Method of fabricating a bonded cascade assembly for an aircraft thrust reverser
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.
1. 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.
2. The method of claim 1 , wherein the elongated stiffeners and the frame piece are made of composite material integrally formed of one-piece construction by molding or pultrusion.
3. The method of claim 1 , wherein the turning vanes are formed of one-piece construction by molding composite material.
4. The method of claim 1 , wherein the closeout cap is made of composite material integrally formed of one-piece construction by molding, injection molding, or pultrusion.
5. The method of claim 1 , wherein the closeout cap comprises end cap flanges configured for cooperatively preventing or limiting circumferential movement of the elongated stiffeners positioned therebetween during the step of attaching the closeout cap.
6. The method of claim 1 , wherein the closeout cap is bonded to the elongated stiffeners with structural adhesive.
7. The method of claim 1 , wherein the turning vanes comprise flow-directing portions with opposing side edges and opposing positioning flanges extending forward and aft from the side edges of the flow-directing portions, wherein the elongated stiffeners are configured to cooperatively trap the positioning flanges circumferentially and radially after the step of attaching the turning vanes and the frame piece and the closeout cap are configured to cooperatively trap the turning vanes therebetween after the step of attaching the closeout cap.
8. The method of claim 7 , wherein the positioning flanges comprise forward and aft edges configured to abut forward or aft edges of adjacent ones of the positioning flanges when positioned within the structural frame, such that a resulting trapped geometry of the positioning flanges within the elongated stiffeners properly clocks the flow-directing portions in a desired attitude relative to the structural frame.
9. 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.
10. The method of claim 9 , wherein the elongated stiffeners and the front frame piece are made of composite material integrally formed of one-piece construction by resin transfer molding, compression molding, or pultrusion, wherein the turning vanes are each individually formed of composite material by injection molding, compression molding, or transfer molding, wherein the closeout cap is made of composite material integrally formed of one-piece construction by compression molding, transfer molding, injection molding, or pultrusion.
11. The method of claim 9 , wherein the closeout cap comprises end cap flanges configured for cooperatively preventing or limiting circumferential movement, relative to the nacelle, of the elongated stiffeners, wherein the step of attaching the closeout cap to the aft ends of the elongated stiffeners further comprises positioning the aft ends of the elongated stiffeners between pairs of the end cap flanges.
12. The method of claim 9 , wherein the turning vanes each comprise flow-directing portions with opposing side edges and opposing positioning flanges extending forward and aft from the side edges of the flow-directing portions, wherein the elongated stiffeners are configured to cooperatively trap the positioning flanges circumferentially and radially relative to the nacelle after the turning vanes are attached to the elongated stiffeners and the front frame piece and the closeout cap are configured to cooperatively trap the turning vanes therebetween after the step of attaching the closeout cap.
13. The method of claim 12 , wherein the positioning flanges comprise forward and aft edges configured to abut forward or aft edges of adjacent ones of the positioning flanges when positioned within the structural frame, such that a resulting trapped geometry of the positioning flanges within the elongated stiffeners properly clocks the flow-directing portions in a desired attitude relative to the structural frame.
14. 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.
15. The assembly of claim 14 , wherein the elongated stiffeners each further include an inner flange and an outer flange, the inner flanges and the outer flanges being cooperatively configured for preventing or limiting radial movement of the turning vanes relative to the nacelle.
16. The assembly of claim 14 , wherein the turning vanes each comprise flow-directing portions with opposing side edges and opposing positioning flanges extending forward and aft from the side edges of the flow-directing portions, wherein the elongated stiffeners cooperatively trap the positioning flanges circumferentially and radially relative to the nacelle, and the front frame piece and the closeout cap cooperatively trap the turning vanes therebetween.
17. 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.