Guiding ring for variable-pitch blades and method of mounting said rings

A ring 17 for guiding variable pitch vanes of an aircraft turbomachine comprises a radially inner crown 29, which is divided into sectors and supports an abradable coating 33, and a radially outer annular ferrule 20, which is divided into sectors and comprises radial orifices 18 in which are mounted...

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Bibliographische Detailangaben
Hauptverfasser:	Kamel Benderradji, Thomas Nolwenn Emmanuel Delahaye, Delphine Hermance Maxime Parent, Sandrine Helene Quevreux
Format:	Patent
Sprache:	eng
Schlagworte:	BLASTING ENGINE PLANTS IN GENERAL HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES NON-POSITIVE DISPLACEMENT PUMPS POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS PUMPS FOR LIQUIDS OR ELASTIC FLUIDS STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	A ring 17 for guiding variable pitch vanes of an aircraft turbomachine comprises a radially inner crown 29, which is divided into sectors and supports an abradable coating 33, and a radially outer annular ferrule 20, which is divided into sectors and comprises radial orifices 18 in which are mounted guiding sleeves 24 that each receive a pivot of one of the vanes. Each ferule sector is mounted about a crown sector by a circumferential sliding connection. Each crown sector has a cylindrical tab 36 that is engaged in a transverse notch 28 of the sleeves to immobilize the sleeves in rotation. A method of mounting the ring comprises mounting the sleeves in the orifices of the ferule sectors and mounting the ferrule sectors by circumferential sliding around the crown sectors so that the sleeves are in rotational immobilization about their axes of rotation.