Abstract: A leading-edge shield for a turbomachine blade includes a pressure-side wing and a suction-side wing. Both the pressure-side wing and suction-side wing extend heightwise from a bottom edge to a top edge and lengthwise from the leading edge to a respective rear edge. They are connected together via the leading edge. The rear edge of the suction-side wing presents at least one shaped segment that is shaped in such a manner that the length of the suction-side wing within this segment is shorter than the length of the suction-side wing at each end of this segment.

Abstract: The invention provides a blade (16) comprising a blade body (30) made of organic matrix composite material reinforced by fibers and a leading edge shield (32) made of a material that withstands point impacts better than the composite material of the blade body. The leading edge shield (32) is assembled on the blade body (30) and the blade (16) includes bonding reinforcement (46) adhesively bonded on the leading edge shield (32) and on the blade body (16). The invention also provides a turbojet including a fan including such blades, and also a method of fabricating such a blade.

Abstract: The invention relates to comprising a blade body (9) made of composite material having a polymer matrix reinforced by fibers and a leading edge shield (10) made of material having greater ability to withstand point impacts than the composite material of the blade body. The leading edge shield (10) is assembled on the blade body (9) by means of a first adhesive (16) and a second adhesive (17), both adhesives (16, 17) being deposited between the blade body (9) and the leading edge shield (10). Both adhesives (16, 17) form respective continuous films between the blade body (9) and the leading edge shield (10).

Abstract: The invention relates to the field of turbomachine blades, and more specifically to a leading-edge shield (32) for a turbomachine blade (16), said leading-edge shield (32) having a pressure-side wing (34) and a suction-side wing (36), each extending along a height and along a length, the wings being connected together over their height, the pressure-side wing (34) presenting a greater length than the suction-side wing (36) over a first segment (S1) of the leading-edge shield (32), and an equal or smaller length than the suction-side wing (36) over a second segment (S2) of the leading-edge shield (32).

Abstract: A blade including a blade body made of organic matrix composite material and a leading edge shield made of a material that withstands point impacts better than the composite material of the blade body. The blade includes a blade tip. The leading edge shield is assembled on the blade body and includes a pressure-side fin and a suction-side fin. The pressure-side fin includes a pressure-side tab and the suction-side fin includes a suction-side tab, the pressure-side tab and the suction-side tab are folded one on the other and being secured to each other so as to form a partial covering of the blade tip. A turbojet includes a fan including such blades, and also a method of fabricating such a blade.

Abstract: A leading edge shield for a turbomachine blade extends heightwise from a bottom end to a top end, presents an outside face overlying a leading edge and an inside face for fastening to a blade body, and includes a pressure side wing, a suction side wing, and a central section joining together the pressure side wing and the suction side wing. Between the outside face and the inside face, the central section presents thickness that is greater than the thicknesses of the pressure side and suction side wings. The thickness of the central section increases with a gradient that is stable or increasing over a first segment from the bottom end of the leading-edge shield, but it presents a gradient that decreases beyond said first segment.

Abstract: A leading edge shield for a turbomachine blade extends heightwise from a bottom end to a top end, presents an outside face overlying a leading edge and an inside face for fastening to a blade body, and includes a pressure side wing, a suction side wing, and a central section joining together the pressure side wing and the suction side wing. Between the outside face and the inside face, the central section presents thickness that is greater than the thicknesses of the pressure side and suction side wings. The thickness of the central section increases with a gradient that is stable or increasing over a first segment from the bottom end of the leading-edge shield, but it presents a gradient that decreases beyond said first segment.

Abstract: A leading-edge shield (32) for a turbomachine blade (16) includes a pressure-side wing (34) and a suction-side wing (36). Each of the wings (34, 36) extends along a height (H) from a bottom edge (50) to a top edge (51) and along a length, from the leading edge to a respective rear edge, and are connected together over the leading edge. At least one of the wings from among the suction-side wing (36) and the pressure-side wing (34) presents a segment (S1), adjacent to the top edge (51) and extending over at least 10% of the height (H), wherein the rear edge (42) slopes towards the top edge (51).

