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AssigneeSafran Aircraft Engines
InventorsFrédéric Jean-Bernard POUZADOUX, ALAIN JACQUES MICHEL BASSOT, Jérémy GUIVARC'H, GILLES PIERRE-MARIE NOTARIANNI, THIBAULT RUF
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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.
A leading edge shield for a turbomachine blade, said leading edge shield extending heightwise from a bottom end to a top end, presenting an outside face overlying a leading edge and an inside face for fastening to a blade body, and including a pressure side wing, a suction side wing, and a central section joining together the pressure side wing and the suction side wing, the shield being characterized in that the central section presents a thickness between the outside face and the inside face that is greater both than a corresponding thickness of the pressure side wing and also than a corresponding thickness of the suction side wing, the thickness of the central section firstly increasing with a gradient that is stable or increasing over a first segment extending over at least 60% of the height of the leading-edge shield starting from the bottom end of the leading edge shield, and secondly presenting a gradient that decreases beyond said first segment.
Dependencies are inferred from the claim text.