Replacing an aperture with an annular bushing in a composite laminated composite component
An annular bushing includes an annular cylindrical portion with a flange that defines a fastener aperture along an axis. A multiple of spacers extend from an outer surface of the annular cylindrical portion and the flange. The multiple of spacers are operable to control a bond line thickness.
1. A laminated composite intake cowl of a nacelle assembly, the assembly comprising:
a first laminated composite component;
a second component;
a third component that is a laminated composite component;
an annular bushing bonded to the first laminated composite component;
a second annular bushing bonded to the third component;
a fastener through the annular bushing to at least partially retain the first laminated composite component to the second component;
a second fastener through the second annular bushing to at least partially retain the third component to the second component,
wherein the first laminated composite component is an outer component,
wherein the second component is a bulkhead, and
wherein the third component is an inner component,
wherein a first surface of the annular bushing extends above a first surface of the first laminated composite for a distance by which a second surface of the annular bushing is recessed relative to a second surface of the first laminated composite component.
2. The assembly as recited in claim 1 , wherein the annular bushing is manufactured from a polyimide material.
3. The assembly as recited in claim 1 , wherein the annular bushing is manufactured from a polyetherimide material.
4. The assembly as recited in claim 1 , wherein the annular bushing is countersunk within the first composite laminate component.
5. The assembly as recited in claim 1 , wherein the fastener is countersunk within the annular bushing.
6. The assembly as recited in claim 1 , wherein the annular bushing is countersunk within the first laminated composite component and the fastener is countersunk within the annular bushing.
7. The assembly as recited in claim 1 , wherein the fastener is a rivet.
8. The assembly as recited in claim 1 , wherein the first laminated component is a skin of a gas turbine engine nacelle.