Casing comprising a peripheral shroud for a turbomachine rotor

Abstract

The present invention relates to a casing ( 5 ) for a rotor of a turbomachine, more particularly for a fan ( 1 ) of a turbojet engine ( 2 ), comprising a peripheral shroud ( 6 ) designed to form a clamping collar around the casing, characterized in that the shroud has at least one fitting ( 12, 13 ) or flange for the attachment of equipment.

1 . A casing for a turbomachine rotor, more particularly for a turbojet engine fan, comprising a peripheral shroud designed to form a clamping collar around the casing, wherein the shroud has at least one fitting or a flange for the attachment of equipment. 
     
     
         2 . The casing according to  claim 1 , wherein the shroud is made from a strip that can be closed on itself. 
     
     
         3 . The casing according to  claim 1 , wherein the shroud is made from at least two partially peripheral strips that are able to be joined to each other. 
     
     
         4 . The casing according to  claim 3 , wherein the shroud is made from two substantially half-peripheral strips. 
     
     
         5 . The casing according to  claim 1 , wherein the shroud is primarily metal. 
     
     
         6 . The casing according to  claim 1 , wherein the shroud is primarily made of a composite material in particular from woven composite fibers. 
     
     
         7 . The casing according to  claim 1 , further comprising stops situated on either side of the shroud so as to ensure positioning and centering thereof and/or stops able to prevent any rotational movement of the latter part. 
     
     
         8 . The casing according to  claim 1 , wherein the shroud is glued on the casing. 
     
     
         9 . The casing according to  claim 1 , further comprising, at least at the shroud, a surface having a coefficient of friction with at least part of a surface of the shroud sufficient to limit or even prevent the rotation of the shroud around the casing. 
     
     
         10 . The casing according to  claim 1 , further comprising at least two shrouds capable of each retaining at least one base of at least one fitting, said base being introduced between the shroud and the casing. 
     
     
         11 . The casing according to  claim 1 , wherein the shroud is retained on the casing by at least one discrete fastening means. 
     
     
         12 . A propulsion assembly comprising a turbojet engine housed in a nacelle, wherein it comprises a fan casing according to  claim 1 .