Leading edge shield
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 (S 1 ) of the leading-edge shield ( 32 ), and an equal or smaller length than the suction-side wing ( 36 ) over a second segment (S 2 ) of the leading-edge shield ( 32 ).
1. A leading-edge shield for a turbomachine blade, said leading-edge shield having a pressure-side wing and a suction-side wing, each extending along a height and along a length, the wings being connected together over their height, the pressure-side wing presenting a greater length than the suction-side wing over a first segment of the leading-edge shield, and an equal or smaller length than the suction-side wing over a second segment of the leading-edge shield, wherein the first segment of the shield extends over at least 60% of the height of the pressure-side and suction-side wings.
2. The leading-edge shield according to claim 1 , wherein in said second segment of the shield, the length of the pressure-side wing remains equal to or greater than 70% of the length of the suction-side wing.
3. The leading-edge shield according to claim 2 , wherein in said second segment of the shield, the length of the pressure-side wing remains equal to or greater than 85% of the length of the suction-side wing.
4. The shield according to claim 1 , made of metal material.
5. A blade extending along a height from a blade root to a blade tip and comprising a blade body and the leading-edge shield according to claim 1 assembled on the blade body, the blade body being made of a composite material having a polymer matrix reinforced by fibers, and the leading-edge shield being made of a material with better point impact resistance than the composite material of the blade body.
6. The blade according to claim 5 , wherein the first segment of the leading-edge shield is closer to the blade root than is the second segment of the leading-edge shield.
7. A turbomachine including a plurality of blades according to claim 5 .
8. A fan including a plurality of blades according to claim 5 .
9. A turbofan including an engine and the fan according to claim 8 .
10. The turbofan according to claim 9 , further comprising:
a fan casing surrounding the fan, and including an inlet smaller than the fan.