AIR FLOW STRAIGHTENING STAGE FOR A TURBOMACHINE

A bypass turbomachine is disclosed. The turbomachine includes a longitudinal axis having an upstream blower impeller and a downstream air-flow straightening assembly of a secondary annular passage delimited radially on the inside by a radially inner shroud and radially on the outside by a radially o...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser: Riera, William Henri Joseph, Zaccardi, Cédric, Perdrigeon, Christophe Marcel Lucien
Format: Patent
Sprache:eng
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Beschreibung
Zusammenfassung:A bypass turbomachine is disclosed. The turbomachine includes a longitudinal axis having an upstream blower impeller and a downstream air-flow straightening assembly of a secondary annular passage delimited radially on the inside by a radially inner shroud and radially on the outside by a radially outer shroud, blades extending between the radially inner and outer shrouds and being attached at a first end portion to the radially inner shroud and at a second end portion to the radially outer shroud, the blades including a useful portion extending between the first and second end portions and defining a lower face and an upper face. For each blade, in a plane perpendicular to the longitudinal axis, each aerodynamically useful portion is bent into a C-shape in the circumferential direction.