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AssigneesSafran, Safran Aircraft Engines
InventorsNgadia Taha NIANE, Didier Maurice Marceau GUERCHE, Ming LONG, Hervé Bruno Marc OSMONT
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A turbine engine blade blank obtained by metal casting has a first direction along which a blade, a platform, and a root are consecutively formed, the platform extending in a second direction substantially perpendicular to the first direction. The blade has a pressure-side face and a suction-side face which are connected to one another by a trailing edge and a leading edge. The root has retaining surfaces along the first direction which are intended to cooperate with corresponding surfaces of a turbine engine disc to radially hold the root during rotation. The blade blank also includes at least one shroud extending in a third direction substantially perpendicular to the first and second directions, this shroud connecting a retaining surface to the platform in the first direction.
A turbine engine blade blank obtained by metal casting, comprising a first direction (Z) along which a blade (13), a platform (12), and a root (11) are consecutively formed, the platform (12) extending in a second direction (X) substantially perpendicular to the first direction (Z), the blade (13) comprising a pressure-side face (14) and a suction-side face (15) which are connected to each other by a trailing edge (16) and a leading edge (17), the root comprising retaining surfaces (23, 24) along the first direction (Z) which are intended to cooperate with corresponding surfaces of a turbine engine disc to radially hold the root during rotation,
Dependencies are inferred from the claim text.