Crack and delamination stoppers for aircraft propulsion system components

Abstract

An inner fixed structure of a thrust reverser includes an inner skin, an outer skin, a cellular core disposed between the inner skin and the outer skin, and at least one crack and delamination stopper extending radially between the inner skin and the outer skin.

What is claimed is: 
     
         1 . An aircraft propulsion system component comprising:
 a perforate first skin;   an imperforate second skin;   an acoustic cellular core disposed between, and bonded to, the first skin and the second skin; and   at least two reinforcement members extending radially through the acoustic cellular core, each reinforcement member comprising:
 a central segment extending radially through the acoustic cellular core and adhesively bonded to circumferentially opposing surfaces of the acoustic cellular core; and 
 an end segment extending from the central segment substantially parallel to the second skin, the end segment being positioned between the acoustic cellular core and the second skin, and adhesively bonded to the second skin. 
   
     
     
         2 . The aircraft propulsion system component of  claim 1 , wherein the end segment of each reinforcement member is bonded to the acoustic cellular core. 
     
     
         3 . The aircraft propulsion system component of  claim 1 , wherein each reinforcement member has unitary one-piece construction. 
     
     
         4 . The aircraft propulsion system component of  claim 1 , wherein each reinforcement member comprises at least two similarly shaped plies that are joined to one another. 
     
     
         5 . The aircraft propulsion system component of  claim 1 , wherein each of the first skin, the second skin and the at least two reinforcement members is constructed from a graphite composite material. 
     
     
         6 . The aircraft propulsion system component of  claim 1 , comprising a 360-degree, one-piece annular structure. 
     
     
         7 . The aircraft propulsion system component of  claim 1 , wherein the component is devoid of fasteners which pass through the second skin to secure the end segment to the second skin. 
     
     
         8 . The aircraft propulsion system component of  claim 1 , wherein:
 the end segment of each reinforcement member is bonded to the acoustic cellular core;   the assembly is devoid of fasteners which pass through the second skin to secure the end segment to the second skin; and   each of the first skin, the second skin and the at least two reinforcement members is constructed from a graphite composite material.   
     
     
         9 . The aircraft propulsion system component of  claim 8 , comprising a 360-degree, one-piece annular structure. 
     
     
         10 . The aircraft propulsion system component of  claim 9 , wherein:
 each reinforcement member has unitary one-piece construction;   
     
     
         11 . The aircraft propulsion system component of  claim 9 , wherein:
 each reinforcement member comprises at least two similarly shaped plies that are joined to one another.   
     
     
         12 . The aircraft propulsion system component of  claim 8 , wherein:
 each reinforcement member has unitary one-piece construction;   
     
     
         13 . The aircraft propulsion system component of  claim 8 , wherein:
 each reinforcement member comprises at least two similarly shaped plies that are joined to one another.