US2013108432A1PendingUtilityA1

Airflow-straightening structure for the nacelle of an aircraft engine

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Assignee: AIRCELLE SAPriority: Jun 18, 2010Filed: Dec 18, 2012Published: May 2, 2013
Est. expiryJun 18, 2030(~3.9 yrs left)· nominal 20-yr term from priority
Inventors:Bertrand DesjoyeauxNicolas DezeustreWouter BalkFrancois Gallet
F01D 5/282Y02T50/60F02C 7/20F02C 7/04F05D 2240/14F02K 3/06F01D 25/24F05D 2300/603F05D 2250/51F01D 9/04F01D 5/34F01D 9/02
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Claims

Abstract

An airflow-straightening structure for an aircraft engine is provided that includes a hoop inside which there are arranged a plurality of flow-straightening vanes bearing a hub of a fan. Also includes is a clevis for connecting to a suspension strut, the clevis being fixed to said hoop. The structure has at least two elements chosen from the group of the hoop, the plurality of vanes, the hub and the clevis, which are formed in one piece, that is to say without any assembly operation. Additionally, at least one of the elements chosen from the group is at least partially formed of a composite material.

Claims

exact text as granted — not AI-modified
What is claimed is: 
     
         1  An airflow-straightening structure for an aircraft engine, comprising:
 a hoop inside which there are arranged a plurality of flow-straightening vanes bearing a hub of a fan; and 
 a clevis for connecting to a suspension strut, said clevis being fixed to said hoop, the structure being characterized in that at least two elements chosen from a group consisting of said hoop, said plurality of vanes, said hub and said clevis are formed in one piece, that is to say without any assembly operation, 
 
       and in that at least one of the elements chosen from the group consisting of said hoop, said plurality of vanes, said hub and said clevis is at least partially formed of a composite material. 
     
     
         2 . The structure according to  claim 1 , characterized in that all of said elements are made in a single piece and from a composite material. 
     
     
         3 . The structure according to  claim 1 , characterized in that said hoop incorporates the case of said fan. 
     
     
         4 . The structure according to  claim 1 , characterized in that said hoop incorporates an air intake shroud. 
     
     
         5 . The structure according to  claim 1 , characterized in that said hoop incorporates a thrust reverser cascade edge. 
     
     
         6 . A nacelle for an aircraft engine, characterized in that it comprises an airflow-straightening structure according to  claim 1 .

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