a blade tip defining therebetween the height of the blade, each blade cross section including a leading edge (16) and a trailing edge (17) and a chord defined by the length of the segment which extends from the leading edge to the trailing edge and ensuring that: the ratio of the chord at mid-height and of the chord at the blade root is comprised between 140% and 160%; the ratio of the chord at the blade tip and of the chord at the blade root is comprised between 115% and 135%; the chord is locally constant in a blade root zone and in a blade mid-height zone.

Abstract: A fibrous texture to form the fibrous reinforcement of a turbomachine blade made of composite material, the texture being made in one piece and having a three-dimensional weaving, and includes blade root, blade airfoil and blade support portions. The blade support portion includes a first area extending transversely from a first edge of the texture to form a leading edge and a second area extending transversely from the first area up to a second edge of the texture to form a trailing edge, the first area including warp yarns or strands made of second fibers different from the first fibers, the second fibers having an elongation at break greater than that of the first fibers, the first area having a first volume ratio in yarns or strands made of second fibers strictly greater than a second volume ratio in yarns or strands made of second fibers in the second area.

Abstract: The invention relates to a fan blink (28) for an aircraft turbomachine, comprising a hub, an annular platform (42) and fan blades (44) arranged projecting from the annual platform. It also comprises a mechanical discharge slit (52) from a trailing edge (49) of the fan blade, associated with at least one of the fan blades (44), for the case of ingestion of a bird, the slit being made on the annular platform (42) going around the trailing edge (49).