Method of fabricating a bonded cascade assembly for an aircraft thrust reverser
AssigneeSpirit AeroSystems, Inc.
InventorsHenry A. Schaefer, Mark A. Wadsworth
Life of this patent
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Abstract
A method of fabricating a bonded cascade assembly of a thrust reverser for an aircraft nacelle. The method may include inserting individual turning vanes between spaced apart elongated stiffeners at an aft end thereof and sliding the turning vanes toward a front frame piece attached to or integrally formed with forward ends of the elongated stiffeners. The elongated stiffeners may have inner and outer flanges for trapping and limiting radial movement of the turning vanes. The method may further include bonding the turning vanes to the structural frame with a structural adhesive and attaching a closeout cap to the aft ends of each of the elongated stiffeners.
Claims17
A method of fabricating a cascade assembly, the method comprising:
- attaching a plurality of turning vanes to a structural frame, the structural frame comprising a plurality of elongated stiffeners each having forward and aft ends and inner and outer flanges between which at least portions of the turning vanes are located after the turning vanes are attached to the structural frame, the inner and outer flanges being configured for cooperatively preventing or limiting radial movement of the turning vanes positioned therebetween, and a frame piece attached to or integrally formed with the forward or aft ends of the elongated stiffeners;
- and
- attaching a closeout cap to each of the elongated stiffeners at the aft or forward ends opposite of the frame piece.
A method of fabricating a cascade assembly of a cascade thrust reverser of an aircraft engine nacelle, the method comprising:
- attaching turning vanes between elongated stiffeners of a structural frame, the elongated stiffeners each having forward and aft ends and inner and outer flanges or protruded portions between which at least portions of the turning vanes are located after the turning vanes are attached between the elongated stiffeners, the inner and outer flanges or protruded portions being configured for cooperatively preventing or limiting radial movement of the turning vanes relative to the nacelle, the elongated stiffeners being spaced from each other via a front frame piece integrally-formed with the forward ends of the elongate stiffeners;
- and
- attaching a closeout cap to the aft ends of each of the elongated stiffeners.
A bonded cascade assembly of a cascade thrust reverser of an aircraft engine nacelle, the bonded cascade assembly comprising:
- a structural frame made of composite material and comprising:
- a plurality of elongated stiffeners each having a forward end and an aft end, and
- a front frame piece integrally-formed with the forward ends of the elongated stiffeners;
- a plurality of turning vanes made of composite material and each positioned between two of the elongated stiffeners and attached thereto;
- and
- a closeout cap made of composite material and attached at the aft ends of the elongated stiffeners.
A method of fabricating a cascade assembly, the method comprising:
- attaching a plurality of turning vanes to a structural frame, the structural frame comprising a plurality of elongated stiffeners each having forward and aft ends and C-channels or hourglass-shaped configurations configured for cooperatively preventing or limiting radial movement of the turning vanes, and a frame piece attached to or integrally formed with the forward or aft ends of the elongated stiffeners;
- and
- attaching a closeout cap to each of the elongated stiffeners at the aft or forward ends opposite of the frame piece.
Dependencies are inferred from the claim text.