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US 2003/0118447 A1Published application
Bladed member, in particular for an axial turbine of an aircraft engine
AssigneeFiatavio S.p.A.
InventorsSergio Salvano, Stefano Protto
Life of this patent
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Abstract
A bladed member, particularly for an axial turbine of an aircraft engine; the bladed member having at least one aerodynamic profile defined by a back face and an underside face connected to each other along a leading edge and a trailing edge and defining respective nozzles for a stream of gas; the underside face having a projecting rib elongated in a direction crosswise to the leading and trailing edges.
Claims12
1) a bladed member (1), particularly for an axial turbine of an aircraft engine;
- the bladed member comprising at least one aerodynamic profile (6) defined by a leading edge (10), a trailing edge (11), a back face (13), and an underside face (14);
- said underside and back faces (14)(13) being connected along said leading and trailing edges (10)(11), and defining respective nozzles (9) for a stream of fluid;
- characterized by also comprising at least one rib (17) projecting from one (14) of said underside and back faces, and elongated in a direction (a) crosswise to said leading and trailing edges (10)(11).
Dependencies are inferred from the claim text.