Safran Aircraft Engines

Alain Jacques Michel Bassot

Jérémy Guivarc'h

Thibault Ruf

Jean-Louis Romero

Frédéric Jean-Bernard Pouzadoux

Matthieu Arnaud Gimat

Gilles Pierre-Marie Notarianni

Jean-Noël Mahieu

Eric Gvozdenovic

Gérald Diogo

Hervé Gignoux

Gaël Loro

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.

Leading edge shield

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

Blade comprising a blade body made of composite material and a leading-edge shield

The invention relates to the field of turbomachine blades, and more specifically to 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 (S) of the leading-edge shield (), and an equal or smaller length than the suction-side wing () over a second segment (S) of the leading-edge shield ().

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 () includes a pressure-side wing () and a suction-side wing (). Each of the wings () extends along a height (H) from a bottom edge () to a top edge () 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 () and the pressure-side wing () presents a segment (S), adjacent to the top edge () and extending over at least 10% of the height (H), wherein the rear edge () slopes towards the top edge ().

Growing community of inventors

Moissy-Cramayel, France

Alain Jacques Michel Bassot