Abstract: A blade made of organic matrix composite material for a gas turbine aeroengine, includes an airfoil extending transversely between a leading edge and a trailing edge; and a metal strip positioned on the leading edge of the airfoil, the metal strip having two flanges extending on either side of the leading edge over portions of the side faces of the airfoil forming a pressure side face and a suction side face so that the strip fits closely to the profile of the leading edge, the metal strip being fastened to the leading edge of the airfoil by at least one stitching thread; wherein the stitching thread has at least one external thread segment extending substantially transversely between a hole formed through a flange of the strip and a passage formed in a portion of the airfoil that has at least one face that is not covered by the metal strip.

Abstract: The invention relates to the field of turbomachine blades, and more specifically to a leading-edge shield (32) for a turbomachine blade (16), said leading-edge shield (32) having a pressure-side wing (34) and a suction-side wing (36), each extending along a height and along a length, the wings being connected together over their height, the pressure-side wing (34) presenting a greater length than the suction-side wing (36) over a first segment (S1) of the leading-edge shield (32), and an equal or smaller length than the suction-side wing (36) over a second segment (S2) of the leading-edge shield (32).

Abstract: A leading-edge shield (32) for a turbomachine blade (16) includes a pressure-side wing (34) and a suction-side wing (36). Each of the wings (34, 36) extends along a height (H) from a bottom edge (50) to a top edge (51) and along a length, from the leading edge to a respective rear edge, and are connected together over the leading edge. At least one of the wings from among the suction-side wing (36) and the pressure-side wing (34) presents a segment (S1), adjacent to the top edge (51) and extending over at least 10% of the height (H), wherein the rear edge (42) slopes towards the top edge (51).

Abstract: The invention relates to the field of turbomachine blades, and more specifically to a leading-edge shield (32) for a turbomachine blade (16), said leading-edge shield (32) including a pressure-side wing (34) and a suction-side wing (36). Each pressure-side wing (34) and suction-side wing (36) extends heightwise from a bottom edge (50) to a top edge (51) and lengthwise from the leading edge (18) to a rear edge (40, 42), and they are connected together via the leading edge (18), and wherein the rear edge (42) of the suction-side wing (36) presents at least one shaped segment (S1, S2) that is shaped in such a manner that the length of the suction-side wing (36) within this segment is shorter than the length (l2, l3, l21, l22, l31, l32) of the suction-side wing (36) at each end of this segment (S1, S2).

Abstract: A blade including a blade body made of organic matrix composite material and a leading edge shield made of a material that withstands point impacts better than the composite material of the blade body. The blade includes a blade tip. The leading edge shield is assembled on the blade body and includes a pressure-side fin and a suction-side fin. The pressure-side fin includes a pressure-side tab and the suction-side fin includes a suction-side tab, the pressure-side tab and the suction-side tab are folded one on the other and being secured to each other so as to form a partial covering of the blade tip. A turbojet includes a fan including such blades, and also a method of fabricating such a blade.

Abstract: The invention provides a blade (16) comprising a blade body (30) made of organic matrix composite material reinforced by fibers and a leading edge shield (32) made of a material that withstands point impacts better than the composite material of the blade body. The leading edge shield (32) is assembled on the blade body (30) and the blade (16) includes bonding reinforcement (46) adhesively bonded on the leading edge shield (32) and on the blade body (16). The invention also provides a turbojet including a fan including such blades, and also a method of fabricating such a blade.

Abstract: The invention relates to comprising a blade body (9) made of composite material having a polymer matrix reinforced by fibers and a leading edge shield (10) made of material having greater ability to withstand point impacts than the composite material of the blade body. The leading edge shield (10) is assembled on the blade body (9) by means of a first adhesive (16) and a second adhesive (17), both adhesives (16, 17) being deposited between the blade body (9) and the leading edge shield (10). Both adhesives (16, 17) form respective continuous films between the blade body (9) and the leading edge shield (10).

Abstract: A blade made of organic matrix composite material for a gas turbine aeroengine, includes an airfoil extending transversely between a leading edge and a trailing edge; and a metal strip positioned on the leading edge of the airfoil, the metal strip having two flanges extending on either side of the leading edge over portions of the side faces of the airfoil forming a pressure side face and a suction side face so that the strip fits closely to the profile of the leading edge, the metal strip being fastened to the leading edge of the airfoil by at least one stitching thread; wherein the stitching thread has at least one external thread segment extending substantially transversely between a hole formed through a flange of the strip and a passage formed in a portion of the airfoil that has at least one face that is not covered by the metal strip.