Containment casing

Abstract

A containment casing 1 is provided in which tubular composite layers 2, 3 are arranged in an angular staggered relationship to minimise overlap between the interstitial spacing between tubes in each respective layer 2, 3 . In such circumstances, with a continuous planar layer 4, 5 on one or both sides, operational integrity is maintained with a lightweight containment casing 1 in comparison with prior arrangements but retaining resistance to fragment penetration.

1 . A containment casing for a rotating assembly, the casing comprising a first tubular composite layer comprising a plurality of tubular members and a second tubular composite layer comprising a plurality of tubular members, the first tubular composite layer and the second tubular composite layer angularly staggered relative to each other to limit overlap of interstices between tubular members in each respective composite layer with the other composite layer.  
   
   
       2 . A containment casing as in  claim 1 , wherein the rotating assembly is part of an aircraft engine.  
   
   
       3 . A casing as claimed in  claim 1 , wherein a continuous planar ring is secured to one side of the casing.  
   
   
       4 . A casing as claimed in  claim 3 , wherein continuous planar rings are secured either side of the casing with the first tubular composite layer and the second tubular composite layer sandwiched between them.  
   
   
       5 . A casing as claimed in  claim 1 , wherein the tubular members are hollow.  
   
   
       6 . A casing as claimed in  claim 1 , wherein the tubular members are filled in order to alter at least one mechanical property of the tubular composite layer overall or in selective parts thereof.  
   
   
       7 . A casing as claimed in  claim 6 , wherein the or each mechanical property altered by filling the tubular member is selected from the list consisting of: acoustic damping, vibration damping, mechanical stiffness of the composite layer.  
   
   
       8 . A casing as claimed in  claim 1 , wherein the casing is cylindrical.  
   
   
       9 . A casing as claimed in  claim 1 , wherein the angular stagger between the first composite layer and the second composite layer is perpendicular.  
   
   
       10 . A method of forming a containment casing for a rotating assembly, the method comprising: 
 a) forming a first composite tubular layer of tubular members and a second composite tubular layer of tubular members, associating the first composite tubular layer with the second composite tubular layer with an angular stagger relation between them; and,    b) fixing the first composite layer and the second composite layer with the angular stagger relation between them to limit overlap of interstices between tubular members in each respective composite layer with the other composite layer.    
   
   
       11 . A method as claimed in  claim 10 , wherein the method also includes association securing a continuous planar ring to one side of the casing.  
   
   
       12 . A method as claimed in  claim 11 , wherein a continuous planar ring is secured upon both sides of the casing.  
   
   
       13 . An aircraft engine incorporating a containment casing as claimed in  claim 1 .  
   
   
       14 . An aircraft engine incorporating a containment casing manufactured in accordance with the method of  claim 10.